Balancing the heat flow between components associated with a gas turbine engine
US4773212A · kind A · utility
139Cited by
10References
8Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 1, 1981 |
| Grant date | Sep 27, 1988 |
| Priority date | — |
| Expiry date | Apr 1, 2001 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02C7/224
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Heat transfer systems for maintaining a thermal balance between a gas turbine engine and heat generating accessory components of the engine are disclosed. In the embodiment illustrated, heat is removed from the cooling system 48 of an electrical generator 46 and is transferred to the fuel supply system 32 of the engine. In one detailed embodiment, the cooling system 48 is in direct heat transfer communication with the downstream portion 62 of the fuel supply system through a heat exchanger 76 and in indirect heat transfer communication with the upstream portion 60 of the fuel supply system through the fuel recirculation system 42.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.