AIR COOLING SYSTEMS FOR GAS TURBINE ENGINES
Assignee
ROLLS-ROYCE LIMITED
Filed
Sep 18, 1981
Granted
Apr 14, 1987
Location
DERBY GB
Abstract
A gas turbine engine in which a rotating component (such as a turbine shaft or disc) is cooled by directing preswirled air at it by flowing the air along a passageway defined by the rotating component and a static wall. To reduce the viscous drag on the swirling air due to the presence of the static wall, the static wall is transpired to cause the boundary layer of air adjacent the wall to move in the same direction as the swirling air. The wall may be transpired by sucking or blowing air through air passages through the wall.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Apr 23, 1982
Rescinded
Jan 26, 1983
Duration
9 months
Inventor
- 1PETER F. NEAL
Record Details
- Patent number
- US 4657482
- Application
- 06308188
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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