The influence of turbine stator well coolant flow rate and passage configuration on cooling effectiveness

D. D. Coren, N. R. Atkins, C. A. Long, D. Eastwood, P. R.N. Childs, A. Guijarro-Valencia, J. A. Dixon

Research output: Chapter in Book/Report/Conference proceedingConference contribution

5 Citations (Scopus)

Abstract

Market competitiveness for aero engine power plant dictates that improvements in engine performance and reliability are guaranteed a priori by manufacturers. The requirement to accurately predict the life of engine components makes exacting demands of the internal air system, which must provide effective cooling over the engine duty cycle with the minimum consumption of compressor section air. Tests have been conducted at the University of Sussex using a turbine test facility which comprises a two stage turbine with an individual stage pressure ratio of 1.7:1. Main annulus air is supplied by an adapted Rolls-Royce Dart compressor at up to 440 K and 4.8 kg s-1. Cooling flow rates ranging from 0.71 to 1.46 Cw, ent, a disc entrainment parameter, have been used to allow ingress or egress dominated stator well flow conditions. The mechanical design of the test section allows internal cooling geometry to be rapidly re-configured, allowing the effect of jet momentum and coolant trajectory to be investigated. An important facet to this investigation is the use of CFD to model and analyse the flow structures associated with the cavity conditions tested, as well as to inform the design of cooling path geometry. This paper reports on the effectiveness of stator well coolant flow rate and delivery configurations using experimental data and also CFD analysis to better quantify the effect of stator well flow distribution on component temperatures.

Original languageEnglish
Title of host publicationASME 2011 Turbo Expo
Subtitle of host publicationTurbine Technical Conference and Exposition, GT2011
PublisherAmerican Society of Mechanical Engineers (ASME)
Pages981-992
Number of pages12
EditionPARTS A AND B
ISBN (Print)9780791854655
DOIs
Publication statusPublished - 31 Dec 2011
EventASME 2011 Turbo Expo: Turbine Technical Conference and Exposition, GT2011 - Vancouver, BC, Canada
Duration: 6 Jun 201110 Jun 2011

Publication series

NameProceedings of the ASME Turbo Expo
NumberPARTS A AND B
Volume5

Conference

ConferenceASME 2011 Turbo Expo: Turbine Technical Conference and Exposition, GT2011
CountryCanada
CityVancouver, BC
Period6/06/1110/06/11

ASJC Scopus subject areas

  • Engineering(all)

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