A technique for computing thermal state and radial displacements of the gas turbine engine hull for application as a part of mathematical model of radial clearance control active control system

Aeronautical and Space-Rocket Engineering


DOI: 10.34759/vst-2023-2-139-147

Аuthors

Samoilenko N. A.1*, Kashin N. N.2**, Samokhvalov N. Y.2***

1. Perm National Research Polytechnic University, PNRPU, 29, Komsomolsky Prospekt, Perm, 614990, Russia
2. "UEC-Aviadvigatel"JSC, 93, Komsomolsky Prospect, Perm, 614990, Russia

*e-mail: nikita5am@yandex.ru
**e-mail: kashin-nn@avid.ru
***e-mail: samohvalov@avid.ru

Abstract

This article considers techniques for the thermal state and radial displacements computing of the GTE turbine hull in the context of their application as a part of the mathematical model of the active clearance control system (ACCS) integrated into the electronic engine controller. The first technique is the of displacements computing based on the direct measurement of the hull temperature with the running engine. This scheme is realized on the CFM56-7B engine. It was revealed by the results of the analysis that it was quite enough to determine deformations of the external turbine hull only, and deformations caused by the pressure difference could be neglected, since were of no more than 3% of the temperature ones. These simplifications are being applied for the analysis of the rest techniques. The result of the hull displacements modeling results at the known temperature at the single point comparison with the results of axisymmetric modeling by the field verified by the temperature determined that the said technique ensures enough accuracy and computing speed. The second technique, namely displacements computing based on the temperature state, determined with the finite element method. Modeling results and technique verification are presented in the opened sources. They demonstrate that the error of the stationary thermal state modeling relative to the experimental data reaches 25% for the ground based gas turbine engine hull. Hence, this error will be much higher at the transient modes of the non-stationary computations. On the assumption of the performed analysis, the second technique does not satisfy the accuracy requirements to be integrated into the engine electronic controller. The third technique was developed by the authors, and based on the turbine hull displacements determining by the heat dissipation, calculated by the time constants dynamic computing. The hull temperature computing is performed by the two parameters, such as predicted stationary temperature and time constant, which are being computed at each time instant of the engine parameters registration in the automatic control system (ACS). Parameters computing is divided into the modes at turned-on and turned-off ACCS , since the time constants computing is based on the intrinsic heat transfer coefficients determining, and substantial heat exchange intensification occurs at the ACCS turning on, since the blow-off type changes from the smooth channel to the jet with the barrier. Stationary temperatures are being computed at the turned-off ACCS by the engine operation modes, while with the turned-on ACCS the air consumption and temperature in the blow-off collector are being accounted for additionally since these parameters are being used directly for the hull thermal state control and, hence, radial clearances. The calculated temperatures are compared with the data on the turbine housing thermometry on a full-size engine from the two test cycles. It is confirmed that this technique reliably reproduces the values and dynamics of temperature changes. Thus, it can be integrated into the ACC mathematical model. On the assumption of the accuracy and quick response, the first and the third of the considered methods can be applied to simulate the hull displacements on a real-time scale, and account for the control parameters of the ACCs, such as temperature and airflow in the blow manifold. Thus, they may be integrated into dynamic ACC, optimizing radial clearances in the turbine at all engine operating modes, and as the result, enhance its efficiency.

Keywords:

turbine stator thermo-mechanical model, radial clearance active control system (RCACS), radial clearances in GTE turbines, GTE turbine thermal state, GTE turbines radial clearances adjustment

References

  1. Inozemtsev A.A., Nikhamkin M.A., Sandratskii V.L. Osnovy konstruirovaniya aviatsionnykh dvigatelei i energeticheskikh ustanovok (Principles of aero-engines and power generation gas turbines designing), Moscow, Mashinostroenie, 2008, vol. 2, 368 p.
  2. Kratz J.L., Chapman J.W. Active turbine tip clearance control trade space analysis of an advanced geared turbofan engine. 2018 Joint Propulsion Conference (9-11 July 2018; Cincinnati, Ohio). DOI: 10.2514/6.2018-4822
  3. Ezrokhi Y.A., Gusmanova A.A. On accounting for turbine efficiency, while gas turbine engine parameters determining. Aerospace MAI Journal, 2022, vol. 29, no. 2, pp. 77-87. DOI: 10.34759/vst-2022-2-77-87
  4. Samoilenko N.A., Popova D.D., Popov D.A. Vestnik PNIPU. Aerokosmicheskaya tekhnika, 2021, no. 65, pp. 45–56. DOI: 10.15593/2224-9982/2021.65.05
  5. Bondarchuk P.V., Tisarev A.Yu., Lavrushin M.V. Vestnik Samarskogo gosudarstvennogo aerokosmicheskogo universiteta im. akademika S.P. Koroleva (natsional’nogo issledovatel’skogo universiteta), 2012, no. 3-3(34), pp. 272–278.
  6. Kumar R., Kumar V.S., Butt M.M. et al. Thermo-mechanical analysis and estimation of turbine blade tip clearance of a small gas turbine engine under transient operating conditions. Applied Thermal Engineering, 2020, vol. 179: 115700. DOI: 10.1016/j.applthermaleng.2020.115700
  7. Yurtaev A.A., Badykov R.R., Benedyuk M.A., Senchev M.N. Determining radial gaps values of centrifugal compressor and turbine of a small-sized gas turbine engine at maximum operation mode. Aerospace MAI Journal, 2022, vol. 29, no. 1, pp. 131-143. DOI: 10.34759/vst-2022-1-131-143
  8. Samoilenko N.A., Kashin N.N. Aviatsionnye dvigateli, 2021, no. 4(13), pp. 39-50. DOI: 10.54349/26586061_2021_4_39
  9. Gol’berg F.D., Gurevich O.S., Zuev S.A., Petukhov A. A. The onboard mathematical model application to control gas turbine engine with extra combustion chamber. Aerospace MAI Journal, 2019, vol. 26, no. 4, pp. 90-97. DOI: 10.34759/vst-2019-4-90-97
  10. Linke-Diesinger A. Systems of commercial turbofan engines. An introduction to system functions. Leipzig, Springer-Verlag Berlin Heidelberg, 2008, 239 p. DOI: 10.1007/978-3-540-73619-6
  11. Chapman J.W., Guo T.-H., Kratz J.L., Litt J.S. Integrated Turbine Tip Clearance and Gas Turbine Engine Simulation. 52nd AIAA/SAE/ASEE Joint Propulsion Conference (25-27 July 2016; Salt Lake City, UT). DOI: 10.2514/6.2016-5047
  12. Peng K., Fan D., Yang F. et al. Active generalized predictive control of turbine tip clearance for aero-engines. Chinese Journal of Aeronautics, 2013, vol. 26, no. 5, pp. 1147-1155. DOI: 10.1016/j.cja.2013.07.005
  13. Kypuros J., Melcher K.J. A reduced model for prediction of thermal and rotational effects on turbine tip clearance. Technical Memorandum NASA/TM—2003-212226. URL: 20030032933.pdf
  14. Andropov A.S., Tikhomirov B.A., Erokhin S.K. Gazovaya promyshlennost’, 2017, no. 4(751), pp. 68-74.
  15. Krol’ D.G. Vestnik Gomel’skogo gosudarstvennogo tekhnicheskogo universiteta im. P.O. Sukhogo, 2002, no. 3-4(9), pp. 146-150.
  16. Eliseev V.N., Tovstonog V.A., Borovkova T.V. Vestnik Moskovskogo gosudarstvennogo tekhnicheskogo universiteta im. E. Baumana. Seriya Mashinostroenie, 2017, no. 1(112), pp. 112-128.
  17. Kutateladze S.S. Osnovy teorii teploobmena (Fundamentals of the theory of heat transfer), 5th ed. Moscow, Atomizdat, 1979, 416 p.
  18. Creci G., de Mendoca M.T., Menezes J.C., Barbosa J.R. Heat Transfer Analysis in a Single Spool Gas Turbine by Using Calculated-Estimated Coeffcients with the Finite Element Method. Applied Sciences, 2020, vol. 10, no. 23: 8328. DOI: 10.3390/app10238328
  19. Grechishnikov O.V., Balakin A.Yu., Roslyakov A.D. Vestnik Samarskogo gosudarstvennogo aerokosmicheskogo universiteta, 2013, no. 3(41), pp. 57-64.
  20. Dhopade P., Kirollos B., Ireland P., Lewis L. A Comparison of Single-Entry and Multiple-Entry Casing Impingement Manifolds for Active Thermal Tip Clearance Control. International Journal of Turbomachinery Propulsion and Power, 2021, vol. 6, no. 2. DOI: 10.3390/ijtpp6020010
  21. Da Soghe R., Facchini B., Micio M., Andreini A. Aerothermal Analysis of a Turbine Casing Impingement Cooling System. International Journal of Rotating Machinery, 2012. DOI: 10.1155/2012/103583
  22. Zaitsev D.K., Smirnov E.M. Nauchno-tekhnicheskie vedomosti SPbGPU. Fiziko-matematicheskie nauki, 2019, no. 12, pp. 39-49.

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