The effect of combustor-turbine interface gap leakage on the endwall heat transfer for a nozzle guide vane

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

10 Citations (Scopus)

Abstract

To enable turbine components to withstand high combustion temperatures, they are cooled by air routed from the compressor, which can leak through gaps between components. These gaps vary in size from thermal expansions that take place. The leakage flow between the interface of the combustor and the turbine, in particular, interacts with the flowfield along the endwall. This study presents measurements of adiabatic cooling effectiveness and heat transfer coefficients on the endwall of a first vane, with the presence of leakage flow through a flush slot upstream of the vane. The effect of axial contraction of the slot width due to thermal expansion of the engine was tested for two blowing rates. Contracting the slot width, while maintaining the slot mass flow, resulted in a larger coolant coverage area and higher effectiveness values, as well as slightly lower heat transfer coefficients. Matching the momentum flux ratio of the leakage flow from the nominal and contracted slot widths lowered both cooling effectiveness and heat transfer coefficients for the contracted slot flow. Comparison of the coolant coverage pattern to the measured endwall shear stress topology indicated that the trajectory of the slot coolant was dictated by the complex endwall flow.

Original languageEnglish (US)
Title of host publicationProceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air
Pages671-682
Number of pages12
Volume4 PART A
DOIs
StatePublished - Sep 24 2007
Event2007 ASME Turbo Expo - Montreal, Que., Canada
Duration: May 14 2007May 17 2007

Other

Other2007 ASME Turbo Expo
CountryCanada
CityMontreal, Que.
Period5/14/075/17/07

Fingerprint

Combustors
Coolants
Heat transfer coefficients
Nozzles
Turbines
Heat transfer
Thermal expansion
Cooling
Turbine components
Blow molding
Compressors
Shear stress
Momentum
Trajectories
Topology
Fluxes
Engines
Air
Temperature

All Science Journal Classification (ASJC) codes

  • Engineering(all)

Cite this

Lynch, S. P., & Thole, K. A. (2007). The effect of combustor-turbine interface gap leakage on the endwall heat transfer for a nozzle guide vane. In Proceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air (Vol. 4 PART A, pp. 671-682) https://doi.org/10.1115/GT2007-27867
Lynch, Stephen P. ; Thole, Karen Ann. / The effect of combustor-turbine interface gap leakage on the endwall heat transfer for a nozzle guide vane. Proceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air. Vol. 4 PART A 2007. pp. 671-682
@inproceedings{9b6d66bcc0c34e7f97ed808b63ca8e97,
title = "The effect of combustor-turbine interface gap leakage on the endwall heat transfer for a nozzle guide vane",
abstract = "To enable turbine components to withstand high combustion temperatures, they are cooled by air routed from the compressor, which can leak through gaps between components. These gaps vary in size from thermal expansions that take place. The leakage flow between the interface of the combustor and the turbine, in particular, interacts with the flowfield along the endwall. This study presents measurements of adiabatic cooling effectiveness and heat transfer coefficients on the endwall of a first vane, with the presence of leakage flow through a flush slot upstream of the vane. The effect of axial contraction of the slot width due to thermal expansion of the engine was tested for two blowing rates. Contracting the slot width, while maintaining the slot mass flow, resulted in a larger coolant coverage area and higher effectiveness values, as well as slightly lower heat transfer coefficients. Matching the momentum flux ratio of the leakage flow from the nominal and contracted slot widths lowered both cooling effectiveness and heat transfer coefficients for the contracted slot flow. Comparison of the coolant coverage pattern to the measured endwall shear stress topology indicated that the trajectory of the slot coolant was dictated by the complex endwall flow.",
author = "Lynch, {Stephen P.} and Thole, {Karen Ann}",
year = "2007",
month = "9",
day = "24",
doi = "10.1115/GT2007-27867",
language = "English (US)",
isbn = "079184790X",
volume = "4 PART A",
pages = "671--682",
booktitle = "Proceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air",

}

Lynch, SP & Thole, KA 2007, The effect of combustor-turbine interface gap leakage on the endwall heat transfer for a nozzle guide vane. in Proceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air. vol. 4 PART A, pp. 671-682, 2007 ASME Turbo Expo, Montreal, Que., Canada, 5/14/07. https://doi.org/10.1115/GT2007-27867

The effect of combustor-turbine interface gap leakage on the endwall heat transfer for a nozzle guide vane. / Lynch, Stephen P.; Thole, Karen Ann.

Proceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air. Vol. 4 PART A 2007. p. 671-682.

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

TY - GEN

T1 - The effect of combustor-turbine interface gap leakage on the endwall heat transfer for a nozzle guide vane

AU - Lynch, Stephen P.

AU - Thole, Karen Ann

PY - 2007/9/24

Y1 - 2007/9/24

N2 - To enable turbine components to withstand high combustion temperatures, they are cooled by air routed from the compressor, which can leak through gaps between components. These gaps vary in size from thermal expansions that take place. The leakage flow between the interface of the combustor and the turbine, in particular, interacts with the flowfield along the endwall. This study presents measurements of adiabatic cooling effectiveness and heat transfer coefficients on the endwall of a first vane, with the presence of leakage flow through a flush slot upstream of the vane. The effect of axial contraction of the slot width due to thermal expansion of the engine was tested for two blowing rates. Contracting the slot width, while maintaining the slot mass flow, resulted in a larger coolant coverage area and higher effectiveness values, as well as slightly lower heat transfer coefficients. Matching the momentum flux ratio of the leakage flow from the nominal and contracted slot widths lowered both cooling effectiveness and heat transfer coefficients for the contracted slot flow. Comparison of the coolant coverage pattern to the measured endwall shear stress topology indicated that the trajectory of the slot coolant was dictated by the complex endwall flow.

AB - To enable turbine components to withstand high combustion temperatures, they are cooled by air routed from the compressor, which can leak through gaps between components. These gaps vary in size from thermal expansions that take place. The leakage flow between the interface of the combustor and the turbine, in particular, interacts with the flowfield along the endwall. This study presents measurements of adiabatic cooling effectiveness and heat transfer coefficients on the endwall of a first vane, with the presence of leakage flow through a flush slot upstream of the vane. The effect of axial contraction of the slot width due to thermal expansion of the engine was tested for two blowing rates. Contracting the slot width, while maintaining the slot mass flow, resulted in a larger coolant coverage area and higher effectiveness values, as well as slightly lower heat transfer coefficients. Matching the momentum flux ratio of the leakage flow from the nominal and contracted slot widths lowered both cooling effectiveness and heat transfer coefficients for the contracted slot flow. Comparison of the coolant coverage pattern to the measured endwall shear stress topology indicated that the trajectory of the slot coolant was dictated by the complex endwall flow.

UR - http://www.scopus.com/inward/record.url?scp=34548765496&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=34548765496&partnerID=8YFLogxK

U2 - 10.1115/GT2007-27867

DO - 10.1115/GT2007-27867

M3 - Conference contribution

AN - SCOPUS:34548765496

SN - 079184790X

SN - 9780791847909

VL - 4 PART A

SP - 671

EP - 682

BT - Proceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air

ER -

Lynch SP, Thole KA. The effect of combustor-turbine interface gap leakage on the endwall heat transfer for a nozzle guide vane. In Proceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air. Vol. 4 PART A. 2007. p. 671-682 https://doi.org/10.1115/GT2007-27867