The effects of varying the combustor-turbine gap

N. D. Cardwell, N. Sundaram, Karen Ann Thole

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

6 Scopus citations

Abstract

To protect hot turbine components, cooler air is bled from the high pressure section of the compressor and routed around the combustor where it is then injected through the turbine surfaces. Some of this high pressure air also leaks through the mating gaps formed between assembled turbine components where these components experience expansions and contractions as the turbine goes through operational cycles. This study presents endwall adiabatic effectiveness levels measured using a scaled up, two-passage turbine vane cascade. The focus of this study is evaluating the effects of thermal expansion and contraction for the combustor-turbine interface. Increasing the mass flow rate for the slot leakage between the combustor and turbine showed increased local adiabatic effectiveness levels while increasing the momentum flux ratio for the slot leakage dictated the coverage area for the cooling. With the mass flow held constant, decreasing the combustor-turbine interface width caused an increase in uniformity of coolant exiting the slot, particularly across the pressure side endwall surface. Increasing the width of the interface had the opposite effect thereby reducing coolant coverage on the endwall surface.

Original languageEnglish (US)
Title of host publicationProceedings of the ASME Turbo Expo 2006 - Power for Land, Sea, and Air
Pages91-102
Number of pages12
DOIs
StatePublished - Nov 15 2006
Event2006 ASME 51st Turbo Expo - Barcelona, Spain
Duration: May 6 2006May 11 2006

Publication series

NameProceedings of the ASME Turbo Expo
Volume3 PART A

Other

Other2006 ASME 51st Turbo Expo
CountrySpain
CityBarcelona
Period5/6/065/11/06

All Science Journal Classification (ASJC) codes

  • Engineering(all)

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