Effects of deposits on film cooling of a vane endwall along the pressure side

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

Abstract

Film-cooling is influenced by surface roughness and depositions that occur from contaminants present in the hot gas path, whether that film-cooling occurs on the vane itself or on the endwalls associated with the vanes. Secondary flows in the endwall region also affect the film-cooling performance along the endwall. An experimental investigation was conducted to study the effect of surface deposition on film-cooling along the pressure side of a first-stage turbine vane endwall. A large-scale wind tunnel with a turbine vane cascade was used to perform the experiments. The vane endwall was cooled by an array of filmcooling holes along the pressure side of the airfoil. Deposits having a semi-elliptical shape were placed along the pressure side to simulate individual row and multiple row depositions. Results indicated that the deposits lowered the average adiabatic effectiveness levels downstream of the film-cooling rows by deflecting the coolant jets towards the vane endwall junction on the pressure side. Results also indicated that there was a steady decrease in adiabatic effectiveness with a sequential increase in the number of rows with the deposits.

Original languageEnglish (US)
Title of host publicationProceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air
Pages185-195
Number of pages11
DOIs
StatePublished - Sep 24 2007
Event2007 ASME Turbo Expo - Montreal, Que., Canada
Duration: May 14 2007May 17 2007

Publication series

NameProceedings of the ASME Turbo Expo
Volume4 PART A

Other

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

All Science Journal Classification (ASJC) codes

  • Engineering(all)

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