Gas turbine engine combustor and method of forming same
US10337736B2 · kind B2 · utility
0Cited by
17References
11Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 24, 2015 |
| Grant date | Jul 2, 2019 |
| Priority date | — |
| Expiry date | Oct 16, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine combustor is described which includes outer and inner annular combustor liners formed of sheet metal. The exit duct circumscribes an annular combustor exit and defines a combustion gas path. The exit duct includes a large exit duct having an annular forged metal section which is butt welded at an upstream end to the outer combustor liner to form a first annular joint. The annular forged metal section is fixed at a downstream end to an annular sheet metal wall to form a second annular joint. Methods of forming and of repairing a gas turbine engine combustor are also disclosed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.