- 专利标题: TURBINE ENGINE ADVANCED COOLING SYSTEM
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申请号: US14871382申请日: 2015-09-30
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公开(公告)号: US20170089263A1公开(公告)日: 2017-03-30
- 发明人: Joseph Clegg , Craig English , Behram Kapadia , Kenneth M. Pesyna , Jason Lee Swindle , Jason Wayne Rector , Christopher Vincent , Nicholas D. Metzger , Daniel G. Edwards
- 申请人: Rolls-Royce Corporation , Rolls-Royce North American Technologies Inc.
- 主分类号: F02C7/12
- IPC分类号: F02C7/12 ; F02C7/24 ; F04D29/58 ; F01D25/12 ; F04D29/32 ; F02C3/04 ; F01D5/02
摘要:
A cooling system for a gas turbine is provided that may include a drive shaft, a shield of a combustor of the gas turbine engine, and a conduit. The drive shaft may be configured to mechanically couple a compressor of the gas turbine engine to a turbine of the gas turbine engine. The shield may be positioned between the compressor and the turbine. The combustor may be configured to drive the turbine. The conduit may be configured to supply a cooling fluid to a gap between an outer surface of the drive shaft and the shield of the combustor.
公开/授权文献
- US10208668B2 Turbine engine advanced cooling system 公开/授权日:2019-02-19