TWO-DIMENSIONAL, UNILATERAL OBLIQUE SHOCK DIFFUSER AS THE AIR INLET FOR A GAS TURBINE JET ENGINE FOR THE PROPULSION OF HEAVY-DUTY AIRCRAFT
Assignee
MESSERSCHMITT-BOLKOW-BLOHM GESELLSCHAFT MIT BESCHRANKTER HAFTUNG, POSTFACH 801109, 8000 MUNICH 80, GERMANY
Filed
Feb 24, 1981
Granted
Dec 6, 1983
Location
GOTTING DE
Abstract
A two-dimensional, unidirectional oblique air impact diffuser is used as an air inlet for a gas turbine jet engine for aircraft. The air inlet includes an upper rigid air inlet ramp and an air inlet bottom spaced below the ramp. An air scoop lip is pivotally attached to the air inlet bottom so that it can be pivoted from a standard setting point downwardly away from the air inlet ramp and also from the standard setting point toward the ramp. The pivotal displacement of the air scoop lip is a function of the aircraft angle of attack and the flight Mach number. The angular displacement of the air scoop lip from the standard setting point increases downwardly as the aircraft angle of attack increases and decreases as the Mach number increases.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Oct 21, 1981
Rescinded
Dec 14, 1982
Duration
1 year, 1 month
Inventor
- 1CARSTEN SCHULZE
Record Details
- Patent number
- US 4418708
- Application
- 06239021
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
Browse by Assignee
MESSERSCHMITT-BOLKOW-BLOHM GESELLSCHAFT MIT BESCHRANKTER HAFTUNG, POSTFACH 801109, 8000 MUNICH 80, GERMANYRelated 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