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Preliminary aerodynamic design methodology for aero engine lean direct injection combustors

Part of: Sustainable Aerospace ISABE 2017

Published online by Cambridge University Press:  21 June 2017

J. Li ,
X. Sun ,
Y. Liu  and
V. Sethi
J. Li*
Affiliation:
AECC Shenyang Engine Research Institute, Shenyang, Liaoning, China
X. Sun*
Affiliation:
Centre for Propulsion Engineering, School of Aerospace, Transport and Manufacturing, Cranfield University, Bedfordshire, UK
Y. Liu
Affiliation:
Centre for Propulsion Engineering, School of Aerospace, Transport and Manufacturing, Cranfield University, Bedfordshire, UK
V. Sethi
Affiliation:
Centre for Propulsion Engineering, School of Aerospace, Transport and Manufacturing, Cranfield University, Bedfordshire, UK
*
[email protected]
[email protected]
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Abstract

The Lean Direct Injection (LDI) combustor is one of the low-emissions combustors with great potential in aero-engine applications, especially those with high overall pressure ratio. A preliminary design tool providing basic combustor sizing information and qualitative assessment of performance and emission characteristics of the LDI combustor within a short period of time will be of great value to designers. In this research, the methodology of preliminary aerodynamic design for a second-generation LDI (LDI-2) combustor was explored. A computer code was developed based on this method covering the design of air distribution, combustor sizing, diffuser, dilution holes and swirlers. The NASA correlations for NOx emissions are also embedded in the program in order to estimate the NOx production of the designed LDI combustor. A case study was carried out through the design of an LDI-2 combustor named as CULDI2015 and the comparison with an existing rich-burn, quick-quench, lean-burn combustor operating at identical conditions. It is discovered that the LDI combustor could potentially achieve a reduction in liner length and NOx emissions by 18% and 67%, respectively. A sensitivity study on parameters such as equivalence ratio, dome and passage velocity and fuel staging is performed to investigate the effect of design uncertainties on both preliminary design results and NOx production. A summary on the variation of design parameters and their impact is presented. The developed tool is proved to be valuable to preliminarily evaluate the LDI combustor performance and NOx emission at the early design stage.

Keywords

LDIpreliminary designNOx emission
Type
Research Article
Information
The Aeronautical Journal , Volume 121 , Special Issue 1242: The International Society of Air-breathing Engines (ISABE) 2017 Conference Special Issue , August 2017 , pp. 1087 - 1108
Copyright
Copyright © Royal Aeronautical Society 2017 

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Footnotes

This paper will be presented at the ISABE 2017 Conference, 3-8 September 2017, Manchester, UK.

References

REFERENCES

1. Foust, M., Thomsen, D., Stickles, D., Cooper, C. and Dodds, W. Development of the GE aviation low emissions TAPS combustor for next generation aircraft engines, 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, 2012, Nashville, Tennessee, US.CrossRefGoogle Scholar
2. Colantuoni, S. Sub-project 6 innovative combustor, presented at European Engine Technology, June 2009. Available at http://www.newac.eu/uploads/media/NEWAC_Warsaw_Workshop_SP6_presentation_01.pdf Google Scholar
3. Reddy, D.R. and Lee, C. An overview of low-emission combustion research at NASA Glenn, Proceedings of ASME Turbo Expo 2016: Turbomachinery Technical Conference, 2016, Seoul, South Korea.CrossRefGoogle Scholar
4. Mongia, H. TAPS: A fourth generation propulsion combustor technology for low emissions, AIAA International Air and Space Symposium and Exposition: The Next 100 Years, 2003, AIAA, Dayton, Ohio, US.CrossRefGoogle Scholar
5. Klinger, H., Lazik, W. and Wunderlich, T. The engine 3E core engine, ASME Turbo Expo 2008: Power for Land, Sea, and Air, 2008, pp 93-102. Berlin, Germany, Paper No. GT2008-50679.Google Scholar
6. Tacina, R., Mao, C. and Wey, C. Experimental investigation of a multiplex fuel injector module with discrete jet swirlers for low emission combustors, 41st Aerospace Sciences Meeting and Exhibit, 6-9 January 2003, Reno, Nevada, US, AIAA Papers, 2004, 135.Google Scholar
7. Tacina, K.M., Chang, C.T., He, Z.J., Lee, P., Dam, B. and Mongia, H.C. A second generation swirl-Venturi lean direct injection combustion concept, AIAA Propulsion and Energy Forum, July 28-30, 2014, Cleveland, OH 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, AIAA Paper, 2014, 3434.Google Scholar
8. Mellor, A.M. Design of Modern Turbine Combustors, 1990, Academic Press.Google Scholar
9. Mattingly, J.D. Aircraft Engine Design, American Institute of Aeronautics and Astronautics, 2002.CrossRefGoogle Scholar
10. Walsh, P.P. and Fletcher, P. Gas Turbine Performance, 2008, John Wiley & Sons.Google Scholar
11. Zhao, Y. Preliminary Aerodynamic Desin of Rich-burn Quick-quench Lean-burn Combustor for Civil Transport Aircraft Engine, MSc Thesis, 2015, Cranfield University, UK.Google Scholar
12. Lefebvre, A.H. Gas Turbine Combustion, 1998, CRC Press.Google Scholar
13. Mohammad, B.S. and Jeng, S.M. Design procedures and a developed computer code for preliminary single annular combustor design, 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 2-5 August 2009, Denver, Colorado, US, AIAA Paper, 2009, 5208.Google Scholar
14. Lefebvre, A.H. and Ballal, D.R. Gas Turbine Combustion, 2010, CRC Press.CrossRefGoogle Scholar
15. Béer, J.M. and Chigier, N.A. Combustion Aerodynamics, 1972, Halsted Press Division, Wiley, 1972.Google Scholar
16. Glass, S.J., The Effect of Primary Zone Swirler Aerodynamics on Spray, MSc Thesis, 1989, Cranfield University, UK.Google Scholar
17. Lee, K.M., Tacina, C.M. and Wey, C. NASA Glenn high-pressure low-NOx emissions research, NASA TM-2008-214974, 2008.Google Scholar
18. Tacina, R., Wey, C., Liang, P. and Mansour, A. A low- NOx lean-direct injection, multipoint integrated module combustor concept for advanced aircraft gas turbines, NASA/TM-2002-211347, 2005.CrossRefGoogle Scholar
19. Cai, J., Jeng, S.M. and Tacina, R. The structure of a swirl-stabilized reacting spray issued from an axial swirler, 43rd AIAA Aerospace Sciences Meeting and Exhibit, 2005, Reno, Nevada, US.CrossRefGoogle Scholar
20. Fu, Y. and Jeng, S.M. Experimental investigation of swirling air flows in a multipoint LDI combustor, 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 8–11 July 2007, Cincinnati, Ohio, US AIAA, 2007, 5685, p 43.Google Scholar
21. Yang, S.L., Siow, Y.K., Peschke, B.D. and Tacina, R.R. Numerical study of nonreacting gas turbine combustor swirl flow using Reynolds stress model, J Engineering for Gas Turbines and Power, 2003, 125, pp 804-811.CrossRefGoogle Scholar
22. Cai, J. Aerodynamics of Lean Direct Injection Combustor with Multi-swirler Arrays, PhD Thesis, 2006, University of Cincinnati, Cincinnati, Ohio, US.Google Scholar
23. Fu, Y., Jeng, S.M. and Tacina, R.R. Characteristics of the swirling flow in a multipoint LDI combustor, 45th AIAA Aerospace Sciences Meeting and Exhibit, 8-11 January 2007, Reno, Nevada, US, p 846.CrossRefGoogle Scholar
24. Ajmani, K., Mongia, H. and Lee, P., CFD computations of emissions for LDI-2 combustors with simplex and airblast injectors, AIAA Paper, 2014, 3529.Google Scholar
25. Hernandez, R.M. V2500 general familiarisation, [Online]. Available at http://www.slideshare.net/RafaelHernandezM/v2500-gf-issue-01.Google Scholar