Fluidic control of airflow in combustion chambers

Patent · Tue May 08 04:00:00 EDT 1984

OSTI ID:6326409

Adkins, R C

The airflow from the compressor of a gas turbine engine into the combustion chamber or chambers principally comprises combustion air which enters the upstream end of the combustion chamber and dilution air which enters the combustion chamber at some point downstream of the combustion chamber inlet, the combustion air being made up of primary and secondary air entering the combustion chamber primary and secondary zones. In order to cope with the control of emissions from the combustion chambers, it is desirable to control the combustion air fuel ratio over the engine operating range by controlling air mass flow to the combustion and dilution zones of the combustion chamber. The invention proposes that this control can be achieved by providing a variable rate diffuser upstream of the primary, secondary and dilution air inlets, the variable rate diffuser comprising vortex generator having an associated variable air bleed. The air bleed functions to control the strength of the generated vortex which in turn controls the rate of diffusion of the air supply to the combustion chamber.

• Assignee: Roll-Royce Limited (United Kingdom)
• Patent Number(s): US 4446692
• OSTI ID: 6326409
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
330103* -- Internal Combustion Engines-- Turbine
AIR FLOW
BYPASSES
COMBUSTION CHAMBERS
COMBUSTION WAVES
COMPRESSORS
CONTROL EQUIPMENT
DILUTION
ENGINES
EQUIPMENT
FLUID FLOW
FLUIDIC CONTROL DEVICES
FLUIDIC DEVICES
FUEL INJECTION SYSTEMS
FUEL SYSTEMS
FUEL-AIR RATIO
GAS COMPRESSORS
GAS FLOW
GAS TURBINE ENGINES
HEAT ENGINES
INTERNAL COMBUSTION ENGINES