Invention Grant
- Patent Title: Cooling system for aircraft gas turbine engine
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Application No.: US17304947Application Date: 2021-06-29
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Publication No.: US11408344B2Publication Date: 2022-08-09
- Inventor: Fuminori Suzuki , Naoki Seki , Toshikazu Kobayashi
- Applicant: IHI Corporation
- Applicant Address: JP Tokyo
- Assignee: IHI Corporation
- Current Assignee: IHI Corporation
- Current Assignee Address: JP Tokyo
- Agency: Oblon, McClelland, Maier & Neustadt, L.L.P.
- Priority: JPJP2019-023511 20190213
- Main IPC: F02C7/12
- IPC: F02C7/12

Abstract:
A cooling system includes: a core casing configured to house a compressor, a combustion chamber, and a turbine; a tail cone configured to form at least part of an exhaust passage of the turbine together with the core casing; struts configured to connect the core casing with a support body of the tail cone; a housing installed in the tail cone, configured to house an electrical apparatus; and at least one primary duct configured to connect between an internal space of the housing and an outlet passage of the compressor or a discharge port of a blower installed in a gas turbine engine via at least one of the struts and a radial outside of the core casing.
Public/Granted literature
- US20210324799A1 COOLING SYSTEM FOR AIRCRAFT GAS TURBINE ENGINE Public/Granted day:2021-10-21
Information query
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