AXIAL FLOW GAS TURBINES
Assignee
ROLLS-ROYCE LIMITED
Filed
Jan 18, 1984
Granted
Dec 7, 1993
Location
DERBY GB
Abstract
An axial flow gas turbine is provided with a shroud ring which is defined by two axially adjacent heat pipes. The radially inner face of the shroud ring has a plurality of axially extending cooling air passages located adjacent to it. Cooling air, which in operation is directed through the passages serves to provide cooling of the shroud ring and the substantial elimination of any radial heat flux in the shroud ring.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Apr 30, 1984
Rescinded
Oct 22, 1992
Duration
8 years, 5 months
Inventor
- 1PETER A. DAMIRAL
Record Details
- Patent number
- US 5267831
- Application
- 06573947
- 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
GAS TURBINE ENGINE
ROLLS-ROYCE LIMITED
COOLED TURBINE BLADE
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