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US 5,687,572 AGranted
Thin wall combustor with backside impingement cooling
AssigneeAlliedSignal Inc.
InventorsJeffrey P. Schrantz, David R. Squire
Life of this patent
Estimating the term…
Abstract
A combustor for a gas turbine engine having a porous outer metallic shell and a thin-walled, nonporous ceramic liner whose backside is impingement cooled, with only primary and secondary openings in the ceramic liner for delivering pressurized primary air and dilution air to the combustion zone.
Claims21
A combustor for a gas turbine engine, comprising:
- a combustor housing having an inlet for recieving pressurized air for combustion therein;
- an outer metallic shell inside said housing and mounted thereto, said outer shell having primary and secondary air holes and a plurality of smaller cooling air holes;
- and
- an inner, thin walled, ceramic liner mounted to and disposed within said outer shell, and cooperating therewith to define a cooling space between said outer shell and said ceramic liner, said ceramic liner having primary and secondary openings respectively communicating with said primary and secondary air holes, said ceramic liner being otherwise nonporous, said cooling air holes adapted to direct the pressurized air into said cooling space for impingement cooling of said ceramic liner.
1 more element
A combustor for a gas turbine engine, comprising:
- a combustor housing having inlets for recieving pressurized air and fuel for combustion therein;
- an outer metallic shell in said housing and mounted thereto for carrying mechanical and pressure loads, said outer shell having primary and secondary air holes and a plurality of smaller cooling air holes;
- and
- an inner, thin walled, ceramic liner mounted within said outer shell for carrying substantially only thermal loads, said ceramic liner defining the outer aerodynamic boundary of the combustion process and defining a cooling space between outer shell and said ceramic liner, said ceramic liner having corresponding primary and secondary openings communicating with said primary and secondary air holes for delivery of primary air and dilution air for the combustion process, said ceramic liner being otherwise nonporous, said cooling air holes adapted to direct cooling airflow into said cooling space for impingement cooling of said ceramic liner, said cooling space communicating with said primary and secondary openings in said ceramic liner for exhaust of the cooling airflow from said cooling space substantially only through said primary and secondary openings.
1 more element
A gas turbine engine comprising:
- compressor means for generating a pressurized air flow;
- a combustor having a housing communicating with said compressor means to receive said pressurized airflow;
- an outer, cylindrical metallic shell disposed within said housing and mounted thereto to carry mechanical and pressure loads, said shell having primary and secondary air holes and a plurality of smaller cooling air holes;
- an inner, cylindrical, thin-walled, ceramic liner mounted to and disposed inside said shell to define a combustion zone inside said liner and an annular cooling space between said liner and said shell, said cooling air holes directing pressurized air into said annular cooling space to impingement cool said liner, said liner having primary and secondary openings respectively communicating with said primary and secondary air holes to deliver said pressurized airflow to said combustion zone, said liner being otherwise substantially nonporous;
- and
- means for delivering fuel to said combustion zone.
3 more elements
Dependencies are inferred from the claim text.