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Total pressure distortion levels at the aerodynamic interface plane of a military aircraft

Published online by Cambridge University Press:  27 January 2016

T. Triantafyllou ,
T. Nikolaidis ,
M. Diakostefanis  and
P. Pilidis
T. Triantafyllou*
Affiliation:
Cranfield University, School of Aerospace, Transport and Manufacturing, Propulsion Engineering Centre, Bedford, UK
T. Nikolaidis
Affiliation:
Cranfield University, School of Aerospace, Transport and Manufacturing, Propulsion Engineering Centre, Bedford, UK
M. Diakostefanis
Affiliation:
Cranfield University, School of Aerospace, Transport and Manufacturing, Propulsion Engineering Centre, Bedford, UK
P. Pilidis
Affiliation:
Cranfield University, School of Aerospace, Transport and Manufacturing, Propulsion Engineering Centre, Bedford, UK
*
[email protected]
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Abstract

Military aircrafts are often subjected to severe flight maneuvers with high Angles-of -Attack (AOA) and Angles of Sideslip (AOSS). These flight attitudes induce non-uniform in flow conditions to their gas turbine engines which may include distortion of inlet total pressure and total temperature at the Aerodynamic Interface Plane (AIP). Operation of the downstream compression system with distorted inflow typically results in reduced aerodynamic performance, reduced stall margin, and increased blade stress levels. In the present study the steady state total pressure distortion induced to the Aerodynamic Interface Plane due to the aircraft’s flight attitude have been estimated in terms of distortion descriptors. The distorted conditions at the interface between the intake and the engine have been predicted by using Computational Fluid Dynamics (CFD), where 33 different aircraft flight attitudes have been tested. Based on the obtained results the effect of Angle-of-Attack (AOA) and Angle of Side Slip (AOSS) on the distortion descriptors have been studied. The results showed that the distortion effect becomes more pronounced whenever this specific airframe configuration is exposed to incoming flow with an AOSS. Among the tested cases, the greatest total pressure defect at the AIP in terms of difference from the average value and of circumferential extent was calculated for the flight attitudes of 0·35M flight with 0° AOA and 8° AOSS and 0·35M fight with 16° AOA and 16° AOSS.

Type
Research Article
Information
The Aeronautical Journal , Volume 119 , Issue 1219 , September 2015 , pp. 1147 - 1166
Copyright
Copyright © Royal Aeronautical Society 2015

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References

1.Gregory, S.B. An Assessment of Inlet Total-Pressure Distortion Requirements for the Compressor Research Facility, 1992, WL-TR-92-2066, Aero Propulsion and Power Directorate, Wright Laboratory, Wright-Patterson Air Force Base.Google Scholar
2. ANSYS FLUENT 12.0, Theory Guide, AMSYS Inc, 2009-01-23.Google Scholar
3.Triantafyllou, T., Nikolaidis, T., Diakostefanis, M. and Pilidis, P. Numerical simulation of the airflow over a military aircraft with active intake, Submitted for publication In Aeronaut J, September 2014, AeroJ-D-14-04252Google Scholar
4. Technical Committee S-16, 1983, Inlet Total Pressure Distortion Considerations for Gas Turbine Engines, SAE Air 1419, May 1983.Google Scholar
5.Crites, R.C. and Heckert, M.V. Application of Random Data Techniques on Aircraft Inlet Diagnostics, AIAA70-597, May 1970.Google Scholar
6.Johnson, R.H., Bayati, J.E., Lum, E.L. and Martin, A.W. Compressor Stability Assessment Program. Final Technical Report Air Induction System Considerations, Rockwell Report No. NA-70-615, February 1972.Google Scholar
7.Jane’s Aero-Engines, 2003, Issue 14, Jane’s Information Group.Google Scholar
8.Lee, A.S., Singh, R. and Probert, S.D. Modelling of the Performance of a F100-PW229 Equivalent Engine under Sea-level Static Conditions, 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2009, AIAA 2009-5018.Google Scholar
9. SAE, 2002, Gas Turbine Engine Inlet Flow Distortion Guidelines, SAE Air 1420, Rev B, 2002-02.Google Scholar
10.Rademakers, R.P.M., Kachele, T., Bindl, S. and Niehuis, R.Approach for an Optimized Evaluation of Pressure and Swirl Distortion in S-Shaped Engine Inlet Configurations, Propulsion and Energy Forum, 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, 28-30 July, 2014, Cleveland, Ohio, US.Google Scholar
11.Zhipeng, L., Chao, L., Hui, W., Zhang, L.X. and Guowang, Z.Applying CFD Technology to Determine the Effect of Two New Designed Fan Inlet Distortion Generators, Procedia Engineering, 99, (2015), pp 646–653, APISAT2014, Elsevier.Google Scholar
12.Brehm, S., Kachele, T. and Niehuis, R.CFD Investigations on the Influence of varying Inflow Conditions on the Aero dynamics in an S-Shaped Inlet Duct, Propulsion and Energy Forum, 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, 28-30 July 2014, Cleveland, Ohio, US.Google Scholar