COOLED AEROFOIL BLADE OR VANE FOR A GAS TURBINE ENGINE
Assignee
ROLS-ROYCE PLC, A BRITISH COMPANY
Filed
Sep 4, 1986
Granted
Nov 23, 1993
Location
DERBY EN GB
Abstract
A cooled aerofoil blade for a gas turbine engine has a hollow trailing edge region in which bridging members interconnect the convex and concave flanks of the blade. The bridging members are each provided with angled cooling passages which are in operation exposed to a cooling air flow and direct that flow onto the internal surfaces of the convex and concave flanks so as to provide impingement cooling thereof.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
May 1, 1987
Rescinded
Jan 14, 1993
Duration
5 years, 8 months
Inventor
- 1HENRY TUBBS
Record Details
- Patent number
- US 5263820
- Application
- 06906252
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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