发明名称 Closed loop cooling system for a gas turbine
摘要 A system for removing heat from a gas turbine generally includes a plurality of stationary nozzles arranged in an annular array within the gas turbine. Each of the plurality of stationary nozzles may include a radially outer platform and a radially extending cooling passage. The radially extending cooling passage may have an inlet that extends generally axially and circumferentially across a portion of the radially outer platform. A closed loop cooling coil may extend continuously circumferentially around the radially outer platform of two or more of the plurality of stationary nozzles. The closed loop cooling coil may be disposed circumferentially across and outside of the inlet of the radially extending cooling passage of each of the two or more stationary nozzles, and a cooling medium may flow through the cooling coil and out of the gas turbine so as to remove heat from the gas turbine.
申请公布号 US9382810(B2) 申请公布日期 2016.07.05
申请号 US201213560042 申请日期 2012.07.27
申请人 GENERAL ELECTRIC COMPANY 发明人 Lacy Benjamin Paul;Crum Gregory Allan;Vehr James William
分类号 F01D25/08;F01D25/12;F01D9/06 主分类号 F01D25/08
代理机构 Dority & Manning, PA 代理人 Dority & Manning, PA
主权项 1. A system for cooling a gas turbine, comprising: a. a compressor generally upstream from the gas turbine; b. a plurality of rotor disks axially spaced along and coupled to a rotor shaft that extends axially through the turbine, at least one of the rotor disks defining a cooling passage that extends generally radially through the respective rotor disk, wherein two adjacent rotor disks of the plurality of rotor disks defines at least one wheel space therebetween; c. a compressed working fluid that flows from the compressor into the rotor disk cooling passage and into the at least one wheel space; d. a closed loop cooling coil enclosed within the gas turbine between the compressor and the rotor disk cooling passage and the at least one wheel space; and e. a cooling medium source in fluid communication with the cooling coil, wherein the cooling medium source provides a cooling medium to the cooling coil, wherein the cooling medium flows through the cooling coil and out of the gas turbine to remove heat from the compressed working fluid flowing into the rotor disk cooling passage and into the at least one wheel space.
地址 Schenectady NY US