Method for cooling a gas turbine system and a gas turbine system for performing this method
US6532744B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 5, 2001 |
| Grant date | Mar 18, 2003 |
| Priority date | — |
| Expiry date | Jun 5, 2021 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/205
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine system comprises a compressor that takes in suction air on the inlet side and compresses it to compressor end air that is available on the outlet side, a combustor in which a fuel is burned by using the compressor end air while resulting in the formation of hot gas, as well as a turbine in which the hot gas is expanded while providing work output. In a method for cooling this gas turbine system, compressed air is removed from the compressor, is fed as cooling air for cooling inside an internal cooling channel through thermally loaded components of the combustor and/or the turbine, is then recooled and subsequently compressed and added to the compressor end air. The influence of the cooling on the efficiency of the system is minimized by the fact that at least part of the compressor end air is used to recool the cooling air.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.