TURBO MACHINE SHROUD-T0-ROTOR BLADE DYNAMIC CLEARANCE CONTROL
Assignee
Filed
Jun 6, 1986
Granted
Feb 11, 1997
Location
LAWRENCEBURG IN US
Abstract
A clearance control arrangement for the rotor blade-to-stator shroud clearance in an aircraft engine or other turbo machine. The disclosed arrangements use large area piston-like structures located circumferential to the turbo machine and capable of operation from pressures developed within the machine. One disclosed arrangement incorporates static adjustment capability that can be disposed to provide symmetrical or asymmetrical clearances. The disclosed clearance control can be used as a fast-acting supplement or in lieu of other clearance control arrangements and is arranged to be actuated upon sensing the onset of rotor-to-stator collision pinch point conditions in the turbo machine.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Aug 8, 1986
Rescinded
Nov 8, 1993
Duration
7 years, 3 months
Inventor
- 1THOMAS G. WAKEMAN
Record Details
- Patent number
- US 5601402
- Application
- 06874201
- 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
V/STOL AIRCRAFT
BRITISH AEROSPACE PUBLIC LIMITED COMPANY
CRYOGENIC TANKS FOR LAUNCH VEHICLES
KISTLER AEROSPACE CORPORATION, A WASHINGTON CORPORATION
PROCESS FOR PREVENTING TURNING OVER DURING THE LANDING OF AN AIRCRAFT OR SPACECRAFT
DAIMLER-BENZ AEROSPACE AG
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