Mitsubishi Heavy Industries Aero Engines, Ltd.

Mitsubishi Hitachi Power Systems, Ltd.

Takaaki Hase

Tadayuki Hanada

Daigo Fujimura

Hirokazu Hagiwara

Hiroshi Watanabe

Satoshi Tanimura

Yoshihiro Kuwamura

Tetsu Konishi

Taiki Kinoshita

Satoshi Mizukami

Hikaru Kurosaki

Yoshiaki Yamaguchi

Masaki Mitani

Hiroshi Makigano

Osamu Morii

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

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 cylinder for a combustor includes a cylindrical member, a first cooling passage defined in the cylindrical member and a second cooling passage defined in the cylindrical member, and a supply port extender. The first cooling passage includes a supply port that opens to an outer peripheral surface of the cylindrical member. The second cooling passage includes a discharge port that opens to the outer peripheral surface of the cylindrical member downstream of the supply port. The supply port extender includes a first wall that is disposed between the supply port and the discharge port and extends away from the outer peripheral surface of the cylindrical member and a second wall that is disposed upstream of the supply port and extends away from the outer peripheral surface of the cylindrical member.

Cylinder for combustor, combustor, and gas turbine

A gas turbine includes downstream side members that face a passage and have guide faces arranged in the passage side as it goes toward the upstream side. In a cross section including an axis center of a rotor shaft extending in a flow direction of a gas main stream, extension sections of the guide faces continuing to the upstream end portion of the guide faces are arranged downstream from the cavity inner wall portion of the upstream side member facing the cavities.

Gas turbine

Growing community of inventors

Komaki, Japan

Takaaki Hase