Impact of the combustor-turbine interface slot orientation on the durability of a nozzle guide vane endwall

A. A. Thrift, K. A. Thole, S. Hada

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

3 Citations (Scopus)

Abstract

The combustor-turbine interface is an essential component in a gas turbine engine as it allows for thermal expansion between the first stage turbine vanes and combustor section. Although not considered as part of the external cooling scheme, leakage flow from the combustor-turbine interface can be utilized as coolant. This paper reports on the effects of orientation of a two-dimensional leakage slot, simulating the combustor-turbine interface, on the net heat flux reduction to a nozzle guide vane endwall. In addition to adiabatic effectiveness and heat transfer measurements, timeresolved, digital particle image velocimetry (TRDPIV) measurements were performed in the vane stagnation plane. Four interface slot orientations of 90°, 65°, 45°, and 30° located at 17% axial chord upstream of a first vane in a linear cascade were studied. Results indicate that reducing the slot angle to 45° can provide as much as a 137% reduction to the average heat load experienced by the endwall. Velocity measurements indicate the formation of a large leading edge vortex for coolant injected at 90° and 65° while coolant injected at 45° and 30° flows along the endwall and washes up the vane surface at the endwall junction.

Original languageEnglish (US)
Title of host publicationASME Turbo Expo 2012
Subtitle of host publicationTurbine Technical Conference and Exposition, GT 2012
Pages31-43
Number of pages13
EditionPARTS A AND B
DOIs
StatePublished - Dec 1 2012
EventASME Turbo Expo 2012: Turbine Technical Conference and Exposition, GT 2012 - Copenhagen, Denmark
Duration: Jun 11 2012Jun 15 2012

Publication series

NameProceedings of the ASME Turbo Expo
NumberPARTS A AND B
Volume4

Other

OtherASME Turbo Expo 2012: Turbine Technical Conference and Exposition, GT 2012
CountryDenmark
CityCopenhagen
Period6/11/126/15/12

Fingerprint

Combustors
Nozzles
Durability
Turbines
Coolants
Velocity measurement
Thermal load
Thermal expansion
Gas turbines
Heat flux
Vortex flow
Heat transfer
Cooling

All Science Journal Classification (ASJC) codes

  • Engineering(all)

Cite this

Thrift, A. A., Thole, K. A., & Hada, S. (2012). Impact of the combustor-turbine interface slot orientation on the durability of a nozzle guide vane endwall. In ASME Turbo Expo 2012: Turbine Technical Conference and Exposition, GT 2012 (PARTS A AND B ed., pp. 31-43). (Proceedings of the ASME Turbo Expo; Vol. 4, No. PARTS A AND B). https://doi.org/10.1115/GT2012-68096
Thrift, A. A. ; Thole, K. A. ; Hada, S. / Impact of the combustor-turbine interface slot orientation on the durability of a nozzle guide vane endwall. ASME Turbo Expo 2012: Turbine Technical Conference and Exposition, GT 2012. PARTS A AND B. ed. 2012. pp. 31-43 (Proceedings of the ASME Turbo Expo; PARTS A AND B).
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abstract = "The combustor-turbine interface is an essential component in a gas turbine engine as it allows for thermal expansion between the first stage turbine vanes and combustor section. Although not considered as part of the external cooling scheme, leakage flow from the combustor-turbine interface can be utilized as coolant. This paper reports on the effects of orientation of a two-dimensional leakage slot, simulating the combustor-turbine interface, on the net heat flux reduction to a nozzle guide vane endwall. In addition to adiabatic effectiveness and heat transfer measurements, timeresolved, digital particle image velocimetry (TRDPIV) measurements were performed in the vane stagnation plane. Four interface slot orientations of 90°, 65°, 45°, and 30° located at 17{\%} axial chord upstream of a first vane in a linear cascade were studied. Results indicate that reducing the slot angle to 45° can provide as much as a 137{\%} reduction to the average heat load experienced by the endwall. Velocity measurements indicate the formation of a large leading edge vortex for coolant injected at 90° and 65° while coolant injected at 45° and 30° flows along the endwall and washes up the vane surface at the endwall junction.",
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Thrift, AA, Thole, KA & Hada, S 2012, Impact of the combustor-turbine interface slot orientation on the durability of a nozzle guide vane endwall. in ASME Turbo Expo 2012: Turbine Technical Conference and Exposition, GT 2012. PARTS A AND B edn, Proceedings of the ASME Turbo Expo, no. PARTS A AND B, vol. 4, pp. 31-43, ASME Turbo Expo 2012: Turbine Technical Conference and Exposition, GT 2012, Copenhagen, Denmark, 6/11/12. https://doi.org/10.1115/GT2012-68096

Impact of the combustor-turbine interface slot orientation on the durability of a nozzle guide vane endwall. / Thrift, A. A.; Thole, K. A.; Hada, S.

ASME Turbo Expo 2012: Turbine Technical Conference and Exposition, GT 2012. PARTS A AND B. ed. 2012. p. 31-43 (Proceedings of the ASME Turbo Expo; Vol. 4, No. PARTS A AND B).

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

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Thrift AA, Thole KA, Hada S. Impact of the combustor-turbine interface slot orientation on the durability of a nozzle guide vane endwall. In ASME Turbo Expo 2012: Turbine Technical Conference and Exposition, GT 2012. PARTS A AND B ed. 2012. p. 31-43. (Proceedings of the ASME Turbo Expo; PARTS A AND B). https://doi.org/10.1115/GT2012-68096