Plasma flow controlled diffuser system
AssigneeHoneywell International Inc.
InventorNick Nolcheff
Life of this patent
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Abstract
A diffuser system for a compressor for a gas turbine engine includes a diffuser and a plasma actuator. The diffuser comprises a first wall and a second wall. The first and second walls form a diffuser flow passage therebetween. The plasma actuator is disposed at least partially proximate the second wall. The plasma actuator is adapted to generate an electric field to ionize a portion of air flowing through the flow passage.
Claims20
A diffuser system disposed downstream of a compressor section of a gas turbine engine, the diffuser system comprising:
- a diffuser of the diffuser system comprising a first wall, a second wall and de-swirl vanes, the first and second walls forming a diffuser flow passage therebetween;
- and
- a plasma actuator disposed downstream of a leading edge of the de-swirl vanes and at least partially proximate the second wall, the plasma actuator generate an electric field to ionize a portion of air flowing through the flow passage and supply to a combustor.
A compressor for a gas turbine engine, the compressor comprising:
- a housing;
- an impeller rotationally mounted within the housing and configured to supply compressed air;
- a first diffuser disposed radially outward from the impeller, the first diffuser formed within the housing and configured to receive compressed air from the impeller;
- a de-swirl section formed within the housing and configured to receive diffused air from the first diffuser and to de-swirl the air;
- a second diffuser disposed downstream from the first diffuser, the second diffuser formed within the housing and coupled to receive the de-swirled air from the de-swirl section, the second diffuser comprising a first wall formed within the housing and a wall formed within the housing, the first and second walls forming a flow passage therebetween;
- and
- a plasma actuator disposed proximate the second wall, the plasma actuator adapted to generate an electric field to ionize a portion of air flowing through the flow passage and supply to a combustor.
A gas turbine engine, comprising:
- a housing;
- a turbine formed within the housing and configured to receive a combustion gas and operable, upon receipt thereof, to supply a first drive force;
- a combustor formed within the housing and configured to receive compressed air and fuel and operable, upon receipt thereof, to supply the combustion gas to the turbine;
- and
- a centrifugal compressor formed within the housing and configured to supply the compressed air to the combustor, the compressor comprising:
- an impeller rotationally mounted within the housing and configured to supply compressed air;
- a first diffuser formed within the housing and configured to receive compressed air from the impeller;
- a de-swirl section formed within the housing and configured to receive diffused air from the first diffuser and to de-swirl the air;
- a second diffuser formed within the housing and coupled to receive the de-swirled air from the de-swirl section, the second diffuser comprising a first wall formed within the housing and a wall formed within the housing, the first and second walls forming a flow passage therebetween;
- and
- a plasma actuator disposed proximate the second wall, the plasma actuator adapted to generate an electric field to ionize a portion of air flowing through the flow passage.
Dependencies are inferred from the claim text.