STRESS RELIEF FEATURE FOR AERATED GAS TURBINE FUEL INJECTOR
摘要
Thermal stress relief in a nozzle head of a gas turbine fuel nozzle is provided by forming a slit through each selected air passages of the nozzle head. The strategic location of stress-relief slits contributes to extend the fatigue life of the nozzle with minimal cost and impact on the nozzle aerodynamics.
申请公布号
CA2496908(C)
申请公布日期
2011.03.22
申请号
CA20032496908
申请日期
2003.08.22
申请人
PRATT & WHITNEY CANADA CORP.
发明人
PROCIW, LEV ALEXANDER;SHAFIQUE, HARRIS;GANDZA, VICTOR