Turbine disc ingress prevention method and apparatus
US5759012A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Dec 13, 1996 |
| Grant date | Jun 2, 1998 |
| Priority date | — |
| Expiry date | Dec 13, 2016 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The invention disclosed and taught herein teaches method and apparatus for restricting the ingress of hot combustion gases into the turbine disc plenum of a gas turbine engine as the hot gases flow from a turbine nozzle assembly and into the turbine blades. A jet of engine cooling air is injected into the wake region immediately behind and down stream of the nozzle assembly's stator vanes thereby reducing the static pressure recovery otherwise occurring within the wake region. Thus, a lessor amount of buffering air is required within the turbine disc plenum to prevent the ingress of hot gases thereby resulting in an increased efficiency of the engine's cooling air delivery system and over all engine performance.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.