CC BY
67
Подано результати чисельного аналiзу aepoóuHaMÍ4Hoi взаемодй лопатевих вЫщв осьового компресора у mpueuMÏp^My пото-щ идеального газу. Показано, що основний внесок в нестащонарт обурювання вносять гармошки з частотами, як дорiвнюють добутку частоти обертання на числа лопаток суЫдтх втщв
Ключовi слова: тривимiрний потш идеального газу, аеродинамiчна взаeмодiя,
чисельний метод
□-□
Представлены результаты численного анализа аэродинамического взаимодействия лопаточных венцов осевого компрессора в трехмерном потоке идеального газа. Показано, что основной вклад в нестационарные возмущения вносят гармоники с частотами равными произведению оборотной частоты на числа лопаток соседних венцов
Ключевые слова: трехмерный поток идеального газа, аэродинамическое взаимодействие, численный метод
□-□
The numerical analysis results for aerodynamic interaction of the blade rows of axial compressor in 3D ideal gas flow have been presented. There shown that the principal contribution in unsteady disturbance is brought by the harmonics with frequencies which is equal to the product of rotation frequency into the stator blades numbers
Key words:3D ideal flow, aerodynamic interaction, numerical method
■о о
УДК 621.165
THE AERODYNAMIC INTERACTION OF THE BLADE ROWS IN THE THREE STAGE COMPARTMENT OF AXIAL COMPRESSOR
В.И. Гнесин
Доктор технических наук, профессор, заведующий
отделом
Отдел нестационарной газодинамики и аэроупругости Институт проблем машиностроения им. А.Н. Подгорного Национальной академии наук Украины
г. Харьков Контактный тел.: 94-18-67 E-mail: gnesin@ipmach.kharkov.ua
Л.В. Колодяжная
Кандидат технических наук, старший научный сотрудник Институт проблем машиностроения им. А.Н. Подгорного Национальной академии наук Украины
г. Харьков Контактный тел.: 95-96-39 E-mail:lubov.kolodyazhnaya@gmail.com
Жандковски Ромуальд
Доктор технических наук, заведующий отделом Отдел динамики машин Институт проточных машин Польской академии наук
г. Гданьск
(Institute of Flow Fluid Machinery Poland, Gdansk)
E-mail: z3@imp.gda.pl
1. Introduction
The numerical analysis of unsteady aerodynamic loads for compressor So3 with taking into account the aerodynamic interaction of 3 stages in 3D ideal gas flow has presented.
The numerical method is based on the solution of the aerodynamic problem for the 3D ideal gas flow through the mutually moving rotor and stator blade rows [1-6].
3D ideal gas flow through the compressor stage with periodicity on the whole annulus is described by unsteady Euler equations in the form of conservation laws, which are integrated with use of the explicit monotonous finite-volume Godunov's difference scheme and hybrid H-H grid.
The algorithm proposed allows to calculate the compressor department with an arbitrary pitch ratio of rotor and stator blades by action of unsteady loads caused of flow nonuniformity.
There shown that the principal contribution in unsteady disturbance is brought by the harmonics with frequencies which is equal to the product of rotation frequency into the stator blades numbers.
1. Problem formulation
Three-dimensional (3D) transonic flow of inviscid non-heat conductive gas through a three stage compartment of axial compressor is considered in the physical domain (Fig.1), including the stator0 (ST0),the rotor wheel 1 (RW1), rotating with constant angular velocity, stator1
(ST1), the rotor wheel 2 (RW2), stator2 (ST2), the rotor wheel 3 (RW3), stator3 (ST3).
The meridional sections of compressor has been shown in Fig 1.
Fig. 1. The calculation domain
Taking into account unperiodicity of flow in circumferential direction the calculated domain includes all the rotor and stator blades. The calculated domain divides on seven subdomains having the common intersection in an axial gap. In each of subdomains the geometric and aerodynamic characteristics of rotor and stator are written in relative or absolute coordinate system rigidly fixed with rotating rotor wheel or stator blade respectively.
In which time moment the flow structure is characterized with periodicity on minimal angular step.
T - =
2n (kS0 + kR1 + kS1 + kR2 + kS2 + kR3 + kS3> (ZS0 + ZR1 + ZS1 + ZR2 + ZS2 + ZR3 + ZS3)
where zRi and zSi are the rotor and stator blades numbers, kSi and kRi are mutually simple numbers which are proportional to zRi and zSi.
In this case the calculated domain has the angular step Tmin and includes kS0 interblade passages of stator 0 , kR1 interblade passages of rotor 1, . kS1 interblade passages of stator 1, kR2 interblade passages of rotor 2, . kS2 interblade passages of stator 2, kR3 interblade passages of rotor 3, . kS3 interblade passages of stator 3.
The calculated domain divides on kS0 + kR1 + kS1 + kR2 + kS2 + kR3 + kS3 - segments, which of them includes a blade and has extent in circumferential direction equal to rotor blade row step or stator blade row step. In turn each of segments is discretized with use of H-H hybrid grid for rotor passage and H-grid for stator passage.
The tangential grids for peripheral sections of rotor blade and stator blade are shown in Fig. 2 respectively.
The every grid segment includes correspondently 10*10*84 grid sells for stator 0, 10*60*78 sells for rotor 1, 10*48*64 - for stator 1, 10*40*64 - for rotor 2, . 10*40*62 - for stator 2, 10*40*60 - for rotor 3, .10*30*60 - for stator 3.
d)
e)
g)
Fig. 2. The tangential grid for rotors and stators a) - ST0; b) - Rotorl; c) - ST1; d) - Rotor2; e) - ST2; f) - Rotor3; g) - ST3
The equations for the spatial transonic flow, including in general case strong discontinuities in the form of shock waves and wakes behind the exit edges of blades, are written in the relative Cartesians coordinate system rotating with constant angular velocity m, according to the full non-stationary Euler equations, presented in the form of integral conservation laws of mass, impulse and energy
[1, 7]:
—J fdQ + J F • n do + J HdQ = 0.
d t Q o Q
(1)
a)
b)
" p " pu 0
PU1 pu1 u + S1ip P ae1 - 2 P®u2
f = Pu2 ; F = pU2 u+Ô2iP ; H = P ae2 + 2P®u1
pu3 PU3 U + Ó3ÍP 0
E (E + p)u 0
Ô. .J'j=i
J1 [0j * i
c
f)
where f is the symbolic vector of conservative variables; F is the inviscid flux through the lateral area o with normal n , bounding the finite volume Q ; H is source vector which contains the noninertial terms due to the rotation of the coordinate system.
It is assumed that the unsteady flow fluctuations are due to rotor wheel rotation in nonuniform flow and the flow far upstream and far downstream from the blade row contains at most small perturbations of a uniform free stream. So, the boundary conditions formulation is based on one-dimensional theory of characteristics. The total system of boundary conditions can be represented in the following form [1, 7]: - before stator
To = To (x,y), p0 = p0 (x,y), a = a(x,y), y = y(x,y),
2a
V1
= 0;
- behind the rotor
p = p (x,y); dp - a2dp = 0; du1 -(ra2r - 2rau2) dt = 0; 2a
d
x-1
= 0.
+[(F3o)k+i -(F3o)k]+ H„Q„ = 0.
(2)
Here F1, F2, F3 are inviscid flux vectors ( F1, F2, F3)= F ■ n ; subscripts and superscripts correspond to previous and next time iterations. The gasdynamic parameters on the lateral sides (expressions in square brackets) are defined by the solving of the problem about the break-down of an arbitrary discontinuity on the moving interfaces between two adjacent cells (Rieman problem) by using a piecewise linear approximation of parameters in grid cells.
The time step At is constant for all calculated domain and is defined from the stability condition of the difference scheme
T ■ T ■ T
A t =-^^^-,
T =
1 max((jijl + a),(|u¡| - a) )
, i=x,y,z.
2. Numerical results
The numerical investigation has been performed for axial compressor, including the nozzle cascade and 3 compressor stages.
The blade rows number ratio is:
ZS0 = 42 ; ZR1 = 28 ; zS1 = 35 ; ZR2 = 42 ; zS2 = 42 ;
zR3 = 42; zS3 = 56. So calculated zone of periodicity includes 6 interblade passages of stator 0, 4 interblade passages of rotor 1, 5 interblade passages of stator 1, 6 interblade passages of rotor 2, 6 interblade passages of stator 2, 6 interblade passages of rotor 3 and 8 interbl-ade passages of stator 3.
The rotor rotation speed is 15000 rpm.
The boundary conditions at inlet and outlet have been accepted as follows:
- total pressure in absolute system p0 = 101000 Pa ;
- total temperature in absolute system T0 = 288 K ;
- flow angles in absolute system in radial and circumferential directions are given.
The backpressure at outlet behind stator blade row was given as it has shown in Fig. 3.
Here a = ^/%(p/ p) is the sound velocity; T0 and p0 are the total temperature and pressure; a and y are the flow angles in circumferential and meridional directions; x is the adiabatic coefficient.
On the blade surface moving with velocity w the normal relative velocity is set to zero
u-n = 0 .
The discretized form of equations (1) was obtained for an arbitrary moving grid by use of Godunov-Kolgan difference scheme with the 2nd order of accuracy, but in more universal
form, extended to three spatial coordinates [8] 1
—[3fn+1Qn+1 - 4f„Q„ + f„-iQ„-i] + [ (Fio)i+i - (Fe) ] +
[M;+1 - (F2°)j] +
Fig. 3. The total pressure at inlet and backpressure behind stator 3 distribution along the blade length
Below there presented numerical analysis of unsteady aerodynamic loads acting on the rotor blades of 1-3 rotor blade rows for the regime of 15000 rpm. This regime is characterized with mass flow rate of 20.1 kg/sec and pressure increase degree of 2.2.
In Figure 4 there shown the graphs of unsteady loads components (circumferential, axial and moment relatively the gravity center) acting on the blade radial layer for rotor 1 from periphery during the time of a rotor revolution and their amplitude-frequency spectrums.
To process the numerical results obtained it has been used a Fourier transformation of the unsteady time domain solution
F(t) = F0 + ^ F1i cos(2 n v it) +F2isin(2 nv it),
where F(t) is a physical unsteady load; F0 is the averaged value of load; F1i, F2i are the Fourier coefficients; i is the harmonic number; v is the 1st harmonic frequency. In the capacity of v there chosen the frequency of 250 Hz corresponding to time of a rotor revolution:
the time of rotor revolution is 0.004 sec; the revolution frequency is 250 Hz.
d
T - T +T - T +T - T
x y x z y z
h
their amplitude - frequency spectrum. It should be noted that predominant frequency for unsteady loads for rotor 2 is frequency 8750 Hz, while predominant frequency for rotor 3 is 10500 Hz. It can be explained that the principal contribution to unsteady loads is brought by disturbance which disseminates down the flow from previous stator blade row.
AO=-0 028
e) f)
Fig. 4. The aerodynamic force acting on the blade of rotor 1 (peripheral layer ) a),c),e) -circumferential, axial force and aerodynamic moment change; b),d),f) - amplitude-frequency spectrum
As we can see from graphs the principal contribution to the unsteady components of aerodynamic load acting on blade of rotor 1 is brought by harmonic corresponding to running frequency from stator 1 which is equal to vrev x zS1 = 250 x 35 = 8750 Hz (the maximum value in root layer), and by harmonic corresponding to running frequency from stator 0 which is equal to vrev x zS0 = 250 x 42 = 10500 Hz (the maximum value in peripheral blade layer). The amplitude of harmonic is equal to 2.5 ^ 3.0% from averaged value for axial and circumferential components, and 10 ^ 40% for aerodynamic moment.
Besides the amplitude-frequency spectrum of unsteady loads includes the harmonic with frequency of 250 Hz (rotation frequency) and 1750 Hz, corresponding to the frequency or periodicity zone.
The maximum values of aerodynamic load for circumferential force takes place at the root layer and decreases to the periphery, but axial force and moment increase from root to periphery.
In Figures 5-6 there presented the unsteady aerodynamic loads acting on the blade of rotor 2 and rotor 3, and
e) f)
Fig. 5. The aerodynamic force acting on the blade of rotor 2 (peripheral layer): a),c),e) -circumferential, axial force and aerodynamic moment change; b),d),f) - amplitude-frequency spectrum
a)
b)
c)
d)
e) f)
Fig. 6. The aerodynamic force acting on the blade of rotor 3 (peripheral layer ) a),c),e) - circumferential, axial force and aerodynamic moment change; b),d),f) - amplitude-frequency spectrum
Conclusions
The numerical calculations of 3D unsteady ideal gas flow through the compressor stage at n = 15000 rpm has been performed.
There presented the numerical analysis of aerodynamic loads acting on blades.
There shown that the principal contribution in unsteady disturbance is brought by the harmonic corresponding to running frequency which is equal to the product of rotation frequency into the stator blades number.
References
1. Gnesin V. Three-dimensional Transonic Unsteady Flow and
Variable Aerodynamic Forces in Transonic Unsteady Flow Turbine and Compressor Stages/ V. Gnesin // Proceedings of 7th Intern. Symp.on Unsteady Aerodynamics and Aero-elasticity of Turbomachines.- 1995.- Sept. 25-29, Fukuoka, Japan.- P.515- 532.
2. Haldemann C.W. Experimental Investigation of Vane Clocki-
ng in a One and 1/2 Stage High Pressure Turbine//ASME J. of Turbomachines.- 2005. - 127.- P.512-521.
3. Konig S. Experimental Investigation of the Clocking Effect in
a 1.5 - Stage Axial Turbine - Part1: Time Averaged Results/ S. Konig, B. Stoffel, M.T. Schobeiri// ASME J. of Turbomachines.- 2009. - 131. - P. 021003-1-12.
4. Konig S. Experimental Investigation of the Clocking Effect
in a 1.5- Stage Axial Turbine-Part 2: Unsteady Results and Boundary Layer Behaviour/ S. Konig, B. Stoffel, M.T. Schobeiri// ASME J. of Turbomachines.- 2009. - 131. - P. 021004-1-8.
5. Walker G.J. Periodic Transition on an Axial Compressor Sta-
tor-Incidence and Clocking Effects, Part 1 and Part 2 / G.J. Walker, J.D. Hughes and W.J. Solomon// ASME Paper No 98-GT-363 and 98-GT-364.-1998.
6. Dorney D.J. Full Annulus Simulations of Airfoil Clocking in a
1.5 Stage Axial Compressor/ D. J. Dorney// Intern. J.Turbo Jet Engines.- 1999. - 16. - P. 149-160.
7. Gnesin V. A Coupled Fluid-Structure Analysis for 3D Flu-
tter in Turbomachines/ V. Gnesin, R. Rzadkowski and L. Kolodyazhnaya// ASME 2000-GT-380, Intern. Gas Turbine and Aeroengine Congress, Munich, Germany, 8-11th, May.- 2000.- P. 1-9.
8. Gnesin V.I. A numerical modelling of stator- rotor interaction
in a turbine stage with oscillating blades/ V.I. Gnesin, L.V. Kolodyazhnaya and R. Rzadkowski// Fluid and Structure.- 2004. - 19.- P.1141-1153.
