Radial-flow turbomachine

Claim 2

A radial-flow turbomachine including a rotor comprising a rotatably mounted body of circular cross-section having a hub portion and a disk portion extending radially from the hub portion, the disk and hub portions defining the inner boundary of an annular gas flow path through the rotor, the rotor also comprising an annular array of circumferentially spaced blades extending outwardly from the hub portion and forwardly from the disk portion, the blades extending from an annular gas inlet to an annular gas outlet and defining gas flow passages between them and being effective to transfer energy between the rotor and gas flowing through the passages, the blades each having a pressure face and a suction face in operation of the rotor, each blade having a free bounding edge remote from the rotor body extending along a course trending from near axial at one end of the gas flow passages to near radial at the other end of the gas flow passages, the turbomachine also including a stator enclosing the rotor and defining the gas inlet to and outlet from the rotor, the stator including a fixed rotor shroud extending continuously around the rotor closely adjacent to the free edges of the blades providing the outer boundary of the flow path through the rotor and acting to minimize leakage over the said free edges of the blades; wherein the improvement comprises a lip extending circumferentially of the rotor from the pressure face of each blade along the free edge of the blade with the outer surface of the lip extending closely parallel to the adjacent rotor shroud adapted to deflect gas flowing over the pressure face toward the said edge away from the pressure face toward the suction face of the blade at the opposite side of the passage and to obstruct leakage flow between the said edge of the blade and the rotor shroud into the adjoining passage.

Claim 3

A radial-flow compressor including a rotor comprising a rotatably mounted body of circular cross-section having a hub portion and a disk portion extending radially from the hub portion, the disk and hub portions defining the inner boundary of an annular gas flow path through the rotor, the rotor also comprising an annular array of circumferentially spaced blades extending outwardly from the hub portion and forwardly from the disk portion, the blades extending from an annular gas inlet to an annular gas outlet at the periphery of the rotor and defining gas flow passages between them and being effective to transfer energy from the rotor to gas flowing outwardly through the passages, the blades each having a pressure face and a suction face in operation of the rotor, each blade having a free bounding edge remote from the rotor body extending along a course trending from near axial at the gas inlet end of the blades to near radial at the gas outlet end of the blades, the compressor also including a stator enclosing the rotor and defining the gas inlet to and outlet from the rotor, the stator including a fixed rotor shroud extending continuously around the rotor closely adjacent to the free edges of the blades providing the outer boundary of the flow path through the rotor and acting to minimize leakage over the said free edges of the blades; wherein the improvement comprises a lip extending circumferentially of the rotor from the pressure face of each blade along the free edge of the blade with the outer surface of the lip extending closely parallel to the adjacent rotor shroud adapted to deflect gas flowing over the pressure face toward the said edge away from the pressure face toward the suction face of the blade at the opposite side of the passage and to obstruct leakage flow between the said edge of the blade and the rotor shroud into the adjoining passage.

Claim 4

A radial-flow compressor including a rotor comprising a rotatably mounted body of circular cross-section having a hub portion and a disk portion extending radially from the hub portion, the disk and hub portions defining the inner boundary of an annular gas flow path through the rotor, the rotor also comprising an annular array of circumferentially spaced blades extending outwardly from the hub portion and forwardly from the disk portion, the blades extending from an annular gas inlet to an annular gas outlet at the periphery of the rotor and defining gas flow passages between them and being effective to transfer energy from the rotor to gas flowing outwardly through the passages, the blades each having a pressure face and a suction face in operation of the rotor, each blade having a free bounding edge remote from the rotor body extending along a course trending from near axial at the gas inlet end of the blades to near radial at the gas outlet end of the blades, the compressor also including a stator enclosing the rotor and defining the gas inlet to and outlet from the rotor, the stator including a fixed rotor shroud extending continuously around the rotor closely adjacent to the free edges of the blades providing the outer boundary of the flow path through the rotor and acting to minimize leakage over the said free edges of the blades; wherein the improvement comprises a lip extending circumferentially of the rotor from the pressure face of each blade along the free edge of the blade with the outer surface of the lip extending closely parallel to the adjacent rotor shroud adapted to deflect gas flowing over the pressure face toward the said edge away from the pressure face toward the suction face of the blade at the opposite side of the passage and to obstruct leakage flow between the said edge of the blade and the rotor shroud into the adjoining passage.

Claim 5

A radial-flow turbine including a rotor comprising a rotatably mounted body of circular cross-section having a hub portion and a disk portion extending radially from the hub portion, the disk and hub portions defining the inner boundary of an annular gas flow path through the rotor, the rotor also comprising an annular array of circumferentially spaced blades extending outwardly from the hub portion and forwardly from the disk portion, the blades extending from an annular gas inlet at the periphery of the rotor to an annular gas outlet and defining gas flow passages between them and being effective to transfer energy to the rotor from gas flowing inwardly through the passages, the blades each having a pressure face and a suction face in operation of the rotor, each blade having a free bounding edge remote from the rotor body extending along a course trending from near radial at the gas inlet end of the blades to near axial at the gas outlet end of the blades, the turbine also including a stator enclosing the rotor and defining the gas inlet to and outlet from the rotor, the stator including a fixed rotor shroud extending continuously around the rotor closely adjacent to the free edges of the blades providing the outer boundary of the flow path through the rotor and acting to minimize leakage over the said free edges of the blades; wherein the improvement comprises a lip extending circumferentially of the rotor from the pressure face of each blade along the free edge of the blade with the outer surface of the lip extending closely parallel to the adjacent rotor shroud adapted to deflect gas flowing over the pressure face toward the said edge away from the pressure face toward the suction face of the blade at the opposite side of the passage and to obstruct leakage flow between the said edge of the blade and the rotor shroud into the adjoining passage.

Claim 6

A radial-flow turbine including a rotor comprising a rotatably mounted body of circular cross-section having a hub portion and a disk portion extending radially from the hub portion, the disk and hub portions defining the inner boundary of an annular gas flow path through the rotor, the rotor also comprising an annular array of circumferentially spaced blades extending outwardly from the hub portion and forwardly from the disk portion, the blades extending from an annular gas inlet at the periphery of the rotor to an annular gas outlet and defining gas flow passages between them and being effective to transfer energy to the rotor from gas flowing inwardly through the passages, the blades each having a pressure face and a suction face in operation of the rotor, each blade having a free bounding edge remote from the rotor body extending along a course trending from near radial at the gas inlet end of the blades to near axial at the gas outlet end of the blades, the turbine also including a stator enclosing the rotor and defining the gas inlet to and outlet from the rotor, the stator including a fixed rotor shroud extending continuously around the rotor closely adjacent to the free edges of the blades providing the outer boundary of the flow path through the rotor and acting to minimize leakage over the said free edges of the blades; wherein the improvement comprises a lip extending circumferentially of the rotor from the pressure face of each blade along the free edge of the blade with the outer surface of the lip extending closely parallel to the adjacent rotor shroud adapted to deflect gas flowing over the pressure face toward the said edge away from the pressure face toward the suction face of the blade at the opposite side of the passage and to obstruct leakage flow between the said edge of the blade and the rotor shroud into the adjoining passage.