The relationship between the circumferential velocity and energy losses in the flow part of the inflow turbine with partial blading of the runner Текст научной статьи по специальности «Строительство и архитектура»

Vestnik of Astrakhan State Technical University. Series: Marine engineering and technologies. 2024. N. 2 ISSN 2073-1574 (Print), ISSN 2225-0352 (Online)

Ship power plants and propulsion systems

Original article UDC 621.515.001.5

https://doi.org/10.24143/2073-1574-2024-2-57-64 EDN OWRZQM

The relationship between the circumferential velocity and energy losses in the flow part of the inflow turbine with partial blading of the runner

Aleksei A. Kriukov

The Far Eastern State Technical Fisheries University, Vladivostok, Russia, [email protected]

Abstract. Low-consumption turbomachines are devices that play an important role in the drive of various units in the field of shipbuilding, aircraft engineering and other branches of heavy engineering. They have some advantages over a high-average power turbine. The largest number of low-consumption turbomachines are made partial, i.e. with partial intake. The principle of a turbine with partial flapping of the impeller is considered as one of the types of partial turbomachines. The influence of the main velocity characteristic of the turbine stage on the loss of kinetic energy in the stage is investigated. The simulation of gas dynamic processes occurring in the turbine stage was carried out using the ANSYS Workbench software package. With the help of this complex, a three-dimensional geometric model of the turbine stage with varying degrees of impeller damping was created. By applying the finite element method, a computational grid, a computational model are generated, and boundary conditions of a numerical experiment are set. The result of the numerical experiment is graphs of the dependence of kinetic energy loss on the circumferential velocity (speed characteristics of the turbine stage). This dependence can be represented not only graphically, but also with the help of mathematical apparatus. An example of such an apparatus is the polynomial dependence. The considered mathematical design can be used in order to optimize mathematical models of gas flow in the flow part of a low-flow turbine. Cubic two-parameter polynomials of kinetic energy losses in the flow part of the nozzle and impeller are obtained, and an assessment of its applicability in the current mathematical model is given.

Keywords: nozzle diaphragm, loss coefficient, runner, kinetic energy, numerical method, experiment, calculation grid, gas dynamics, low-consumption turbine

For citation: Kriukov A. A. The relationship between the circumferential velocity and energy losses in the flow part of the inflow turbine with partial blading of the runner. Vestnik of Astrakhan State Technical University. Series: Marine engineering and technologies. 2024;2:57-64. (In Russ.). https://doi.org/10.24143/2073-1574-2024-2-57-64. EDN OWRZQM.

Научная статья

Взаимосвязь окружной скорости и потерь энергии в проточной части центростремительной турбины с частичным облопачиванием рабочего колеса

Алексей Алексеевич Крюков

Дальневосточный государственный техническийрыбохозяйственныйуниверситет, Владивосток, Россия, [email protected]

Аннотация. Малорасходные турбомашины - это устройства, которые играют важную роль в приводе различных агрегатов в области судостроения, авиастроения и других отраслях тяжелого машиностроения. Они имеют некоторые преимущества по сравнению с турбиной высокой средней мощности. Наибольшее количество малорасходных турбомашин изготавливают парциальными, т. е. с частичным впуском. Рассматривается принцип турбины с частичным облопачиванием рабочего колеса как один из видов парциальных турбомашин. Исследуется влияние основной скоростной характеристики турбинной ступени на потери кинетической энергии в ступени. Моделирование газодинамических процессов, происходящих в турбинной ступени, проводилось с использованием программного комплекса ANSYS Workbench. С помощью данного комплекса была создана трехмерная геометрическая модель турбинной ступени с различной степенью облопачивания рабочего

© Kriukov A. A., 2024

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Судовые энергетические установки и машинно-движительные комплексы

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колеса. Посредством применения метода конечных элементов сгенерирована расчетная сетка, расчетная модель, а также заданы граничные условия численного эксперимента. Результатом численного эксперимента являются графики зависимости потери кинетической энергии от окружной скорости (скоростной характеристики турбинной ступени). Данная зависимость может быть представлена не только графически, но и с помощью математического аппарата. Примером такого аппарата является полиномная зависимость. Рассматриваемая математическая конструкция может применяться в целях оптимизации математических моделей течения газа в проточной части малорасходной турбины. Получены кубические двухпараметрические полиномы потерь кинетической энергии в поточной части соплового аппарата и рабочего колеса, дана оценка его применимости в действующей математической модели.

Ключевые слова: сопловой аппарат, коэффициент потерь, рабочее колесо, кинетическая энергия, численный метод, эксперимент, расчетная сетка, газодинамика, малорасходная турбина

Для цитирования: Крюков А. А. Взаимосвязь окружной скорости и потерь энергии в проточной части центростремительной турбины с частичным облопачиванием рабочего колеса // Вестник Астраханского государственного технического университета. Серия: Морская техника и технология. 2024. № 2. С. 57-64. https://doi.org/10.24143/2073-1574-2024-2-57-64. EDN OWRZQM.

&

Introduction

The vast maj ority of low-consumption marine turbomachines are manufactured with partial intake - partial. This is due to a number of advantages compared to the use of small full-size underwater turbines. The paper considers the very principle of a turbine with partial blading of the runner (TPBR) without reference to the thermodynamic properties of the working fluid. Low-cost marine turbines that can be considered in this study, including steam turbines, gas turbines, have their advantages and limitations. For example, steam turbines have high efficiency and good reliability, but they require large dimensions and a long time to heat. Gas turbines, on the other hand, are compact and can quickly achieve operating parameters, but their efficiency may be lower, especially at low loads. Therefore, the choice of turbine type should be based on specific requirements and operating conditions [1-4].

The optimal choice will allow achieving high efficiency of utilization turbo generators, which will lead to a reduction in fuel consumption and material costs in marine engines [5]. The use of utilization turbogenerators in collaboration with internal combustion engines is one of the measures that can improve the efficiency of marine engines. This is an important step in the development of marine energy, which will help reduce the negative impact on the environment and ensure more efficient use of resources [6].

The main graphs characterizing the efficiency of turbine stages that are found in the scientific literature are graphs of the dependence of the efficiency coefficient on u1/C0. This parameter is the main speed characteristic of the stage. According to this parameter, the optimum point of kinetic energy losses, the velocity coefficient of the nozzle diaphragm and the runner are also fixed. Determining the optimal operating mode of the turbine stage while obtaining maximum efficiency with minimal kinetic energy losses is an urgent topic for research.

Goals and objectives of the study

The purpose of this study is to obtain polynomial dependences of energy losses in the flow part of the nozzle diaphragm and runner from the main speed characteristic of the uj/C0 stage.

Research objectives:

- based on previous numerical experiments conducted in this field [7-9]. The loss coefficients in the nozzle diaphragm and runner are determined;

- the method of mathematical approximation determines the polynomial dependences of kinetic energy losses on partiality and uj/C0;

- comparison of the values of the velocity coefficients of the nozzle diaphragm and runner obtained numerically with the result of the obtained mathematical dependencies.

The article [7] examines the study of models in which the velocity coefficients of nozzle diaphragm (ND) and runner (R) are determined based on experimental data. However, using a numerical experiment, it is possible to identify the distinctive features of the flow in these models and decide on the need for a semi-experimental study of the flow characteristics in ND and R using a simulation bench. Such a study was carried out in a scientific paper [8] on a simulation stand using the ANSYS CFX software. In Fig. 1 shows one of the stages of an inflow low-consumption TPBR.

The simulation of gas dynamic processes occurring in the turbine stage in the study was carried out using the ANSYS Workbench software package [9]. With the help of this complex, a three-dimensional model of the turbine stage with varying degrees of impeller damping was created. Using the finite element method, a computational grid was generated, a computational model was created, and boundary conditions for a numerical experiment were set.

Vestnik of Astrakhan State Technical University. Series: Marine engineering and technologies. 2024. N. 2 ISSN 2073-1574 (Print), ISSN 2225-0352 (Online)

_Ship power plants and propulsion systems

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Fig. 1. Diagram (a) and three-dimensional model (b) of a low-flow turbine stage

The results of the study

In [7], a TPBR was studied at various degrees of partial R. The values of the velocity coefficient ND and the velocity coefficient R were obtained. The velocity coefficients of ND and R with the energy loss coefficients in the flow part of ND and R have a cer-

tain interdependence expressed by the formulas [8]. Fig. 2 shows the dependences of the loss coefficients in the flow part of the ND for the stage in the range of e from 0.059 to 1.00 and nt from 1.5 to 2.5 from u1/C0 [10, 11].

a b c

Fig. 2. Two-dimensional dependence of the loss coefficient in the flow part of ND on u1/C0 with a degree of partiality e from 0.059 to 1.00: a - by nt = 1.5; b - by nt = 2.0; c - by nt = 2.5

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The graphs of the dependence of the loss coefficient in the flow part of ND are a graphical representation of energy losses, which can be used to create polynomials expressing the dependence of ZND on the parameters u1/C0 and e. The loss coefficient in ND can be expressed as a function of u1/C0 has the general form:

ZND(e) = A^/Q)4 + B(ul/C() + C(uj/C0)2 + + D(uj/C0) + E.

For each degree of partiality in the range from 0.059 to 1.00, the polynomial has coefficients shown in Tables 1-3 [12].

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a

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Судовые энергетические установки и машинно-движительные комплексы

Table 1

Coefficients of the nozzle diaphragm unit polynomial at the degree of expansion nt = 1.5

Degree of partiality e Coefficients of the nozzle diaphragm unit polynomial

A B C D E

0.059 -1.271 2.863 -2.086 0.541 0.302

0.188 -0.871 1.861 -1.233 0.265 0.316

0.206 -0.529 1.135 -0.682 0.067 0.265

0.412 -1.142 2.507 -1.729 0.384 0.193

1.000 0.477 -1.264 1.212 -0.477 0.247

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Coefficients of the nozzle diaphragm unit polynomial at the degree of expansion = 2.0

Table 2

Degree of partiality e Coefficients of the nozzle diaphragm unit polynomial

A B C D E

0.059 -11.644 21.558 -14.025 3.741 0.025

0.188 -6.674 12.729 -8.203 2.064 0.131

0.206 -1.629 3.023 -1.683 0.202 0.281

0.412 -1.057 2.116 -1.259 0.137 0.253

1.000 1.211 -2.474 1.846 -0.647 0.295

Table 3

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Coefficients of the nozzle diaphragm unit polynomial at the degree of expansion = 2.5

Degree of partiality e Coefficients of the nozzle diaphragm unit polynomial

A B C D E

0.059 -3.947 6.456 -3.446 0.635 0.306

0.188 -3.508 5.704 -2.952 0.482 0.318

0.206 -4.588 7.598 -4.192 0.813 0.227

0.412 -6.856 11.293 -6.243 1.238 0.175

1.000 4.748 -6.223 2.919 -0.736 0.304

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A mathematical model that allows us to determine £ the loss coefficient in the flow part of the ND dependS ing on two factors (e and ui/C0) is presented in the sa form of a two-parameter dependence Znd = f(e, uJC0), | for each nt.

& With the degree of expansion nt = 1.5:

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« ZND(e, M1t) = 0.205 - 0.062e - 0.002(u1/C0) + 0.083e2 -

| - 0.0014e(u1/C0) + 0.0077(u1/C0)2 - 0.03e3 +

| + 0.0013e2(u1/C0) - 0.0022e(u1/C0)2 - 0.0013(u1/C0)3.

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g With the degree of expansion nt = 2.0:

ZND(e, M1t) = 0.213 - 0.035e - 0.0015(u1/C0) + + 0.071e2 - 0.001e(u1/C0) + 0.0063(u1/C0)2 - 0.03e3 + + 0.007e2(u1/C0) - 0.003e(u1/C0)2 - 0.0013(u1/C0)3.

With the degree of expansion nt = 2.5:

ZND(e, M1t) = 0.228 - 0.47e - 0.0016(u1/C0) + 0.063e2 -- 0.0066e(u1/C0) + 0.0072(u1/C0)2 - 0.025e3 + + 0.001e2(u1/C0) - 0.0048e(u1/C0)2 - 0.0026(u1/C0)3.

A graphical representation of the two-parameter dependence ZND = f(e, u1/C0), with nt = 1.5 is shown in Fig. 3.

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Fig. 3. Three-dimensional dependence of the loss coefficient in the flow part of the ND on u1/C0 and the degree of partiality e, with nt = 1.5

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Ship power plants and propulsion systems

This model makes it possible to more accurately estimate the value of ZND for various combinations of the values of e and uj/C0. Similarly, the empirical

dependences for the loss coefficient in the runner are determined (Fig. 4) [13].

a b c

Fig. 4. Two-dimensional dependence of the loss coefficient in the flow part of R on uj/C0 with a degree of partiality e from 0.059 to 1.00: a - by nt = 1.5; b - by nt = 2.0; c - by nt = 2.5

The loss coefficient in R can also be expressed as a function wi/Co has the general form:

ZR(e) = A(u1/C0)4 + B(u1/C0)3 + C(u1/C0)2 + + D(u1/C0) + E.

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For each degree of partiality in the range from 0.059 to 1.00, the polynomial has coefficients shown in Tables 4-6.

Table 4

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Coefficients of the runner unit polynomial at the degree of expansion n, = 1.5

Degree of partiality e Coefficients of the runner unit polynomial

A B C D E

0.059 -1.205 2.722 -2.000 0.509 0.595

0.188 -1.106 2.466 -1.741 0.393 0.577

0.206 -1.374 3.048 -2.194 0.546 0.550

0.412 -0.723 1.557 -1.029 0.200 0.524

1.000 -0.646 1.565 -1.182 0.271 0.491

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Coefficients of the runner unit polynomial at the degree of expansion nt = 2.0

Table 5 n

Degree of partiality e Coefficients of the runner unit polynomial

A B C D E

0.059 1.735 -1.312 -0.047 0.054 0.5824

0.188 12.288 -20.268 12.125 -3.207 0.874

0.206 6.000 -9.947 6.122 -1.744 0.735

0.412 -1.092 3.139 -2.571 0.695 0.447

1.000 17.107 -28.445 16.933 -4.440 0.927

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Table 6

Coefficients of the runner unit polynomial at the degree of expansion nt = 2.5

Degree of partiality e Coefficients of the runner unit polynomial

A B C D E

0.059 -2.714 4.583 -2.508 0.468 0.519

0.188 -6.135 10.859 -6.314 1.309 0.404

0.206 -8.315 14.135 -7.956 1.621 0.374

0.412 -8.478 14.357 -8.080 1.655 0.363

1.000 16.260 -23.339 11.425 -2.426 0.642

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Судовые энергетические установки и машинно-движительные комплексы

In general, the analysis of the dependence graphs presented in Fig. 4 shows the possibility of obtaining cubic two-parameter polynomials ZR = f(e, u1/C0). With the degree of expansion nt = 1.5:

ZR(e, M1t) = 0.527 - 0.072e - 0.001(u1/C0) + 0.026e2 +

+ 0.0017e(u1/C0) + 0.0085(u1/C0)2 + 0.01e3 -- 0.002e2(u1/C0) - 0.0002e(u1/C0)2 - 0.0002(u1/C0)3.

With the degree of expansion nt = 2.0:

ZR(e, M1t) = 0.495 - 0.077e - 0.016(u1/C0) - 0.001e2 -- 0.001e(u1/C0) + 0.004(u1/C0)2 + 0.018e3 -

- 0.004e2(u1/C0) - 0.0018e(u1/C0)2 + 0.0035(u1/C0)3.

With the degree of expansion nt = 2.5:

ZR(e, M1t) = 0.435 + 0.49e - 0.018(u1/C0) + 0.104e2 -- 0.0067e(u1/C0) + 0.0081(u1/C0)2 - 0.074e3 -

- 0.004e2(u1/C0) - 0.0038e(u1/C0)2 + 0.053(u1/C0)3.

A graphical representation of the two-parameter dependence ZR = f(e, u1/C0), with nt = 1.5 is shown in Fig. 5.

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Fig. 5. Three-dimensional dependence of the loss coefficient in the flow part of the R on u1/C0 and the degree of partiality e, with nt = 1.5

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The adequacy of any mathematical model must be verified by a physical experiment. Due to the lack of results of a physical experiment on the energy loss coefficients in the flow part of the runner and nozzle diaphragm for the stage under study, the adequacy of the polynomial dependence can be performed using such an integral characteristic as efficiency.

When introducing the obtained energy loss dependencies into the existing mathematical model, the deviation of the internal efficiency between the calculated and the obtained input of the physical experiment is no more than 2.5%, which does not exceed the experimental error.

Conclusion

In the course of the study, the following tasks were completed and the relevant conclusions were obtained:

- based on previous studies, graphs of the dependence of energy losses in the flow part of ND and R on u1/C0 were constructed;

- using mathematical approximation methods, mathematical dependences of energy losses in were obtained for each degree of partiality ZND = f(£, ui/C0) and Zr = fe, U1/C0);

- the obtained polynomial dependencies can be used to calculate the flow part from a turbine stage of this type and will allow modeling the parameters for further improvement.

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Вестник Астраханского государственного технического университета.

Серия: Морская техника и технология. 2024. № 2 ISSN 2073-1574 (Print), ISSN 2225-0352 (Online)

Судовые энергетические установки и машинно-движительные комплексы

13. Крюков А. А. Влияния шага сопловой лопатки на Гос. ун-та мор. и реч. флота им. адм. С. О. Макарова. коэффициент скорости центростремительной турбины 2023. Т. 15. № 1. С. 73-81. с частичным облопачиванием рабочего колеса // Вестн.

The article was submitted 28.09.2023; approved after reviewing 12.02.2024; accepted for publication 01.04.2024 Статья поступила в редакцию 28.09.2023; одобрена после рецензирования 12.02.2024; принята к публикации 01.04.2024

Information about the author / Информация об авторе

Aleksei A. Kriukov — Senior Lecturer of the Department Алексей Алексеевич Крюков — старший преподава-of Engineering Disciplines; The Far Eastern State Technical тель кафедры инженерных дисциплин; Дальневосточный Fisheries University; [email protected] государственный технический рыбохозяйственный уни-

верситет; [email protected]

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