Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

Renesas Electronics Corporation

Mitsubishi Heavy Industries Aero Engines, Ltd.

Yoshiyuki Okabe

Masato Araki

Yoshiko Oya

Yoshinori Tanaka

Shinya Hashimoto

Shin Nishimoto

Hidekazu Uehara

Kazuyuki Matsumoto

Yoshihiro Kuwamura

Hiroharu Oyama

Toshinori Imai

Tsuyoshi Fujiwara

Keita Takamura

Tadayuki Hanada

Koichiro Iida

Koichi Ishizaka

Kazufumi Ikeda

Takeshi Saikawa

Hitoshi Kitagawa

Shigenari Horie

Ryosuke Mito

Yoshinori Kawasaki

Mitsuhiro Toya

Shunji Mori

A gas turbine includes a rotor that has a rotor disk at each of a plurality of stages and a plurality of blades fixed to the respective stages, a casing, a plurality of vanes fixed to the casing, and an annular member fixed to a radially inner side of each of the vanes. The rotor disk has a seal arm. The annular member has an outer opposing portion that is radially opposed to the seal arm. The gas turbine further includes a seal fin that protrudes from the outer opposing portion toward the seal arm, a first cavity that is defined in the annular member and extends in a circumferential direction to straddle at least two of the vanes, a second cavity that is on a radially inner side of the first cavity, and a plurality of compressed air discharge paths that connect the first cavity to the second cavity.

Gas turbine

A compressor rotor includes a first outer cavity formed in a rotor main body and into which air on a high-pressure side of blades is to be introduced, a first inner cavity formed in the rotor main body on an inner side in a radial direction of the first outer cavity; and a first communication passage which connects the first outer cavity and the first inner cavity to each other in the radial direction of the first outer cavity. Along an entire length of the first communication passage from the first outer cavity to the first inner cavity, the first communication passage is inclined toward a forward side of a rotation direction of the rotor main body.

Compressor rotor, compressor and gas turbine

A gas turbine includes a compressor, a combustor, and a turbine. The compressor, the combustor, and the turbine are arranged along an extending direction of a rotating shaft. The gas turbine also includes a combustor casing housing the combustor and a turbine casing housing the turbine. The combustor casing and the turbine casing are joined to each other via respective flanges thereof projecting toward the outside. The gas turbine further includes a projection part on an inner face of the combustor casing. The projection part projects toward the inside in a radial direction in at least part of a range in the extending direction of the rotating shaft between the flanges and an end of a combustion chamber on the compressor side in the combustor.

Gas turbine combustor casing having a projection part

A rotary machine includes a seal device capable of restricting a flow of a fluid in a clearance between a stationary member and a rotational member. The seal device includes a pressure loss element mounted to the stationary member, a first non-contact type seal protruding from the rotational member toward the pressure loss element and facing the pressure loss element via a first gap, and a second non-contact type seal protruding from the stationary member toward the rotational member, facing the rotational member via a second gap, and being positioned on one side of the pressure loss element in a flow direction of the fluid. The seal device also includes a contact type seal protruding from the stationary member toward the rotational member and being disposed downstream of the pressure loss element and the second non-contact type seal in the flow direction of the fluid.

Rotary machine with seal device

A sealing apparatus includes a sealing portion configured to be positioned between a platform of a turbine blade and an inner shroud of a turbine vane of a turbine, and an acoustic damper having a closed space portion which is configured to communicate, via an opening, with a disc cavity configured to be positioned between the turbine blade and the turbine vane.

Sealing apparatus for gas turbine, gas turbine, and aircraft engine

A rotary machine includes turbine moving blades (); a casing () covering the turbine moving blades () so as to define a gap at an outer circumferential side of the turbine moving blades; a leaf seal () having a seal body () that is disposed in the gap so as to protrude radially inward from the casing () and is capable of coming into contact with the turbine moving blades (), and a high-pressure-side plate member () that is disposed along a face facing a high pressure side of the seal body (); and a swirling flow inhibitor () that is provided on the high pressure side of the leaf seal () in the gap and inhibits a swirl flow flowing through the gap in a circumferential direction.

Rotary machine

Provided is a technology capable of reducing parasitic capacitance of a capacitor while reducing the space occupied by the capacitor. A stacked structure is obtained by forming, over a capacitor composed of a lower electrode, a capacitor insulating film and an intermediate electrode, another capacitor composed of the intermediate electrode, another capacitor insulating film and an upper electrode. Since the intermediate electrode has a step difference, each of the distance between the intermediate electrode and lower electrode and the distance between the intermediate electrode and upper electrode in a region other than the capacitor formation region becomes greater than that in the capacitor formation region. For example, the lower electrode is brought into direct contact with the capacitor insulating film in the capacitor formation region, while the lower electrode is not brought into direct contact with the capacitor insulating film in the region other than the capacitor formation region.

Semiconductor device, RF-IC and manufacturing method of the same

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Tokyo, Japan

Yoshiyuki Okabe