Turbine cooling system
US5142859A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Feb 22, 1991 |
| Grant date | Sep 1, 1992 |
| Priority date | — |
| Expiry date | Feb 22, 2011 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02C7/18
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Cooling air delivery systems for gas turbine engines are used to increase component life and increase power and efficiencies. The present system increases the component life and increases efficiencies by better utilizing the cooling air bled from the compressor section of the gas turbine engine. For example, a first flow of cooling air is directed to the nozzle and shroud assembly and another portion of the first flow is exited from the nozzle plenum into an annular reservoir to improve cooling of a rotor assembly and to at least reduce ingestion of hot power gases into the internal portion of the engine. The system further includes a second flow of cooling air which is directed through internal passages of the engine and into the annular reservoir and is used to cool the rotor assembly and to at least reduce ingestion of hot power gases into the internal portion of the gas turbine engine. To insure that the least amount of hot power gas is ingested into the internal portion of the engine is minimized a radial blade flange arrangement and a radial shroud flange arrangement axially overlap each other in a preestablished radially spaced proximity forming a buffering zone therebetween…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.