Integrated thermal management and coolant system for an aircraft
US6415595B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 22, 2000 |
| Grant date | Jul 9, 2002 |
| Priority date | — |
| Expiry date | Aug 22, 2020 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A thermal management system avoids problems associated with the recirculation of fuel through a fuel tank on an aircraft in a system that includes a fuel reservoir (70), a pump (72) for pumping fuel from the reservoir (70) to a first heat load (74) and then to a check valve (76) to a junction (78). At least one second heat load (80), (82), (84) is connected to the junction (78) and a fuel/fan air heat exchanger (104) having a fan air flow path in heat exchange relation with a fuel flow path having a fuel discharge end (106) connected to the junction (78). The fan air flow path is adapted to be connected to receive compressed air from the fan (30) of an engine (10). A bleed air/fuel heat exchanger (92) receives fuel from the second heat load and bleed air from the engine (10) and is connected to deliver fuel to the engine (10). A control valve (86) is interposed between the second heat load and the engine (10) for proportioning the flow of fuel to the engine (10) and the fuel fan heat exchanger (104) so that excess fuel is recirculated without reintroduction into the fuel reservoir (70).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.