Mitsubishi Heavy Industries Limited

Mitsubishi Jukogyo Kabushiki Kaisha

Mitsubishi Hitachi Power Systems, Ltd.

Mistubishi Heavy Industries, Ltd.

Shigemi Mandai

Wataru Akizuki

Katsunori Tanaka

Keijirou Saitoh

Koichi Nishida

Satoshi Tanimura

Shinji Akamatsu

Masataka Ohta

Hideki Haruta

Kiyoshi Suenaga

Kuniaki Aoyama

Mitsuru Inada

Yutaka Kawata

Satoshi Takiguchi

Kenji Sato

Masaki Ono

Kotaro Miyauchi

Eiji Akita

Kazufumi Ikeda

Ichiro Fukue

Tatsuo Ishiguro

Keijiro Saito

Koichi Akagi

Rintaro Chikami

Satoshi Hada

Hideaki Sugishita

Takashi Kawano

Eisaku Ito

Keisuke Matsuyama

Ryotaro Magoshi

Masataka Ota

Tetsuo Gora

Yoshichika Sato

Kazuya Kobayashi

Hiroyuki Nishida

Hitoshi Kawabata

Nobuo Sato

Teruya Tachibana

Kouichi Nishida

Yoji Kochi

Satoshi Mizukami

Kouichi Akagi

Hidetaka Mori

Atsushi Maekawa

Atsushi Yuasa

Masaharu Nishimura

Mitsuru Kondo

Masaaki Matsuura

Jun Kubota

Yoshiaki Tsukuda

Masahito Kataoka

Mitsunori Isono

Hikaru Katano

Mitsuo Hasegawa

Yoshikuni Kasai

Hisato Arimura

Yuichiro Kimura

Keijiro Saitoh

Teruhiro Matsumoto

Tomohisa Takasaki

Nobuo Satoh

Hisanari Nakajima

Jyunji Hashimura

Hidenobu Tamai

Satoshi Sometani

Hidemi Niinai

Soichiro Tomimoto

Takehiko Shimizu

Masahiro Kamogawa

An object is to realize combustion flame which can further reduce the amount of NOx generation. A combustor () includes a pilot nozzle (); a plurality of main nozzles () arranged apart from the pilot nozzle () in the circumferential direction on the outer peripheral side of the pilot nozzle () and configured to perform premix combustion; a combustor basket () surrounding the pilot nozzle () and each main nozzle (); an outlet outer ring () provided at a tip end of the combustor basket (); and a combustion liner () fitted, at an inner surface thereof, onto the outer periphery of the combustor basket () and surrounding the outlet outer ring (). The outlet outer ring () is formed parallel to an inner wall surface () of the combustion liner ().

Combustor and gas turbine

A combustor () according to the invention includes: a combustor basket () in which compressed air and fuel are mixed with each other and the mixture is combusted; a transition piece () in which a tip portion of the combustor basket () is inserted with a gap (C) therebetween; a spring clip () that seals the gap between the combustor basket () and the transition piece (); a throttle section () that is provided in an opening portion (Ck) of the gap (C) that is opened to the transition piece () on the tip side of the combustor basket (), and narrows an opening area of the opening portion (Ck), compared to the base end side; and cooling device () for cooling the throttle section ().

Combustor and gas turbine provided with same

A gas turbine combustor includes: an external cylinder (); an inner cylinder () provided inside the external cylinder () to form an air passage () between the external cylinder () and the inner cylinder (); a pilot nozzle () provided in a center part of the inner cylinder () along a direction of a combustor axis (S); a plurality of main nozzles () provided on an inner peripheral surface of the inner cylinder () along a circumferential direction thereof so as to surround the pilot nozzle (), the plurality of main nozzles () premixing fuel with combustion air introduced to the air passage () and ejecting the fuel into the inner cylinder (); and a top hat nozzle () provided inside the air passage () across a circumferential direction to mix fuel with the combustion air prior to reaching the plurality of main nozzles ().

Gas turbine combustor with top hat nozzle arrangements

A combustor includes a combustion chamber and an acoustic liner, wherein through-holes through are formed in a wall of the combustion chamber, a plurality of rows of the through-holes is arranged in a lengthwise direction of the combustor, the through-holes of a first through-hole row are shifted with respect to the through-holes of a second through-hole row so that centers of the through-holes of the first and second through-hole rows adjacent each other are staggered in the circumferential direction, cooling grooves are formed so as to avoid the through-holes inside that is sandwiched between the outer peripheral surface and the inner peripheral surface of the combustion chamber, and the cooling grooves include transverse cooling grooves extending in the circumferential direction between rows of the through-holes, and longitudinal cooling grooves extending in the lengthwise direction between the through-holes and connecting the transverse cooling grooves adjacent to each other.

Combustor with acoustic liner

In a gas turbine combustor and a gas turbine, an air passage () that supplies combustion high-pressure air, a pilot nozzle (), a main fuel nozzle (), and a top hat nozzle () that supply fuel, and openings () that supply film air (cooling air) are provided with respect to a combustor inner cylinder (), and contraction members (, and) are arranged along a circumferential direction on an inner wall surface in a downstream of a flow direction of combustion gas in the inner cylinder (). The contraction members (, and) are provided in a predetermined area in the circumferential direction excluding penetrating portions (, and), which do not disturb the flow of cooling air, thereby enabling to suppress generation of carbon monoxide and the like and to suppress the occurrence of unstable combustion.

Gas turbine combustor having contraction member on inner wall surface

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

Pilot fuel injected from fuel injection portsof a pilot nozzlebumps against an inner wall surface of a tapered portion of an inner circumference of a coneof a pilot cone. At this time, the position where a pilot fuel from the fuel injection portshits is located in a range from a middle of the tapered portion of the inner circumference of a coneto a downstream-side tip thereof.

Installation structure of pilot nozzle of combustor

A gas turbine combustor having an inner tube and a transition pipe connected together is provided. The combustor includes an internal swirler and an external swirler. The internal swirler is composed of a cylindrical inward swirler ring disposed concentrically with respect to a central axis of the inner tube, and a plurality of inward swirler vanes provided on an outer peripheral surface of the inward swirler ring. The external swirler is composed of a cylindrical outward swirler ring disposed on an outer peripheral side of the inward swirler vanes and concentrically with respect to the inward swirler ring, and a plurality of outward swirler vanes provided on an outer peripheral surface of the outward swirler ring. The internal swirler and the external swirler are disposed within the inner tube.

Combustor of gas turbine with concentric swirler vanes

A premixing nozzle includes swirler blades for agitating combustion air inside a nozzle body. Each one end of the swirler blades is fitted to the nozzle body, and the other end is connected to a hub, respectively. The tip portion of a fuel nozzle shaft is conical, and a part of the tip portion is arranged inside the hub. A combustion gas flows into the hub from a space between the tip portion of the fuel nozzle shaft and the upstream end of the hub, passes through between the tip portion and the inner peripheral surface of the hub, and flows toward the downstream of the hub.

Premixing nozzle, combustor, and gas turbine

A combustor for a gas turbine has an arrangement to form a layer of cooling-air on an inner surface of a liner of a combustion chamber. This layer of the cooling air extends from a fuel nozzle block of the combustor toward a downstream side with respect to the liner.

Gas turbine combustor

For the purpose of reduced NOx gas emission, a gas turbine engine comprises a cylinder having a combustion region inside of the cylinder; a resonator having a cavity and provided around the surface of the cylinder and sound absorption holes formed on the cylinder and having opening ends on the cylinder.

Gas turbine combustor, gas turbine, and jet engine

There is provided a combustor comprising a fuel nozzle which is comprised of a rodlike body which has a fuel passage and which is located in an air passage; a plurality of hollow members which are connected to the fuel passage and which extend in radial directions from the rodlike body into the air passage; at least one injection port formed in each hollow member to inject a fuel from the fuel passage into the air passage; and a projection which extends from a farmost inner wall of each hollow member that is most distant from an axis of the rodlike body to the injection port that is most distant from the axis. A hole for leaking fuel that is connected to an air passage may be formed in a farmost inner wall of the hollow member that is more distant from an axis of a rodlike body than the injection port that is most distant from the axis, or may be formed to be adjacent to all the injection ports on an upstream or downstream side in the direction of the airflow. Thus, a vortex does not occur in the hollow column.

Combustor containing fuel nozzle

There is provided a combustor to burn fuel, comprising a bypass passage connected to one side of the combustor to supply air into the combustor; and an annular passage provided around the combustor and connected to the bypass passage, wherein air supplied through the bypass passage passes in the annular passage in the circumferential direction, and is uniformly supplied into the combustor in the circumferential direction thereof through an opening which connects the combustor and the annular passage. Accordingly, compressed air passing through the bypass passage can be supplied uniformly into a tail portion of the combustor, and unevenness of temperature distribution in a cross section of the combustor tail portion can be reduced.

Gas turbine combustor having bypass and annular gas passage for reducing uneven temperature distribution in combustor tail cross section

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.

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Takasago, Japan

Shigemi Mandai