Mounting assembly for igniter in a gas turbine engine combustor having a ceramic matrix composite liner
US6920762B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 14, 2003 |
| Grant date | Jul 26, 2005 |
| Priority date | — |
| Expiry date | Mar 30, 2023 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/00012
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An assembly for mounting an igniter in a gas turbine engine combustor between an outer casing and an outer liner, wherein a longitudinal centerline axis extends through the gas turbine engine. The igniter mounting assembly includes a first spring member encircling a portion of said igniter and being positioned between a surface adjacent the outer casing and an outer surface of the outer liner, a first ring member connected to a first end of the first spring member adjacent the outer surface of the outer liner, and a second ring member connected to a second end of the first spring member adjacent the surface adjacent the outer casing. Accordingly, the igniter is able to maintain substantial alignment with respect to an opening in the outer liner while moving radially and/or axially with respect to the outer liner as the outer casing experiences thermal growth greater than the outer liner.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.