Nozzle passage endwall effectiveness values with various combustor coolant flow rates: Part 2 - Endwall and vicinity surface effectiveness measurements

Kedar P. Nawathe, Rui Zhu, Enci Lin, Yong W. Kim, Terrence W. Simon

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

Abstract

Effective coolant schemes are required for providing cooling to the first stage stator vanes of gas turbines. To correctly predict coolant performance on the endwall and vane surfaces, these coolant schemes should also consider the effects of coolant streams introduced upstream in the combustor section of a gas turbine engine. This two-part paper presents measurements taken on a first-stage nozzle guide vane cascade that includes combustor coolant injection. The first part of this paper explains how coolant transport and coolant-mainstream interaction in the vane passage is affected by changing the combustor coolant and endwall film coolant flow rates. This paper explains how those flows affect the coolant effectiveness on the endwall. Part one showed that a significant amount of coolant injected upstream of the endwall is present along the pressure surface of the vanes as well as over the endwall. Part two shows effectiveness measurement results taken in this study on the endwall and pressure and suction surfaces of the vanes. Sustained endwall coolant effectiveness is observed along the whole passage for all cases. It is uniform in the pitch-wise direction. Combustor coolant flow significantly affects cooling performance even near the trailing edge. The modified flow field results in the pressure surface being cooled more effectively than the suction surface. While the effectiveness distribution on the pressure surface varies with combustor and film coolant flow rates, the suction surface remains largely unchanged.

Original languageEnglish (US)
Title of host publicationHeat Transfer
PublisherAmerican Society of Mechanical Engineers (ASME)
ISBN (Electronic)9780791884171
DOIs
StatePublished - 2020
EventASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition, GT 2020 - Virtual, Online
Duration: Sep 21 2020Sep 25 2020

Publication series

NameProceedings of the ASME Turbo Expo
Volume7B-2020

Conference

ConferenceASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition, GT 2020
CityVirtual, Online
Period9/21/209/25/20

Bibliographical note

Funding Information:
The authors would like to acknowledge the financial support provided by Solar Turbines, Incorporated for this project and thank Alex Li for his help during the measurements.

Publisher Copyright:
Copyright © 2020 ASME and Solar Turbines Incorporated

Copyright:
Copyright 2021 Elsevier B.V., All rights reserved.

Keywords

  • Endwall Cooling
  • Impingement Vortex
  • Secondary Flows
  • Vane Surface Cooling

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