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公开(公告)号：EP2971673A1
公开(公告)日：2016-01-20
申请号：EP14774334.8
申请日：2014-03-10
发明人： MOSLEY, John H. , CHRISIKOS, James P. , GATES, Roger , O'CONNOR, John J. , WU, Charles C. , GLASSPOOLE, David
CPC分类号： F02C9/18 , F01D5/082 , F02C7/18 , F05D2220/3215 , Y02T50/673 , Y02T50/676
摘要： A cooling system for a gas turbine engine turbine section includes a rotor supporting a blade having a cooling passage. A disc is secured relative to the rotor and it forms a cavity between the rotor and the disc. A bleed air source is in fluid communication with the cavity. An impeller is arranged in the cavity. The impeller is configured to increase a fluid pressure within the cavity to drive bleed air from the bleed air source and thereby provide a pressurized cooling fluid to the cooling passage.
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公开(公告)号：EP2855884B1
公开(公告)日：2019-08-14
申请号：EP13797827.6
申请日：2013-05-15
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公开(公告)号：EP2855884A1
公开(公告)日：2015-04-08
申请号：EP13797827.6
申请日：2013-05-15
发明人： MOSLEY, John H. , ALVANOS, Ioannis , STRIPINIS, Philip S. , FREIBERG, Douglas Paul , PINERO, Hector M. , O'CONNOR, John J. , PIETROBON, Jon
摘要： A gas turbine engine configured to rotate in a circumferential direction about an axis extending through a center of the gas turbine engine comprises a turbine stage. The turbine stage comprises a disk, a plurality of blades and a mini-disk. The disk comprises an outer diameter edge having slots, an inner diameter bore surrounding the axis, a forward face, and an aft face. The plurality of blades is coupled to the slots. The mini-disk is coupled to the aft face of the rotor to define a cooling plenum therebetween in order to direct cooling air to the slots. In one embodiment of the invention, the cooling plenum is connected to a radially inner compressor bleed air inlet through all rotating components so that cooling air passes against the inner diameter bore.
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