COMBUSTOR
Assignee
UNITED TECHNOLOGIES CORPORATION, HARTFORD, CT., A CORP OF DE.
Filed
May 31, 1988
Granted
Jan 9, 1996
Location
PALM BEACH GARD FL US
Abstract
An annular combustor for a gas turbine engine is constructed to include a sector that has a reduced airflow distribution than the remainder of the circumference by supplying a reduced airflow in a judiciously located portion of the fuel nozzles and the single stage of radially ingested combustion airflow. This single stage circumferential zoned annular combustor serves to accommodate higher fuel/air ratios.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Dec 12, 1988
Rescinded
Sep 19, 1994
Duration
5 years, 9 months
Inventor
- 1THOMAS L. DUBELL
Record Details
- Patent number
- US 5481867
- Application
- 07200479
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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