DIVERTER VALVE WITH BYPASS DUCT OBTURATOR
Assignee
ROLLS-ROYCE LIMITED
Filed
Nov 15, 1985
Granted
Dec 25, 1990
Location
BRISTOL EN GB
Abstract
A fluid flow diverter system for use with twin engine vertical take-off aircraft. The diverter sysstem is employed to direct a portion of, or all, the working fluid from the first axial flow compressor (14) of either a by-pass engine, a twin fan engine or a variable cycle engine to either a pair of vectorable front nozzles (36) or to a by-pass duct (34). In the event of one engine failing in flight, an attempt at balancing the remaining thrust for vertical landing is made by ducting all the air normally existing from the operative engine's front nozzle (36) across to the inoperative engine's front nozzle (36).
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Jun 18, 1986
Rescinded
Aug 1, 1990
Duration
4 years, 1 month
Inventor
- 1MALCOLM C. HITCHCOCK
Record Details
- Patent number
- US 4979363
- Application
- 06820249
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
Browse by Assignee
ROLLS-ROYCE LIMITEDMore from this assignee
FUEL CONTROL SYSTEM
ROLLS-ROYCE LIMITED
AXIAL FLOW GAS TURBINES
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
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
AIRCRAFT INFRARED GUIDED DEFENSE MISSILE SYSTEM
LOW OBSERVABLE ENGINE AIR INLET SYSTEM
UNITED TECHNOLOGIES CORPORATION