COOLED TURBINE BLADE
Assignee
ROLLS-ROYCE LIMITED
Filed
Oct 26, 1982
Granted
Aug 4, 1987
Location
GLOUCESTERSHIRE GB
Abstract
The blade has an aerofoil body 10 having a leading edge surface 11 which is cooled by air passing through a helical first passage 12 having first portions passing close to said leading edge surface and alternating with second portions passing through a more nearly central part of the blade section remote from said leading edge. A spanwise but straight second passage 15 extends through the blade in a position within the helical passage and closer to the second than the first portions thereof. Heat abstracted from the leading edge by air flow in said first portions is transferred by the flow to the second portions and from there through the blade material to the flow in the straight passage.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Apr 20, 1983
Rescinded
Apr 25, 1986
Duration
3 years
Inventor
- 1RODNEY J. CLIFFORD
Record Details
- Patent number
- US 4684322
- Application
- 06445072
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
Browse by Assignee
ROLLS-ROYCE LIMITEDMore from this assignee
DIVERTER VALVE WITH BYPASS DUCT OBTURATOR
ROLLS-ROYCE LIMITED
FUEL CONTROL SYSTEM
ROLLS-ROYCE LIMITED
AXIAL FLOW GAS TURBINES
ROLLS-ROYCE LIMITED
GAS TURBINE ENGINE
ROLLS-ROYCE LIMITED
GAS TURBINE ENGINE SHROUD RING MOUNTING
ROLLS-ROYCE LIMITED
JET PROPULSION NOZZLE
ROLLS-ROYCE LIMITED
Related by domain
GAS TURBINE ENGINE COMBUSTOR HAVING TRAPPED DUAL VORTEX CAVITY
General Electric
SOLID ROCKET PROPELLANT
GAS TURBINE ENGINE FAN (U)
General Electric
TURNING VANE ARRANGEMENT FOR IR SUPPRESSORS
SIKORSKY AIRCRAFT CORPORATION
MODULAR ROCKET BOOSTED PENETRATING WARHEAD
LOCKHEED MARTIN CORP.
INTEGRAL SOLID BOOSTER AND HYBRID THRUST SUSTAINING SYSTEM AND PROJECTILE INCORPORATING THE SAME
ENVIRONMENTAL AEROSCIENCE CORPORATION