Mounting a turbine nozzle on a combustion chamber having CMC walls in a gas turbine
US7249462B2 · kind B2 · utility
58Cited by
7References
22Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jun 16, 2005 |
| Grant date | Jul 31, 2007 |
| Priority date | — |
| Expiry date | Jan 13, 2026 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The gas turbine comprises an annular combustion chamber having inner and outer walls made of ceramic matrix composite material, and a high pressure turbine nozzle secured to a downstream end of the combustion chamber and comprising a plurality of stationary airfoils extending between the inner and outer walls of an annular flow path through the nozzle for the gas stream coming from the combustion chamber. The turbine nozzle is made of ceramic matrix composite material and it is connected to the downstream end of the combustion chamber by brazing.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.