Abstract: A compressor includes a rotor including a plurality of disks, a shaft portion connected on a downstream side of the disks; and rotor blade rows fixed to the plurality of disks; a stator including a compressor casing; and a plurality of stator vane rows each provided between corresponding adjacent ones of the rotor blade rows; an outlet guide vane including blade main bodies disposed at an interval in a circumferential direction on the downstream side of the disk located most downstream, and inner shrouds connecting the blade main bodies in the circumferential direction, on an inner side in a radial direction; and an inner casing disposed on the downstream side of the disk located most downstream with a gap between the disk and the inner casing.

Abstract: The impeller of a rotating machine according to at least one embodiment of the present discloser is provided with: a disc; a cover disposed on an opposite side of a radial passage from the disc in an axial direction; and a blade disposed between the disc and the cover. In a dimensionless position along a camber line of the blade when the position of a leading edge of the blade is defined as 0 and the position of a trailing edge of the blade is defined as 1, a position where an angle difference between a first blade angle at a disc-side end portion of the blade and a second blade angle at a cover-side end portion of the blade is maximum is in a range of 0.5 or more and 1 or less. The first blade angle is ?10 degrees or more and 0 degrees or less at the position where the angle difference is maximum.

Abstract: A compressor includes a rotor including a plurality of disks, a shaft portion connected on a downstream side of the disks; and rotor blade rows fixed to the plurality of disks; a stator including a compressor casing; and a plurality of stator vane rows each provided between corresponding adjacent ones of the rotor blade rows; an outlet guide vane including blade main bodies disposed at an interval in a circumferential direction on the downstream side of the disk located most downstream, and inner shrouds connecting the blade main bodies in the circumferential direction, on an inner side in a radial direction; and an inner casing disposed on the downstream side of the disk located most downstream with a gap between the disk and the inner casing.

Abstract: The impeller of a rotating machine according to at least one embodiment of the present discloser is provided with: a disc; a cover disposed on an opposite side of a radial passage from the disc in an axial direction; and a blade disposed between the disc and the cover. In a dimensionless position along a camber line of the blade when the position of a leading edge of the blade is defined as 0 and the position of a trailing edge of the blade is defined as 1, a position where an angle difference between a first blade angle at a disc-side end portion of the blade and a second blade angle at a cover-side end portion of the blade is maximum is in a range of 0.5 or more and 1 or less. The first blade angle is ?10 degrees or more and 0 degrees or less at the position where the angle difference is maximum.

Abstract: A centrifugal compressor is provided with a return vane including a suction surface facing a front side in a rotation direction of a rotation shaft and a pressure surface facing a rear side. A casing includes a hub side wall surface and a shroud side wall surface that form a placement region of the return vane in the straight flow path, and an intermediate suction port formed on the shroud side wall surface, the intermediate suction port ejecting fluid guided from outside toward the straight flow path; and inside the return vane, an internal flow path is formed in which one end communicates with the intermediate suction port and another end is an outlet port that opens to the suction surface of the return vane.

Abstract: Provided is a blade for an axial flow turbomachine, including: a blade profile section; an endwall having a flow path wall surface disposed at least on a hub side of the blade profile section and adapted to demarcate a part of an annular flow path of a working fluid; and a fillet disposed at the boundary between the blade profile section and the flow path wall surface. The fillet is externally shaped so as to have an arc-shaped curved surface having a radius of R as viewed in a cross-section orthogonal to the flow path wall surface and the blade surface of the blade profile section. A narrow portion existing on the flow path wall surface is configured such that the distance d between the outer edge of a projection of the blade profile section onto the flow path wall surface and the outer edge of the flow path wall surface is smaller than the maximum value of the radius R of the fillet.

Abstract: A compressor includes a rotation shaft that is capable of rotating around a main axis, an impeller provided integrally with the rotation shaft, a casing that covers the impeller from an outer circumferential side and forms a flow path through which a working fluid circulates, a discharge scroll that is provided at an end of the flow path on a downstream side and extends in a spiral shape around the main axis, a discharge nozzle that communicates with the discharge scroll on the downstream side and extends from the discharge scroll in a tangent direction around the main axis, and a pressure loss body that has a plate shape extending in a direction orthogonal to an axis of the discharge nozzle extending in a radial direction orthogonal to the main axis and is capable of blocking a part of a flow path cross-section of the discharge nozzle.

Abstract: A multi-stage centrifugal compressor according to at least one embodiment includes: multiple stages of impellers arranged in an axial direction; a casing surrounding the impellers; and a diffuser channel for guiding a working fluid discharged from the impellers outward in a radial direction. In a cross-section along the axial direction, a first diffuser wall surface on a hub side of a pair of diffuser wall surfaces that are opposed in the axial direction across the diffuser channel has a retreating surface retreating toward the hub side from a connection position with a downstream end of a first upstream wall surface to a radially outer side with respect to a tangential direction of the first upstream wall surface at the downstream end of the first upstream wall surface, the first upstream wall surface being positioned upstream of the first diffuser wall surface and connected to the first diffuser wall surface.

Abstract: A centrifugal compressor is provided with a return vane including a suction surface facing a front side in a rotation direction of a rotation shaft and a pressure surface facing a rear side. A casing includes a hub side wall surface and a shroud side wall surface that form a placement region of the return vane in the straight flow path, and an intermediate suction port formed on the shroud side wall surface, the intermediate suction port ejecting fluid guided from outside toward the straight flow path; and inside the return vane, an internal flow path is formed in which one end communicates with the intermediate suction port and another end is an outlet port that opens to the suction surface of the return vane.

Abstract: A ceiling-embedded air conditioner includes, a casing, a motor including an output shaft protruding downward, the output shaft being driven to rotate about an axis, a main plate fixed to the output shaft and extending radially outward, a turbofan including an impeller, a heat exchanger passed through by air that is sent from the turbofan. And the main plate includes, a tapered portion, a recess formed to be recessed radially inward from the tapered portion, the recess being defined by a cylindrical plate portion extending along the axis, and a disk plate portion extending radially outward from the upper end of the cylindrical plate portion. And an opening is formed in the cylindrical plate portion, the opening penetrates the cylindrical plate portion in the radial direction, and configured such that a circulation flow that exits from the impeller and flows around above the main plate passes through the opening.

Abstract: A multi-stage centrifugal compressor according to at least one embodiment includes: multiple stages of impellers arranged in an axial direction; a casing surrounding the impellers; and a diffuser channel for guiding a working fluid discharged from the impellers outward in a radial direction. In a cross-section along the axial direction, a first diffuser wall surface on a hub side of a pair of diffuser wall surfaces that are opposed in the axial direction across the diffuser channel has a retreating surface retreating toward the hub side from a connection position with a downstream end of a first upstream wall surface to a radially outer side with respect to a tangential direction of the first upstream wall surface at the downstream end of the first upstream wall surface, the first upstream wall surface being positioned upstream of the first diffuser wall surface and connected to the first diffuser wall surface.

Abstract: A compressor includes a rotation shaft that is capable of rotating around a main axis, an impeller provided integrally with the rotation shaft, a casing that covers the impeller from an outer circumferential side and forms a flow path through which a working fluid circulates, a discharge scroll that is provided at an end of the flow path on a downstream side and extends in a spiral shape around the main axis, a discharge nozzle that communicates with the discharge scroll on the downstream side and extends from the discharge scroll in a tangent direction around the main axis, and a pressure loss body that has a plate shape extending in a direction orthogonal to an axis of the discharge nozzle extending in a radial direction orthogonal to the main axis and is capable of blocking a part of a flow path cross-section of the discharge nozzle.

Abstract: In a gas turbine manufacturing method for manufacturing a derivative gas turbine having a different cycle from a reference gas turbine including a reference compressor, a compressor of the derivative gas turbine is designed to add at least one additional stage further on an upstream side than a last stage of the reference compressor and on a downstream side of a bleed slit of a bleed chamber of the reference compressor, the compressor of the derivative gas turbine is manufactured on the basis of the design, and the derivative gas turbine is manufactured. Consequently, it is possible to manufacture a gas turbine that can secure a surge margin of a compressor with respect to fluctuation in the composition of fuel.

Abstract: Provided is a blade for an axial flow turbomachine, including: a blade profile section; an endwall having a flow path wall surface disposed at least on a hub side of the blade profile section and adapted to demarcate a part of an annular flow path of a working fluid; and a fillet disposed at the boundary between the blade profile section and the flow path wall surface. The fillet is externally shaped so as to have an arc-shaped curved surface having a radius of R as viewed in a cross-section orthogonal to the flow path wall surface and the blade surface of the blade profile section. A narrow portion existing on the flow path wall surface is configured such that the distance d between the outer edge of a projection of the blade profile section onto the flow path wall surface and the outer edge of the flow path wall surface is smaller than the maximum value of the radius R of the fillet.

Abstract: An axial flow compressor includes multiple rotor blade rows configured to include multiple rotor blades and multiple stator blade rows configured to include multiple stator blades, the multiple rotor blades and the multiple stator blades being arranged in an annular channel through which a working fluid flows. A portion of at least one wall surface on an inner peripheral side and an outer peripheral side of the annular channel, the portion being at an arrangement portion where at least any one blade row of the rotor blade rows and the stator blade rows is located, has a protruding portion such that downstream side part of the portion is curved so as to further protrude to the annular channel than upstream side part of the portion.

Abstract: A two-shaft gas turbine of the present invention, in which a mass flow of an air into a compressor is regulated by controlling a set angle of an inlet guide vane (IGV) on an air intake side of the compressor, comprises, as a device to control the set angle of the IGV, a first controller to control the set angle of the IGV based on a corrected speed of the gas generator shaft during low speed rotation of the gas generator shaft, the corrected speed having been corrected according to an ambient temperature; a second controller to control the set angle of the IGV to maintain a constant actual speed of the gas generator shaft during high speed rotation of the gas generator shaft; and an ambient temperature correction part to increase the actual speed maintained constant by the second controller if the ambient temperature is equal to or more than a threshold value.

Abstract: A 2-shaft gas turbine has a controller which controls the opening degree of an air inlet guide vane to adjust the inlet mass flow rate to a compressor. The air inlet guide vane control unit includes a first control unit that adjusts the opening degree of the inlet guide vane to keep the speed of a high pressure turbine shaft constant; a control status confirmation unit that confirms the actual speed and the opening degree of the inlet guide vane; and a low ambient temperature correction unit that reduces the actual speed in a case where the actual speed is equal to or greater than a predetermined threshold value, the opening degree of the inlet guide vane is equal to or greater than a predetermined threshold value, and the ambient temperature is equal to or less than a predetermined threshold value.

Abstract: In a gas turbine manufacturing method for manufacturing a derivative gas turbine having a different cycle from a reference gas turbine including a reference compressor, a compressor of the derivative gas turbine is designed to add at least one additional stage further on an upstream side than a last stage of the reference compressor and on a downstream side of a bleed slit of a bleed chamber of the reference compressor, the compressor of the derivative gas turbine is manufactured on the basis of the design, and the derivative gas turbine is manufactured. Consequently, it is possible to manufacture a gas turbine that can secure a surge margin of a compressor with respect to fluctuation in the composition of fuel.

Abstract: A 2-shaft gas turbine has a controller which controls the opening degree of an air inlet guide vane to adjust the inlet mass flow rate to a compressor. The air inlet guide vane control unit includes a first control unit that adjusts the opening degree of the inlet guide vane to keep the speed of a high pressure turbine shaft constant; a control status confirmation unit that confirms the actual speed and the opening degree of the inlet guide vane; and a low ambient temperature correction unit that reduces the actual speed in a case where the actual speed is equal to or greater than a predetermined threshold value, the opening degree of the inlet guide vane is equal to or greater than a predetermined threshold value, and the ambient temperature is equal to or less than a predetermined threshold value.

Abstract: A two-shaft gas turbine having a steam injection mechanism, comprising: a compressor having an inlet guide vane, a combustor, turbines, a heat recovery steam generator, a steam valve to control a flow rate of steam to be supplied to the combustor, a fuel valve to control a flow rate of fuel to be supplied to the combustor, characterized in that, the two-shaft gas turbine further comprising: a rotational frequency meter, a flow rate meter to measure the flow rate of the steam to be supplied to the combustor from the heat recovery steam generator, an inlet guide vane position gauge provided to the compressor, a steam valve position gauge, and a control system calculates and outputs command signals to operate openings of the fuel valve, the steam valve, and the inlet guide vane based on measurement signals obtained by the rotational frequency meter, the inlet guide vane position gauge, or the steam valve position gauge, and an output increase command value to the gas turbine.