COOLING SYSTEM FOR AIRCRAFT GAS TURBINE ENGINE

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 tai...

Full description

Saved in:
Bibliographic Details
Main Authors KOBAYASHI, Toshikazu, SEKI, Naoki, SUZUKI, Fuminori
Format Patent
LanguageEnglish
Published 21.10.2021
Subjects
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
GAS-TURBINE PLANTS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
Online AccessGet full text

Cover

More Information
Summary: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.
Bibliography:Application Number: US202117304947