Method and apparatus for cooling gas turbine engine igniter tubes
US6557350B2 · kind B2 · utility
31Cited by
10References
19Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 17, 2001 |
| Grant date | May 6, 2003 |
| Priority date | — |
| Expiry date | Jul 5, 2021 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/03044
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor for a gas turbine engine includes a plurality of igniter tubes that facilitate reducing temperature gradients within the combustor in a cost effective and reliable manner. The combustor includes an annular outer liner that includes a plurality of openings sized to receive igniter tubes. Each igniter tube maintains an alignment of each igniter received therein, and includes an air impingement device that extends radially outward from the igniter tube. During operation, airflow contacting the air impingement device is channeled radially inward for impingement cooling of the igniter tubes and the combustor outer liner.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.