TURBINE ROTOR COOLING
Assignee
Filed
Nov 21, 1979
Granted
Jun 11, 1985
Location
MELUN FR
Abstract
The present invention concerns the cooling of turbine rotors, especially those of aircraft turboreactors, and discloses a turbine disc equipped with two sets of channels bored respectively close to each of the sides of the disc and in conformity with its profile, in which flows the cooling air of the turbine blades in order to superficially cool the disc.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Aug 3, 1982
Rescinded
Dec 17, 1984
Duration
2 years, 4 months
Inventor
- 1PIERRE A. GLOWACKI
Record Details
- Patent number
- US 4522562
- Application
- 06097741
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
More from this assignee
IMPROVED CATALITIC SYNTHESIS OF CAGED POLYNITRAMINE COMPOUNDS
SOLID ROCKET PROPELLANT
DUAL INFRARED BAND OBJECTIVE LENS
BANDGAP RADIATION DETECTOR
METHOD OF FORMING TEXTURED HIGH-TEMPERATURE SUPERCONDUCTORS
APPARATUS FOR CONTROLLING THE POSITION AND DIRECTION OF A LASER BEAM
Related by domain
NEURAL NETWORK CONTROLLER FOR A PULSED ROCKET MOTOR TACTICAL MISSILE SYSTEM
Raytheon
VTOL AIRCRAFT NOZZLE
ROLLS-ROYCE PLC
MISSILE JET VANE CONTROL SYSTEM AND METHOD
HUGHES MISSILE SYSTEMS COMPANY
COOLED AIRFOILS FOR A GAS TURBINE ENGINE
UNITED TECHNOLOGIES CORPORATION
LOW OBSERVABLE ENGINE AIR INLET SYSTEM
UNITED TECHNOLOGIES CORPORATION
VECTORABLE NOZZLE FOR AIRCRAFT
ROLLS-ROYCE PLC