Hostname: page-component-cd9895bd7-dzt6s Total loading time: 0 Render date: 2024-12-25T06:50:21.816Z Has data issue: false hasContentIssue false
  • English
  • Français

Towards a full two dimensional gas turbine performance simulator

Published online by Cambridge University Press:  03 February 2016

V. Pachidis ,
P. Pilidis ,
L. Marinai  and
I. Templalexis
V. Pachidis
Affiliation:
Department of Power and Propulsion, Cranfield University Gas, Turbine Engineering Group, Cranfield, UK
P. Pilidis
Affiliation:
Department of Power and Propulsion, Cranfield University Gas, Turbine Engineering Group, Cranfield, UK
L. Marinai
Affiliation:
Department of Power and Propulsion, Cranfield University Gas, Turbine Engineering Group, Cranfield, UK
I. Templalexis
Affiliation:
Section of Thermodynamics Power and Propulsion, Hellenic Air Force Academy, Dekeleia Air Base, Greece
Get access Rights & Permissions [Opens in a new window]

Abstract

In commercially available gas turbine performance simulation tools, individual engine components are typically represented with non-dimensional maps of experimental or default data. In those cases where actual component characteristics are not available and default characteristics are used instead, conventional tools can deviate substantially at off-design and transient conditions. Similarly, when real component characteristics are available, conventional engine cycle simulation tools can not predict the performance of the engine at other than nominal conditions satisfactorily, or account for the impact of changes in component geometry.

This study looked into the full integration of two-dimensional streamline curvature component models with a low fidelity cycle program. Firstly, the obtained engine performance was compared against the one calculated based on default component characteristics. As a second case study, a range of flight Mach numbers and angles of attack were examined together with the effect of three different intake lip geometries on the performance of a notional, two-spool, low-bypass ratio, military engine. Two-dimensional models were used in the engine cycle analysis to provide a more accurate, physics- and geometry-based estimate of intake and fan performances.

The analysis carried out by this study demonstrated relative changes in the predicted engine performance larger than 1%. For briefness, representative results are presented and discussed in this paper for one flight Mach number and angle of attack setting. More importantly, this research effort established the necessary methodology and technology required towards a full, two-dimensional engine cycle analysis at an affordable computational resource in the very short term.

Type
Research Article
Information
The Aeronautical Journal , Volume 111 , Issue 1121 , July 2007 , pp. 433 - 442
Copyright
Copyright © Royal Aeronautical Society 2007 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Pachidis, V., Pilidis, P., Guindeuil, G., Kalfas, A. and Templalexis, I., A partially integrated approach to component zooming using computational fluid dynamics, June 2005, GT2005-68457, ASME Turbo Expo, Power For Land, Sea and Air, Reno-Tahoe, NV, USA.Google Scholar
2. Pachidis, V., Pilidis, P., Alexander, T., Kalfas, A. and Templalexis, I., Advanced performance simulation of a turbofan engine intake, AIAA J Propulsion and Power, January-February 2006, 22, (1), pp 201.Google Scholar
3. Pachidis, V., Pilidis, P., Talhouarn, F., Kalfas, A. and Templalexis, I., A fully integrated approach to component zooming using computational fluid dynamics, ASME J Eng for Gas Turbines and Power, July 2006, 128, (3), pp 579.Google Scholar
4. Pachidis, V., Pilidis, P., Templalexis, I., Barbosa, J. and Nantua, N., A de-coupled approach to component high-fidelity analysis using computational fluid dynamics, IMechE J Aerospace Eng, 2006, 37, (220), Part G.Google Scholar
5. Turner, M.G., Reed, J.A., Ryder, R. and Veres, J.P., Multi-fidelity simulation of a turbofan engine with results zoomed into mini-maps for a zero-d cycle simulation, June 2004, GT2004-53956, ASME Turbo Expo 2004, Vienna, Austria.Google Scholar
6. Reed, J.A. and Afjeh, A.A., Development of an interactive graphical propulsion system simulator, June 1994, AIAA 94-3216, 30th AIAA/ASIVIEISAE/ASEE Joint Propulsion Conference, University of Toledo.Google Scholar
7. Reed, J.A. and Afjeh, A.A., Distributed and parallel programming in support of zooming in numerical propulsion system simulation, April 1994, NASA Symposium on Applications of Parallel and Distributed Computing, Columbus OH, USA.Google Scholar
8. Reed, J.A. and Afjeh, A.A., An interactive graphical system for engine component zooming in a numerical propulsion system simulation, January 1995, A1AA 95-0118, 33rd Aerospace Sciences Meeting and Exhibition, University of Toledo.Google Scholar
9. Reed, J.A. and Afjeh, A.A., A comparative study of high and low fidelity fan models for turbofan engine system simulation, July 1997, IASTED International Conference on Applied modelling and simulation, Banff, Canada.Google Scholar
10. Smith, L.H., NASA/GE Fan and Compressor Research Accomplishments, ASME J Turbomachinery, 1994, 116, (4), pp 554–568.Google Scholar
11. Schluter, J., Apte, S., Kalitzin, G., Pitsch, H., Van Der Weide, E. and Alonso, J., Unsteady CFD simulation of an entire gas turbine high-spool, May 2006, GT2006-90090, ASME Turbo Expo 06, Barcelona, Spain.Google Scholar
12. Novak, R.A., Streamline curvature computing procedures for fluid-flow problems, ASME J Eng for Power, 1967, 89, pp 478–490.Google Scholar
13. Jansen, W. and Moffatt, W.C., The off-design analysis of axial flow compressors, ASME J Eng for Power, October 1967, 89, pp 453–462.Google Scholar
14. Denton, J.D., Throughflow calculations for transonic axial flow turbines, ASME J Eng for Power, 1978, 100, pp 212–18.Google Scholar
15. Jennions, I.K. and Stow, P., The quazi-three-dimensional turboma-chinery blade design system, Part I: Throughflow analysis, Part II: Computerized system, ASME J Eng for Gas Turbines and Power, 1985, 107, pp 308–16.Google Scholar
16. Jennions, I.K. and Stow, P., The importance of circumferential non- uniformities in a passage averaged quasi-three-dimensional turbomachinery design system, ASME J Eng for Gas Turbines and Power, 1986,108, pp 240–5.Google Scholar
17. Barbosa, J.R., A Streamline Curvature Computer Program for Axial Compressor Performance Prediction, 1987, PhD thesis, Vol 1, School of Mechanical Engineering, Cranfield Institute of Technology.Google Scholar
18. Templalexis, I., Pilidis, P., Pachidis, V. and Kotsiopoulos, P., Development of a 2D compressor streamline curvature code, May 2006, GT2006-90867, ASME Turbo Expo, Power For Land, Sea and Air, Barcelona, Spain.Google Scholar
19. Pachidis, V., Pilidis, P., Templalexis, I., Alexander, T. and Kotsiopoulos, P., Prediction of engine performance under compressor inlet flow distortion using streamline curvature, May 2006, GT2006-90806, ASME Turbo Expo, Power For Land, Sea and Air, Barcelona, Spain.Google Scholar
20. Pachidis, V., Gas Turbine Advanced Performance Simulation, January 2006, PhD thesis, School of Engineering, Cranfield University.Google Scholar
21. Barger, R.L., Streamline curvature design procedure for subsonic and transonic ducts, December 1973, NASA Technical Note TN D-7368, Langley Research Center, Washington, DC.Google Scholar
22. Esdu, , Pressure recovery of axi-symmetric intakes at subsonic speeds, November 1980, Item No 80037, Engineering Sciences Data Unit, London.Google Scholar
23. Pachidis, V., Gas Turbine Simulation – PYTHIA Workshop Guide, Part I and II Department of Power, Propulsion and Aerospace Engineering, March 2004, Cranfield University, ASME/IGTI Aero Engine Life Management Conference, London.Google Scholar
24. Palmer, J.R., The TURBOMATCH Scheme for aero/industrial gas turbine engine design point/off design performance calculation, 1990, SME, Thermal Power Group, Cranfield University.Google Scholar
25. Urasek, D.C., Gorell, W.T. and Cunnan, W.S., Performance of two-stage fan having low-aspect-ratio, first stage rotor blading, 1979, NASA Technical Paper 1493.Google Scholar
26. Schmidt, J.F. and Ruggeri, R.S., Performance with and without inlet radial distortion of a transonic fan stage designed for reduced loading in the tip region, August 1978, NASA Technical Paper 1294.Google Scholar