CO-SWIRL ORIENTATION OF COMBUSTOR EFFUSION PASSAGES FOR GAS TURBINE ENGINE COMBUSTOR
摘要
A liner panel for use in a combustor for a gas turbine engine includes a forward region including a multiple of effusion passages each directed at an orientation consistent with a local swirl direction of combustion gases. Another liner panel for use in a combustor for a gas turbine engine includes a forward region forward of a dilution passage and an aft region aft of the forward region. The forward region includes a multiple of effusion passages each directed generally circumferentially. The aft region includes a multiple of effusion passages each directed at an orientation generally axially. A method of cooling a wall assembly within a combustor of a gas turbine engine includes orienting a multiple of effusion passages within a forward region consistent with a local swirl direction of combustion gases.
申请公布号
WO2015126501(A3)
申请公布日期
2015.10.22
申请号
WO2014US68377
申请日期
2014.12.03
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
TU, JOHN S.;SNYDER, TIMOTHY S.;HOKE, JAMES B.;BANGERTER, JAMES P.;DUHAMEL, DENNIS J.;BURNS, DAVID A.