Gas turbine engine combustor

Patent · Tue Mar 24 00:00:00 EST 1987

OSTI ID:6659318

Stroem, S

A combustor for a gas turbine engine is described comprising: (a) a burner defining an axial fluid-flow path between upstream and downstream ends thereof. The burner includes a first portion having a constant cross-sectional area and defining a first combustion zone proximate the upstream end, a second portion having constant cross-sectional area greater than the first area and defining a second combustion zone axially downstream of the first combustion zone, and a third portion defining an exhaust zone proximate the downstream end. The first and second cross-sectional flow areas are sized to provide a combustion gas axial velocity of about 150 ft/sec.; (b) a burner casing coaxially surrounding the burner and defining an annular conduit for a flow of inlet air from the downstream to the upstream end of the burner, the burner casing being separated from the burner by the air in the inlet air flow; (c) means at the upstream end of the burner for introducing fuel into the first combustion zone; and (d) first primary means at the upstream end of the burner and communicating with the annular conduit for introducing a first primary portion of the inlet air into the first combustion zone and for directing the first primary portion into mixing contact with the fuel.

• Assignee: Kongsberg Vapenfabrikk
• Patent Number(s): US 4651534
• OSTI ID: 6659318
• Resource Relation: Patent File Date: Filed date 16 May 1986
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
GAS TURBINE ENGINES
COMBUSTORS
EXHAUST SYSTEMS
AIR FLOW
COMBUSTION CHAMBERS
CONVECTION
COOLING
EXHAUST GASES
FLOW RATE
GAS BURNERS
INTAKE STRUCTURES
POSITIONING
SIZE
BURNERS
ENERGY TRANSFER
ENGINES
FLUID FLOW
FLUIDS
GAS FLOW
GASEOUS WASTES
GASES
HEAT ENGINES
HEAT TRANSFER
INTERNAL COMBUSTION ENGINES
MASS TRANSFER
MECHANICAL STRUCTURES
WASTES
330103* - Internal Combustion Engines- Turbine