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Effects of Inlet Distortion on the Stability of an Advanced Military Swept Fan Stage With Casing Treatment

[+] Author Affiliations
Donald S. Madden, Matt A. West

Rolls-Royce plc, Derby, UK

Paper No. GT2005-68693, pp. 269-279; 11 pages
doi:10.1115/GT2005-68693
From:
  • ASME Turbo Expo 2005: Power for Land, Sea, and Air
  • Volume 6: Turbo Expo 2005, Parts A and B
  • Reno, Nevada, USA, June 6–9, 2005
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4730-6 | eISBN: 0-7918-3754-8
  • Copyright © 2005 by ASME

abstract

It is possible to improve the stability of a fan in both clean and distorted inlet flow through the use of forward sweep and/or rotor casing treatment. However, for a practical design, there is the need to know whether sweep, casing treatment or a combination of both is most effective for enhancing stability. A further complication is that both these measures can have implications on downstream blade rows. There is therefore a requirement to be able to analyse 3D blade designs with casing treatments within a multi-stage environment. This paper presents both experimental and numerical studies of an advanced low hub-tip-ratio military fan stage of pressure ratio 2.2 subjected to an undistorted and tip-low radial distorted inlet total pressure profile. The case discussed is the second build of this research stage and features a rotor which has been successfully re-designed with forward sweep to improve stability. The stage was tested with and without casing treatment. The intention of this paper is therefore to outline an efficient method whereby a rotor casing treatment can be modelled unsteadily as part of the full compressor or fan stage. To the authors knowledge, all previously published unsteady numerical simulations of slotted casing treatments have been confined to rotor only calculations. Numerical studies of the stage use a mixed approach to speed convergence, employing a fully unsteady simulation of a single rotor passage with casing treatment coupled via a mixing plane to a steady simulation of the downstream stator vane. These studies, supported by test results, indicate that the swept blade in undistorted flow does not stall at the rotor tip and interacts significantly towards stall with the downstream stator vane. However, with the introduction of tip-low inlet distortion the swept rotor can be made to stall at the tip. Both experimental and numerical studies show that in the case of tip-low radial distortion the stability line can be successfully extended by employing rotor casing treatment.

Copyright © 2005 by ASME

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