COMBUSTION LINER
Assignee
CHEMICAL BANK, AS AGENT
Filed
Nov 13, 1969
Granted
Jul 12, 1983
Location
INDIANAPOLIS IN US
Abstract
A combustion liner for a gas turbine engine operating at high temperatures has portions of the combustion liner double-walled, with a narrow clearance between the inner and outer walls through which cooling air flows to cool the liner. The surfaces of the walls which define these cooling air inlets are roughened to increase heat transfer from the air to the wall. The walls are joined and held apart by spacing strips extending axially of the liner and bonded to the overlapping wall sections. Large combustion air inlet holes extend through the overlapping wall sections at some points. Auxiliary air inlets for liner cooling are provided downstream of these combustion air inlet holes.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Dec 18, 1981
Rescinded
Jan 26, 1983
Duration
1 year, 1 month
Inventor
- 1ALBERT JAN WERDOUW
Record Details
- Patent number
- US 4392355
- Application
- 04876254
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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