Turbine engine heat recuperator system
US9068506B2 · kind B2 · utility
19Cited by
21References
15Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 30, 2012 |
| Grant date | Jun 30, 2015 |
| Priority date | — |
| Expiry date | Jan 11, 2034 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/17
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine recuperator system includes a heat recuperator positioned in a gas turbine exhaust gas duct for recovering heat from turbine exhaust gases to preheat a compressor flow being supplied to the combustor. A continuous bleed flow of the turbine exhaust gases is provided to bypass the heat recuperator. The continuous bleed flow of the turbine exhaust gases is adjustable to reduce turbine exhaust gas pressure loss at a high engine operation level and to provide efficient heat recovery at low and/or medium engine operation levels.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.