Gas turbine installation with cooling by two separate cooling air flows
US4127988A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Jul 20, 1977 |
| Grant date | Dec 5, 1978 |
| Priority date | — |
| Expiry date | Jul 20, 1997 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D5/08
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Gas turbine installation includes a compressor and a gas turbine and has a rotor including rotary parts of the compressor and the gas turbine, the compressor having an air flow path therethrough external to the rotor. The gas turbine installation further includes a system for cooling the parts of the gas turbine including means defining two different air flow paths within the rotor, one of the cooling air flow paths within the rotor branching from the external air flow path at an intermediate stage of the compressor at which the absolute velocity of the air flow into the rotor is relatively low and extending to an axial region of the rotor, and the other of the cooling air flow paths within the rotor branching from the external air flow path at a location downstream from the compressor in flow direction of the external air flow at which the circumferential velocity of the air flow into the rotor is relatively high and extending into a radially outwardly disposed region of the rotor, both of the cooling air flow paths extending mutually concentrically through a nonpartioned chamber in the rotor to the rotary parts of the gas turbine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.