Mitsubishi Heavy Industries Limited

Mitsubishi Heavy Industries Aero Engines, Ltd.

Mitsubishi Power, Ltd.

Daigo Fujimura

Takashi Hiyama

Takaaki Hase

Hiroshi Watanabe

Kazuya Nishimura

Tadayuki Hanada

Hiroyuki Yamamoto

Satoshi Hada

Kiyoshi Suenaga

Hideaki Sugishita

Eisaku Ito

Shunsuke Torii

Keita Takamura

Susumu Wakazono

Koichi Ishizaka

Hirokazu Hagiwara

Masaaki Matsuura

Kenji Umeda

Hitoshi Kitagawa

Katsuyuki Nakayama

Yuko Suenaga

Teruyuki Nagano

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

Aircraft gas turbine, and rotor blade of aircraft gas turbine

A turbine blade includes a blade body in which a suction side () facing one side in a circumferential direction and a pressure side () 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 (P), 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 (P), and a contact surface provided on both sides in the circumferential direction, and a reinforcing portion which protrudes from the outer circumferential surface.

Turbine moving blade and gas turbine

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 Athat 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.

Transition duct, turbine, and gas turbine engine

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.

Gas turbine for aircraft

A turbine is equipped with a turbine rotor (), a turbine casing, a turbine blade (), a turbine stator and a diffuser (A). The diffuser (A) is equipped with an inner cylinder () extending along an axis, an outer cylinder covering the inner cylinder () from an outer circumferential side and forming an exhaust flow path (C) between the inner cylinder () and the outer cylinder. The inner cylinder () is equipped with an inclined surface () 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 () is disposed to intersect an extension () obtained by extending platforms () of a plurality of turbine blades () to the other side in the direction of the axis, in a cross sectional view including the axis.

Turbine and gas turbine

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

Shroud, blade member, and rotary machine

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.

Turbine blade and gas turbine

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.

Cooling structure for turbine, and gas turbine

A blade cooling structure of a gas turbine, which can reduce the pressure loss of a cooling medium without decreasing the heat transfer coefficient, is provided. The blade cooling structure comprises a cooling passage () for flowing cooling air (A) from a proximal end portion () toward a blade portion () of a moving blade (), a plurality of turbulators () arranged, on both wall surfaces of the cooling passage () opposing each other, in such a manner as to be inclined with respect to the flowing direction of the cooling air (A), and a plurality of dimples () formed in a downstream region (N) downstream of a center position (O) in the flowing direction of the cooling air (A) on the wall surface of the cooling passage () between the adjacent turbulators ().

Blade cooling structure of gas turbine

In a nuclear reactor internal structure, generation and promotion of object-downstream separating vortices are suppressed so that coolant uniformly flows in a reactor core and pressure loss of flow of the coolant is reduced so that the flow of the coolant is stabilized. A lower connecting platearranged in a lower plenumcomprises a ring portionin which an arcuate portionand a cut-off portion are alternately formed. An outer peripheral portion of the ring portionis asymmetric relative to a flow direction of main flow and also asymmetric relative to a separating flow generation direction.

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Tokyo, Japan

Daigo Fujimura