Heat exchanger for gas turbine engine mounted in intermediate case
US10982595B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 23, 2016 |
| Grant date | Apr 20, 2021 |
| Priority date | — |
| Expiry date | Mar 19, 2039 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.