Turbine vane cooling
US3936215A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Dec 20, 1974 |
| Grant date | Feb 3, 1976 |
| Priority date | — |
| Expiry date | Dec 20, 1994 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method and apparatus for providing high pressure cooling air to the turbine vanes of a gas turbine engine is disclosed. A centrifugal compressor stage is interposed in the flow path of cooling air to the turbine vanes. The centrifugal compressor stage raises the pressure of the cooling air to a value substantially greater than the pressure of the combustion gases entering the turbine. The availability of high pressure cooling air allows the incorporation of improved cooling systems in the turbine vanes. Increasingly effective cooling systems are necessary to the continued development of low pressure drop combustion chambers which discharge high temperature gases to the inlet of the turbine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.