A gas turbine engine shroud includes a row of different first and second shroud segments alternating circumferentially therearound. The first segments have a first pattern of first cooling holes extending therethrough. The second segments have a second pattern of second cooling holes extending therethrough. The corresponding patterns have different collective flowrate capabilities.
申请公布号
US2009155051(A1)
申请公布日期
2009.06.18
申请号
US20070957653
申请日期
2007.12.17
申请人
LEE CHING-PANG;ROBINSON GEOFFREY DOUGLAS;ORLANDO ROBERT JOSEPH
发明人
LEE CHING-PANG;ROBINSON GEOFFREY DOUGLAS;ORLANDO ROBERT JOSEPH