Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

Mitsubishi Power, Ltd.

Kotaro Miyauchi

Shinji Akamatsu

Koichi Nishida

Keijiro Saito

Satoshi Takiguchi

Toshihiko Saito

Kenji Miyamoto

Shigemi Mandai

Hideki Haruta

Masataka Ota

Masumi Nomura

Taiki Kinoshita

Koichi Akagi

Rintaro Chikami

Tomo Kawakami

Yoshichika Sato

Shuhei Kajimura

Kazuya Kobayashi

Yoji Kochi

Katsunori Tanaka

Satoshi Tanimura

Tatsuo Ishiguro

Kiyoshi Fujimoto

Kenta Taniguchi

Keisuke Matsuyama

Sosuke Nakamura

Kei Inoue

Makoto Kishi

Susumu Wakazono

Kenji Sato

Satoshi Mizukami

Kozo Toyama

Kentaro Tokuyama

Hiroaki Kishida

Kazushige Takaki

Atsushi Yuasa

Mitsuru Inada

Hisashi Nakahara

Hiroyuki Sakaki

Mitsunori Isono

Yoshinori Wakita

Kohei Hidaka

Issei Tamura

Scott Cloyd

Kuniharu Fujibayashi

Brandon Ruiz

Bob Provitola

Yuta Hitomi

Takahiko Sakaki

A tail pipe () comprises: a pipe (); an acoustic attenuator () that forms an acoustic space (Ss) on the outer peripheral side of the pipe (); and a cooling air jacket () that forms a cooling air space (Sa) isolated from the outer space (So), which is the space on the outer peripheral side of the pipe (). The pipe () has: a first air flow path () that is formed between the outer peripheral surface () and the inner peripheral surface (); and an acoustic hole () that penetrates from the acoustic space (Ss) to a combustion space (Sc), which is a space on the inner peripheral side of the pipe (). The first air flow path () has: an inlet () that faces into the cooling air space (Sa) and guides the air in the cooling air space (Sa) into the first air flow path (); and an outlet () that faces into the acoustic space (Ss) and guides the air passing through the first air flow path () into the acoustic space (Ss).

Transition piece, combustor, gas turbine, and gas turbine equipment

A combustion control device including a bleed valve control unit for controlling a bleed valve disposed on a bleed pipe for performing bleeding so that a part of the compressed air flowing into the casing is not used as combustion air in the combustor, a fuel control unit for controlling a fuel regulating valve for regulating a fuel flow rate of fuel supplied to the combustor, and a temperature acquisition unit. Upon reception of a load rejection signal for cutting off a load from the gas turbine, the bleed valve control unit controls a valve opening degree of the bleed valve from a closed state to an open state with a prescribed opening degree, and the fuel control unit controls the fuel regulating valve such that the acquired flame temperature falls within a predetermined temperature range defined by an upper limit value and a lower limit value.

Combustion control device for gas turbine, combustion control method, and program

A fuel control device includes a stem fuel valve opening degree determination unit, a branch line flow rate determination unit, and a correction value determination unit. The stem fuel valve opening degree determination unit is configured to determine an opening degree of a flow rate adjustment valve of a stem fuel supply line. The branch line flow rate determination unit is configured to determine an opening degree of a flow rate adjustment valve of at least one branch line. The correction value determination unit is configured to determine a correction value of the opening degree of the flow rate adjustment valve of the at least one branch line based on a value of a pressure difference between a fuel pressure upstream of a nozzle connected to the at least one branch line and a corrected fuel pressure for a fuel pressure at an outlet.

Fuel control device, combustor, gas turbine, fuel control method, and program

A gas turbine combustor provided with: a plurality of swirler tubes that are disposed inside a combustor basket and impart a swirl to a premixed gas, the premixed gas being obtained by premixing a fuel and air for combustion; and an outer ring that is disposed between the plurality of swirler tubes and the combustor basket with a gap provided between the outer ring and the combustor basket, and generates film-shaped air inside a combustor transition piece connected to the combustor basket via injection through the gap into the combustor transition piece, and at a downstream end of the outer ring, the outer ring includes a tapered surface formed such that the outer ring gradually decreases in thickness from an upstream side toward a downstream side.

Gas turbine combustor

A combustor includes a nozzle, a burner cylinder surrounding the outer circumference of the nozzle, and an outside flow path cylinder surrounding the outer circumference of a downstream end portion of the burner cylinder. A purge air flow path through which air flows is formed between the inner circumferential side of the outside flow path cylinder and the outer circumferential side of the burner cylinder. A tapered surface is formed in the downstream end portion of the burner cylinder such that the plate thickness of a burner cylinder-forming plate that forms the burner cylinder gradually thins toward the downstream side.

Combustor and gas turbine comprising same

A combustor () includes: a fuel nozzle configured to inject fuel; a tubular body () having a tubular shape in which a combustion region through which combustion gas flows is formed inside, and in which a plurality of slits () are formed extending in the circumferential direction at intervals in the circumferential direction; and throttle pieces () which are fitted into the slits (), project radially inward from the inner circumferential side of the tubular body (), and have a throttle face that extends along the flow direction of the combustion gas as it extends from the radially outer side inward.

Combustor and method for improving combustor performance

A combustion apparatus includes a nozzle in which a fuel injection port for injecting a fuel is formed on the center of a tip. A plurality of water injection ports are formed with intervals therebetween in a circumferential direction around the fuel injection port of the tip of the nozzle, and the water injection ports are non-uniformly formed in the circumferential direction.

Nozzle, combustion apparatus, and gas turbine

A combustor includes fuel nozzles that extend in an axial direction of a combustor main body and are capable of injecting fuel from injection holes on a combustion chamber side. The combustor includes a phase adjusting unit which partially changes a flow path cross-sectional area of at least one of the fuel nozzles in the axial direction such that phases of flow rate fluctuation of fuel do not match with respect to at least two of the fuel nozzles.

Combustor and gas turbine with phase adjusting units in the fuel nozzles

A fuel spray nozzle provided with: a liquid fuel channel (), which is a channel for liquid fuel; a liquid fuel injection hole (), which is a hole for communicating the liquid fuel channel () and the inside of a combustion burner, and injecting the liquid fuel into the combustion burner; an additive channel (), which is a channel for an additive; and an additive injection hole (), which is a hole for communicating the additive channel () and the inside of the combustion burner, and injecting the additive into the combustion burner at an angle at which the additive collides with the liquid fuel injected from the liquid fuel injection hole ().

Fuel spray nozzle

A combustor is equipped with a burner case, and a base plate spreading from a downstream end of the burner case in a radial direction. The base plate defines a purging air space at an upstream side of the base plate. The combustor includes a purging air flow passage configured to inject purging air in the purging air space to a downstream side relative to the base plate. An outflow opening of the purging air flow passage is defined within at least one of a radial range from an inner circumferential surface of the burner case and an axial range from the downstream end of the burner case.

Combustor and gas turbine having the same

A cylinder of a combustor includes a cylinder body inside of which combustion gas flows, a jacket plate that covers the cylinder body from the outside and forms a fluid space into which high-pressure fluid flows between an inner peripheral surface of the jacket plate and an outer peripheral surface of the cylinder body, and a rib that connects the cylinder body and the jacket plate. The rib is connected to the cylinder body by a cylinder side end portion on the cylinder body side in a radial direction with respect to an axis of the cylinder body being welded from both sides in an axial direction of the axis. The rib is connected to the jacket plate by a jacket side end portion on the jacket plate side in the radial direction being welded from both sides in the axial direction.

Cylinder of combustor, method of manufacturing of cylinder of combustor, and pressure vessel

A combustor includes: a combustor basket configured to surround a fuel nozzle from an outer circumferential side, and a plurality of connecting members formed in a circumferential direction at intervals to connect a rear end of the combustor basket and a casing and configured to define a flow path through which compressed air introduced into the combustor basket flows. A circulation direction of the compressed air flowing through the flow path is configured to be reversed at a rear end of the combustor basket and the compressed air is introduced into the fuel nozzle. The flow path is partially or entirely inclined in the circumferential direction to blow the compressed air.

Combustor and rotating machine

A gas turbine including a combustion oscillation suppressing device disposed to a transition piece of a combustor to define a gas space S, and having a plurality of vent holes through which a gas space L and the inside of the transition piece communicate. The combustion oscillation suppressing device is formed of a first member and a second member which define the gas space, the second member having the plurality of vent holes, and a portion of a transition piece wall includes the second member. A distance from the second member to the first member in the radial direction of the transition piece is a height of the gas space, and when the height of the gas space varies along an axial direction of the transition piece, an opening ratio &#x3c3;p of each of the plurality of vent holes is adjusted depending on the height of the gas space.

Gas turbine having a combustion oscillation suppressing device

It is required for a gas turbine combustor to exhaust low NOx. The gas turbine combustor is provided with a combustion tube which has a cooling passage through which cooling air flows in a double wall structure. The cooling passage has a main cooling air supply opening opened to a side of a combustion zone. The cooling air supplied from the main cooling air supply opening is guided to a direction along an inner wall surface of the combustion tube by a guide. The cooling air flows through the cooling passage inside the combustion tube, and then is reused for film cooling along the inner wall surface. Thus, it is possible to save cooling air. Therefore, a more part of the air supplied from a compressor can be used as air for combustion and it becomes possible to exhaust low NOx.

Cooling structure of gas turbine combustor

A gas turbine control device having a gas turbine control unit for the gas turbine operation control that computes adjustment increments regarding at least one of the airflow rate into the combustor and the pilot ratio, and makes revisions to the actuating variables comprising the airflow rate and the pilot ratio so that the actuating variables are contrasted with the status signals and the variables are modified toward initial design conditions. The gas turbine control unit resets the revisions made to the actuating variables in a case where the level of the combustion vibration is restrained below the predetermined control criterion for a predetermined time span, and the gas turbine is operated under the control settings of the initial design stage.

Gas turbine control method and device

Growing community of inventors

Yokohama, Japan

Kotaro Miyauchi