Heat exchanger for gas turbine engine mounted in intermediate case

Patent metadata

Field	Value
Publication number	US-10982595-B2
Application number	US-201615244025-A
Country	US
Kind code	B2
Filing date	Aug 23, 2016
Priority date	Aug 23, 2016
Publication date	Apr 20, 2021
Grant date	Apr 20, 2021

Abstract

A gas turbine engine has a compressor section including a lower pressure compressor and a higher pressure compressor, and a turbine section. A core engine housing surrounds the compressor section and the turbine section. An outer intermediate housing wall defines an internal chamber between the core housing and the outer intermediate housing. A fan rotor and a fan casing surround the fan rotor to define a bypass duct between the fan case and the outer intermediate housing. A heat exchanger is mounted in the internal chamber and receives high pressure air for cooling the high pressure air and delivering the high pressure air into the core engine housing to be utilized as cooling air for a component. Air from the lower pressure compressor is utilized to cool the higher pressure air in the heat exchanger.

First claim

The invention claimed is:

1. A gas turbine engine comprising:
a compressor section including a lower pressure compressor and a higher pressure compressor, and a turbine section;
a core engine housing surrounding said compressor section and said turbine section, and
an outer intermediate housing having a wall defining an internal chamber between said core housing and said outer intermediate housing;
a fan rotor and a fan casing surrounding said fan rotor to define a bypass duct between said fan case and said outer intermediate housing, and a heat exchanger mounted in said internal chamber and receiving high pressure air for cooling said high pressure air and delivering said high pressure air into said core engine housing to be utilized as cooling air for a component;
air from said lower pressure compressor being utilized to cool the higher pressure air in said heat exchanger;
wherein a valve is selectively opened and closed to bleed air from said lower pressure compressor, and said valve being opened to provide air across said heat exchange for cooling said higher pressure air;
wherein said valve is controlled to be at least partially open at a takeoff condition;
wherein said valve is controlled to be moved towards a closed position at lower power operation but at least partially open at idle;
wherein said valve is a bleed valve controlled to lower a load on said compressor section;
wherein said heat exchanger is formed of elongated members having fins on an outer surface;
wherein said heat exchanger is formed of a cast nickel alloy material; and
wherein said cast nickel alloy material includes more than 50-percent per volume gamma-prime (Y′).

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Schwarz Frederick M
• Duesler Paul W

Classifications

• F02C9/18 Primary

  by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} · CPC title

• F02C7/18

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F05D2300/176

  Heat-stable alloys · CPC title

• F05C2201/90

  Alloys not otherwise provided for · CPC title

• F05D2260/213

  by the provision of a heat exchanger within the cooling circuit · CPC title