Gas turbine engine
US12078106B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 11, 2023 |
| Grant date | Sep 3, 2024 |
| Priority date | — |
| Expiry date | Sep 11, 2043 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF25B9/04
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine for an aircraft including: a compressor stage; a bleed air line diverted from the compressor stage; and a thermoelectric generator system, the thermoelectric generator system including a thermoelectric generator; a vortex tube and a radiator system, the vortex tube including a flow input fluidically connected to the bleed air line to receive an input of compressed gas from the bleed air line, wherein the vortex tube is configured to separate the compressed gas into a hot flow discharged from a first output of the vortex tube, and a cold flow discharged from a second output of the vortex tube; the radiator system including a first heat exchanger and a second heat exchanger disposed on opposing sides of the thermoelectric generator; and at least one of the hot flow is directed to the first heat exchanger, and the cold flow is directed to the second heat exchanger.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.