Mitsubishi Hitachi Power Systems, Ltd.

Mitsubishi Heavy Industries Limited

Mitsubishi Heavy Industries Compressor Corporation

Hitachi, Ltd.

Mitsubishi Power, Ltd.

Chihiro Myoren

Kazuo Takahashi

Yasuo Takahashi

Takanori Shibata

Shinya Marushima

Hiroki Takeda

Jo Masutani

Shuichi Yamashita

Kenji Nanataki

Miku Kuroda

Kohta Kawamura

Kota Kawamura

Akihiro Nakaniwa

Shinichiro Tokuyama

Nobuyori Yagi

Kazuhiro Imai

Daisuke Morita

Shinichi Higuchi

Takashi Oda

Ryo Akiyama

Noriyuki Okada

Ryou Akiyama

Ichiro Miyoshi

Hirofumi Higuchi

Tetsuro Morisaki

Ryosuke Mito

Takuya Takeda

Tadashi Murakata

Yasunori Kimura

Yuji Koike

Naoto Omura

Yuta Okumura

An aircraft includes a fuselage body extending in a front-rear direction; a tail wing at a rear portion of the fuselage body in the front-rear direction; a main wing in front of the tail wing in the front-rear direction on the fuselage body; and a fan device on an outer surface of the fuselage body. The fan device includes a rotor shaft outside the outer surface of the fuselage body, a rotor blade on an outer side of the rotor shaft in a rotor radial direction with the rotor shaft as a center, a housing fixed to the fuselage body, extending in the front-rear direction, including respective openings at a front and a rear in the front-rear direction, and provided to cover the rotor shaft and the rotor blade, a stator blade.

Aircraft

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. The inner casing includes an outer peripheral wall surface having recesses accommodating the inner shrouds and forming, together with an inside surface of the compressor casing, a diffuser on the downstream side of the recesses, and an inner peripheral wall surface forming an air extraction cavity. An air extraction hole is formed in a portion, in the recesses, on the downstream side.

Compressor and gas turbine

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 &#x2212;10 degrees or more and 0 degrees or less at the position where the angle difference is maximum.

Impeller of rotating machine and rotating machine

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.

Centrifugal compressor

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. The upper end of the fillet is positioned lower in the narrow portion than that in a region other than the narrow portion, and the lower end of the arc-shaped curved surface coincides with the flow path wall surface along the entire circumference of the blade profile section.

Axial flow turbomachine and blade thereof

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.

Compressor

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.

Multi-stage centrifugal compressor

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.

Gas turbine manufacturing method

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. Each blade of the blade row located at the protruding portion of the wall surface is configured such that an increase rate in a wall surface direction of a blade outlet angle in a blade end portion on the side of the wall surface having the protruding portion is greater than an increase rate in the wall surface direction of a blade outlet angle in a blade height intermediate portion.

Axial flow compressor, gas turbine including the same, and stator blade of axial flow compressor

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.

Two-shaft gas turbine, and control system and control method of the gas turbine

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.

2-shaft gas turbine, and the control method of opening degree of inlet guide vane of the gas turbine

An axial compressor comprising liquid drop feed means for feeding liquid drops to an operating fluid of the compressor, a casing for forming a flow path through which the operating fluid flows down and a plurality of stages, each of which is composed of one continuous rotor blade row and one continuous stator vane row, the axial compressor being structured so that the liquid drops evaporate inside the compressor, characterized in that: the casing is provided with a cavity therein, and the cavity is formed by an outer casing and an inner casing which is enclosing a periphery of the rotor blade rows at the plurality of stages and forming internally a flow path of the operating fluid, and a flow path is provided for feeding the operating fluid to the cavity on a downstream side of a region forming the cavity of the inner casing.

Axial compressor and operation method of the same

An axial compressor includes a plurality of stator vanes attached to an inner surface of a casing defining an annular flow path and a plurality of rotor blades attached to a rotating rotor defining the annular flow path. A flow path is defined between a pressure surface of a stator vane and a suction surface of a stator vane, the vanes being circumferentially adjacent to each other, or between a pressure surface of a rotor blade and a suction surface of a rotor blade, the blades being circumferentially adjacent to each other. The flow path is formed so that a throat portion at which a flow path width is minimized is provided on the upstream side of 50% of an axial chord length.

Axial compressor

An axial compressor that can remove an attachment within a groove of a casing and recover an effect of suppressing stall on rotor blades, and a gas turbine provided with the axial compressor, are provided. The axial compressor includes a compressor bodyand a sprayerfor spraying droplets in suction gas of the compressor bodyso that the droplets are introduced into the compressor bodyand evaporate. The compressor bodyincludes a casing, a rotor, rotor blades, and stator vanes. A grooveis formed in an inner circumferential surface of the casingso as to be positioned around rotor bladesarranged on a front stage side. A purge systemis provided that supplies high-pressure air to the groovethrough communication holes

Axial compressor and gas turbine having axial compressor

An axial compressor includes: a rotor as a rotational shaft, rotor blades mounted on the rotor, a compressor casing that covers the rotor and the rotor blades, and stator vanes mounted on the compressor casing. The rotor blades and the stator vanes are each disposed in a circumferential direction of the rotational shaft to form a rotor-blade cascade and a stator-vane cascade, respectively. The rotor-blade cascade and the stator-vane cascade are arranged in plural rows, respectively, in an axial direction of the rotational shaft. The stator vane has a dovetail, and the compressor casing has a dovetail groove that extends in the circumferential direction of the rotational shaft to receive the dovetail inserted therein to fix the stator vanes. Two or more stator vanes, the stator vanes belonging to stator-vane cascades different from each other, are fixed in the dovetail groove.

Growing community of inventors

Tokai, Japan

Chihiro Myoren