Hostname: page-component-78c5997874-t5tsf Total loading time: 0 Render date: 2024-11-04T21:18:16.867Z Has data issue: false hasContentIssue false
  • English
  • Français

Enhancement of thrust reverser cascade performance using aerodynamic and structural integration

Published online by Cambridge University Press:  03 February 2016

J. Butterfield ,
H. Yao ,
M. Price ,
C. Armstrong ,
S. Raghunathan ,
E. Benard ,
R. Cooper  and
D. Monaghan
J. Butterfield
Affiliation:
Queen’s University, Belfast, UK
H. Yao
Affiliation:
Queen’s University, Belfast, UK
M. Price
Affiliation:
Queen’s University, Belfast, UK
C. Armstrong
Affiliation:
Queen’s University, Belfast, UK
S. Raghunathan
Affiliation:
Queen’s University, Belfast, UK
E. Benard
Affiliation:
Queen’s University, Belfast, UK
R. Cooper
Affiliation:
Queen’s University, Belfast, UK
D. Monaghan
Affiliation:
Queen’s University, Belfast, UK
Get access Rights & Permissions [Opens in a new window]

Abstract

This paper focuses on the design of a cascade within a cold stream thrust reverser during the early, conceptual stage of the product development process. A reliable procedure is developed for the exchange of geometric and load data between a two dimensional aerodynamic model and a three dimensional structural model. Aerodynamic and structural simulations are carried out using realistic operating conditions, for three different design configurations with a view to minimising weight for equivalent or improved aerodynamic and structural performance. For normal operational conditions the simulations show that total reverse thrust is unaffected when the performance of the deformed vanes is compared to the un-deformed case. This shows that for the conditions tested, the minimal deformation of the cascade vanes has no significant affect on aerodynamic efficiency and that there is scope for reducing the weight of the cascade. The pressure distribution through a two dimensional thrust reverser section is determined for two additional cascade vane configurations and it is shown that with a small decrease in total reverse thrust, it is possible to reduce weight and eliminate supersonic flow regimes through the nacelle section. By increasing vane sections in high pressure areas and decreasing sections in low pressure areas the structural performance of the cascade vanes in the weight reduced designs, is improved with significantly reduced levels of vane displacement and stress.

Type
Research Article
Information
The Aeronautical Journal , Volume 108 , Issue 1090 , December 2004 , pp. 621 - 628
Copyright
Copyright © Royal Aeronautical Society 2004 

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. Broede, J. Saving costs in design, manufacturing and operation of aero engine parts, Aeronaut J, November 2001, 105, (1053), pp 619–626.Google Scholar
2. Asbury, S.C. and Yetter, J.A. Static performance of six innovative thrust reverser concepts for subsonic transport applications, NASA/TM-2000-210300, July 2000.Google Scholar
3. Raju, J. A Conceptual design and cost optimisation methodology. American Institute of Aeronautics & Astronautics, 44th AIAA/ASME/AHS Structures, Structural Dynamics and Materials Conference, Norfolk, Virginia, April 2003.Google Scholar
4. Anon, , Rolls-Royce Aerospace Group, The Jet Engine, Renault Printing Co Ltd, Birmingham, England. 5th ed, 1996, pp 159–169.Google Scholar
5. Gunston, B. The Development of Jet and Turbine Aero Engines, Haynes Publishing, Sparkford, England. 2nd ed, 1997, pp 59–62.Google Scholar
6. Malaek, S.M. and Parastari, J. Thrust reverser modulation – a tool to command landing ground run, Aircraft Design, (4), 2001, pp 179–191.Google Scholar
7. Trapp, L.G. and Olivera, G.L. Aircraft thrust reverser cascade configuration evaluation through CFD. Paper Reference: AIAA-2003-0723. American Institute of Aeronautics & Astronautics, Jan 2003, 41st Aerospace Sciences Meeting and Exhibit, Reno, Nevada.Google Scholar
8. Butterfield, J. et al, Methodologies for structural optimisation of a thrust reverser cascade using a multidisciplinary approach. AIAA 41st Aerospace Sciences and Exhibit, 6–9 January 2003, Reno Hilton, Reno, Nevada.Google Scholar
9. Yao, H., Benard, E., Cooper, R.K. and Raghunathan, S. Aerodynamics of natural blockage thrust reverser. 9th Aerodynamics Symposium, Montreal, Canada, 28-30 April 2003.Google Scholar