Closed cycle heat engine for a gas turbine engine
US10941706B2 · kind B2 · utility
10Cited by
102References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Feb 13, 2018 |
| Grant date | Mar 9, 2021 |
| Priority date | — |
| Expiry date | Oct 31, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An aeronautical gas turbine engine includes a turbomachine including a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order. The aeronautical gas turbine engine additionally includes a closed cycle heat engine including a compressor configured to compress a working fluid; a primary heat exchanger in thermal communication with the turbomachine and the working fluid, the primary heat exchanger configured to transfer heat from the turbomachine to the working fluid; an expander coupled to the compressor for expanding the working fluid; and an output shaft driven by the expander.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.