Thermal management system for a gas turbine engine with an integral oil tank and heat exchanger in the nacelle
US10233841B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 5, 2015 |
| Grant date | Mar 19, 2019 |
| Priority date | — |
| Expiry date | Apr 3, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
In one exemplary embodiment, a gas turbine engine system for cooling engine components includes an engine core, a core housing containing the engine core, an engine core driven fan forward of the core housing, a nacelle surrounding the fan and the core housing, and a bypass duct defined between an outer diameter of the core housing and an inner diameter of the nacelle. Also included is a thermal management system having a coolant circuit including at least one of a first heat exchanger disposed on the inner diameter of the nacelle and a second heat exchanger disposed on a leading edge of a BiFi spanning the bypass duct. The first heat exchanger is in thermal communication with the second heat exchanger.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.