Abstract: A sheet type discrimination device includes: a first light source unit that irradiates a sheet with light having a first wavelength and light having a second wavelength; a detection unit that detects light from the sheet and acquires a detection value based on the light; and a control unit that derives a determination result of a type of the sheet, wherein the first light source unit and the detection unit are located on a same side with respect to the sheet, the detection value includes: a first detection value; and a second detection value, and the control unit discriminates first-type recycled paper by first processing using the first detection value, and discriminates second-type recycled paper different from the first-type recycled paper by second processing using the second detection value.

Abstract: A gas turbine engine, in which a compressed gas from a compressor is burned in a combustor and obtained combustion gas drives a turbine, includes: a compressed gas supply portion configured to supply the compressed gas obtained from the compressor to the combustor; an annular dividing guide body disposed in a diffuser that forms an upstream-side portion of the compressed gas supply portion, the dividing guide body being configured to divide the compressed gas in a radial direction; and a guide support body that supports the dividing guide body on an inner diameter side wall of the compressed gas supply portion.

Abstract: Provided is a structure for bleeding gas from a chamber for receiving compressed gas from a compressor of a gas turbine engine and supplying the compressed gas to a combustor. The structure includes: a turbine casing covering an outer circumference of a turbine; an engine housing forming, between the engine housing and the turbine casing, a bleeding space that communicates with the chamber; a bleeding duct through which compressed gas in the bleeding space is guided to the outside of the engine housing; and an annular partitioning member arranged on an upstream side, relative to the bleeding duct in the bleeding space so as to separate the bleeding space from the chamber, and having a plurality of communication holes through which an upstream side and a downstream side relative to the partitioning member communicate with each other.

Abstract: A gas turbine engine includes: a plurality of combustors disposed so as to incline radially outward from a turbine side toward a compressor side; and a diffuser inner tube and outer tube forming a diffuser as an upstream portion of a path that introduces a compressed gas from the compressor to the combustors. A transition duct portion of each combustor has such a shape that a circumferential dimension thereof gradually decreases from the turbine side to the compressor side so that a circumferential gap is formed between the transition duct portions. Downstream-side portions of the diffuser inner tube and outer tube each have a shape gradually increasing in diameter toward the downstream side. A turbine-side end of the circumferential gap at an inner diameter side of the transition duct portion is positioned radially inward of an imaginary extension conical surface continuous from the diffuser inner tube.

Abstract: A gas turbine engine, in which a compressed gas from a compressor of an axial-flow type is burned in a combustor and an obtained combustion gas drives a turbine, includes: a diffuser of an annular shape connected to an outlet of the compressor, the diffuser including a diffuser inner tube and a diffuser outer tube that are tubular members disposed concentrically with each other; and a plurality of partition members that are disposed in a diffuser flow path, which is an annular space formed between the diffuser inner tube and the diffuser outer tube, and divide the diffuser flow path in a circumferential direction.

Abstract: A gas turbine engine, in which a compressed gas from a compressor is burned in a combustor and obtained combustion gas drives a turbine, includes: a compressed gas supply portion configured to supply the compressed gas obtained from the compressor to the combustor; an annular dividing guide body disposed in a diffuser that forms an upstream-side portion of the compressed gas supply portion, the dividing guide body being configured to divide the compressed gas in a radial direction; and a guide support body that supports the dividing guide body on an inner diameter side wall of the compressed gas supply portion.

Abstract: A compressor rotor including a structure for bleeding air flowing through a compressed air flowpath of an axial compressor to an inner passage provided on an inner peripheral side of the axial compressor, includes rotor blades and a rotor disc. The rotor disc includes a blade groove provided in an outer peripheral surface thereof and being continuous in a circumferential direction and a passage which communicates an inner region of the blade groove with the inner passage. The rotor blade has a root part and a platform which are fitted to the blade groove, and a blade part provided on a side opposite to the root part with the platform interposed between the root part and the blade part. An opening is provided in the platform or a region that is in the vicinity of the platform and configured to communicate the inner region of the blade groove with the compressed air flowpath.

Abstract: A gas turbine engine, in which a compressed gas from a compressor of an axial-flow type is burned in a combustor and an obtained combustion gas drives a turbine, includes: a diffuser of an annular shape connected to an outlet of the compressor, the diffuser including a diffuser inner tube and a diffuser outer tube that are tubular members disposed concentrically with each other; and a plurality of partition members that are disposed in a diffuser flow path, which is an annular space formed between the diffuser inner tube and the diffuser outer tube, and divide the diffuser flow path in a circumferential direction.

Abstract: A gas turbine engine includes: a plurality of combustors disposed so as to incline radially outward from a turbine side toward a compressor side; and a diffuser inner tube and outer tube forming a diffuser as an upstream portion of a path that introduces a compressed gas from the compressor to the combustors. A transition duct portion of each combustor has such a shape that a circumferential dimension thereof gradually decreases from the turbine side to the compressor side so that a circumferential gap is formed between the transition duct portions. Downstream-side portions of the diffuser inner tube and outer tube each have a shape gradually increasing in diameter toward the downstream side. A turbine-side end of the circumferential gap at an inner diameter side of the transition duct portion is positioned radially inward of an imaginary extension conical surface continuous from the diffuser inner tube.

Abstract: Provided is a structure for bleeding gas from a chamber for receiving compressed gas from a compressor of a gas turbine engine and supplying the compressed gas to a combustor. The structure includes: a turbine casing covering an outer circumference of a turbine; an engine housing forming, between the engine housing and the turbine casing, a bleeding space that communicates with the chamber; a bleeding duct through which compressed gas in the bleeding space is guided to the outside of the engine housing; and an annular partitioning member arranged on an upstream side, relative to the bleeding duct in the bleeding space so as to separate the bleeding space from the chamber, and having a plurality of communication holes through which an upstream side and a downstream side relative to the partitioning member communicate with each other.

Abstract: A starting method for a gas turbine engine includes a primary warming step of warming up the gas turbine engine while a constant primary warm-up rotation speed is maintained by an inverter motor and a secondary warming step of warming up the gas turbine engine while a constant secondary warm-up rotation speed is maintained by further increasing the speed of the inverter motor. The primary warming step terminates when an electric power required by the inverter motor attains a predetermined preset electric power value. The preset electric power value is so chosen as to decrease as the intake air temperature is low.

Abstract: A gas turbine engine having high reliability is provided by suppressing occurrence of thermal stress between a scroll and a support member thereof. A gas turbine engine equipped with a combustor of a single-can type includes a scroll to guide a combustion gas fed from a combustor to a turbine while swirling the combustion gas about a rotation axis, a flange member to support the scroll with respect to the gas turbine engine from an inner peripheral side of the scroll, and a coupling member of an annular shape to couple the scroll and the flange member with each other. The scroll and the flange member are connected to the coupling member such that the scroll and the flange member are not in direct contact with each other.

Abstract: A novel cyclic heptapeptide that is useful as a preadipocyte differentiation-inhibitory agent or an adipocyte fat accumulation-inhibitory agent, and the use of such agents, are provided. A novel cyclic heptapeptide represented by the following formula is provided. wherein R is CH3, CH2CH(CH3)2, CH2OCH2C6H5, CH(OH)CH3, or CH2OH.

Abstract: A novel cyclic heptapeptide that is useful as a preadipocyte differentiation-inhibitory agent or an adipocyte fat accumulation-inhibitory agent, and the use of such agents, are provided. A novel cyclic heptapeptide represented by the following formula is provided. wherein R is CH3, CH2CH(CH3)2, CH2OCH2C6H5, CH(OH)CH3, or CH2OH.

Abstract: This invention relates to 12,13-dihydro-6H-indolo[2,3-a]pyrrolo[3,4-c]carbazole-5,7(6H)-dione derivatives represented by the following general formula, pharmaceutically acceptable salts thereof, a method for preparation thereof and a use thereof: ##STR1## [wherein R.sup.1 denotes a monosaccharide group having 5 to 7 carbon atoms, and the hydroxyl groups of this monosaccharide group can be replaced by the same or different 1 to 3 groups selected from the group consisting of a hydrogen atom, lower alkyl group, lower alkylcarbonyloxy group and lower alkoxy group.

Abstract: This invention relates to 12,13-dihydro-6H-indolo[2,3-a]pyrrolo[3,4-c]carbazole-5,7(6H)-dione derivatives represented by the following general formula, pharmaceutically acceptable salts thereof, a method for preparation thereof and a use thereof: ##STR1## [wherein R.sup.1 denotes a monosaccharide group having 5 to 7 carbon atoms, and the hydroxyl groups of this monosaccharide group can be replaced by the same or different 1 to 3 groups selected from the group consisting of a hydrogen atom, lower alkyl group, lower alkylcarbonyloxy group and lower alkoxy group.

Abstract: The present invention provides glycookadaic acid or salts thereof, processes for the preparation of such compounds, methods for treating and preventing cachexia and a side effect caused by TNF, and pharmaceutical compositions comprising such compounds as active components for treating and preventing cachexia and a side effect caused by TNF.