Hostname: page-component-848d4c4894-xm8r8 Total loading time: 0 Render date: 2024-07-04T03:55:43.491Z Has data issue: false hasContentIssue false
  • English
  • Français

An unsteady, moving mesh CFD simulation for Harrier hot-gas ingestion control analysis

Published online by Cambridge University Press:  03 February 2016

G. A. Richardson ,
W. N. Dawes  and
A. M. Savill
G. A. Richardson
Affiliation:
Engineering Department, Cambridge University, Cambridge, UK
W. N. Dawes
Affiliation:
Engineering Department, Cambridge University, Cambridge, UK
A. M. Savill
Affiliation:
Computational Aerodynamics Design Group School of Engineering, Cranfield University, Cranfield, UK
Get access Rights & Permissions [Opens in a new window]

Abstract

Hot gas ingestion (HGI) can be a problematic feature of short take-off vertical landing (STOVL) aircraft during the descent phase of landing, or while on the ground. The hot exhaust gases from the downwards pointing nozzles can be re-ingested into the engine intakes, causing power degradation or reduced engine surge margin. The flow-fields that characterise this phenomenon are complex, with supersonic impinging jets and cross-flows creating large ground vortices and fountain up-wash flows.

A flow solver has been developed to include a suitable linear mesh deformation technique for the descending aircraft configuration. The code has been applied to predict the occurrence of HGI, by simulating experimental results from a 1/15th scale model of a descending Harrier. This has enabled an understanding of the aerodynamic mechanisms that govern HGI, in terms of the near-field and far-field effects and their impact on the magnitude of temperatures at the engine intake.

This paper presents three sets of CFD results. First a validation exercise shows predicted results from the twin-jet with intake in crossflow test-case. This is an unsteady Reynolds averaged Navier Stokes (URANS) solution for a static geometry (there is no moving mesh). This allows comparison with experiment. Secondly, a full descent phase URANS Spalart-Allmaras (SA) turbulence model calculation is done on an 8·5m cell mesh for half the flow domain of the Harrier model and test-rig without dams/strakes. This shows how the HGI flow mechanisms affect the engine intake temperature profiles, for the case where there are no flow control methods on the underside of the aircraft. Thirdly, the full descent phase URANS SA turbulence model calculation is done on a 22·4m cell mesh for the full flow domain of the Harrier model and test-rig, with the dam/strake geometry included in the structured mesh region.

Type
Research Article
Information
The Aeronautical Journal , Volume 111 , Issue 1117 , March 2007 , pp. 133 - 144
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. Richardson, G.A., Dawes, W.N. and Savill, A.M., Hot gas ingestion modelling for the vertical descent phase of a Harrier, 2005, Paper AIAA-5338-2005, 17th AIAA CFD Conference, Toronto, 6–9 June 2005.Google Scholar
2. Richardson, G.A., Dawes, W.N. and Savill, A.M., CFD analysis of hot gas ingestion mechanisms for the vertical descent phase of a Harrier aircraft, 2006, Paper GT2006-90766, GT2006 ASME Turbo Expo, 8-11 May 2006, Barcelona, Spain.Google Scholar
3. Behrouzi, P. and Mcguirk, J.J., Experimental Data for CFD validation of the intake ingestion process in STOVL aircraft, Flow Turbulence and Combustion, 2000, 64, pp 233–251.Google Scholar
4. Pandya, S.A., Murman, S.M. and Sankaran, V., Unsteady computations of a jet in crossflow with ground effect, 2003, AIAA Paper 2003-3890, 23rd AIAA Fluid Dynamics Conference and Exhibit, 23-26 June 2003, Orlando, FL.Google Scholar
5. Page, G.J., Mcguirk, J.J., et al Application of computational fluid dynamics to hot gas ingestion modelling, September 1998, International Powered Lift Conference.Google Scholar
6. Chaderjian, N.M. and Pandya, S.A. (NASA Ames), Ahmad, J.U. and Murman, S.M., (ELORET). Progress towards generation of a Navier-Stokes database for a Harrier in ground effect, AIAA 2002-5966.Google Scholar
7. Moinier, P. and Giles, M.B., Preconditioned Euler and Navier-Stokes calculations on unstructured grids, 1998, Sixth ICFD Conference on Numerical Methods for Fluid Dynamics, Oxford, UK.Google Scholar
8. Spalart, P.R. and Allmaras, S.R., A one-equation turbulence model for aerodynamic flows, La Recherche Aerospatiale, 1994, 1, pp 5–21.Google Scholar
9. Martinelli, L., Calculations of Viscous Flows with a Multigrid Method, 1987, PhD thesis, Dept of Mech and Aerospace Eng, Princeton University, USA.Google Scholar
10. Muller, J.D. and Giles, M.B., Edge-based multigrid schemes for hybrid grids, 1998, Sixth ICFD Conference on Numerical Methods for Fluid Dynamics, Oxford.Google Scholar
11. Giles, M., Unsflo: a numerical method for the calculation of unsteady flow in turbo machinery, May 1991, GTL Report No 205.Google Scholar
12. Li, Q., Page, G.J. and McGuirk, J.J., Large-eddy simulation of twin impinging jets in crossflow, Aeronaut J, 111, (1117), March 2006.Google Scholar
13. Penrose, C.J., Harrier 2 hot gas reingestion model tests, INTERNAL Rolls-Royce (Bristol) Report, GN 30224, August 1990 Google Scholar
14. Harper, L.R., Harrier 2 hot gas reingestion model tests, phase II, INTERNAL Rolls-Royce (Bristol) Report, GN 30345, September 1990.Google Scholar