Method for intermediate cooling and gas turbine system with intermediate cooling
US6966745B2 · kind B2 · utility
1Cited by
7References
10Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jun 20, 2003 |
| Grant date | Nov 22, 2005 |
| Priority date | — |
| Expiry date | Jun 20, 2023 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02C7/143
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
In a method and a device for intermediate cooling during compression in a gas turbine system, the gas turbine system includes at least one first (1) and one second compressor (2), a combustion chamber (3), and a turbine (4). At least one intermediate cooler (9) is located between the first (1) and second compressor (2). The intermediate cooling takes place at least in part or for the most part isentropically.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.