- 专利标题： ENGINE DRIVEN BY SC02 CYCLE WITH INDEPENDENT SHAFTS FOR COMBUSTION CYCLE ELEMENTS AND PROPULSION ELEMENTS
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申请号： EP16174191.3申请日： 2016-06-13
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公开(公告)号： EP3109433B1公开(公告)日： 2018-08-15
- 发明人: Vaisman, Igor , Armstrong, Michael James
- 申请人： Rolls-Royce Corporation , Rolls-Royce North American Technologies, Inc.
- 申请人地址： 450 South Meridian Street Indianapolis, Indiana 46225-1103 US
- 专利权人： Rolls-Royce Corporation,Rolls-Royce North American Technologies, Inc.
- 当前专利权人： Rolls-Royce Corporation,Rolls-Royce North American Technologies, Inc.
- 当前专利权人地址： 450 South Meridian Street Indianapolis, Indiana 46225-1103 US
- 代理机构： Ström & Gulliksson AB
- 优先权： US201562181887P 20150619
- 主分类号： F02C1/00
- IPC分类号： F02C1/00 ; F02C1/10 ; F02C6/20 ; F02C7/08 ; F02C7/141 ; F02C7/18 ; F01K23/10 ; F02K3/077
摘要：
A gas turbine engine (10, 200, 300, 400, 500, 600, 700, 800) includes a first shaft (202) coupled to a first turbine (204, 506) and a first compressor (206, 608), a second shaft (208) coupled to a second turbine (210) and a second compressor (212), and a third shaft (214) coupled to a third turbine (216) and a fan assembly (218, 306, 318, 414, 416). The turbine engine includes a heat rejection heat exchanger (220, 402) configured to reject heat from a closed loop system (222, 314) with air passed from the fan assembly (218, 306, 318, 414, 416), and a combustor (224) positioned to receive compressed air from the second compressor (212) as a core stream (226, 320, 418). The closed-loop system (222, 314) includes the first, second, and third turbines (204, 210, 216, 506) and the first compressor (206, 608) and receives energy input from the combustor (224).
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