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Title: Effects of surface deposition, hole blockage, and thermal barrier coating spallation on vane endwall film cooling

Abstract

With the increase in usage of gas turbines for power generation and given that natural gas resources continue to be depleted, it has become increasingly important to search for alternate fuels. One source of alternate fuels is coal derived synthetic fuels. Coal derived fuels, however, contain traces of ash and other contaminants that can deposit on vane and turbine surfaces affecting their heat transfer through reduced film cooling. The endwall of a first stage vane is one such region that can be susceptible to depositions from these contaminants. This study uses a large-scale turbine vane cascade in which the following effects on film cooling adiabatic effectiveness were investigated in the endwall region: the effect of near-hole deposition, the effect of partial film cooling hole blockage, and the effect of spallation of a thermal barrier coating. The results indicated that deposits near the hole exit can sometimes improve the cooling effectiveness at the leading edge, but with increased deposition heights the cooling deteriorates. Partial hole blockage studies revealed that the cooling effectiveness deteriorates with increases in the number of blocked holes. Spallation studies showed that for a spalled endwall surface downstream of the leading edge cooling row, cooling effectiveness worsened withmore » an increase in blowing ratio.« less

Authors:
;  [1]
  1. Virginia Polytechnic Institute & State University, Blacksburg, VA (USA)
Publication Date:
OSTI Identifier:
21004567
Resource Type:
Journal Article
Journal Name:
Journal of Turbomachinery
Additional Journal Information:
Journal Volume: 129; Journal Issue: 3; Journal ID: ISSN 0889-504X
Country of Publication:
United States
Language:
English
Subject:
20 FOSSIL-FUELED POWER PLANTS; GAS TURBINES; FUEL GAS; TURBINE BLADES; COAL GASIFICATION; FLY ASH; DEPOSITION; DEPOSITS; PERFORMANCE

Citation Formats

Sundaram, N, and Thole, K A. Effects of surface deposition, hole blockage, and thermal barrier coating spallation on vane endwall film cooling. United States: N. p., 2007. Web. doi:10.1115/1.2720485.
Sundaram, N, & Thole, K A. Effects of surface deposition, hole blockage, and thermal barrier coating spallation on vane endwall film cooling. United States. https://doi.org/10.1115/1.2720485
Sundaram, N, and Thole, K A. 2007. "Effects of surface deposition, hole blockage, and thermal barrier coating spallation on vane endwall film cooling". United States. https://doi.org/10.1115/1.2720485.
@article{osti_21004567,
title = {Effects of surface deposition, hole blockage, and thermal barrier coating spallation on vane endwall film cooling},
author = {Sundaram, N and Thole, K A},
abstractNote = {With the increase in usage of gas turbines for power generation and given that natural gas resources continue to be depleted, it has become increasingly important to search for alternate fuels. One source of alternate fuels is coal derived synthetic fuels. Coal derived fuels, however, contain traces of ash and other contaminants that can deposit on vane and turbine surfaces affecting their heat transfer through reduced film cooling. The endwall of a first stage vane is one such region that can be susceptible to depositions from these contaminants. This study uses a large-scale turbine vane cascade in which the following effects on film cooling adiabatic effectiveness were investigated in the endwall region: the effect of near-hole deposition, the effect of partial film cooling hole blockage, and the effect of spallation of a thermal barrier coating. The results indicated that deposits near the hole exit can sometimes improve the cooling effectiveness at the leading edge, but with increased deposition heights the cooling deteriorates. Partial hole blockage studies revealed that the cooling effectiveness deteriorates with increases in the number of blocked holes. Spallation studies showed that for a spalled endwall surface downstream of the leading edge cooling row, cooling effectiveness worsened with an increase in blowing ratio.},
doi = {10.1115/1.2720485},
url = {https://www.osti.gov/biblio/21004567}, journal = {Journal of Turbomachinery},
issn = {0889-504X},
number = 3,
volume = 129,
place = {United States},
year = {Sun Jul 15 00:00:00 EDT 2007},
month = {Sun Jul 15 00:00:00 EDT 2007}
}