Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

Kazufumi Ikeda

Katsunori Tanaka

Masaki Ono

Satoshi Tanimura

Shigemi Mandai

Kuniaki Aoyama

Keisuke Matsuyama

Takanori Ito

Keizo Ohnishi

Kiyoshi Suenaga

Shinji Akamatsu

Masaharu Nishimura

Tatsuo Ishiguro

Shinichiro Watanabe

Masato Araki

Yutaka Kawata

Yoshiyuki Okabe

Yoshifumi Masuda

Toyosei Aota

Hitoshi Kitagawa

Mitsunori Isono

Tomonori Toda

Yasuhiko Ikegami

Hideto Kawashima

Hiroyasu Manako

Tei Yamato

Tetsuya Nagao

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

An injection device, a combustor, and a rocket engine include a device main body partitioned into a fuel manifold and an oxidant manifold, and a plurality of injectors arranged at predetermined intervals in the device main body to inject fuel and oxidant into a combustion chamber, each of the injectors includes a LOx channel including a proximal end portion communicating with the oxidant manifold and a distal end portion communicating with the combustion chamber, a restrictor provided on the proximal end portion of the LOx channel and a GHchannel including a proximal end portion communicating with the fuel manifold and a distal end portion communicating with the combustion chamber, and the restrictors have different shapes.

Injection device, combustor, and rocket engine with restrictors shaped to amplify predetermined pressure oscillation

An exhaust flue includes an exhaust chimney body, and an open end multi-hole area. The exhaust chimney body defines a passage for discharging exhaust gas. The open end multi-hole area is an area in which multiple holes are defined around a total circumference of an open end of the exhaust chimney body.

Exhaust flue

In a damping device according to the present invention, a damping deviceis mounted on a bypass pipethat supplies an amount of high-pressure air to a combustor transition piece. The damping deviceincludes a fluid introducing unitthat forms a fluid introduction space B by covering an outer peripheral portion of the bypass pipe, a plurality of acoustic boxesandthat forms resonance spaces Da and Db with the base portions connected to the fluid introducing unitand the end portions extending along the outer peripheral portion of the bypass pipein the circumferential direction, and partition platesandthat form resonance ducts Ea and Eb of a predetermined length by partitioning the resonance spaces Da and Db.

Damping device and gas turbine combustor

In order to realize a stable decrease in NOx, a gas turbine combustor is supplied which can reduce combustion vibration. A combustor () is provided with a first box body (), which is installed outside an object body () such as a combustor basket (), a transition piece () or a bypass duct () so as to form a first internal space () having a predetermined capacity; and a first throat () having a predetermined length which has one end () open to a side wall () of the object body () and has the other end () open to a first internal space (); wherein, a first resistive element () having a multiple number of through-holes is inserted and engaged to one end (). Fluid particles serving as vibration elements of combustion vibration caused in a combustion region are effectively trapped by the first resistive element () and at the same time resonate with the air of the first internal space () being connected through the first throat () and vibrate in the neighborhood of the first resistive element (), thereby damping vibration amplitude thereof.

Gas turbine combustor and a gas turbine equipped therewith

A gas turbine combustor includes a combustion liner in which a combustion region is formed; and a housing provided for a wall of the combustion liner in a predetermined circumferential region of the combustion liner to form a resonance space between the combustion liner and the housing. The combustion region and the resonance space are connected by a plurality of combustion liner through-holes, and a circumferential length of the housing is longer than a diameter of the combustion liner.

Gas turbine combustor

The objective is to provide a gas turbine and the combustor thereof in which super high frequency combustion oscillation and the generation of NOx are reduced. The fluctuation in pressure which induces the fluctuation in heat liberation is suppressed in the gas turbine combustor comprising a plurality of main fuel supply nozzles, each having a premixing nozzle at the top end part thereof, by providing in the space upstream from the premixing nozzles partition elements for dividing the space along the axis of the combustor or a honeycomb element having air passages in the axial direction, or by providing premixing nozzles composed of cylindrical elements with many holes.

Gas turbine and the combustor thereof

A gas turbine combustor in which a part or all of the wall of the combustor disposed within an intake chamber is formed as an acoustic energy absorbing member that can absorb the acoustic energy of a combustion variation generated within the combustor. The acoustic energy absorbing member is constructed of a thin corrugated plate in a circumferential direction, a high-temperature-proof perforated material, or a back plate disposed at the outside of a perforated plate in a radial direction with a distance from the perforated plate. It is also possible to provide a covering member at the outside of the acoustic energy absorbing member in a radial direction, for covering the acoustic energy absorbing member with a distance from the acoustic energy absorbing member. It is preferable that the acoustic energy-absorbing member and/or the covering member are reinforced with a frame that extends in a circumferential direction and/or a longitudinal direction.

Gas turbine combustor having an acoustic energy absorbing wall

A gas turbine combustor includes a side wall, for defining a combustion volume, having upstream and downstream ends, a pilot nozzle, disposed adjacent the upstream end of the side wall, for discharging a pilot fuel to form a diffusion flame in the combustion volume, and a plurality of main nozzles, provided around the pilot nozzles, for discharging a fuel-air mixture to form premixed flames in the combustion volume. Film air is supplied into the combustion volume downstream of the main nozzles along the inner surface of the side wall to reduce the fuel-air ratio in a region adjacent the inner surface of the side wall and to restrain a combustion-driven oscillation in the combustion volume.

A gas turbine combustion device comprises a plurality of combustion devices. Each combustion device has an inner cylinder and a tail cylinder in a vehicle chamber. An acoustic sleeve is provided between each inner cylinder and a corresponding outer cylinder in the vehicle chamber. An acoustic coupling effect with a vehicle chamber can be reduced.

Gas turbine combustion device

In a noise measuring system comprising a microphone array and a directivity forming section for controlling the direction of directivity of the microphone array, the directivity forming section includes delay section and adding section, and the optimal value of a delay time of the delay section is set in such a manner that a noise isolation characteristic for causing any mobile noise generator not targeted for noise measurement to come off a directional plane or a directional line formed in the direction of directivity of the microphone array and a deterioration characteristic of the directivity of the microphone array balance with each other.

Growing community of inventors

Hyogo, Japan

Kazufumi Ikeda