Combustion liner for gas turbine formed of cast nickel-based superalloy
US7540156B2 · kind B2 · utility
5Cited by
6References
6Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 21, 2005 |
| Grant date | Jun 2, 2009 |
| Priority date | — |
| Expiry date | Jun 16, 2027 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/00018
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustion liner for a gas turbine combustion system is provided. The combustion liner comprises a combustion zone between an inlet end and an exhaust end. The combustion liner comprises a one-piece casting construction. The combustion liner is formed from a nickel-based superalloy having strength characteristics.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.