System for cooling a gas turbine by bleeding air from the compressor
US4415310A · kind A · utility
42Cited by
10References
5Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 6, 1981 |
| Grant date | Nov 15, 1983 |
| Priority date | — |
| Expiry date | Oct 6, 2001 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A system for cooling a gas turbine by bleeding air from the compressor and channeling the air at the center of the engine towards the turbine in order to cool it. The air is bled from the plane of the disc bearing the blades of the compressor, said disc having radial ducts for the flow of the air. The invention is utilized in gas turbine engines to cool the turbine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.