Gas turbine cooling system
US4086757A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Oct 6, 1976 |
| Grant date | May 2, 1978 |
| Priority date | — |
| Expiry date | Oct 6, 1996 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D5/3015
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A cooling system for a gas turbine engine having a gasifier turbine and a power turbine each interconnected by a turbine casing utilizes compressed cooling air communicated to axial cavities in the ends of the respective turbine shafts. This compressed air is directed outwardly between a flange integrally formed with the turbine shaft and the turbine wheel for communication to the turbine blades. In the gasifier turbine the cooling air passes through longitudinal passages formed in each blade, while in the power turbine the cooling air is discharged adjacent the blade root. Wheel flanges affixed on either side of the turbine wheel serve to retain the blades axially on the wheel. Compressed cooling air is also communicated to the nozzle vanes of the gasifier turbine wherein internal passages communicate the air into the main gas stream. Certain nozzle vanes are equipped with passage means to communicate air to an annular chamber surrounding the gasifier turbine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.