COMBUSTOR
Assignee
UNITED TECHNOLOGIES CORPORATION, HARTFORD, CT., A CORP OF DE.
Filed
May 31, 1988
Granted
Mar 29, 1994
Location
PALM BEACH GARD FL US
Abstract
An annular combustor for a gas turbine engine includes a sector in the primary combustion zone that operates at a reduced level of airflow than the remaining portion of the combustor by providing fixed air openings in the dome or fuel nozzles and in the combustion air admission holes. This allows the combustor to operate at higher fuel/air ratios with a minimum of complexity in the hardware.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Dec 12, 1988
Rescinded
May 26, 1993
Duration
4 years, 5 months
Inventor
- 1THOMAS L. DUBELL
Record Details
- Patent number
- US 5297385
- Application
- 00720048
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
Browse by Assignee
UNITED TECHNOLOGIES CORPORATION, HARTFORD, CT., A CORP OF DE.More from this assignee
Related by domain
GAS TURBINE ENGINE COMBUSTOR HAVING TRAPPED DUAL VORTEX CAVITY
General Electric
SOLID ROCKET PROPELLANT
GAS TURBINE ENGINE FAN (U)
General Electric
TURNING VANE ARRANGEMENT FOR IR SUPPRESSORS
SIKORSKY AIRCRAFT CORPORATION
MODULAR ROCKET BOOSTED PENETRATING WARHEAD
LOCKHEED MARTIN CORP.
INTEGRAL SOLID BOOSTER AND HYBRID THRUST SUSTAINING SYSTEM AND PROJECTILE INCORPORATING THE SAME
ENVIRONMENTAL AEROSCIENCE CORPORATION