Abstract: There is provided an axial flow turbine capable of realizing a reduction in gland leakage amount. The axial flow turbine in an embodiment is of a single flow type and includes an upstream-side gland part located on an upstream side of a working medium in an axial direction of a turbine rotor and a downstream-side gland part located on a downstream side of the working medium in the axial direction of the turbine rotor. The axial flow turbine is configured such that a cooling medium lower in temperature and higher in pressure than the working medium is extracted in a middle of flowing from the inside to the outside of the turbine casing in the upstream-side gland part, and the extracted cooling medium is introduced into the stationary blade.

Abstract: There is provided a turbine power generation system with a single casing configuration capable of easily executing the inhibition of an over-rotation speed. A turbine power generation system in an embodiment includes: a turbine including a turbine casing and a turbine rotor that rotates by a working medium to be introduced into the turbine casing; and a power generator including a power generator rotor connected to the turbine rotor, the power generator being caused to generate power by rotation of the power generator rotor caused by the rotation of the turbine rotor. The turbine casing of the turbine is single, and a moment of inertia of the power generator rotor is larger than a moment of inertia of the turbine rotor.

Abstract: There are provided a throttle mechanism and the like that are capable of easily changing a cross-sectional area of a flow path according to an operating state. The throttle mechanism in an embodiment is a throttle mechanism that controls a flow rate of a fluid flowing through a flow path, and is configured to make a cross-sectional area of the flow path change autonomously according to temperature.

Abstract: According to an embodiment, a turbine stage sealing mechanism reduces leak flow, which bypasses a working fluid flow path, between a rotating part and a stationary part in each turbine stage of a gas turbine. A radially inner side end portion of the stationary part is formed to be on a circle centered at a center axis of the rotating part under a predetermined operating condition of the gas turbine.

Abstract: A turbine rotor in an embodiment includes: a rotor body portion; and a plurality of turbine disks provided on the rotor body portion in a center axis direction of the rotor body portion. The turbine rotor includes: a high-pressure cooling passage formed in the rotor body portion, the high-pressure cooling passage to which a high-pressure cooling medium is supplied, and the high-pressure cooling passage that discharges the high-pressure cooling medium to the high-pressure side turbine stage; and a low-pressure cooling passage formed in the rotor body portion, the low-pressure cooling passage to which a low-pressure cooling medium whose pressure is lower than the pressure of the high-pressure cooling medium is supplied, and the low-pressure cooling passage that discharges the low-pressure cooling medium to the low-pressure side turbine stage.

Abstract: In order to miniaturize an image forming system, the present invention provides an image forming system which is provided with a sheet feed apparatus including a transport roller pair capable of transporting a sheet in a sheet transport direction S, and an image forming apparatus including an image forming section capable of forming an image on the sheet acquired from the sheet feed apparatus, including a switch member disposed on the downstream side of the transport roller pair in the sheet transport direction to be switched between a first position for guiding the sheet transported by the transport roller pair to the image forming apparatus, and a second position for guiding the sheet transported by the transport roller pair downward, and a storage tray disposed below the switch member predetermined space apart to be able to store the sheet guided to below the switch member positioned in the second position.

Abstract: According to an embodiment, a gas turbine includes: a casing; a rotor shaft penetrating through the casing; a plurality of turbine stages which are in the casing and are arranged along an axial direction of the rotor shaft and through which a working fluid passes; two bearings disposed on outer sides of the casing in terms of the axial direction and supporting the rotor shaft in a rotatable manner; and a plurality of outlet pipes through which the working fluid having finished work in the turbine stages is discharged. The outlet pipes are provided in an upper half and a lower half of the casing.

Abstract: There are provided a throttle mechanism and the like that are capable of easily changing a cross-sectional area of a flow path according to an operating state. The throttle mechanism in an embodiment is a throttle mechanism that controls a flow rate of a fluid flowing through a flow path, and is configured to make a cross-sectional area of the flow path change autonomously according to temperature.

Abstract: The invention provides a CO2 turbine power generation system that can be easily prevented from reaching an overspeed condition. A CO2 turbine power generation system of an embodiment includes a CO2 medium shutoff valve installed in a medium flow path between a regenerative heat exchanger and a combustor. When load rejection is to be performed, the CO2 medium shutoff valve closes to shut off the supply of the medium from the regenerative heat exchanger to the combustor.

Abstract: According to an embodiment, a turbine stator blade disposed in a working fluid flow path in a casing of a gas turbine, includes: a blade effective part disposed in the working fluid flow path; an outer circumferential sidewall having a plate-shaped part that is connected to a radially outer end portion of the blade effective part, and hooks each extending radially outward and circumferentially from the plate-shaped part and having a tip engaged with the casing; and an inner circumferential sidewall connected to a radially inner end portion of the blade effective part. At least one slit is formed at the rear hook or front hook to divide the hook in a circumferential direction, and the hook has a seal member to seal the slit.

Abstract: A sheet folding apparatus includes: a conveying roller conveying a sheet in a predetermined conveying direction; a folding roller pair disposed downstream of the conveying roller in the conveying direction and rotating while nipping a predetermined position of the sheet to form a fold; a conveying path for conveying the sheet in the conveying direction from the conveying roller to the folding roller pair; an abutting member moving downstream in the conveying direction and abutting against the predetermined position of the sheet to bend the sheet downstream; and a loop space where the sheet is bent between the conveying roller and folding roller pair in a direction crossing the conveying direction. The folding roller pair stops while nipping a front end of the sheet fed from to form a loop of the sheet in the loop space, and the abutting member moves to abut against the loop.

Abstract: Shaft stability is enhanced and reliability is improved. In a gas turbine power generation system of an embodiment, a pressurizing unit, a rotation control unit, a diaphragm coupling, a turbine, and a generator are disposed to line up sequentially on the same shaft. A thrust bearing is provided between the turbine and the generator. The turbine is configured such that a working medium flows from the diaphragm coupling side toward the rotation control unit side.

Abstract: The present invention is to provide an image forming system including a sheet folding processing apparatus and a sheet pressing apparatus capable of performing additional folding processing without decreasing productivity. The sheet pressing apparatus of the present invention includes a pressing roller including a pressing surface configured to press a fold line part of a folding processed sheet conveyed from a carry-in port in a thickness direction of the sheet and a guide portion configured to guide the folding processed sheet so that the fold line part is positioned at the pressing surface, a nipping member configured to nip the fold line part between the pressing surface and the nipping member, a first moving unit configured to move the pressing roller to a nipping position at which the fold line part is nipped between the nipping member and the pressing surface of the pressing roller and a retracting position.

Abstract: There is provided a manufacturing method of a turbine casing capable of easily realizing improvement of reliability. A manufacturing method of a turbine casing according to an embodiment is a manufacturing method of a turbine casing which includes an outer casing formed of ferritic heat resistant steel and an inner casing disposed inside the outer casing and formed of austenitic heat resistant steel, and in which an exhaust hood to which a working medium after performing work in turbine stages is exhausted, is covered by the inner casing. Here, the inner casing is manufactured by using members produced by at least either forging or rolling.

Abstract: A turbine rotor of an embodiment includes a rotor body portion having turbine discs in plural stages in an axial direction protruding radially outside from an outer peripheral surface of the rotor body portion over a circumferential direction. The turbine rotor includes a plurality of axial passages, through which a cooling medium flows, formed at the rotor body portion radially outside than a center axis of the turbine rotor and radially inside than an outer peripheral surface of the rotor body portion in the axial direction; an introduction passage introducing the cooling medium into each of the axial passages; and discharge passages that penetrate from each of the axial passages to the outer peripheral surface of the rotor body portion to discharge the cooling medium.

Abstract: According to an embodiment, a gas turbine includes: a casing; a rotor shaft penetrating through the casing; a plurality of turbine stages which are in the casing and are arranged along an axial direction of the rotor shaft and through which a working fluid passes; two bearings disposed on outer sides of the casing in terms of the axial direction and supporting the rotor shaft in a rotatable manner; and a plurality of outlet pipes through which the working fluid having finished work in the turbine stages is discharged. The outlet pipes are provided in an upper half and a lower half of the casing.

Abstract: There is provided a turbine power generation system with a single casing configuration capable of easily executing the inhibition of an over-rotation speed. A turbine power generation system in an embodiment includes: a turbine including a turbine casing and a turbine rotor that rotates by a working medium to be introduced into the turbine casing; and a power generator including a power generator rotor connected to the turbine rotor, the power generator being caused to generate power by rotation of the power generator rotor caused by the rotation of the turbine rotor. The turbine casing of the turbine is single, and a moment of inertia of the power generator rotor is larger than a moment of inertia of the turbine rotor.

Abstract: A CO2 gas turbine facility of an embodiment includes: a combustion apparatus which combusts fuel and an oxidant to produce a combustion gas to be introduced into a turbine; a pipe which circulates carbon dioxide in a working fluid discharged from the turbine through the combustion apparatus as a cooling medium; and a bypass pipe which introduces a fluid at a lower temperature than a temperature of carbon dioxide flowing through the pipe into the pipe.

Abstract: The supercritical CO2 turbine in an embodiment includes: a rotary body; a stationary body housing the rotary body inside; and a turbine stage including a stator blade cascade in which a plurality of stator blades are supported inside the stationary body, and a rotor blade cascade in which a plurality of rotor blades are supported by the rotary body inside the stationary body, in which a supercritical CO2 working medium is introduced into the inside of the stationary body and flows via the turbine stage in an axial direction of the rotary body to thereby rotate the rotary body. Here, a thermal conductivity k1 and a specific heat c1 of a material constituting the rotary body and a thermal conductivity k2 and a specific heat c2 of a material constituting the stationary body satisfy a relationship represented by the following formula (A).

Abstract: A turbine rotor in an embodiment includes: a rotor body portion; and a plurality of turbine disks provided on the rotor body portion in a center axis direction of the rotor body portion. The turbine rotor includes: a high-pressure cooling passage formed in the rotor body portion, the high-pressure cooling passage to which a high-pressure cooling medium is supplied, and the high-pressure cooling passage that discharges the high-pressure cooling medium to the high-pressure side turbine stage; and a low-pressure cooling passage formed in the rotor body portion, the low-pressure cooling passage to which a low-pressure cooling medium whose pressure is lower than the pressure of the high-pressure cooling medium is supplied, and the low-pressure cooling passage that discharges the low-pressure cooling medium to the low-pressure side turbine stage.