Abstract: An output voltage is stabilized at a predetermined target voltage by using a charge pump circuit. A first voltage divider that is arranged between an output line to which the output voltage is applied and a feedback line and that generates a first division voltage commensurate with the output voltage and a second voltage divider arranged between the feedback line and the ground and that generates a second division voltage commensurate with the output voltage are provided to generate on the feedback line, as a feedback voltage, a voltage lower than the output voltage by the first division voltage. The second voltage divider includes an N-type particular transistor whose gate receives a reference voltage and whose drain is connected to the feedback line.

Abstract: A memory circuit includes a first switch provided for each pair of first and second bit lines and connected to a first and a second memory cell, a first all bit line selection circuit that, if an input test signal indicates a test, can turn on all the first switches regardless of the bit data of an input switch control signal, and a sensing circuit that can sense the magnitude relationship between the sum of currents flowing through the first bit lines and a reference current and the magnitude relationship between the sum of currents flowing through the second bit lines and the reference current. The gate of a first memory transistor and the gate of a second memory transistor can be fed with a direct-current voltage.

Abstract: An output voltage is stabilized at a predetermined target voltage by using a charge pump circuit. A first voltage divider that is arranged between an output line to which the output voltage is applied and a feedback line and that generates a first division voltage commensurate with the output voltage and a second voltage divider arranged between the feedback line and the ground and that generates a second division voltage commensurate with the output voltage are provided to generate on the feedback line, as a feedback voltage, a voltage lower than the output voltage by the first division voltage. The second voltage divider includes an N-type particular transistor whose gate receives a reference voltage and whose drain is connected to the feedback line.

Abstract: This aircraft gas turbine is provided with a rotor, a rotor blade (24), a casing, a stationary blade (26), and a guide member (53). The rotor blade (24) has fins (43) projecting from the outer peripheral surface (42a) of a rotor blade shroud (42). A stationary blade shroud (51) of the stationary blade (26) forms a cavity (Ct) with at least the rotor blade shroud (42) and the fins (43). The guide member (53) is provided inside the cavity (Ct) and extends inward from the radial outer side, and an inner-side end part (53a) on the radial inner side faces the outer peripheral surface (42a) of the rotor blade shroud (42) with a gap therebetween.

Abstract: A turbine blade includes a blade body in which a suction side (51) facing one side in a circumferential direction and a pressure side (52) facing the other side in the circumferential direction are connected at a leading edge and a trailing edge; and a shroud provided at a tip which is a radially outer end portion of the blade body. The shroud includes a shroud body having an outer circumferential surface facing radially outward, a front end surface extending to both sides in the circumferential direction with a leading edge side of the blade body as a reference point (P1), a rear end surface extending to both sides in the circumferential direction with a trailing edge side of the blade body as a reference point (P2), and a contact surface provided on both sides in the circumferential direction, and a reinforcing portion which protrudes from the outer circumferential surface.

Abstract: Provided is a transition duct that forms an annular gas flow channel through which a main flow gas flows from a high-pressure turbine to a low-pressure turbine, wherein the gas flow channel has an inner peripheral flow channel surface and an outer peripheral flow channel surface, the inner peripheral flow channel surface and the outer peripheral flow channel surface extend radially outward while angles of inclination relative to an axial direction of a rotating shaft change from the high-pressure turbine (first turbine) toward the low-pressure turbine (second turbine), and an inner peripheral maximum inclined part is provided in a range A2 that extends in the axial direction from a position of alignment with an outer peripheral maximum inclined part to a position advanced toward the low-pressure turbine by a length no more than 20% of the duct length.

Abstract: A gas turbine for an aircraft includes: blades each including a blade body extending outward from a rotor rotating about an axis in a radial direction of the rotor and a fin protruding from an outer peripheral surface of a blade shroud formed on a distal end of the blade body; a casing installed to form gaps between the casing and the fins; and vanes each including a vane shroud formed such that at least a leading end portion of the vane shroud formed upstream in an axial direction is located outside with respect to an extended line of an inner peripheral surface of the casing in the radial direction.

Abstract: This aircraft gas turbine is provided with a rotor, a rotor blade (24), a casing, a stationary blade (26), and a guide member (53). The rotor blade (24) has fins (43) projecting from the outer peripheral surface (42a) of a rotor blade shroud (42). A stationary blade shroud (51) of the stationary blade (26) forms a cavity (Ct) with at least the rotor blade shroud (42) and the fins (43). The guide member (53) is provided inside the cavity (Ct) and extends inward from the radial outer side, and an inner-side end part (53a) on the radial inner side faces the outer peripheral surface (42a) of the rotor blade shroud (42) with a gap therebetween.

Abstract: A turbine is equipped with a turbine rotor (21), a turbine casing, a turbine blade (24), a turbine stator and a diffuser (4A). The diffuser (4A) is equipped with an inner cylinder (41) extending along an axis, an outer cylinder covering the inner cylinder (41) from an outer circumferential side and forming an exhaust flow path (C) between the inner cylinder (41) and the outer cylinder. The inner cylinder (41) is equipped with an inclined surface (51) extending from an inner side to an outer side in the radial direction centering on the axis as going from one side to the other side in the direction of the axis. The inclined surface (51) is disposed to intersect an extension (55) obtained by extending platforms (54) of a plurality of turbine blades (24) to the other side in the direction of the axis, in a cross sectional view including the axis.

Abstract: A gas turbine for an aircraft includes: blades each including a blade body extending outward from a rotor rotating about an axis in a radial direction of the rotor and a fin protruding from an outer peripheral surface of a blade shroud formed on a distal end of the blade body; a casing installed to form gaps between the casing and the fins; and vanes each including a vane shroud formed such that at least a leading end portion of the vane shroud formed upstream in an axial direction is located outside with respect to an extended line of an inner peripheral surface of the casing in the radial direction.

Abstract: A shroud (22) comprises shroud bodies (22) fixed to blade tips of blades (18) mounted to a rotor body to extend in a radial direction, the shroud bodies (22) being disposed adjacent to one another in a circumferential direction, wherein each of the shroud bodies (22) includes a circumferential end surface (27, 28) that includes an abutting end surface where adjacent shroud bodies (22) abut, and an opposing surface (34) where adjacent shroud bodies (22) face one another with a clearance (32) therebetween, the opposing surface (34) being contiguous with the abutting end surface; and an outer surface (24) that includes a radially outward protruding protrusion (40) formed to extend along the opposing surface (34).

Abstract: A turbine rotor blade includes an airfoil portion having an airfoil defined by a pressure surface and a suction surface; and a squealer rib on a tip surface of the turbine rotor blade, the squealer rib extending from a leading-edge side (toward a trailing-edge side. The squealer rib has a ridge extending in an extending direction of the squealer rib. The turbine rotor blade is configured to provide a clearance between the tip surface of the turbine rotor blade and an inner wall surface of a casing of a turbine such that the inner wall surface of the casing of the turbine faces the tip surface of the turbine rotor blade and the clearance has a local minimum value on the ridge. The clearance is greater than the local minimum value at both sides of the ridge in a width direction of the squealer rib.

Abstract: A turbo machine includes a casing in which fluid flows; turbine blades arranged side by side in a circumferential direction with respect to a rotational shaft rotatably provided in the casing; a ring segment forming an inner surface of the casing; a seal fin provided as an extension at a tip end part of each turbine blade and facing the ring segment; and a seal member through which the turbo machine faces the seal fin, the seal member having a first inner surface that accepts contact of the seal fin. The ring segment has a second inner surface incrementally enlarging toward a downstream side in an axial direction of the rotational shaft. The first and second inner surfaces are connected with each other without a step between the inner surfaces on the downstream side of the first inner surface in the axial direction.

Abstract: A turbine blade includes a blade body in which a suction side (51) facing one side in a circumferential direction and a pressure side (52) facing the other side in the circumferential direction are connected at a leading edge and a trailing edge; and a shroud provided at a tip which is a radially outer end portion of the blade body. The shroud includes a shroud body having an outer circumferential surface facing radially outward, a front end surface extending to both sides in the circumferential direction with a leading edge side of the blade body as a reference point (P1), a rear end surface extending to both sides in the circumferential direction with a trailing edge side of the blade body as a reference point (P2), and a contact surface provided on both sides in the circumferential direction, and a reinforcing portion which protrudes from the outer circumferential surface.

Abstract: A turbine is equipped with a turbine rotor (21), a turbine casing, a turbine blade (24), a turbine stator and a diffuser (4A). The diffuser (4A) is equipped with an inner cylinder (41) extending along an axis, an outer cylinder covering the inner cylinder (41) from an outer circumferential side and forming an exhaust flow path (C) between the inner cylinder (41) and the outer cylinder. The inner cylinder (41) is equipped with an inclined surface (51) extending from an inner side to an outer side in the radial direction centering on the axis as going from one side to the other side in the direction of the axis. The inclined surface (51) is disposed to intersect an extension (55) obtained by extending platforms (54) of a plurality of turbine blades (24) to the other side in the direction of the axis, in a cross sectional view including the axis.

Abstract: A cooling structure for a turbine includes a plurality of disks configured to rotate integrally with blades, the disks being arranged along a rotational axis; and the disks have disk holes defined therein and arranged in a circumferential direction for supplying cooling air for cooling the blades to downstream disks. At least one of the disk holes is set such that, when a rotational direction of the disk is defined as a positive direction and a direction opposite the rotational direction is defined as a negative direction, an outlet absolute circumferential velocity vector which is a component in the rotational direction of a velocity vector of the cooling air at an outlet of the disk hole is smaller than an inlet absolute circumferential velocity vector which is a component in the rotational direction of a velocity vector of the cooling air at an inlet of the disk hole.

Abstract: Provided is a transition duct that forms an annular gas flow channel through which a main flow gas flows from a high-pressure turbine to a low-pressure turbine, wherein the gas flow channel has an inner peripheral flow channel surface and an outer peripheral flow channel surface, the inner peripheral flow channel surface and the outer peripheral flow channel surface extend radially outward while angles of inclination relative to an axial direction of a rotating shaft change from the high-pressure turbine (first turbine) toward the low-pressure turbine (second turbine), and an inner peripheral maximum inclined part is provided in a range A2 that extends in the axial direction from a position of alignment with an outer peripheral maximum inclined part to a position advanced toward the low-pressure turbine by a length no more than 20% of the duct length.

Abstract: A cooling structure for a turbine is configured such that: a plurality of disks rotating integrally with blades are arranged along a rotational axis; and the disks have formed therein disk holes arranged in a circumferential direction to supply cooling air for cooling the rotor blades to downstream disks. At least one of the disk holes is set such that, when the rotational direction of the disk is defined as the positive direction and the direction opposite the rotational direction is defined as the negative direction, an outlet absolute circumferential velocity vector which is a component in a rotational direction U of the velocity vector of the cooling air at an outlet of a disk hole is smaller than an inlet absolute circumferential velocity vector which is a component in the rotational direction of the velocity vector of the cooling air at an inlet of the disk hole.

Abstract: A turbine rotor blade (26) for a turbine includes an airfoil portion (30) having an airfoil formed by a pressure surface (31) and a suction surface (32); and at least one squealer rib (40, 42, 44) disposed on a tip surface (35) of the turbine rotor blade so as to extend from a leading-edge side (33) toward a trailing-edge side (34). At least one (42) of the at least one squealer rib has a ridge (43) extending in an extending direction of the squealer rib. A clearance (100) between the tip surface and an inner wall surface of a casing of the turbine, the inner wall surface facing the tip surface, has a local minimum value on the ridge. The clearance is greater than the local minimum value at both sides of the ridge in a width direction of the squealer rib.

Abstract: A shroud (22) comprises shroud bodies (22) fixed to blade tips of blades (18) mounted to a rotor body to extend in a radial direction, the shroud bodies (22) being disposed adjacent to one another in a circumferential direction, wherein each of the shroud bodies (22) includes a circumferential end surface (27, 28) that includes an abutting end surface where adjacent shroud bodies (22) abut, and an opposing surface (34) where adjacent shroud bodies (22) face one another with a clearance (32) therebetween, the opposing surface (34) being contiguous with the abutting end surface; and an outer surface (24) that includes a radially outward protruding protrusion (40) formed to extend along the opposing surface (34).