Axial turbomachine compressor with controlled recirculation between the inner shroud and the rotor
AssigneeSafran Aero Boosters SA
InventorRémy Henri Pierre Princivalle
Life of this patent
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Abstract
A stage for a turbomachine compressor including a row of stator vanes extending radially inwards from an outer shell to an inner shell housed in a cavity of the rotor, and an air recirculation passage in the cavity, with an air inlet downstream of the inner shell and an air injection outlet between a face guide and an opposite guiding face upstream of the cavity, having profiles inclined radially downstream, relative to a perpendicular to an axial direction. The air injection outlet has a distance greater than or equal to one fifth of a common length, and the air recirculation passage in the cavity is devoid of a device for sealing upstream of the air inlet.
Claims19
A compression stage for a compressor of a turbomachine, comprising:
- an annular row of rotor blades extending radially outward from a rotor;
- an annular row of stator blades extending radially inward from an outer shroud to an inner shroud housed in a cavity of the rotor, said annular row of stator blades being arranged directly downstream of the annular row of rotor blades;
- and
- an air recirculation passage in the cavity, with an air inlet at a downstream part of the inner shroud and an air injection outlet between a guide face upstream of said inner shroud and an opposite guiding face upstream of the cavity, said guide face and said opposite guiding face having axial profiles inclined downstream and radially outward, relative to a direction perpendicular to an axial direction;
- wherein the air injection outlet defines a distance corresponding to a gap between the guide face and the opposite guiding face, and a length corresponding to a common length of said guide face and said opposite guiding face, said distance being greater than or equal to one-fifth of the common length, and the air recirculation passage in the cavity is devoid of a sealing device upstream of the air inlet, wherein upstream defines a main air flow direction in the compression stage.
A compressor of a turbomachine, comprising several compression stages, wherein at least one of said compression stages comprising:
- an annular row of rotor blades extending radially outward from a rotor;
- an annular row of stator blades extending radially inward from an outer shroud to an inner shroud housed in a cavity of the rotor, said annular row of stator blades being arranged directly downstream of the annular row of rotor blades;
- and
- an air recirculation passage in the cavity, with an air inlet at a downstream part of the inner shroud and an air injection outlet between a guide face upstream of said inner shroud and an opposite guiding face upstream of the cavity, said guide face and said opposite guiding face having axial profiles inclined downstream and radially outward, relative to a direction perpendicular to an axial direction;
- wherein the air injection outlet defines a distance corresponding to a gap between the guide face and the opposite guiding face, and a length corresponding to a common length of said guide face and said opposite guiding face, said distance being greater than or equal to one-fifth of the common length, and the air recirculation passage in the cavity is devoid of a sealing device upstream of the air inlet, wherein upstream defines a main air flow direction in the compression stage.
A turbomachine comprising a compressor comprising a plurality compression stages, wherein at least one of said compression stages comprising:
- an annular row of rotor blades extending radially outward from a rotor;
- an annular row of stator blades extending radially inward from an outer shroud to an inner shroud housed in a cavity of the rotor, said annular row of stator blades being arranged directly downstream of the annular row of rotor blades;
- and
- an air recirculation passage in the cavity, with an air inlet at a downstream part of the inner shroud and an air injection outlet between a guide face upstream of said inner shroud and an opposite guiding face upstream of the cavity, said guide face and said opposite guiding face having axial profiles inclined downstream and radially outward, relative to a direction perpendicular to an axial direction;
- wherein the air injection outlet defines a distance corresponding to a gap between the guide face and the opposite guiding face, and a length corresponding to a common length of said guide face and said opposite guiding face, said distance being greater than or equal to one-fifth of the common length, and the air recirculation passage in the cavity is devoid of a sealing device upstream of the air inlet, wherein upstream defines a main air flow direction in the compression stage.
Dependencies are inferred from the claim text.