Gas turbine engine having a heat exchanger arrangement for exhaust gas flows
US7971438B2 · kind B2 · utility
16Cited by
13References
10Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 3, 2007 |
| Grant date | Jul 5, 2011 |
| Priority date | — |
| Expiry date | Apr 25, 2030 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Environmental concerns have resulted in consideration of the effects of condensation trails from gas turbine engines. By provision of a condensation stage in a heat exchanger arrangement for a gas turbine engine the level of condensation within a final exhaust gas flow G from an engine is reduced. Furthermore, by cooling of the exhaust gas flows for mixing with by-pass air flows a water partial pressure at an exhaust gas exit temperature can be provided which is below the eutectic liquid to vapor phase transition and therefore avoid condensation (contrail) formation.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.