CC BY
49
INVESTIGATION OF THE INFLUENCE OF PLASMA SPRAY SEALING COATINGS ON THE EFFECT OF SEALING THE TV2 - 117A TURBOJET ENGINE COMPRESSOR
Mihailo R. Mrdak
Research and Develoopment Center IMTEL, Communications a.d., Belgrade, e-mail: drmrdakmihailo@gmail.com
DOI: 10.5937/vojtehg63-6249
FIELD: Chemical Technology ARTICLE TYPE: Original Scientific Paper ARTICLE LANGUAGE: English
Summary:
This research shows the effect of the application of soft seals deposited by the atmospheric plasma spraying - APS process on the parts of the TV2-117A turbojet engine compressor. Western plasma spray technology and materials were applied for the first time on the parts of the compressor. The aim was to replace the existing sealant with a new class of materials in order to increase the sealing effect and provide air flow under the highest pressure through the compressor. Soft seals are formed as duplex systems consisting of the bonding underlayer based on NiCrAl and NiAl coatings and top sealing layer coatings based on Ni -15% graphite, Ni - 25% graphite and AlSi - polyester. This paper presents the parameters for depositing the coatings on the compressor parts as well as the mechanical and microstructural characteristics of the coatings produced with the optimal deposition parameters. The mechanical properties of the coatings were assessed by testing the microhard-ness of the bonding layers using the HV03 method and the macrohard-ness of the sealing layers using the HR15W method. The tensile bond strength of the duplex coatings system was investigated by tensile testing. The microstructures of the coating layers were evaluated on an optical microscope - OM. The analysis of the microstructure of the deposited layers was performed in accordance with the Pratt & Whitney and TURBOMECA standards. Coating wear was determined from the change in the dimensions of the sealing surfaces before and after testing. The dimensions were measured in the coordinate measuring machine MAUSER ML 28. This paper presents the mean value of wear in milime-ters and compares it with the values of the allowed tolerance in the compressor machined parts. The sealing effect of the compressor parts was tested on a TV2-117A engine at a test station and by flight tests on
<ID
an Mi-8 (HT-40) helicopter. The tests have shown that the new system of sealing coatings increases the degree of efficiency of the compressor by 10% while reducing fuel consumption by 8%.
Key words: Seals, Layers, Engines, Deposits, Compressors, Coatings.
ACKNOWLEDGEMENT: The author is thankful for the financial support from the Ministry of Education and Science of the Republic of Serbia (national projects OI 174004, Tr 34016).
Introduction
Development of new generations of turbo-jet engines and a request for a higher reliability of operation and a wider choice of component resources in exploitation resulted in a wider application of plasma spray coatings. Various quality types of powders have been developed for aircraft components such as low and high pressure compressor components, gas turbine components and landing gear components (Mrdak, 2012b, pp.71-89), (Mrdak, 2013a, pp.69-88), (Vencl, et al., 2011, pp.1281-1288), (Mrdak, et al., 2013, pp.559-567), (Mrdak, 2014a, pp.7-22), (Mrdak, 2014b, pp.7-26). Low and high pressure compressor components of turbojet engines are coated with soft abrasive erosion-resistant coatings which cause low energy conditions of friction. During exploitation, coatings wear instead of causing blade or seam labyrinth wear. These coatings are suitable for eccentric assemblies and they compensate for the changes in machining-induced tolerances. With clearance adjustment to the lowest value, coatings improve engine performances. The precision in machining tolerance is also reflected on a significant reduction of the damage to the blades and on fuel consumption. The most commonly used abrasive coatings are: nickel - graphite, aluminum -silicon - polyester, nickel - chromium - iron and aluminum - boron nitride. The quality and resource of abrasive coatings depend on the deposition parameters (Mrdak, 2012b, pp.71-89), (Mrdak, 2013a, pp.69-88). The sealing coating systems are designed in such a way that the rotor non-axiality and the dimension changes due to temperature change are taken into account and that they wear and tear without damage to the blade tops maintaining a constant clearance (Tosnar, 1988, pp.257-262). The blade tops at high speeds must act as an effective cutting tool in order not to damage the seal or the blades. The characteristics which a material should have are good resistance to erosion from foreign particles and a good possibility of wear without damaging the blades as well as the ability to sustain working temperatures without the degradation of mechanical properties (Naser, 1988, pp.75-84). With wearable sealing systems,there is a need for the balance between material wear due to heat, final surface treatment, erosion resistance and resistance to wear. Plasma spray powder deposition parameters enable a con-
X
o
>
LO
O <N
yy 0£
U O C L A C
X
C E T
Y R
A T
S A L
CD >Q
X
E T O
O
>
trol of the given key characteristics. The plasma spray deposition process enables the control of coating porosity, density and thicknessin order to obtain sealing layers with the required characteristics (Tosnar, 1988, pp.257262). Soft sealing coatings are formed as duplex systems with plasma spray technology. For the production of the bonding layer, NiAl, NiCrAl and NiCrAlY powders are often used (Mrdak, 2010, pp.5-16), (Mrdak, 2013b, pp.7-22), (Mrdak, 2012a, pp.182-201). The thickness of the bonding layer ranges from 0.005 to 0.15 mm and must correspond to the substrate material and the top sealing layer. The role of the bonding layer is to provide good adhesion to the substrate and good bonding with the sealing layer. The powders for soft sealing coatings contain metallic components which provide toughness to the coating as well as non-metallic components which are consumed in the process of exploitation, such as graphite, polyester and others. For the production of seals for the temperatures up to 480°C, Ni -graphite powder is used due to its high resistance to oxidation, wear and sudden changes in temperature. For lower temperatures, up to 345°C, coatings based on AlSi alloy and polyester mixtures are applied. Thus formed soft sealings provide effective sealing with minimal clearance during engine operation and they reduce the loss of pressurein compressors and turbine sections. World wide research in this field has instigated the use of new materials and plasma spray technology in the process of repair of the TV2-117A turbojet engine compressor, produced in Russia. In order to achieve the set goals, the gaps between the components in the compressor must be minimal (Demasi, 1994, pp.1-9). Very good sealing reduces gas loss caused by leakage. Also, seals should provide the thermal insulation of the housing, and reduce the influence of the gas temperature in the casing (Novinski, 1991, pp.451- 454), (Yi, 1999, pp.47-53). For that purpose, coatings consisting of a metallic phase and non-metallic phase for self - lubricating with high porosity are used (Oka, 1990, pp.58-67). The most important properties of sealing coatings are high resistance to wear of scraping blades and resistance to gas erosion and foreign particles present in the gas (Novinski, 1990, pp.151-157), (Yi, 1997, pp.99 -102).
The aim of the study was to use the plasma spray technology and new materials in order to examine the effect of sealing the TV2 - 117A turbojet engine compressor and to replace the existing sealants during the engine overhaul. New generations of materials applied to seal parts of the engine compressor should provide a higher degree of compressor efficiency with lower fuel consumption. The requirements to be met by such materials are to provide air flow at T = 100 - 125°C under the highest pressure through the compressor. The expected effects have been confirmed by 42-hour engine tests on the test station and by flight tests of an Mi-8 (HT-40) helicopter.
Materials and experimental details
Five different powders of the Sulzer Metco company were used: Metco 443NS, Metco 450NS, Metco 307NS-1, Metco 308NS-1 and Metco 601NS. Bonding coating layers were manufactured from Metco 443NS and Metco 450NS composite powders. Their role is to ensure good bonding of the top sealing layers with the compressor parts and to protect the compressor parts from the external influence of gases.. Particles of Metco 443NS (NiCr/Al) and Metco 450NS (Ni/Al) composite powders are made by the dry spray technique. The NiCr/Al powder consists of 94% NiCr (75% Ni, 19%Cr) and 6%Al. The powder had a granulation range of -120 + 45 jm (Metco 443NS Nickel-Chromium / Aluminum Composite Powder, 2000, Technical Bulletin 10-130, Sulzer Metco). Composite powder particles of Ni/Al consist of 95.5% Ni and 4.5% Al. The powder had a granulation range of- 88 + 45jm (Metco 450NS Nickel / Aluminum Composite Powder, 2000, Technical Bulletin 10-136, Sulzer Metco). For soft sealing coatings intended for operation up to 480°C, Metco 307NS-1 (Ni/25% graphite) and Metco 308NS-1 (Ni/15% graphite)composite powders were used (Metco 307NS -1,Metco 308NS - 1 Nickel Graphite Powder, 2000, Technical Bulletin 10115, Sulzer Metco). Powders are manufactured by cladding graphite particles with Ni particles by the dry spray method. The powders had a range granulation of 90 + 30|jm (Metco 307NS - 1,Metco 308NS - 1 Nickel Graphite Powder, 2000, Technical Bulletin 10-115, Sulzer Metco). To produce a soft sealing designed for operations up to 345°C, a mechanical mixture of powders AlSi12 and polyester was used. The powder consists of 60% of the Al-Si12 alloy and 40% of polyester. The powder had a granulation particles of a range of - 106 + 10 jm (Metco 601NS Aluminum - Polyester Powder, 2000, Technical Bulletin 10-141, Sulzer Metco). The substrate material of the samples on which the layers of the sealing coating system were deposited was made of stainless steel X15Cr13 (EN 1.4024) in the thermally unprocessed state. The testing of the mechanical properties of the coating layers was done in accordance with the Pratt & Whitney standard (Turbojet Engine - Standard Practices Manual (PN 582005), 2002, Pratt & Whitney, East Hartford, USA) and TURBOMECA standard (Turbojet engine-standard practices manual, TURBOMECA). For hardness testing and the evaluation of the microstructure of sealing coatings in the deposited state, C.4171 (X15Cr13 EN 10027) steel samples were made, with the dimensions 70x20x1.5mm. The microhardness of the NiAl and NiCrAl coating bond was tested using the HV03 method and the macrohardness of Ni-15% graphite, Ni-25% graphite and AlSi12 polyester sealing coatings was tested using the HR15y method with a Rockwell steel ball of 12.7 mm in diameter and a load of 15 kg. The macrohardness of the coatings was measured along the layers. Out of five performed readings of the hardness values of the layers in
the middle and at the ends of the samples, two extreme values were rejected. The three remaining values are shown in their minimum and maximum values. The samples for testing bond strength were made of the same steel with the dimensions of 025x50 mm. Tensile tests were carried out at room temperature on the hydraulic equipment at a rate of 10 mm/min. For each compression part,a relevant groups of samples,three specimens for each part, were made. The samples were rotated together with the compressor parts at a certain rotational speed in order to obtain the same conditions of depositing sealing coatings. The results obtained were averaged and the bond strength mean values are shown in the paper.
The microstructure of the deposited layers was examined on an optical microscope - OM. The analysis of the share of micro pores in the coating was performed by treating 5 photos at 200X magnification. The paper presents the mean values of the share of micro pores in the coating. Table 1 contains the names of the TV2-117A turbojet engine compressor parts, types of material the parts were made of as well as the working conditions for the parts with deposited new systems of sealing coatings.
The compressor consists of focusing devices of IV - IX degrees, compressor front body, compressor working rings of V degree to X degree and the air labyrinth ring made of titanium alloy intended for military aviation industry. The titanium alloy has the Russian designation OST 1 90173-75 (VT-5) and the aluminum content of 4.3-6.2% Al.
Table 1 - Parts of the TV2-117A turbo-jet engine compressor Tabela 1 - Delovi kompresora turbo-mlaznog motora TV2-117A
No. Name of parts Material Working conditions
1. Compressor focusing devices of IV degree to IX degree VT-5 Air t =100-125°C, P = 4 -7 bar
2. Compressor front body VT-5 Air t =100°C, P = 4 bar
3. Compressor working rings of V degree to X degree VT-5 Air t =100-125°C, P = 4 -7 bar
4. Air labyrinth ring VT-5 Air t =100-125°C P = 4 bar
The powder manufacturer, Sulcer Metko, prescribed that the powder should be deposited by its plasma spray systems labeled Metco 9M, 7M and 3M applying the prescribed deposition parameters. Therefore, the application of other plasma spray depositing systems requires that the depositing parameters must be tested and optimized. In previously published works (Mrdak, 2012b, pp.71-89), (Mrdak, 2013a, pp.69-88), the parameters for SG-100 and MINI - GUN II plasma guns of the Plasmadyne company were opti-
mised using fixed samples on special tools. To obtain identical microstructures and mechanical properties of the sealing coating system on the accompanying samples and on the cylindrical parts of the compressor, the deposition of powders was performed in specially made tools for the deposition on both the compressor parts and specimens. The deposition of powders was performed under the same conditions on the samples and the compressor parts with a particular rotational speed and the plasma gun rate.
In this experiment, the atmospheric plasma system of the Plazmadayn company and the plasma gun MINI - GUN II were used. Numerous samples were made and the paper presents the optimal parameters used for depositing coatings on the compressor parts and tested on the TV2-117A turbojet engine at the test station and on an Mi-8 (HT-40) helicopter intended for flight tests. The coatings were deposited on the roughened and preheated samples and compressor parts at a temperature of 90-120°C. Because of the geometry of the parts - the focusing devices of IV - IX degrees, the front of the compressor body, the compressor work rings of V -X degrees and the air ring labyrinth - the powder depositing was done with a specially constructed plasma gun MINI - GUN II, with the dimensions 025 X 600 mm. The plasma gun consisted of: A 2084 - F65 anode, K1083 - 129 cathode and GI2084 B - 103 gas injector. The deposition of all the coatings was performed with the power supply of 40KW. The bond layers of NiCrAl and NiAl coatings were deposited with an Ar-He mixture of plasma gases, while the sealing layers of the coatings with Ar were deposited withhout the secondary plasma gas of He.
Three types of systems of sealing coatingswere made: NiCrAl/Ni - 15% graphite, NiCrAl/Ni - 25% graphite and NiAl/AlSi12 - polyester. In all parts, the thickness of the NiCrAl bond layers with a single pass of the plasma gun was 25 jm. The thickness of the sealing Ni - 15% graphite and Ni - 25% graphite layers with a single pass of the plasma gun was 60| m. The thickness of the NiAl layer on the air labyrinth ring with a single pass of the plasma gun was 20 jm. The thickness of the sealing AlSi12 - polyester layer on the air ring with one pass of the plasma gun was 100 jm.
Table 2 shows the plasma spray parameters of the powders deposited with a MINI - GUN II plasma gun on the focusing devices of IV degree to IX degree. The thickness of the bond layers deposited with the NiCrAl powder was from 0.1 to 0.15 mm, and the thickness of the sealing coatings made of the powder of Ni-25% of graphite was 0.65 to 0.7 mm. The sealing coating thicknesses were increased by 0.3 mm for machining purposes.
At the front of the compressor body, the thickness of the bond layers with the deposited NiAl powder was from 0.1 to 0.15 mm, and the thickness of the top layer of the sealing coating made of the powder of Ni-15% of graphite was from 0.65 to 0.7 mm. The sealing coating thicknesses were increased by 0.3 mm for machining purposes.
Table 2 - Plasma spray parameters Tabela 2 - Plazma sprej parametri
Deposition parameters NiCrAl Ni -15% graphite Ni -25% graphite NiAl AlSi12-polyester
Plasma current, (A) 800 700 700 800 700
Plasma Voltage, (V) 39 38 38 39 38
Primary plasma gas flow rate, Ar (l/min ) 75 75 75 75 75
Secondary plasma gas flow rate, He (l/min) 50 -- -- 50 --
Carrier gas flow rate, Ar (l/min ) 7 9 9 7 6
Rotation of the powder disk, ( o/min ) 2.5 3.2 3.2 2.5 4.5
Stand-off distance of the plasma gun, ( mm ) 60 65 65 60 80
Circumferential speed of the part ( mm/s ) 500 250 250 500 250
Plasma gun rate, ( mm/s ) 3 3 3 3 3
On the compressor working rings of the V - X degrees, the bond layers of the NiCrAl coatings were deposited with a thickness of 0.15 to 0.2 mm. The thicknesses of the top sealing coatings deposited with powder Ni - 25% of graphite were thicknesses of 0.8 to 0.85 mm. Also, for machining purposes, the coating thicknesses of the sealing coatings were increased by 0.3 mm.
On the air labyrinth ring, the coating bond layer is made of NiAl powder with a thickness of 0.1 to 0.15 mm, and the top sealing layer of the coating is made of AlSi12-polyester powder with a thickness of 0.6 -0.65 mm. The thickness of the sealing layer includes the additional 0.3 mm for machining purposes.
The machining of the Ni-15% graphite and Ni-25% graphite sealing coatings deposited on the compressor parts was performed using the method of coarse finishing of scuffing and fine finishing of scuffing with cutting tools - a knife with a WC plate. During the machining, no cooling of the machining surface was applied.. Table 3 shows the parameters of the machining of Ni-15% graphite and Ni-25% graphite coatings deposited on the compressor focusing device of IV - IX degrees, the compressor front body and the compressor working rings of V - X degrees.
Table 3 - Parameters of machining Ni - 15% graphite and 25% Ni graphite coatings Tabela 3 - Parametri masinske obrade Ni - 15% grafit i Ni -25 % grafit prevlaka
Methods Depth of cut per pass mm Number of revolutions o/min Gait mm/o roughness |jm
Coarse finishing of scuffing 0.2 - 0.5 30 - 60 0.1 10-15
Fine finishing of scuffing 0.1 - 0.2 30 - 60 0.1 10-15
Table 4 shows the parameters of machining the AlSi12 - polyester coating deposited on the air labyrinth ring. The machining of the coating was done by combining coarse and fine grinding finishing. During machining, the treated surface was cooled.
Table 4 - Parameters of machining the AlSi12 - polyester coating Tabela 4 - Parametri masinske obrade AlSi12 - poliester prevlake
Methods Cutting tools Sign Cutting speed m/min Number of revolutions o/min Step mm/o
Coarse finishing of scuffing Knife with plate WC WC r = 0.5 150 20-30 0.2
Fine finishing of scuffing Diamond knife WC r = 0.5 150 30 0.04
The investigation of the coating sealing effect on the parts of the compressor was done at a test station with the operating time of the TV2-117A turbojet engine of 42 hours and on an Mi-8 (HT-40) helicopter intended for testing.
The coating wear was determined based on the change in size of the sealing surfaces before and after the testing. The measurement of the dimesions was done on a MAUSER ML 28 coordinate measuring machine at eight measuring points around the perimeter of the cylindrical parts. This paper presents the mean wear value of sealing coatings in mm, compared with the values of the allowed tolerance of machine-processed parts of the compressor.
dT>
Results and discussion
Figure 1 shows a part of the focusing device of IV to IX degrees of the TV2 - 117A turbojet engine compressor on which the system of NiCrAl / Ni-25% graphite sealing coatings was deposited. The figure shows the microstructures of the bond coating (a) and the top sealing coating (b). The layers of the NiCrAl bond coating are evenly deposited on the focusing device with good mechanical properties and structural characteristics. The red arrows mark the surfaces where the system of sealing coatings was deposited.
Figure 1 - Part of the focusing device of IV - IX degrees of the compressor and the microstructures of the system of the NiCrAl / Ni-25% graphite sealing coatings Slika 1 - Deo usmeravajuceg aparata od IV - IX stepena kompresora i mikrostrukture sistema zaptivne prevlake NiCrAl/ Ni-25%grafit
The NiCrAl bond coating had the microhardness values of 308-325 HV03. The values are above min.170HV03 prescribed by the standard (Turbojet engine-standard practices Manuel, Turbomeca). The even microhardness values indicate an even distribution of oxides and pores in the deposited layers. The tensile bond strength of the system of NiCrAl/Ni - 25% graphite coatings had a value of 43 MPa and is above the minimum value of 32MPa prescribed by the standard (Turbojet engine-standard practices Manuel, Turbomeca). The character of the de-
struction of the coatings was the adhesion on the coating / substrate interface, which indicates the good cohesive strength of the coating lamellae. The analysis of the micrographs revealed that in the NiCrAl coating bond layers the proportion of micro pores was under 2%. The coating consists of the lamellae of the solid solution of chromium and aluminum in light blue y - Ni (Cr, Al) nickel and inter-lamellar oxide phases of NiO, NiCr2O3, Cr2O3, CrO3 evenly distributed on the boundaries of the lamellae of the solid solution, dark blue in color and marked with red arrows (Brossard, et al., 2009, pp.1-9), (Mrdak, 2012, pp.5-16), (Mrdak, 2012a, pp.182-201). The oxides formed during the deposition of the powder which reacts with the oxygen from the air and with the oxygen incorporated into the plasma jet from the surrounding atmosphere. In the coating layers, there are also micro pores, dark blue, marked with red arrows. In the coating layers, unmelted particles and precipitates are not present. The Ni - 25% graphite sealing coating had the macrohardness values in the range of 78-83 HR15y. The hardness values were quite even, which indicates that the layers of the Ni - 25% graphite coating were continuously and uniformly deposited on the bond layers. This was confirmed by the metallographic examination of the coatings. At the cross section of Ni-25% graphite coating there are no unmelted particles, micro cracks networks or macro cracks, which is of essential importance for the good functionality of coatings in exploitation. The structure of Ni -25% graphite coating is lamellar. Nickel, white, is uniformly deposited throughout the cross section, which gives good strength to the coating as well as toughness, and resistance to oxidation, corrosion and erosion. The graphite in light blue marked by red arrows is, as a solid lubricant and a means to control the porosity, uniformly distributed in the coating. It is surrounded and closed by a metal base of Ni, which is very important because it increases the resistance of graphite sealing coatings to thermal shocks. Between the Ni and graphite lamellae, there are micro pores in dark blue. The analysis of the micrographs have shown that the proportion of micro pores was 16% in the layers of Ni - 25% graphite sealing coating, which is in accordance with the standards and the regulations of the powder manufacturer.
Figure 2 shows the front body of the TV2 - 117 A turbojet engine compressor, consisting of two halves. The red arrows mark the places on the compressor body where the systems of NiAl/Ni-15% graphite sealing coatings are deposited. Figure 2(a) shows the microstructure of the NiAl bond coating and Figure 2 (b) shows the microstructure of the top 15% Ni-graphite sealing coating. The NiAl bond coating had the mi-crohardness values of 165 - 181HV03, and the layers of Ni-15% graphite sealing coatings from 86 to 89 HR15y. The sealing system of the NiAl/Ni-15% graphite coating had a value of the bond tensile strength of 44 MPa.
C4D
X
o >
LO
O <N
of
yy
0£ ZD O O
_l
<
o
X
o
LU
I—
>-
Q1 <
I—
OT <
-J
CD >Q
x
LU I—
O
O >
The mechanical properties of microhardness and tensile bond strength of the systems of NiAl/Ni-15% graphite sealing coatings are above the minimum values prescribed by the Pratt & Whitney standard (Min.140 HV03 and Min.35 MPa) (Turbojet Engine - Standard Practices Manual (PN 582005), 2002, Pratt & Whitney, East Hartford, USA ).
Figure 2 - The compressor front body in the TV2 - 117 A turbojet engine and the microstructures of the system of the NiAl / Ni-15% graphite sealing coating Slika 2 - Prednje telo kompresora turbomlaznog motora TV2 - 117 A i mikrostrukture sistema zaptivne prevlake NiAl / Ni-15%grafit
The character of the coatings system destruction was the adhesion at the coating / substrate interface. The analysis of the micrographs of the NiAl bond coating showed that the proportion of pores was below 2%. In the layers of the Ni - 15% graphite sealing coating the proportion of micro pores was 13%, which is a lower proportion compared to the Ni - 25% graphite sealing coating. The microstructure of the NiAl bond coating is lamellar. The coating consists of a lamella of the solid solution of aluminum in nickel a - Ni (Al), light blue, and NiO and Y-Al2O3 inter-lamellar oxides
evenly distributed over the lamellae solid solution boundaries, dark blue and marked with red arrows (Knotek, et al.,1980, pp.282-286), (Mrdak, 2013b, pp.7-22), (Svantesson, Wigren, 1992, pp.65-69).
Figure 3 shows the air labyrinth ring (1) and the working ring of the compressor of the V -X degrees (2) of the TV2 - 117A turbojet engine.
Figure 3 - Air labyrinth ring (1) with the microstructure of the NiAl / AlSi12 polyester coating system and the working ring of the compressor of the V - X degrees (2)
with the microstructure of the NiCrAl / Ni-25% graphite coating system Slika 3 - Prsten vazdusnog labirinta (1) sa mikrostrukturama sistema prevlaka NiAl / AlSi12 poliester i radni prsten kompresora od V - X stepena (2) sa mikrostrukturama sistema prevlaka NiCrAl / Ni-25%grafit
X
o >
LO
o CM
a:
yy
0£ ZD
o
o <
o
X
o
LU
I— >-
CC <
I—
OT <
-J
CD >Q
x
LU I— O
o >
The air labyrinth ring is marked with number 1 and the red arrows mark the surface on which the NiAl/AlSi12-poliester sealing coating system was deposited. Figure (a) shows the microstructure of the NiAl bond coating, and (b) the microstructure of the top AlSi12- poliester sealing coating. The NiAl bond coating was deposited with the values of microhardness of 178 - 203HV03, and the AlSi12-polyester sealing coating with the values of 72-75 HR15y. The hardness values of the coatings are very even, which indicates a smooth and continuous deposition of coating layers on the substrate. The tensile bond strength of the AlSi12 - polyester sealing coating in the system with the NiAl bond coating was 30 MPa. The mechanical properties were consistent with the Pratt & Whitney Standard (Turbojet Engine - Standard Practices Manual (PN 582005), 2002, Pratt & Whitney, East Hartford, USA) and with the characteristics prescribed by the powder manufacturers. In the microstructure of the NiAl bond coating whose base consists of a solid solution of aluminum in nickel a - Ni(Al) in light blue, there are NiO and y-Al2O3 oxides and micro pores as in the previous micrographs shown in Figure 2(a). The analysis of the micrographs of the NiAl bond coating showed that the proportion of micro pores was about 2%. The microstructure of the AlSi12 - polyester sealing coating consists of an AlSi12 alloy (white) which gives strength to the coating as well as resistance to erosion and provides a good bonding of AlSi12 particles with NiAl bond coating particles. The cross section of the AlSi12 -polyester coating does not show unmelted particles or the network of micro and macro cracks, which is very important for the behavior of the coatings during the compressor operation. The second phase of polyester which serves as a solid lubricant for wear control and maintaining a constant gap during the compressor operation is surrounded, and thus closed, by the metal base of the AlSi12 alloy. Thus formed structure of the sealing coating helps to reduce the transmission of the coating on the blades and to reduce the coating breaking or erosion. The analysis of photomicrographs of the AlSi12 sealing coating showed that the proportion of micro pores was 5%. In Figure 3 (b) it can be seen that the layers of AlSi12 and the polyester have a continuous mesh structure. The network of polyester is given in blue.
Number 2 in Figure 3 marks the working ring and the red arrows mark the surface on which the NiCrAl/Ni-25%graphite sealing coating system was deposited. The photomicrograph (a) shows the microstructure of the NiCrAl bond coating and (b) shows the microstructure of the top Ni - 25% graphite sealing coating. The NiCrAl bond coating had the microhardness values of 305-331 HV0 3. The Ni - 25% graphite sealing
coating had the macrohardness values within the range of 79-84 HR15y. The NiCrAl / Ni - 25% graphite sealing coating system had the bond strength value of 43 MPa. The microhardness values and tensile bond strength values are above the minimum values prescribed by the TUR-BOMECA standard (min.170HV03 and 35MPa) (Turbojet engine - standard practices manuel, TURBOMECA). The structure of the NiCrAl coating layer is a lamellar microstructure described above, which consists of a solid solution of y - Ni (Cr, Al) in light blue and oxide phases in dark blue. Between the lamellae of the substrate and the lamellae of oxide phases, there are micro pores in dark blue marked with red arrows (Brossard, et al., 2009, pp.1-9), (Mrdak, 2012, pp.5-16), (Mrdak, 2012a, pp.182-201). In the structure of the Ni - 25% graphite coating,a metal network of Ni in white can be seen. Particles of graphite in light blue are evenly distributed in the Ni network. Micro pores are dark blue, clearly distinct and marked with red arrows. The analysis of the photomicrographs has shown that, in the NiCrAl coating layers, the share of micro pores was below 2%, and in the Ni - 25% graphite coating layers it was 17%, which is in accordance with the standards and recommendations of the powder manufacturer.
The wear of sealing coatings after testing the sealing effect on the coatings applied on the parts of the TV2-117A turbojet engine compressor at the test station and on the Mi-8 (HT-40) helicopter intended for trial testing was less than the tolerance of the machining of sealing coatings. The wear of the Ni-25% graphite coating on the focusing devices of IV - IX degrees of the compressor motor was 0.033 mm. The tolerance of the machining of the Ni-25% graphite sealing layer in the focusing devices is 0.05 mm. The wear of the Ni-15% graphite coating on the compressor front body was 0.015 mm. The tolerance of the machining of the Ni-15% graphite sealing layer in the front body of the compressor is 0.02 mm. The wear of the Ni-25% graphite coating on the compressor working ring of V -X degrees was 0.031 mm. The tolerance of the machining of the Ni-25% graphite sealing layer in the compressor working ring is 0.05 mm. The consumption of the AlSi12 polyester coating on the compressor air ring was 0.025 mm. The tolerance of the machining for the AlSi12 - polyester layer is 0.05 mm. The wear in coatings on all parts was within the permissible machining tolerance for the top sealing layer. Low consumption of sealing coatings has enabled keeping the clearance at the lowest value which reflected to the degree of efficiency of the compressor and fuel consumption. Small wear of APS - sealing coatings increased a degree of efficiency of the compressor by 10% while reducing fuel consumption by 8%.
Conclusion
The research into the application of APS soft abrasive coatings on parts of the TV2 - 117A turbojet engine compressor has shown that there was a significant influence of the type of technology and materials on the effect of sealing the compressor and on keeping the clearance in exploitation at the minimum value. The sealing coating systems have shown that their characteristics significantly affect the performance of the compressor during engine operation. The analysis of the structural and mechanical characteristics of the coatings in the laboratoryas well as the 42-hour testing of the compressor parts at the test station and on the Mi-8 (HT-40) test helicopter has shown the following:
The layers of bond and sealing coatings in the deposited state had good structural - mechanical properties that satisfy the criteria prescribed by Pratt & Whitney and Turbomeca standards. There are no macrocracks and micro-crack networks on the surfaces of the sealing coatings. The surface of the coatings had no traces of cracks and grooves of scraping blades. Segment separation of the coating parts from the surface was not found on the sealing coatings.
The sealing coating systems had good adhesion and cohesive strength of layers in exploitation. The compressor parts did notshow the delamination of coatings, the peeling of coatings through layers or the separation of coating layers from the surface of the parts.
There is no ovality on the inner surfaces of the compressor parts, which shows even wear of sealing coatings in exploitation. The average value of wear on the sealing coating of Ni-25% graphite on the directional devices of IV-IX degrees was 0.033 mm. On the sections of the compressor front body, the average value of wear on the sealing coating of Ni-15% graphite was 0.015 mm. On the compressor working ring of V-X degrees, the average value of the wear of the Ni-25% graphite coating was 0.031 mm. The AlSi - polyester sealing coating on the compressor air labyrinth ring had wear of 0.025 mm. On all parts of the TV2 -117 A engine compressor, the wear of the sealing coatings was less than the permitted machining tolerances. Low consumption of sealing layers provided the minimum clearance and efficient sealing while reducing the loss of pressure in the compressor. This has increased the level of efficiency of the compressor by 10% while reducing fuel consumption by 8%. The results of the research show that binary sealing coatings have been successfully applied in the process of general repair of the TV2 -117A turbojet engine compressor.
Literature
Brossard, S., Munroe, P.R., Tran, A.T.T., & Hyland, M.M. 2009. Study of the effects of surface chemistry on splat formation for plasma sprayed NiCr onto stainless steel substrates. Surface&Coatings Technology, pp.1-9. SCT-15342.
Demasi, J.T. 1994. Protective coating in the gas turbine engine. Surf. Coat. Technol, 68-69, pp.1-9.
Knotek, O., Lugscheider, E., & Cremer, K.H. 1980. Alumina and Alurninide Formation in Nickel Aluminum Spraying Powders. . In: Proceedings of Ninth International Thermal Spray Conference. The Hague, pp.282-286
Metco 443NS Nickel-Chromium/Aluminum Composite Powder 2000. Sulzer Metco. Technical Bulletin 10-130.
Metco 450NS Nickel /Aluminum Composite Powder 2000. Sulzer Metco. Technical Bulletin 10-136.
Metco 307NS - 1,Metco 308NS - 1 Nickel Graphite Powder 2000. Sulzer Metco. Technical Bulletin 10-115.
Metco 601NS Aluminum - Polyester Powder 2000. Sulzer Metco. Technical Bulletin 10-141.
Mrdak, M. 2010. Uticaj brzine depozicije praha na mehanicke karakteristike i strukturu APS - NiCr/Al prevlake. Vojnotehnicki glasnik/Military Technical Courier, 58(4), pp.5-16.
Mrdak, M. 2012a. Study of the properties of plasma deposited layers of nickel-chrome-aluminum-yttrium coatings resistant to oxidation and hot corrosion. Vojnotehnicki glasnik/ MilitaryTechnical Courier, 60(2), pp.182-201.
Mrdak, M. 2012b. Study of the characteristics of plasma spray sealing aluminum -silicon- polyester coatings. Vojnotehnicki glasnik /Military Technical Courier, 60(3), pp.71-89.
Mrdak, M. 2013a. Characterization of nickel - graphite sealing coatings in the system with the nickel - aluminum bonding coating. Vojnotehnicki glasnik / MilitaryTechnical Courier, 61(1), pp.69-88.
Mrdak, M., Vencl, A., Nedeljkovic, B., & Stankovic, M. 2013. Influence of plasma spraying parameters on properties of the thermal barrier coatings. Materials Science and Technology, 29(5), pp.559-567.
Mrdak, M. 2013b. Structure and properties of plasma sprayed APS - Ni20Al coatings. Vojnotehnicki glasnik/ Military Technical Courier, 61(2), pp.7-22.
Mrdak, M. 2014a. Characterization of the wear resistant aluminum oxide 40% titanium dioxide coating. Vojnotehnicki glasnik/Military Technical Courier, 62(1), pp.7-22.
Mrdak, M. 2014b. Mechanical Properties and Microstructure of Vacuum plasma Sprayed Cr3C2-25(Ni20Cr) Coatings. Vojnotehnicki glasnik / Military Technical Courier, 62(2), pp.7-26.
Naser, H. 1988. Some Areas of Application of Plasma Spry Coatings in the Field of Aviation. . In: 1st Plasma Technik Symposium, Lucerne, pp.75-84
Novinski, E.R. 1990. Process parameter impact on the physical properties of an advanced abradable coating. In: Proceedings of 3rd National Thermal Spray Conference. USA, pp.151-157
Novinski, E.R. 1991. The design of thermal sprayed abradable seal coatings for gas turbine engines. In: Proceedings of 4th National Thermal Spray Conference. USA, pp.451-454
Oka, T. 1990. Basic characteristic of different abradable coatings. In: Proceedings of International Thermal Spraying Conference. Germany, pp.58-67
X
о >
ю
о см
ОС
УУ 0£ ZD О
о <
о
X
о ш
н >-
СС <
н
ю <
-j
О ■О
X ш н О
О >
Svantesson, J., & Wigren, J. 1992. A Study of Ni-5wt.% Al coatings produced from different feedstock powder. Journal of Thermal Spray Technology, 1(1), pp.65-70. doi:10.1007/BF02657019
Tosnar, L. 1988. Plasma Sprayed Seal Coatings. . In: Proc. Plasma Technik Symposium, Lucerne. , pp.257-262
Turbojet Engine - Standard Practices Manual (PN 582005) 2002. East Hartford, USA: Pratt & Whitney.
Turbojet engine-standard practices manuel, TURBOMECA .
Vencl, A., Arostegui, S., Favaro, G., Zivic, F., Mrdak, M., Mitrovic, S., & Popovic, V. 2011. Evaluation of adhesion/cohesion bond strength of the thick plasma spray coatings by scratch testing on coatings cross-sections. Tribology International, 44(11), pp.1281-1288.
Yi, M. 1997. Erosion wear of AlSi-graphite and Ni/graphite abradable seal coating. Trans. Nonferrons Met. Soc. China (English letter), 8(2), pp.99-102.
Yi, M. 1999. Friction and wear behaviour and abradability of abradable seal coating. Wear, 231, pp.47-53.
АНАЛИЗ ЭФФЕКТА УПЛОТНЕНИЯ КОМПРЕССОРА ТУРБОРЕАКТИВНОГО ДВИГАТЕЛЯ ТУ2-117А ПОД ВОЗДЕЙСТВИЕМ ПЛАЗМЕННОГО НАПЫЛЕНИЯ ИЗНОСОСТОЙКИХ ПОКРЫТИЙ
ОБЛАСТЬ: химические технологии
ВИД СТАТЬИ: оригинальная научная статья
ЯЗЫК СТАТЬИ: английский
Резюме:
Данное исследование раскрывает эффект уплотнения, нанесенного атмосферным плазменным напылением, на отдельные детали коспрессора турбореактивного двигателя Т^'2-117А. Впервые такой метод покрытия был применен по западной технологии плазменного напыления. С целью замены существующих уплотнительных материалов новыми классами материалов, обеспечивающих лучший эффект уплотнения и проход воздуха под высоким давлением через компрессор. Мягкие уплотнители разработаны в виде двойной системы, состоящей из нижнего слоя на базе N1ОгА1 и №А1 покрытия и верхнего слоя уплотнения на базе N1 -15% графита, N - 25% графита и А1Б1 - полиэстера.
В данной работе приведены параметры нанесения покрытия на детали компрессора, механические и микроструктурные харатеристики покрытия и соответствующий способ его нанесения. При анализе механических свойств покрытия применялся метод измерения микротвёрдости соединительных слоев HV0.3 и макротвердости уплотняющего слоя методом HR15W.
Были проведены испытания на растяжение до разрыва растягивающего напряжения слоев двойного покрытия. Микроструктура слоя была исследована под оптическим микроскопом - ОМ.
Оценка микроструктуры нанесенных слоев покрытия выполнена в соответствии со стандартными требованиями, предписанными производителями Pratt-Whitney и TURBOMECA.
Износ покрытия был определен сравнительным методом деформации уплотнительного слоя до и после проведения испытаний. Контроль формы был выполнен на координатно-измери-тельной машине MAUSER ML 28. В статье приводятся: средний процент износа, выраженный в мм и удельный процент износа механически обработанных деталей компрессора.
Испытания эффекта уплотнения деталей компрессора двигателя TV2-117A были проведены на летно-испытательной станции, при использовании вертолета Mi-8(HT-40). Проведенные испытания показали, что при применении новой системы уплотните-льных покрытий увеличивается эффективность компрессора на 10%, при одновременном снижении расхода топлива на 8%.
Ключевые слова: уплотнители, слои, двигатели, нанесение, компрессоры, покрытие.
ISTRAZIVANJE UTICAJA PLAZMA SPREJ ZAPTIVNIH PREVLAKA NA EFEKAT ZAPTIVANJA KOMPRESORA TURBOMLAZNOG MOTORA TV2 - 117A
OBLAST: hemijske tehnologije VRSTA C LANKA: originalni naucni clanak JEZIK CLANKA: engleski
Sazetak:
U ovom istrazivanju prikazan je efekat primene mekih zaptivki de-ponovanih atmosferski plazma sprej - APS procesom na delovima kompresora turbomlaznog motora TV2-117A. Na delovima kompresora primenjena je prvi put zapadna plazma sprej tehnologija i materijali. Cilj je bio da se izvrsi supstitucija postojeceg zaptivnog materijala sa no-vom klasom materijala, da bi se povecao efekat zaptivanja i obezbedio protok vazduha pod najvecim pritiskom kroz kompresor. Meke zaptivke su formirane kao dupleks sistemi koji se sastoje od donjeg veznog slo-ja na bazi NiCrAl i NiAl prevlaka i gornjih zaptivnih prevlaka na bazi slojeva Ni - 15% grafita, Ni - 25% grafita i AlSi - poliestera. U radu su prikazani parametri sa kojima su deponovane prevlake na delovima kompresora, mehanicke i mikrostrukturne karakteristike prevlaka proiz-vedenih sa optimalnim parametrima depozicije. Procena mehanickih karakteristika prevlaka uraúena je ispitivanjem mikrotvrdoce veznih slojeva metodom HV0.3 i makrotvrdoce zaptivnih slojeva metodom HR15W. Zatezne cvrstoce spoja dupleks sistema prevlaka ispitane su metodom kidanja na zatezanje. Mikrostrukture slojeva prevlaka su pro-cenjene na optickom mikroskopu - OM. Analiza mikrostruktura depono-
vanih slojeva uradena je u skladu sa standardom Pratt-Whitney i TUR-BOMECA. Pohabanost prevlaka odredena je na osnovu promene di-menzija zaptivnih povrsina pre i posle ispitivanja. Merenje dimenzija ra-deno je na koordinatnoj mernoj masini MAUSER ML 28. U radu je pri-kazana srednja vrednost pohabanosti izrazena u mm i uporedena sa vrednostima dozvoljenih tolerancija masinski obradenih delova kom-presora. Efekat zaptivanja delova kompresora ispitan je u sklopu motora TV2-117A na ispitnoj stanici i letnim ispitivanjem na helikopteru Mi-8(HT-40). Ispitivanja su pokazala da je novim sistemom zaptivnih pre-yy vlaka povecan stepen iskoriscenja kompresora za 10% uz smanjenu
§ potrosnju goriva za 8%.
ir
o
o <
o
X
Uvod
Razvoj novih generacija turbomlaznih motora i zahtev za vecu pou-u zdanost rada i resurs delova u eksploataciji, uticao je na vecu primenu
plazma sprej prevlaka. Razvijene su razlicite vrste kvaliteta prahova koji £ se primenjuju na komponentama vazduhoplova kao sto su: komponente
¡< niskog i visokog pritiska kompresora, komponente gasne turbine i kom-
ponente stajnog trapa (Mrdak, M., 2012b, pp. 71-89), (Mrdak, M., 2013a, pp. 69-88), (Vencí, A., et al., 2011, pp.1281-1288), (Mrdak, et al., 2013, pp.559-567), (Mrdak, M., 2014a, pp.7-22), (Mrdak, M., 2014b, pp.7-26). Na komponentama kompresora niskog i visokog pritiska turbomlaznog < motora primenjuju se meke abrazivne prevlake koje uzrokuju niskoener-
ej getske uslove trenja, koje su otporne na eroziju. Sistemi zaptivnih pre-
2 vlaka konstruisani su tako da se uzima u obzir nesaosnost rotora i di-
^ menzionalne promene uzrokovane promenom temperature. Zaptivni si-
i stemi prevlaka konstruisani su tako da se habaju bez ostecenja vrhova
lopatica odrzavajuci konstantan zazor (Tosnar, L., 1988, pp. 257-262). o Kod zaptivnih sistema koji se trose - consumption, potrebno je uravnote-
g zenje izmedu trosenja materijala pod uticajem toplote, zavrsne povrsin-
> ske obrade, otpornosti na eroziju i otpornosti na habanje. Sa plazma
sprej parametrima depozicije prahova omogucena je kontrola navedenih kriticnih karakteristika. Plazma sprej proces depozicije omogucuje kon-trolu poroznosti, gustine i debljine prevlaka da bi se dobili zaptivni slojevi trazenih karakteristika (Tosnar, L., 1988, pp.257-262). Meke zaptivne prevlake formiraju se kao dupleks sistemi sa plazma sprej tehnologijom. Za izradu donjeg veznog sloja cesto se koriste prahovi NiAl, NiCrAl i NiCrAlY (Mrdak, M., 2010, pp.5-16), (Mrdak, M., 2013b, pp.7-22), (Mrdak, M., 2012a, pp. 182-201). Debljina veznog sloja se krece od 0,005 -0,15 mm i mora da bude uskladena sa materijalom substrata i gornjim zaptivnim slojem. Uloga veznog sloja je da omoguci dobru adheziju sa substratom i dobru vezu sa gornjim zaptivnim slojem. Spoljni sloj ima osnovnu funkciju zaptivanja. Svetska istrazivanja u ovoj oblasti su pod-stakla na primenu novih materijala i plazma sprej tehnologije u postupku remonta kompresora turbomlaznog motora TV2-117A koji se proizvodi u Rusiji. Da bi se ostvarili postavljeni ciljevi, zazori izmedu komponenti u
kompresoru moraju da budu minimalni (Demasi, J.T., 1994, pp. 1-9). Ve-oma dobro zaptivanje gasa koji protice kroz kompresor smanjuje gubitke gasa uzrokovane curenjem. Takode, zaptivke treba da obezbede toplot-nu izolaciju kucista, i smanje uticaj temperature gasa u kucistu (Novin-ski, E.R., 1991, pp.451- 454), (Yi, M., 1999, pp.47-53). Za tu namenu ko-riste se prevlake koje se sastoje od metalne faze i nemetalne faze za samo - podmazivanje sa visokom poroznoscu (Oka,T., 1990, pp.58-67). Najvaznija svojstva koja treba da poseduju zaptivne prevlake su velika otpornost na trosenje struganjem lopatica i otpornost na eroziju gasa i stranih cestica koje su prisutne u gasu (Novinski, E.R., 1990, pp.151157), (Yi,M., 1997, pp.99 -102).
Cilj istrazivanja bio je da se plazma sprej tehnologijom i no vim materijalima ispita efekat zaptivanja kompresora turbomlaznog motora TV2 - 117A i izvrsi supstitucija postojecih zaptivnih materijala u remon-tu motora. Nove generacije materijala koje se primenjuju kao zaptivke na delovima kompresora motora trebale bi da boljom zaptivnoscu obezbede veci stepen iskoriscenja kompresora uz smanjenu potrosnju goriva. Uslov koji treba da ispune primenjeni materijali na delovima kompresora su da zaptivanjem obezbede protok vazduha temperature t =100 - 125°C kroz kompresor pod najvecim pritiskom. Ocekivani efekti su potvrdeni 42 casovnim ispitivanjem motora na ispitnoj stanici i letnim ispitivanjem na helikopteru Mi-8 (HT-40).
Materijali i eksperimentalni detalji
Za istrazivanje zaptivnih prevlaka upotrebljeno je pet razlicitih praho-va firme Sulzer Metco sa oznakom: Metco 443NS, Metco 450NS, Metco 307NS-1, Metco 308NS-1 i Metco 601 NS. Cestice kompozitnih prahova Metco 443NS (NiCr/Al) i Metco 450NS (Ni/Al) izradene su tehnikom suvog rasprsivanja. Prah NiCr/Al sastoji se od 94%NiCr (75%Ni, 19%Cr) i 6%Al. Temperatura topljenja NiCr legure je 1339 oC, a aluminijuma 660 oC. Prah je imao raspon granulacije od -120 + 45pm. Cestice kompozitnog praha Ni/Al se sastoje od 95,5% Ni i 4,5%Al. Prah je imao raspon granulacije -88 + 45pm. Za izradu mekih zaptivnih prevlaka namenjenih za rad do 480 °C koristili su se kompozitni prahovi Metco 307NS-1(Ni/25%grafit) i Metco 308NS-1(Ni/15%grafit). Prahovi su proizvedeni oblaganjem cestica grafita sa cesticama Ni postupkom suvog rasprsivanja. Temperatura topljenja prahova Ni-25%grafit i Ni-15%grafit je 145S°C. Prahovi su imali raspon granulata od - 90 + 30pm. Za izradu meke zaptivke namenjene za rad do 345 °C koristila se mehanicka mesavina prahova AlSi12 i polieste-ra. Prah se sastoji od 60% legure Al Si 12 i 40% poliestera. Temperatura topljenja AlSi12 praha je 425 °C koji je imao raspon granulacije cestica od - 106 + 10pm. Materijal substrata uzoraka na kome su deponovani slojevi sistema zaptivnih prevlaka bio je od nerdajuceg celika X15Cr13 (EN 1.4024) u termicki neobradenom stanju. Ispitivanje mehanickih karakteri-stika slojeva prevlake radeno je prema standardu Pratt & Whitney. Za ispitivanje tvrdoce i za procenu mikrostrukture u deponovanom stanju zaptiv-
X
o >
LO
O <N
C¿
ÜÜ
0£ ZD O
o <
o
X
o
LU
I— >-
Q1 <
I—
OT <
-J
O ■O
X LU I— O
O >
nih sistema prevlaka napravljeni su uzorci od celika C.4171 (X15Cr13 EN10027) dimenzija 70x20x1,5mm. Ispitivanje mikrotvrdoce veznih pre-vlaka NiAl i NiCrAl radeno je metodom HV0.3, a makrotvrdoce zaptivnih prevlaka Ni-15%grafit, Ni-25%grafit i AlSi12-poliester radeno je metodom HR15y koriscenjem Rockwell celicne kugle precnika 12,7 mm i opterece-nje od 15 kg. Uzorci za ispitivanje cvrstoce spoja napravljeni su od istog celika dimenzija 025x50 mm. Testovi zatezne cvrstoce spoja su vrseni na sobnoj temperaturi na hidraulicnoj opremi sa brzinom od 10 mm/min. Mi-krostruktura deponovanih slojeva ispitana je na optickom mikroskopu -OM. Kompresor na kome su primenjene prevlake se sastojao od usmera-vajuceg aparata od IV - IX stepena, prednjeg tela kompresora, radnih pr-stenova kompresora od V - X stepena i prstena vazdusnog labirinta na-pravljenih od legure titana namenjene za vazduhoplovnu vojnu industriju. Legura titana je ruske oznake OST 1 90173-75 (VT-5) sa sadrzajem alu-minijuma od 4.3-6.2% Al. U ovom eksperimentu koriscen je atmosferski plazma sistem firme Plazmadayn i plazma pistolj MINI - GUN II. Uraden je veliki broj uzoraka, a u radu su prikazani optimalni parametri sa kojima su deponovane prevlake na delovima kompresora, koji su ispitani u sklopu turbomlaznog motora TV2-117A na ispitnoj stanici i na helikopteru Mi-8 (HT-40) namenjenom za probna letna ispitivanja. Prevlake su deponova-ne na ohrapavljene i predgrejane uzorke i delove kompresora na temperaturi od 90 - 120°C. Zbog geometrije delova: usmeravajuceg aparata od IV - IX stepena, prednjeg tela kompresora, radnih prstenovima kompresora od V - X stepena i prstena vazdusnog labirinta, deponovanje prahova je radeno sa specijalno konstruisanim plazma pistoljem MINI - GUN II dimenzija 025 X 600 mm. Plazma pistolj se sastojao od : anode A 2084 -F65, katode K 1083A - 129 i gas injektora GI 2084 B - 103. Depozicija svih prevlaka uradena je sa snagom napajanja od 40KW. Vezni slojevi NiCrAl i NiAl prevlaka deponovani su sa mesavinom plazma gasovima Ar-He, a slojevi zaptivnih prevlaka sa Ar bez sekundarnog plazma gasa He.
Uradena su tri tipa sistema zaptivnih prevlaka kao sto su: NiCrAl / Ni -15% grafit, NiCrAl / Ni - 25% grafit i NiAl / AlSi12 - poliester. Na svim de-lovima, debljina veznih NiCrAl slojeva po jednom prolazu plazma pistolja bila je 25pm. Debljine zaptivnih Ni - 15%grafit i Ni - 25% grafit slojeva po jednom prolazu plazma pistolja bila je 60pm. Debljina deponovanog NiAl sloja na prstenu vazdusnog labirinta sa jednim prolazom plazma pistolja bila je 20 pm. Debljina zaptivnog AlSi12 - poliester sloja na prstenu vazdusnog labirinta sa jednim prolazom plazma pistolja bila je 100 pm.
Debljina veznih slojeva deponovanih sa prahom NiCrAl bila je od 0,1 - 0,15 mm, a debljina zaptivnih prevlaka izradenih od praha Ni-25%grafit bila je od 0,65 - 0,7 mm. Debljine zaptivnih prevlaka uvecane su za 0,3 mm zbog masinske obrade prevlaka.
Na prednjem telu kompresora, debljina veznih slojeva deponovanih sa prahom NiAl bila je od 0,1 - 0,15 mm, a debljina gornjih zaptivnih prevlaka izradenih od praha Ni-15%grafit bila je od 0,65 - 0,7 mm. Debljine zaptivnih prevlaka uvecane su za 0,3 mm zbog masinske ob-radu prevlaka.
Na radnim prstenovima kompresora od V - X stepena, deponovani su slojevi vezne prevlake NiCrAl debljine od 0,15 - 0,2 mm. Debljine gornjih zaptivnih prevlaka deponovanih sa prahom Ni - 25% grafit bile su debljine od 0,8 - 0,85 mm. Takode, zbog dodataka za masinsku ob-radu prevlaka debljine zaptivnih prevlaka su uvecane za 0,3 mm.
Na prstenu vazdusnog labirinta, vezni sloj prevlake je izraden od pra-ha NiAl sa debljinom od 0,1 - 0,15 mm, a gornji zaptivni sloj prevlake od praha AlSi12-poliester sa debljinom od 0,6 - 0,65 mm. U debljinu zaptiv-nog sloja uracunat je dodatak od 0,3 mm za masinsku obradu prevlake.
Masinska obrada zaptivnih prevlaka Ni-15%grafit, Ni-25%grafit i AlSi12 - poliester prevlake deponovanih na delovima kompresora ura-dena je metodom struganja gruba obrada i struganjem fina obrada sa reznim alatom - nozem sa WC plocicom.
Rezultati i diskusija
Slojevi vezne prevlake NiCrAl ravnomerno su deponovani na usmeravajucem aparatu sa dobrim mehanickim i strukturnim karakteri-stikama. Vezna prevlaka NiCrAl imala je vrednosti mikrotvrdoce od 308 - 325 HV03. Vrednosti su iznad min.170HV03 koje propisuje standard TURBOMECA. Zatezna cvrstoca spoja sistema NiCrAl / Ni - 25% grafit prevlaka je imala vrednost 43 MPa i iznad je minimalne vrednosti 32MPa propisane standardom TURBOMECA. Prevlaka se sastoji od lamela cvrstog rastvora hroma i aluminijuma u niklu y - Ni(Cr,Al) svetlo plave boje i medulamelarni oksidnih faza NiO, NiCr2O3, Cr2O3, CrO3 ravnomerno rasporedenih po granicama lamela cvrstog rastvora tamni-je plave boje oznacene crvenim strelicama (Brossard, et al., 2009, pp.1-9), (Mrdak, 2012, pp.5-16), (Mrdak, 2012a, pp.182-201). Zaptivna prevlaka Ni - 25%grafit imala je vrednosti makrotvrdoce u rasponu od 78 - 83 HR15y. Tvrdoce su bile dosta ujednacene, sto ukazuje da su slojevi Ni - 25%grafit prevlake kontinualno i ravnomerno deponovani na veznim slojevima. Analiza mikrofotografija je pokazala da je u sloje-vima vezne prevlake NiCrAl udeo mikro pora bio do 2%. Analiza mikrofotografija je pokazala da je u slojevima zaptivne Ni - 25% grafit prevlake udeo mikro pora bio 16%, sto je u skladu sa standardom i propisom proizvodac praha. Na telu kompresora deponovani su sistemi zaptivnih prevlaka NiAl/Ni-15%grafit. Vezna prevlaka NiAl imala je vrednosti mikrotvrdoce od 165 - 181HV03, a slojevi zaptivne prevlake Ni-15%grafit od 86 - 89 HR15 y. Cvrstoca spoja sistema NiAl/Ni-15%grafit prevlaka imala je vrednost 44 MPa. Mehanicke karakteristike mikrotvrdoce i za-tezne cvrstoce spoja sistema zaptivnih prevlaka NiAl / Ni-15%grafit iznad su minimalnih vrednosti koje propisuje standard Pratt & Whitney (min.140 HV03 i min.35 MPa). Analiza mikrofotografija vezne prevlake NiAl pokazala je da je udeo mikro pora bio ispod 2%. U slojevima zaptivne Ni - 15%grafit prevlake udeo mikro pora bio je 13%, sto je manji udeo u odnosu na zaptivnu prevlaku Ni - 25%grafit. Sistem zaptivne prevlake NiAl/AlSi12 poliester deponovan je na prstenu vazdusnog la-
d3>
X
o >
LO
O <N
C¿
ÜÜ
0£ ZD O
o <
o
X
o
LU
I— >-
Q1 <
I—
OT <
-J
O ■O
x
LU I— O
O >
birinta. Vezna prevlaka NiAl deponovana je sa vrednostima mikrotvrdoce od 178 - 203HV0 3, a zaptivna prevlaka AlSi12 poliester sa vrednostima od 72 - 75 HR15y. Zatezna cvrstoca spoja zaptivne prevlake Al-Si12 - poliester u sistemu sa veznom prevlakom NiAl iznosila je 30 MPa. Mehanicke karakteristike su bile u skladu sa standardom Pratt & Whitney. Analiza mikrofotografija vezne prevlake NiAl pokazala je da je udeo mikro pora bio oko 2% a u zaptivnoj prevlaci AlSi12 je udeo mikro pora bio 5%. Vezna prevlaka NiCrAl deponovana na radnim prste-novima imala je vrednosti mikrotvrdoce od 305 - 331 HV03. Zaptivna prevlaka Ni - 25%grafit imala je vrednosti makrotvrdoce u rasponu od 79 - 84 HR15y. Cvrstoca spoja sistema NiCrAl / Ni - 25% grafit prevlaka je imala vrednost 43 MPa. Vrednosti mikrotvrdoce i zatezne cvrsto-ce spoja iznad su minimalnih vrednosti koje propisuje standard TUR-BOMECA (min.170HV03 i 35MPa). Analiza mikrofotografija je pokazala da je u slojevima prevlake NiCrAl udeo mikro pora bio ispod 2%, a u slojevima Ni - 25%grafit prevlake 17%, sto je u skladu sa standardom I preporukom proizvodaca praha. Pohabanost Ni-25% grafit prevlake na usmeravajucim aparatima od IV - IX stepena kompresora motora bila je 0,033 mm. Tolerancija masinske obrade za zaptivni sloj Ni-25% grafit na usmeravajucim aparatima je 0,05 mm. Pohabanost Ni-15% grafit prevlake na prednjem telu kompresora bila je 0,015mm.Tolerancija masinske obrade za zaptivni sloj Ni-15% grafit na prednjem telu kompresora je 0,02 mm. Pohabanost Ni-25% grafit prevlake na radnim pr-stenovima kompresora od V - X stepena je bila 0,031 mm.Tolerancija masinske obrade za zaptivni sloj Ni-25% grafit na radnim prstenovima kompresora je 0,05 mm. Potrosnja AlSi12-poliester prevlake na prste-nu vazdusnog labirinta je bila 0,025mm.Tolerancija masinske obrade za AlSi12 - poliester sloj je 0,05 mm. Pohabanost prevlaka na svim de-lovima je bila u dozvoljenim tolerancijama masinske obrade za gornji zaptivni sloj.
Zakljucak
Istrazivanja primene APS mekih abrazivnih prevlaka na delovima kompresora turbomlaznog motora TV2 - 117A pokazala su da postoji veliki uticaj vrste tehnologije i materijala na efekat zaptivanja kompresora i na odrzavanje minimalnog zazora u eksploataciji. Sistemi zaptiv-nih prevlaka su pokazali da sa svojim karakteristikama bitno uticu na performanse kompresora u toku rada motora. Analizom strukturnih i mehanickih karakteristika prevlaka u laboratorijskim uslovima i ispitiva-njima delova kompresora u sklopu na ispitnoj stanici od 42 casa i let-nim ispitivanjem na probnom helikopteru Mi-8(HT-40) ustanovljeno je sledece: Slojevi veznih i zaptivnih prevlaka u deponovanom stanju imali su dobre strukturno - mehanicke karakteristike koje zadovoljavaju kriterijume propisane standardima Pratt & Whitney i TURBOMECA. Na povrsinama zaptivnih prevlaka ni su prisutne makro prskotine i mreze mikro prskotina. Povrsina prevlaka je bila bez tragova riseva i brazda
od struganja lopatica. Na zaptivnim prevlakama nije uoceno segment-no odvajanje delova prevlake sa povrsine. Sistemi zaptivnih prevlaka imali su dobru adhezionu i kohezionu cvrstocu slojeva u eksploataciji. Na delovima kompresora nije uoceno raslojavanje prevlaka, ljustenje prevlaka kroz slojeve i odvajanje slojeva prevlaka sa povrsina delova. Na unutrasnjim povrsinama delova kompresora nema ovalnosti sto go-vori o ravnomernom habanju zaptivnih prevlaka u eksploataciji. Prosecna vrednost pohabanosti zaptivne prevlake Ni-25% grafit na usme-ravajucim aparatima od IV- IX stepena bila je 0,033 mm. Na sekcijama prednjeg tela kompresora, prosecna vrednost pohabanosti zaptivne prevlake Ni-15%grafit bila je 0,015 mm. Na radnim prstenovima kompresora od V-X stepena, prosecna vrednost pohabanosti prevlake Ni-25%grafit bila je 0,031 mm. Zaptivni sloj AlSi - poliester na prstenu va-zdusnog labirinta pohaban je 0,025 mm. Na svim delovima kompresora motora TV2 -117 A pohabanost zaptivnih prevlaka bila je manja od dozvoljene tolerancije za masinsku obradu delova. Mala potrosnja zaptivnih slojeva obezbedila je minimalni zazor i efikasno zaptivanje i sma-njila gubitke pritiska u kompresorima. Ovim je povecan stepen iskori-scenja kompresora za 10% uz smanjenu potrosnju goriva za 8%. Na osnovu dobijenih rezultata istrazivanja, dvojni sistemi zaptivnih prevlka se uspesno primenjeni u postupku opste opravke kompresora turbo-mlaznog motora TV2 - 117A.
Kljucne reci; zaptivke, slojevi, motori, depoziti, kompresori, prevlake.
Datum prijema clanka/Paper received on: 10. 06. 2014.
Datum dostavljanja ispravki rukopisa/Manuscript corrections submitted on: 21. 06. 2014. Datum konacnog prihvatanja clanka za objavljivanje/ Paper accepted for publishing on: 23. 06. 2014.
CID
