Gas turbine combustion chamber arrangement

Patent · Tue Aug 09 00:00:00 EDT 1977

OSTI ID:5245695

Heitmann, A M; Brassert, W L; Chouinard, D N

A gas turbine has a combustion chamber of toroidal configuration that includes separation structure dividing the combustion chamber into an annular primary zone and an annular dilution zone. Injection of compressor discharge air into the primary zone sets up a toroidal recirculation pattern of generally circular cross-sectional configuration. Fuel slinger structure at the inner periphery of the primary zone has a generally cylindrical surface for receiving and distributing fuel in a thin sheet for discharge in a radially outward direction as minute droplets towards the center of the toroidal recirculation pattern. The radial flow of the fuel droplets interacts with the toroidal recirculation pattern and provides intimate mixing of fuel and air, and resulting efficient combustion within the primary zone. The resulting combustion product flows from the primary zone past the separation structure into the dilution zone. Compressor discharge air injected into the dilution zone dilutes the products of combustion from the primary zone.

• Assignee: Northern Research and Engineering Corp.
• Patent Number(s): US 4040251
• OSTI ID: 5245695
• Resource Relation: Patent File Date: Filed date 16 Jan 1976
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
GAS TURBINES
COMBUSTION CHAMBERS
AIR
DESIGN
DROPLETS
FUEL ECONOMY
FUELS
GAS FLOW
MIXING
THERMAL EFFICIENCY
TOROIDAL CONFIGURATION
ANNULAR SPACE
CONFIGURATION
EFFICIENCY
FLUID FLOW
FLUIDS
GASES
PARTICLES
TURBINES
TURBOMACHINERY
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