Numerical study of flows in axial compressors of aircraft gas-turbine engines

Authors

DOI:

https://doi.org/10.15587/1729-4061.2018.139445

Keywords:

calculation of transonic flow, matrix method, multistage axial compressor, fan stage

Abstract

Design and adjustment of compressors at modern gas-turbine engines are based on the wide use of numerical analysis methods of a various level of complexity. Such approaches make it possible to analyze the alignment of joint operation of stages and to perform the required correction of geometrical parameters. The methods for calculating the 1D and 2D flow in compressors are distinguished by high flexibility, which allows the utilization of considerable experience in designing and experimental research. These methods are consequently in demand at all stages of the engine life cycle: when creating, adjusting, at operation.

We present methods for the calculation of parameters and structure of current, as well as the summary characteristics of axial stages and multistage compressors. To solve a system of motion equations, we employed a matrix method, which makes it possible to apply small computation grids in a flow-through part of the compressor. The method is designed to numerically simulate the sub-, trans-, and supersonic flows in the flow-through part of axial compressor stages and multistage axial compressors at aircraft engines. The methods are implemented in the form of software complexes.

The article reports certain results related to the verification of these complexes. We use data from experimental studies into various multi-stage compressors and high-head fan stages. We show a satisfactory agreement between calculated and experimental data over a wide range of modes of consumption and rotation frequency.

The developed software package was used to improve the geometrical parameters for an axial multi-stage compressor, aimed at increasing the air flow rate through the compressor and enhancing the reserve of its gas-dynamic stability.

Employing small computational grids made it possible to undertake a series of studies, previously available only for the calculation methods of spatial flow. We considered different variants for the execution of the bushing surface at a high-head fan stage. When analyzing the structure of flow in a stage, we show the change in the axial component of velocity in a blade-to-blade channel of the impeller along its axis.

Development and application of the new methods of calculation will improve the quality of design of axial compressors and enhance competitiveness of the Ukrainian aircraft gas turbine engines.

Author Biographies

Ludmila Boyko, National Aerospace University named after M. Zhukovsky "Kharkiv Aviation Institute" Chkalova str., 17, Kharkiv, Ukraine, 61070

Doctor of Technical Sciences, Professor

Department of aviation engines theory

Alexandr Dyomin, National Aerospace University Kharkiv Aviation Institute Chkalova str., 17, Kharkiv, Ukraine, 61070

PhD, Senior Researcher

Department of aviation engines theory

References

  1. Smith, Jr. (1966). Uravnenie radial'nogo ravnovesiya turbomashiny. Energeticheskie mashiny i ustanovki, 88 (1), 1–14.
  2. Novak, Dzh. (1967). Metod krivizny liniy toka v vychislitel'nyh zadachah dlya potoka zhidkosti. Energeticheskie mashiny i ustanovki, 4, 30–41.
  3. Boyer, K. M., O’Brien, W. F. (2002). An Improved Streamline Curvature Approach for Off-Design Analysis of Transonic Axial Compression Systems. Volume 5: Turbo Expo 2002, Parts A and B. doi: https://doi.org/10.1115/gt2002-30444
  4. Boyer, K. M., O’Brien, W. F. (2002). Application of an Improved Streamline Curvature Approach to a Modern, Two-Stage Transonic Fan: Comparison With Data and CFD. Volume 5: Turbo Expo 2002, Parts A and B. doi: https://doi.org/10.1115/gt2002-30383
  5. Tiwari, P., Stein, A., Lin, Y.-L. (2011). Dual-Solution and Choked Flow Treatment in a Streamline Curvature Throughflow Solver. Volume 7: Turbomachinery, Parts A, B, and C. doi: https://doi.org/10.1115/gt2011-46545
  6. Xiaoxiong, W., Liu, B., Lei, S., Guochen, Z., Xiaochen, M. (2016). Development of an Improved Streamline Curvature Approach for Transonic Axial Compressor. Volume 2C: Turbomachinery. doi: https://doi.org/10.1115/gt2016-57072
  7. Matzgeller, R., Pichler, R. (2012). Modeling of Discrete Tip Injection in a Two-Dimensional Streamline Curvature Method. Volume 8: Turbomachinery, Parts A, B, and C. doi: https://doi.org/10.1115/gt2012-69554
  8. Marsh, H. (1968). A digital computer program for the throughflow fluid mechanics in an arbitrary turbo machine using a matrix method. Aeronaut. Res. Counc. Reports and Memoranda. No. 3509, 34.
  9. Mermen, E., Saut, Dzh., Hafez, M. (1979). Primenenie metodov iskusstvennoy szhimaemosti dlya chislennogo resheniya polnogo uravneniya potenciala v transzvukovom diapazone skorostey. Raketnaya tekhnika i kosmonavtika, 17 (8), 50–58.
  10. Hafez, M., Louvell, D. (1983). Chislennoe reshenie uravneniya dlya funkcii toka v sluchae transzvukovyh skorostey. Aerokosmicheskaya tekhnika, 1 (11), 63–73.
  11. Kosolapov, Yu. S. (1989). Raschet stacionarnyh do- i transzvukovyh nepotencial'nyh techeniy ideal'nogo gaza v osesimmetrichnyh kanalah. Zhurn. vychisl. matem. i matem. fiz., 29 (5), 765–774.
  12. Petrovic, M. V., Wiedermann, A., Banjac, M. B. (2009). Development and Validation of a New Universal Through Flow Method for Axial Compressors. Volume 7: Turbomachinery, Parts A and B. doi: https://doi.org/10.1115/gt2009-59938
  13. Banjac, M., Petrovic, M. V., Wiedermann, A. (2016). Multistage Axial Compressor Flow Field Predictions Using CFD and Through-Flow Calculations. Volume 2C: Turbomachinery. doi: https://doi.org/10.1115/gt2016-57632
  14. Bosman, C., Marsh, H. (1974). An Improved Method for Calculating the flow in Turbo-Machines, Including a Consistent loss Model. Journal of Mechanical Engineering Science, 16 (1), 25–31. doi: https://doi.org/10.1243/jmes_jour_1974_016_006_02
  15. Lieblein, S. (1959). Loss and stall analysis of compressor cascades. ASME Transactions, Journal of Basic Engineering, 81, 387–400.
  16. Al-Daini, A. J. (1986). Loss and deviation model for a compressor blade element. International Journal of Heat and Fluid Flow, 7 (1), 69–78. doi: https://doi.org/10.1016/0142-727x(86)90046-9
  17. Sven, V. K. (1961). Prakticheskiy metod rascheta harakteristik okolozvukovogo kompressora. Tr. amer. obshch-va inzh.-mekh. Ser.: Energeticheskie mashiny i ustanovki, 83 (3), 130–141.
  18. Novikov, A. S., Shebakpol'skiy, F. Ya. (1978). Raschet koefficienta vtorichnyh poter' v stupeni osevogo kompressora. Uchenye zapiski CAGI, IX (5), 116–119.
  19. Koh, S. S., Smit, L. H. (1976). Istochniki i velichiny poter' v osevyh kompressorah. Tr. amer. obshch-va inzh.-mekh. Ser.: Energeticheskie mashiny i ustanovki, 3, 128–145.
  20. Miller, G. R., Lewis, G. W., Hartmann, M. J. (1961). Shock Losses in Transonic Compressor Blade Rows. Journal of Engineering for Power, 83 (3), 235. doi: https://doi.org/10.1115/1.3673182
  21. Boyko, L. G., Demin, A. E., Kovalev, M. A. (2017). Komp'yuternaya programma AxSym. Rishennia pro reiestratsiyu No. 3570 vid 23.10.2017.
  22. Boyko, L. G., Demin, A. E., Maksimov, Yu. P., Ahtemenko, Yu. F. (2014). Regulirovanie mnogostupenchatogo osevogo kompressora na osnove dvumernogo analiza techeniya. Trudy XVI Mezhdunarodnoy nauchno-tekhnicheskoy konferencii po kompressornoy tekhnike. Sanct-Peterburg, 1, 318–327.
  23. Boyko, L. G., Barysheva, E. S., Demin, A. E., Drynov, O. N. (2013). Raschetnoe issledovanie techeniya v osecentrobezhnom kompressore aviacionnogo GTD. Vestnik Ufimskogo gosudarstvennogo aviacionnogo tekhnicheskogo universiteta, 17 (4 (57)), 29–37.
  24. Boyko, L. G., Demin, A. E., Drynov, O. N., Kalyuzhnaya, V. A. (2015). Metod raschetnogo issledovaniya 2D-techeniya v mnogostupenchatyh osevyh kompressorah aviacionnyh dvigateley. Vestnik UGATU, 19 (1 (67)), 3–12.
  25. Basov, Yu. F., Boyko, L. G., Demin, A. E. (2009). Sovershenstvovanie metoda rascheta techeniya v vysokonapornoy kompressornoy stupeni. Aviacionno-kosmicheskaya tekhnika i tekhnologiya, 2, 63–68.
  26. Basov, Yu. F., Demin, A. E., Maksimov, Yu. P. (2005). Analiz aerodinamicheskih harakteristik i struktury techeniya v transzvukovoy kompressornoy stupeni. Aviacionno-kosmicheskaya tekhnika i tekhnologiya, 2, 37–41.
  27. Reid, L., Moore, R. D. (1978). Design and Overall Performance of Four Highly Loaded, High–Speed Inlet Stages for an Advanced High Pressure Ratio Core Compressor. NASA Technical Paper 1337, 132.
  28. Reid, L., Moore, R. D. (1980). Performance of Single Stage Axial Flow Transonic Compressor With Rotor and Stator Aspect Ratios of 1.19 and 1.26, Respectively, and With Design Pressure Ratio of 2.05. NASA Technical Paper 1659, 104.
  29. Boyko, L. G., Girich, G. D., Ershov, V. N., Yanevich, V. N. (1989). Metod raschet dvumernogo techeniya v mnogostupenchatom osevom kompressore. Izvestiya VUZov, 5, 37–41.
  30. Boyko, L. G., Karpenko, E. L., Akhtemenko, U. F. (2013). Method of calculating GTE gas-thermodynamic parameters with blade row description of an axial multistage compressor. VESTNIK of the Samara State Aerospace University, 3 (41), 31–39. doi: https://doi.org/10.18287/1998-6629-2013-0-3-2(41)-31-39

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Published

2018-07-24

How to Cite

Boyko, L., & Dyomin, A. (2018). Numerical study of flows in axial compressors of aircraft gas-turbine engines. Eastern-European Journal of Enterprise Technologies, 4(8 (94), 40–49. https://doi.org/10.15587/1729-4061.2018.139445

Issue

Vol. 4 No. 8 (94) (2018): Energy-saving technologies and equipment

Section

Energy-saving technologies and equipment

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Copyright (c) 2018 Ludmila Boyko, Alexandr Dyomin

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