Gas turbine engine assemblies with recirculated hot gas ingestion
US8262342B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 10, 2008 |
| Grant date | Sep 11, 2012 |
| Priority date | — |
| Expiry date | Jul 10, 2031 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path configured to receive mainstream hot gas flow. The assembly further includes a stator assembly including a stator vane that extends into the mainstream hot gas flow path and a turbine rotor assembly downstream of the stator assembly that includes a turbine disk and a turbine blade extending from the turbine disk into the mainstream hot gas flow path. The stator assembly and turbine assembly define a turbine disk cavity, and the turbine disk cavity includes a recirculation cavity configured to recirculate gas ingested from the mainstream hot gas flow path back into the mainstream hot gas flow path.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.