Home Technology Installation Characteristics of Variable Cycle Engine Based on Inlet Flow Matching
Article
Licensed
Unlicensed Requires Authentication

Installation Characteristics of Variable Cycle Engine Based on Inlet Flow Matching

  • Haoying Chen , Haibo Zhang EMAIL logo , Yong Wang and Qiangang Zhen
Published/Copyright: January 10, 2019
Become an author with De Gruyter Brill

Abstract

As per few investigation in installed performance for variable cycle engines, an analysis scheme is proposed on the basis of integrating variable cycle engine and supersonic inlet system model. An integrated mathematical model, containing the inlet and the variable cycle engine is built, realizing the simulation of influences on the installation performance by varying geometry components. The impact on engine performance of variable geometric regulation was analyzed and concluded respectively. The experimental results show that the overflow resistance of the variable cycle engine with variable geometry optimization is reduced at subsonic cruise stage, and the installed fuel consumption is reduced, which significantly improves the installation performance.

Funding statement: This study is co-supported by National Natural Science Foundation of China (No: 51576096).

Nomenclature

MSV

Mode Selector Valve

FVABI

front variable area bypass injector

RVABI

rear variable area bypass injector

Wami

inlet flow (kg/s)

σin

total pressure recovery coefficient

Φ

flow coefficient

Fspill

spillage drag

Cspill

spillage drag coefficient

θ

guide vane angle

FA

percentage of installed thrust

θF

fan guide vane angle

θCDFS

CDFS guide vane angle

Sml

surge margin of fan

sfc

specific fuel consumption

Wa22c

fan flow (kg/s)

B

bypass ratio

Fr

installed thrust

References

1. Bruening GB, Chang WS. Cooled cooling air systems for turbine thermal management. ASME Paper, 14, 1999.10.1115/99-GT-014Search in Google Scholar

2. Kurzke J. The mission defines the cycle: turbojet, turbofan and variable cycle engines for high speed propulsion. Brussels, Belgium: NATO, 2010.Search in Google Scholar

3. Krebs JN, Allan RD. Supersonic propulsion-1970 to 1977. AIAA Paper, (77–832), 1977:11–3.10.2514/6.1977-832Search in Google Scholar

4. Baughman JL, Eheart R. U.S. Patent Application No. 12/956,674, (2010).Search in Google Scholar

5. Brown R. Integration of a variable cycle engine concept in a supersonic cruise aircraft. Joint Propulsion Conference, 2013.10.2514/6.1978-1049Search in Google Scholar

6. AIAA. Computational fluid dynamics modeling of a supersonic nozzle and integration into a variable cycle engine model. Aiaa/asme/sae/asee Joint Propulsion Conference, 2014.Search in Google Scholar

7. Lyu Y, Tang H, Chen M. A study on combined variable geometries regulation of adaptive cycle engine during throttling. Appl Sci. 2016;6:374.10.3390/app6120374Search in Google Scholar

8. Kopasakis G, Cheng L, Connolly JW. Stage-by-stage and parallel flow path compressor modeling for a variable cycle engine. Aiaa/sae/asee Joint Propulsion Conference, 2015.10.2514/6.2015-4143Search in Google Scholar

9. Zheng J, Chen M, Tang H. Matching mechanism analysis on an adaptive cycle engine. Chin J Aeronaut. 2017;2:706–18.10.1016/j.cja.2017.02.006Search in Google Scholar

10. Meng X, Zhu ZL, Chen M. Steady-state performance comparison of two different adaptive cycle engine configurations. In: 53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017:4791.10.2514/6.2017-4791Search in Google Scholar

11. Simmons RJ. Design and control of a variable geometry turbofan with an independently modulated third stream, 2009.Search in Google Scholar

12. Farokhi S. Aircraft propulsion. Hoboken, NJ: John Wiley & Sons, 2009:227–35.Search in Google Scholar

13. Orme JS, Conners TR. Supersonic flight test results of a performance seeking control algorithm on a NASA F-15 aircraft. AIAA Paper, 94–3210, 1994.10.2514/6.1994-3210Search in Google Scholar

14. Johnson JE, Foster T, Allan RD. U.S. Patent No. 4,064,692. Washington, DC: U.S. Patent and Trademark Office, 1977.Search in Google Scholar

15. Ball WH, Hickcox TE. Rapid evaluation of propulsion system effects, Volume I. Seattle, WA: Boeing Aerospace Co., 1978.10.21236/ADB031766Search in Google Scholar

16. Zhengjia WU, Ronghua ME, Ji LI. Research on genetic algorithm-based solution method for variable cycle engine model. Appl Mech Mater. 2014;668:633–6.10.4028/www.scientific.net/AMM.668-669.633Search in Google Scholar

17. Xuezhong G, Wenxiang Z, Jinquan H. Technology of variable cycle engine component level modeling. J Aerosp Power. 2013;28:104–11.Search in Google Scholar

18. Kurzkel J. GasTurb 11 Technical Reference[R], 2007.Search in Google Scholar

19. Sirinoglou AA. Implementation of variable geometry for gas turbine performance simulation turbomatch improvement (Doctoral dissertation), 1992.Search in Google Scholar

20. SaravanamuttooHIH, MuirDE, MarshallDJ. Health monitoring of variable geometry gas turbines for the Canadian Navy. In: Proceedings from the 1988 International Gas Turbine and Aeroengine Congress, 1988.Search in Google Scholar

Received: 2018-12-17
Accepted: 2018-12-24
Published Online: 2019-01-10
Published in Print: 2021-08-26

© 2019 Walter de Gruyter GmbH, Berlin/Boston

Downloaded on 19.1.2026 from https://www.degruyterbrill.com/document/doi/10.1515/tjj-2018-0031/pdf
Scroll to top button