Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

Masato Araki

Hidekazu Uehara

Tanehiro Shinohara

Keita Takamura

Yoshiyuki Okabe

Takashi Nakano

Shinya Hashimoto

Shin Nishimoto

Junichiro Masada

Tatsuji Takahashi

Junichi Kobayashi

Shingo Ito

Kenichi Arase

Masanori Yuri

Hitoshi Morimoto

Yoshifumi Iwasaki

Makoto Kishi

Keizo Tsukagoshi

Yukihiro Hashimoto

Kazufumi Ikeda

Kunihiko Waki

Hitoshi Kitagawa

Ryosuke Mito

Keita Fujii

Yuji Komagome

Yoshiko Oya

Kwin Malhotra

Naoki Sakagami

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 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 rotor shaft has: an inlet flow passage through which gas inside a gas compression flow passage flows into an outer cavity of a downstream-side cavity group; a radial flow passage that provides communication between the outer cavity and an axial communication cavity of the downstream-side cavity group; an axial flow passage that provides communication between the axial communication cavity of the downstream-side cavity group and the axial communication cavity of an upstream-side cavity group; another radial flow passage that provides communication between the axial communication cavity and the outer cavity of the upstream-side cavity group; and an outlet flow passage through which the gas inside the outer cavity of the upstream-side cavity group flows out into the gas compression flow passage.

Compressor rotor, compressor, and gas turbine

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 characteristic evaluation device is for a gas turbine that includes a compressor, a combustor, and a turbine includes a processor. The processor calculates, in gas-turbine characteristics including characteristics of at least one of the compressor, the combustor, and the turbine, a correction value for correcting influence due to environmental conditions in which the gas turbine is placed based on operation data of the gas turbine. The processor also calculates the gas-turbine characteristics corrected based on the correction value, and evaluates the gas turbine by comparing the gas-turbine characteristics after correction with a predetermined reference value.

Characteristic evaluation device for gas turbine and characteristic evaluation method for gas turbine

In a seal member, a turbine, and a gas turbine, a plurality of vanes includes a vane main body extending in a radial direction of an axis, an outer shroud, an inner shroud and forming a main flow path of a combustion gas between the outer shrouds and the inner shroud, and a retainer protruding from an inner surface in the radial direction of the inner shroud to the inside in the radial direction. The retainers in the vanes, which are adjacent to each other in the circumferential direction, are adjacent to each other in the circumferential direction via a third gap, and relative to one end of the seal member, the other end is positioned downstream in a direction along the axis in the combustion gas to close the third gap.

Seal member, turbine, and gas turbine

A shaft seal structure capable of preventing a seal body of the shaft seal structure of a rotation body from being held in an inclined posture even when the seal body is inclined is provided. It includes, an accommodation body (), a seal body () including thin plate seal pieces (), and a plate body () covering one end in the axial direction () of the seal body (). A recessed portion () recessing in the axis direction, and a protruding portion projecting to the other side from the recessed portion () are formed on one of the plate surface () of the plate body () and the inner wall surface () of the accommodation body (). When the protruding portion abuts the other side and a pocket (X), the recessed portion () communicates with the pocket (X) and the fluid low pressure region.

Shaft seal mechanism and rotary machine provided with same

In this method of preventing deformation in a turbine casing of a gas turbine, in a turbine casingthere is arranged a buffer tank. In this buffer tankthere are formed a stagnation part agitation air openingwhich ejects part of the air from an air compressoras stagnation part agitation air Gatoward a stagnation partwithin the turbine casing, and an overall agitation air openingwhich ejects overall agitation air Gafor agitating gas held in an upper space within the turbine casing. In the buffer tankthere is provided a partition wallwith through holesformed therein serving to resist air from the air compressor, in order to make the ejection speed of the overall agitation air lower than the ejection speed of the stagnation part agitation air.

Method of preventing deformation in gas turbine casing, purging device for executing this method, and gas turbine provided with this device

An inner wall surface of a low-pressure-side side plate opposite to a lateral surface of a thin plate is formed along a direction crossing an axial direction of a rotating shaft such that a gap between the inner wall surface and the thin plate gradually decreases from a radially inner side toward a radially outer side of the low-pressure-side side plate.

Shaft seal mechanism

A shaft sealing device is provided in an annular space between a rotor and a stator surrounding an outer periphery of the rotor, and divides the annular space in the direction of an axis of the rotor into a high-pressure region and a low-pressure region. The shaft sealing device includes a seal body obtained by stacking a plurality of thin plate sealing pieces in a circumferential direction of the rotor; and a high-pressure side plate that extends from the stator toward the radial inner side so as to run along the high-pressure side of the seal body, and is segmented into a plurality of portions in the circumferential direction, and includes a rigidity imparting member configured to impart rigidity in the direction of the axis to a portion of the surface of the high-pressure side plate that faces the high-pressure region.

Shaft sealing device and rotating machine comprising same

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Tokyo, Japan

Masato Araki