TY - GEN
T1 - Considerations of a double-wall cooling design to reduce sand blockage
AU - Land, Camron C.
AU - Thole, Karen A.
AU - Joe, Chris
PY - 2008
Y1 - 2008
N2 - Gas turbine engines use innovative cooling techniques to keep metal temperatures down while pushing the main gas temperature as high as possible, Cooling technologies such as film-cooling and impingement cooling are generally used to reduce metal temperatures of the various components in the combustor and turbine sections. As cooling passages become more complicated, ingested particles can block these passages and greatly reduce the life of hot section components. This study investigates a double-walled cooling geometry with impingement and film-cooling. A number of parameters were simulated to investigate the success of using impingement jets to reduce the size of particles in the cooling passages. Pressure ratios typically ranged between those used for combustor liner cooling and for blade outer air seal cooling whereby both these locations typically use double-walled liners. The results obtained in this study are applicable to more intricate geometries where the need to promote particle breakup exists. Results indicated that ingested sand had a large distribution of particle sizes where particles greater than 150 um are primarily responsible for blocking the cooling passages. Results also showed that the blockage from these large particles was significantly influenced and can be significantly reduced by controlling the spacing between the film-cooling and impingement cooling plates.
AB - Gas turbine engines use innovative cooling techniques to keep metal temperatures down while pushing the main gas temperature as high as possible, Cooling technologies such as film-cooling and impingement cooling are generally used to reduce metal temperatures of the various components in the combustor and turbine sections. As cooling passages become more complicated, ingested particles can block these passages and greatly reduce the life of hot section components. This study investigates a double-walled cooling geometry with impingement and film-cooling. A number of parameters were simulated to investigate the success of using impingement jets to reduce the size of particles in the cooling passages. Pressure ratios typically ranged between those used for combustor liner cooling and for blade outer air seal cooling whereby both these locations typically use double-walled liners. The results obtained in this study are applicable to more intricate geometries where the need to promote particle breakup exists. Results indicated that ingested sand had a large distribution of particle sizes where particles greater than 150 um are primarily responsible for blocking the cooling passages. Results also showed that the blockage from these large particles was significantly influenced and can be significantly reduced by controlling the spacing between the film-cooling and impingement cooling plates.
UR - http://www.scopus.com/inward/record.url?scp=69949154747&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=69949154747&partnerID=8YFLogxK
U2 - 10.1115/GT2008-50160
DO - 10.1115/GT2008-50160
M3 - Conference contribution
AN - SCOPUS:69949154747
SN - 9780791843130
T3 - Proceedings of the ASME Turbo Expo
SP - 145
EP - 154
BT - 2008 Proceedings of the ASME Turbo Expo
T2 - 2008 ASME Turbo Expo
Y2 - 9 June 2008 through 13 June 2008
ER -