COOLING OF TURBINE COMPONENTS USING COMBUSTOR SHELL AIR
摘要
A turbine engine assembly for a generator including a turbine engine having a compressor section, a combustor section and a turbine section. An air bleed line is in communication with the combustor section for receiving combustor shell air from the combustor section and conveying the combustor shell air as bleed air to a plurality of stages of the turbine section. Bleed air is controlled to flow through the air bleed line when an operating load of the turbine engine assembly is less than a base load of the engine to bypass air exiting the compressor section around a combustor in the combustor section and effect a flow of high pressure combustor shell air to the stages of the turbine section.
申请公布号
WO2011097121(A2)
申请公布日期
2011.08.11
申请号
WO2011US22819
申请日期
2011.01.28
申请人
SIEMENS ENERGY, INC.;FOUST, ADAM, M.;NORDLUND, RAYMOND, S.;CHHABRA, NITIN;LITTLE, DAVID, A.
发明人
FOUST, ADAM, M.;NORDLUND, RAYMOND, S.;CHHABRA, NITIN;LITTLE, DAVID, A.