GAS TURBINE ENGINE COMBUSTOR WITH IMPROVED COOLING
摘要
A gas turbine engine combustor liner having a plurality of holes defined therein for directing air into the combustion chamber. The plurality of holes provide a greater cooling air flow in regions intermediate each diffuser pipe than in other areas of the combustor liner.
申请公布号
CA2583400(A1)
申请公布日期
2007.09.30
申请号
CA20072583400
申请日期
2007.03.30
申请人
PRATT & WHITNEY CANADA CORP.
发明人
SAMPATH, PARTHASARATHY;PATEL, BHAWAN;PARKER, RUSSELL
