Fluid cooling arrangement for a gas turbine engine and method
US9726029B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 18, 2013 |
| Grant date | Aug 8, 2017 |
| Priority date | — |
| Expiry date | Mar 31, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A fluid cooling arrangement in a gas turbine engine for aerospace propulsion includes an inner structure. Also included is an outer structure disposed radially outwardly of the inner structure, the outer structure and the inner structure defining a bypass flow path. Further included is at least one strut operatively coupling the inner structure to the outer structure. Yet further included is at least one cooling tube formed within the at least one strut, the at least one cooling tube configured to cool a fluid passing through the at least one cooling tube upon convective cooling of the at least one strut as air passes through the bypass flow path and over the at least one strut.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.