Turbine cooling for gas turbine engine
US4820116A · kind A · utility
80Cited by
10References
2Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 18, 1987 |
| Grant date | Apr 11, 1989 |
| Priority date | — |
| Expiry date | Sep 18, 2007 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D5/081
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine cooling system has cooling air cooling in order, the first stage disk (50) and blades (22), the second stage vanes (24), and the second stage air seal (82). Air passes to the second stage vane from the rotor through a reaction nozzle (62) effecting a reaction stage adding energy to the rotor and cooling the air.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.