Abstract: A compressor system includes: a compressor having an upstream region into which a working fluid flows, a downstream region in which the pressure of the working fluid is greater than that in the upstream region, inlet guide vanes that are provided further upstream than the upstream region and capable of altering the flow rate of the inflowing working fluid, and an extraction part that is provided to a portion between the upstream region and the downstream region and capable of extracting at least a portion of the working fluid; detection devices, at least one of which is provided in each of the upstream region and the downstream region, for detecting the physical quantity of the working fluid; and a control device for adjusting, on the basis of changes in the physical quantity, the opening degree of the inlet guide vanes and the amount extracted by the extraction part.

Abstract: A compressor system includes: a compressor having an upstream region into which a working fluid flows, a downstream region in which the pressure of the working fluid is greater than that in the upstream region, inlet guide vanes that are provided further upstream than the upstream region and capable of altering the flow rate of the inflowing working fluid, and an extraction part that is provided to a portion between the upstream region and the downstream region and capable of extracting at least a portion of the working fluid; detection devices, at least one of which is provided in each of the upstream region and the downstream region, for detecting the physical quantity of the working fluid; and a control device for adjusting, on the basis of changes in the physical quantity, the opening degree of the inlet guide vanes and the amount extracted by the extraction part.

Abstract: To provide an axial flow turbine that can eliminate a circumferential velocity component of a leakage flow effectively, and attempt to collect motive power. A shroud of the axial flow turbine includes: an annular first protruding portion protruding toward the upstream side in a rotor's axis direction; an annular second protruding portion that is positioned on the outer side in the rotor's radius direction relative to the first protruding portion, protrudes toward the upstream side in the rotor's axis direction, and is longer than the first protruding portion; a circulating-flow generating chamber formed between the first protruding portion and the second protruding portion; and guide plates positioned in the circulating-flow generating chamber.

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: To provide an axial flow turbine that can eliminate a circumferential velocity component of a leakage flow effectively, and attempt to collect motive power. A shroud of the axial flow turbine includes: an annular first protruding portion protruding toward the upstream side in a rotor's axis direction; an annular second protruding portion that is positioned on the outer side in the rotor's radius direction relative to the first protruding portion, protrudes toward the upstream side in the rotor's axis direction, and is longer than the first protruding portion; a circulating-flow generating chamber formed between the first protruding portion and the second protruding portion; and guide plates positioned in the circulating-flow generating chamber.

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: 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: An object is to reduce the compressor flow rate in comparison with the reference model while maintaining a compression ratio equivalent to that in the reference model. Annulus areas required of a compressor 38 of a derivative gas turbine 200 are determined based on a compressor flow rate and a compression ratio required of the compressor 38 of the derivative gas turbine 200.

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 thermal power generation system includes a combustor burning oxygen and fuel with supercritical CO2, a turbine driven by the supercritical CO2 and water vapor fed from the combustor, a low-pressure supercritical CO2 storage storing low-pressure supercritical CO2 from the turbine, a compressor compressing the low-pressure supercritical CO2, a high-pressure supercritical CO2 storage storing high-pressure supercritical CO2 from the compressor, and a high-pressure supercritical CO2 feeder supplying between the high-pressure supercritical CO2 storage and the combustor, in which the high-pressure supercritical CO2 feeder supplies the high-pressure supercritical CO2 to the combustor at a constant pressure.

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: An axial flow turbine that can enhance an effect of reducing a mixing loss is disclosed. The axial flow turbine includes a plurality of stator blades provided on the inner circumferential side of a diaphragm outer ring; a plurality of rotor blades provided on the outer circumferential side of a rotor; a shroud provided on the outer circumferential side of the plurality of rotor blades; an annular groove portion formed in the diaphragm outer ring and housing the shroud therein; a clearance passage defined between the groove portion and the shroud, into which a portion of working fluid flows from the downstream side of the stator blades in a main passage; seal fins provided in the clearance passage; a circulation flow generating chamber defined on the downstream side of the clearance passage; and a plurality of shielding plates secured to the diaphragm outer ring.

Abstract: An axial flow turbine that can enhance an effect of reducing a mixing loss is disclosed. The axial flow turbine includes a plurality of stator blades provided on the inner circumferential side of a diaphragm outer ring; a plurality of rotor blades provided on the outer circumferential side of a rotor; a shroud provided on the outer circumferential side of the plurality of rotor blades; an annular groove portion formed in the diaphragm outer ring and housing the shroud therein; a clearance passage defined between the groove portion and the shroud, into which a portion of working fluid flows from the downstream side of the stator blades in a main passage; seal fins provided in the clearance passage; a circulation flow generating chamber defined on the downstream side of the clearance passage; and a plurality of shielding plates secured to the diaphragm outer ring.

Abstract: An object is to reduce the compressor flow rate in comparison with the reference model while maintaining a compression ratio equivalent to that in the reference model. Annulus areas required of a compressor 38 of a derivative gas turbine 200 are determined based on a compressor flow rate and a compression ratio required of the compressor 38 of the derivative gas turbine 200.

Abstract: An axial turbine includes a plurality of ribs provided in such a way as to be sandwiched between the diaphragm outer ring and the axial seal fin in the gap between the shroud and the diaphragm outer ring, the ribs being extended from the diaphragm outer ring toward the shroud in the radial direction of the rotor and in the direction of the rotation axis thereof, and a guide plate provided in such a way as to be present along the axial seal fin and a face of the diaphragm outer ring, opposed to the rotor, so as to be extended in the rotation radial direction of the rotor.

Abstract: A thermal power generation system includes a combustor burning oxygen and fuel with supercritical CO2, a turbine driven by the supercritical CO2 and water vapor fed from the combustor, a low-pressure supercritical CO2 storage storing low-pressure supercritical CO2 from the turbine, a compressor compressing the low-pressure supercritical CO2, a high-pressure supercritical CO2 storage storing high-pressure supercritical CO2 from the compressor, and a high-pressure supercritical CO2 feeder supplying between the high-pressure supercritical CO2 storage and the combustor, in which the high-pressure supercritical CO2 feeder supplies the high-pressure supercritical CO2 to the combustor at a constant pressure.

Abstract: An axial flow turbine that can enhance an effect of reducing a mixing loss is disclosed. The axial flow turbine includes a plurality of stator blades provided on the inner circumferential side of a diaphragm outer ring; a plurality of rotor blades provided on the outer circumferential side of a rotor; a shroud provided on the outer circumferential side of the plurality of rotor blades; an annular groove portion formed in the diaphragm outer ring and housing the shroud therein; a clearance passage defined between the groove portion and the shroud, into which a portion of working fluid flows from the downstream side of the stator blades in a main passage; seal fins provided in the clearance passage; a circulation flow generating chamber defined on the downstream side of the clearance passage; and a plurality of shielding plates secured to the diaphragm outer ring.

Abstract: A boiling water nuclear power plant supplies steam from a reactor to high-pressure and low-pressure turbines. Feed water generated by condensing steam in a condenser is heated by low-pressure and high-pressure feed water heaters and supplied to the reactor. The steam discharged from the low-pressure turbine is compressed by a steam compressor and supplied to one of the low-pressure feed water heaters to heat feed water. The steam extracted from the low-pressure turbine is supplied to the low-pressure feed water heater. When power required for the steam compressor is Q1, heat energy supplied from the steam compressor is Q3, a coefficient of performance of the steam compressor is COP (=Q3/Q1), and a thermal efficiency of the boiling water nuclear power plant is ?, the steam compression apparatus is connected to a position in a main steam system and to the feed water heater so as to satisfy COP?1/?>0.

Abstract: Turbo machinery comprising an impeller and a diffuser positioned on a downstream side of the impeller that a channel wall surface of the diffuser is composed of a pair of a shroud side diffuser plate and a hub side diffuser plate which surface each other and a channel width is formed so as to be increased downstream, characterized in that guide vanes in a circular arc shape lower in height than the channel width are installed in a line of a plurality of vanes on both channel walls of the shroud side diffuser plate and hub side diffuser plate of the diffuser, and a total of vane heights of the two guide vanes at an outlet of the diffuser is set so as to be within a range from 30 to 70% of the channel width at the outlet of the diffuser.

Abstract: A centrifugal compressor provided with an impeller which is configured to have a plurality of blades arranged at a predetermined interval in a circumferential direction of a hub rotating together with a rotation shaft, in which a blade angle on a shroud side of the blade distributes to have a minimum value at a position between a leading edge of the blade and a midpoint of a camber line on the shroud side, and a maximum value at a position between the midpoint of the camber line on the shroud side and a trailing edge of the blade, and a blade angle of the blade on a hub side distributes so as to have a maximum value at a position between a leading edge and a midpoint of a camber line on the hub side.