COMBUSTION CHAMBER CONSTRUCTION
Assignee
Filed
Dec 19, 1972
Granted
Nov 6, 1984
Location
CINCINNATI OH US
Abstract
A combustion chamber for use in gas turbine engines is provided with a liner formed of a high temperature material. The liner includes a plurality of panels of the material mounted by means of a lost motion mounting arrangement upon a high strength structural frame. As a result of this mounting arrangement, the liner is substantially isolated from structural forces associated with the combustion chamber, while the frame is substantially isolated from thermal stresses associated with the liner. For the purpose of supplying cooling air to the liner panels and frame and cooling air is passed into a plenum to cool the radially outward side of the panels. Transfer means are provided for directing the same air from the plenum to the liner inner surfaces in a cooling film. The liner mounting arrangement disclosed herein is particularly useful with difficult-to-weld liner materials (e.g., oxide dispersion strengthened materials), but its advantages commend its use with other materials also.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Jan 28, 1982
Rescinded
Apr 12, 1984
Duration
2 years, 2 months
Inventor
- 1HARVEY M. MACLIN
Record Details
- Patent number
- US 4480436
- Application
- 05316531
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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