LINER OF A GAS TURBINE ENGINE COMBUSTOR HAVING TRAPPED VORTEX CAVITY
Assignee
General Electric
Filed as: GENERAL ELECTRIC COMPANY
Filed
Jun 7, 1995
Granted
Aug 11, 1998
Location
CINCINNATI OH US
Abstract
A liner for a gas turbine engine combustor is disclosed having a non-linear cavity section, wherein air and fuel injected therein form a trapped vortex for igniting and stabilizing a flame in the combustor. The cavity section, which is substantially rectangular in shape, has an aft wall, a forward wall, and an intermediate wall connected at one end to the aft wall and at the other end to the forward wall. A plurality of passages are provided in the aft wall for injecting fuel therethrough and a plurality of air passages are provided in the aft wall surrounding each fuel passage for injecting air therethrough. Cooling holes are also provided in the aft wall, the forward wall, and the intermediate wall for reinforcing the fuel/air vortex flow in the cavity section.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Mar 20, 1997
Rescinded
Mar 10, 1998
Duration
11 months
Inventor
- 1DAVID L. BURRUS
Record Details
- Patent number
- US 5791148
- Application
- 08473803
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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