Abstract: A radial compressor includes an impeller which is rotatively driven, axially introduces air taken in through an air inlet passage formed in a housing, pressurizes the introduced air, and discharges the pressurized air in a radial direction, wherein an annular concave groove is formed in a peripheral wall of the air inlet passage of the housing, a rear end portion of an opening of the annular concave groove, which rear end portion meets the housing peripheral wall, is provided in the vicinity of a blade front end surface of the impeller, and the rear end portion of the opening of the annular concave groove is formed such that an axial projecting amount X thereof relative to the blade front end surface of the impeller is set to ?1T?X?1.5T (where T denotes the thickness of the distal portion of a blade).

Abstract: A radial turbine includes a radial turbine wheel provided with a main pathway in which blade height progressively increases while curving toward an axial direction from a radial direction. A sub-let is formed on a shroud side of the radial turbine wheel at a position separated from the main inlet in the radial direction and the axial direction. Also, a blade shape that forms the sub-inlet is such that, in a plane orthogonal to the axial line of the radial turbine wheel, a center line of the blade is inclined at a predetermined angle toward the rotation direction with respect to the radial direction.

Abstract: The present invention provides a radial turbine which uses a fluid having a plurality of pressures in a single turbine wheel, to thereby reduce the number of components and lower the cost. A radial turbine (100) includes a single radial turbine wheel (15) which converts, into rotational power, swirling energy of a swirling fluid with a first pressure that flows into the radial turbine wheel (15) from a main inlet (21) formed at an outer circumferential end through a nozzle (27) with a radial flow velocity component, wherein a sub inlet (29) is formed on an outer circumferential side of the radial turbine wheel (15) at a position radially and axially apart from the main inlet (21), and the low-boiling-point medium whose pressure decreases from the first pressure as the low-boiling-point medium travels to a radial inner side flows into the sub inlet (29) through a nozzle (35).

Abstract: To provide a centrifugal compressor having a high pressure ratio, which can achieve a large flow rate while suppressing a decrease in efficiency, the centrifugal compressor being adapted to compress and discharge a gas, which has been sucked in by rotation of an impeller (10) pivotally supported in a casing (11), mainly by centrifugal force, the inlet radius/outlet radius ratio (R1/R2) of the impeller (10) is set at 0.7?R1/R2?0.85, and the inclination angle (74 ) of a back board portion in a hub (10a) of the impeller (10) is set at 5°???15°.

Abstract: An expansion turbine with a radial turbine wheel has a main path that gradually increases in height and axially discharges fluid while swirling from a main inlet located at the outer circumferential side into the main path, with a radial flow as a main component, the radial turbine wheel has a sub-path branching off from the side of a hub of the main path at a position radially inward of the main inlet and extending rearward from the main path, the sub-path has, at an outer circumferential end, a sub-inlet located at a position in the radial direction different from the main inlet and supplied with a fluid having a pressure different from the pressure of the fluid supplied through the main inlet, the main inlet and the sub-inlet are partitioned by a back plate portion, in which the gap between it and the main path or the sub-path is adjusted.

Abstract: Provided is a turbine which handles fluids having a plurality of pressures with a single or integrated turbine wheel so that the number of components is reduced, and costs are reduced.

Abstract: A multi-stage radial turbine that is capable of reducing the number of bearings and of improving the conversion efficiency is provided.

Abstract: Provided is a uni-axial multi-stage radial gas expander which has a high degree of reliability and which can sufficiently cope with the conditions of a high pressure and a high pressure ratio. Two or more radial gas expander sections (11A, 11B) formed of two-or-more-stage impeller vanes (14a to 14h) arranged between bearings (21a, 21b) on a rotor shaft (13) consisting of a single shaft are housed in a signal casing (10).

Abstract: To provide a mixed flow turbine in which supply of working fluid is designed to be supplied at a hub and a shroud, and the shape of the inlet-side edges of the blades is made to work effectively, thereby reducing incidence loss.

Abstract: A mixed flow turbine or radial turbine suppresses a rapid increase in load applied on a leading edge of a blade, and can reduce incidence loss. The mixed flow turbine or radial turbine includes a hub, and a plurality of blades provided on an outer circumference surface of the hub at substantially equal intervals. The camber line of the blade section is convex-curved to the rotational direction side as seen entirely from a leading edge side toward trailing edge side. On a leading edge section of the blade, there is provided an inflected section that is inflected so that a camber line in a sectional surface along the outer circumference surface is concave-curved to the rotational direction side.

Abstract: In a centrifugal compressing apparatus, a height of a blade of an impeller is made to decrease gradually from a front edge thereof to a rear edge thereof, and a rate of change of the height of the blade is relatively large near the rear edge. The height of the blade can be made large at the rear edge side under the design restriction that an exit width of the rear edge of the blade is set to a predetermined design value. The ratio of the width of the clearance and the height of the blade is thereby made relatively large. As a result, the ratio of a flow path area occupied by a clearance flow to a flow path area occupied by a main flow is reduced. Since the pressure loss is thus made small, a drop in the efficiency can be prevented.

Abstract: To provide a centrifugal compressor having a high pressure ratio, which can achieve a large flow rate while suppressing a decrease in efficiency, the centrifugal compressor being adapted to compress and discharge a gas, which has been sucked in by rotation of an impeller (10) pivotally supported in a casing (11), mainly by centrifugal force, the inlet radius/outlet radius ratio (R1/R2) of the impeller (10) is set at 0.7?R1/R2?0.85, and the inclination angle (74 ) of a back board portion in a hub (10a) of the impeller (10) is set at 5°?0?15°.

Abstract: A radial compressor is capable of preventing the occurrence of separation caused by a flow which goes beyond the front end of a blade and turns onto a negative pressure plane from a pressure plane, thereby reducing a surging flow rate to a smaller flow rate. The radial compressor includes an impeller which is rotatively driven, axially introduces air taken in through an air inlet passage formed in a housing, pressurizes the introduced air, and discharges the pressurized air in a radial direction, wherein an annular concave groove is formed in a peripheral wall of the air inlet passage of the housing, a rear end portion of an opening of the annular concave groove, which rear end portion meets the housing peripheral wall, is provided in the vicinity of a blade front end surface of the impeller, and the rear end portion of the opening of the annular concave groove is formed such that an axial projecting amount X thereof relative to the blade front end surface of the impeller is set to ?1T?X?1.

Abstract: There is provided a variable diffuser for a compressor in which the efficiency can be further improved. In a variable diffuser 30 in which a diffuser passage 33, which restores a static pressure from a dynamic pressure by decelerating an air flow that is discharged from an outer peripheral end of an impeller that rotates within a housing, is formed between a hub side wall 32a and a shroud side wall 31a, and diffuser vanes are provided in the diffuser passage 33, fixed vanes 35 and movable vanes 34 that are the diffuser vanes, are alternately fixed in the circumferential direction to a fixed circular plate 32 and a movable circular plate 31 that form the hub side wall 32a and the shroud side wall 31a, and there is provided a driving device 40 that turns the movable circular plate 31 about the same axis as the rotation of the impeller.

Abstract: There is provided a centrifugal compressor having a diffuser structure in which airflow is unlikely to separate from a hub side wall surface on a hub side wall surface downstream side within a diffuser passage. In a centrifugal compressor provided with a diffuser passage 15 for recovering static pressure by slowing down discharged air from an outer circumferential end of an impeller that rotates within a housing 11, a hub side wall surface 15b of the diffuser passage 15 is provided with an inclined plane 20 that approaches toward a shroud side, in a position on a downstream side of a portion parallel with a normal line direction of a section surface of an impeller exit.

Abstract: Intended is to provide a mixed flow turbine or a radial turbine, which can suppress an abrupt increase in a load to be applied to the front edge portion of a blade, thereby to reduce an incidence loss. The mixed flow turbine or the radial turbine comprises a hub (3), and a plurality of blades (7) arranged at substantially equal interval on the outer circumference (5) of the hub (3) and having a warpage (23) curved convexly in the rotating direction, as entirely viewed from the front edge side to the back edge side. Each blade (7) is provided, at its front edge portion, with an inflection point (K), at which the warpage (23) in the section along the outer circumference is curved concavely in the rotating direction.

Abstract: To provide a mixed flow turbine in which supply of working fluid is designed to be supplied at a hub and a shroud, and the shape of the inlet-side edges of the blades is made to work effectively, thereby reducing incidence loss.

Abstract: On a suction surface side of a blade in an impeller, a convex portion is formed to assume a curved line from a front edge portion to a throat portion substantially in the middle in a radial direction, and this convex portion is formed to be flat assuming a curved line from the throat portion toward a rear edge portion, whereby this convex portion is formed in a position where a relative inlet velocity of fluid into the impeller is Mach number Ma?1.

Abstract: In a centrifugal compressing apparatus, a height of a blade of an impeller is made to decrease gradually from a front edge thereof to a rear edge thereof, and a rate of change of the height of the blade is relatively large near the rear edge. The height of the blade can be made large at the rear edge side under the design restriction that an exit width of the rear edge of the blade is set to a predetermined design value. The ratio of the width of the clearance and the height of the blade is thereby made relatively large. As a result, the ratio of a flow path area occupied by a clearance flow to a flow path area occupied by a main flow is reduced. Since the pressure loss is thus made small, a drop in the efficiency can be prevented.

Abstract: In a centrifugal compressing apparatus, a height of a blade of an impeller is made to decrease gradually from a front edge thereof to a rear edge thereof, and a rate of change of the height of the blade is relatively large near the rear edge. The height of the blade can be made large at the rear edge side under the design restriction that an exit width of the rear edge of the blade is set to a predetermined design value. The ratio of the width of the clearance and the height of the blade is thereby made relatively large. As a result, the ratio of a flow path area occupied by a clearance flow to a flow path area occupied by a main flow is reduced. Since the pressure loss is thus made small, a drop in the efficiency can be prevented.