COMBUSTOR WITH FIRST AND SECOND ZONES
Assignee
UNITED TECHNOLOGIES CORPORATION, A CORP. OF DE.
Filed
Nov 30, 1989
Granted
May 12, 1998
Location
PALM BEACH GARD FL US
Abstract
A high performance annular combustor for a gas turbine engine powering aircraft consisting of a primary combustion zone with the fuel nozzles and air swirlers in the dome and having typical combustion/dilution air holes in the liner and a secondary zone downstream of the primary zone having fuel nozzles and air swirlers operational solely when the primary zone is at a predetermined stoichiometric condition and issuing fuel which is at parity with the fuel/air ratio of the primary zone.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Nov 2, 1990
Rescinded
Apr 9, 1997
Duration
6 years, 5 months
Inventor
- 1THOMAS L. DU BELL
Record Details
- Patent number
- US 5749219
- Application
- 07443549
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
Browse by Assignee
UNITED TECHNOLOGIES CORPORATION, A CORP. OF DE.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