Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

Tomo Kawakami

Kenji Miyamoto

Keisuke Miura

Shinichi Fukuba

Keijiro Saito

Kenta Taniguchi

Shinji Akamatsu

Satoshi Takiguchi

Kiyoshi Fujimoto

Masumi Nomura

Kotaro Miyauchi

Tomohiro Asai

Kozo Toyama

Katsunori Tanaka

Koichi Nishida

Sosuke Nakamura

Kei Inoue

Hideki Haruta

Katsuyoshi Tada

Hiroyuki Iba

Eiji Takami

Issei Tamura

Kuniharu Fujibayashi

Taku Egawa

Zhi Zhang

Hiroaki Nagahashi

An operation method for a gas turbine according to at least one embodiment of the present disclosure is an operation method for a gas turbine, including: a step of increasing a co-firing ratio of first fuel the co-firing ratio of which is to be increased and second fuel different from the first fuel. The step of increasing the co-firing ratio includes changing at least either of a turbine inlet temperature or a change rate of the co-firing ratio based on information regarding a relationship between the turbine inlet temperature and the co-firing ratio.

Operation method for gas turbine and control device for gas turbine

A gas turbine combustor according to at least one embodiment, includes: a less combustible fuel flow control part for controlling, independently of each other, amounts of less combustible fuel supplied to a first fuel injector and a second fuel injector; a highly combustible fuel flow control part for controlling, independently of each other, amounts of highly combustible fuel having a higher combustion speed than the less combustible fuel and supplied to the first fuel injector and the second fuel injector; and a controller configured to control the less combustible fuel flow control part and the highly combustible fuel flow control part such that a relative ratio of a first ratio of the highly combustible fuel to whole of first fuel injected by the first fuel injector and a second ratio of the highly combustible fuel to whole of second fuel injected by the second fuel injector changes according to an operating condition of a gas turbine.

Gas turbine combustor with less combustable fuel and highly combustible fuel ratio control

A combustor of the present disclosure includes a combustor plate configured to have a downstream end face perpendicular to a combustor axis; a nozzle segment configured such that a plurality of first nozzles that inject a premixed gas of air and fuel from a side of the downstream end face are collectively disposed; and a plurality of second nozzles configured to inject the fuel from the downstream end face. A plurality of the nozzles segments are provided at intervals in a direction perpendicular to the combustor axis. Each of the second nozzles injects the fuel from a dividing region between the nozzle segments on the downstream end face.

Combustor and gas turbine

A burner assembly includes a plurality of burners for mixing fuel and air. Each of the plurality of burners includes: at least one fuel nozzle for injecting the fuel; and a mixing passage into which the fuel injected from the at least one fuel nozzle and the air are introduced. Each of the at least one fuel nozzle includes a protruding portion protruding upstream of an inlet of the mixing passage in a flow direction of the air. Each of the at least one fuel nozzle includes at least one fuel injection hole formed on a side surface of the protruding portion. A top surface of the protruding portion includes a convex curved surface.

Burner assembly, gas turbine combustor, and gas turbine

A combustor includes: a tube plate having an upstream side end face and a downstream side end face that are orthogonal to a combustor axis, in which an air hole passing through the upstream side end face and the downstream side end face is formed in the tube plate; and a fuel injector that injects fuel into air passing through the air hole. The air hole has: a bent channel that curves toward a direction orthogonal to the combustor axis toward the downstream side; and an inclined channel that is connected to the downstream side of the bent channel so as to be continuous therewith, and that extends inclining with respect to the combustor axis and opens to the downstream side end face. A fuel injection position at which the fuel injector injects fuel is located on the downstream side of the upstream end of the bent channel.

A burner assembly includes a plurality of burners for mixing fuel and air. Each of the plurality of burners includes: a fuel nozzle for injecting the fuel; a mixing passage supplied with the fuel and the air; and a support portion connecting a passage wall of the mixing passage and the fuel nozzle to support the fuel nozzle.

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 fuel nozzle for a gas turbine combustor includes: an internal cylinder; a burner cylinder concentrically provided on the outer circumference of the internal cylinder in the vicinity of its distal end to surround the distal end portion of the internal cylinder; an air passage provided between the burner cylinder and the internal cylinder for delivering combustion air; a space provided at an axial center of the internal cylinder and extending in the axial direction of the internal cylinder; a plurality of inner passages provided at approximately equal intervals in the circumferential direction of the internal cylinder for injecting fluid through its distal end portion; and at least one communication portion provided on the upstream side of the distal end portion of the internal cylinder and extending from the outer wall of the internal cylinder toward the inner side in the radial direction to communicate with the space.

Fuel nozzle, gas turbine combustor with the same, and gas turbine with the same

A gas turbine controller having a first generator for setting the flow rate of fuel or air being supplied to a combustor in correspondence with a target load, a sensor for detecting intake temperature of a compressor, a second generator for setting a correction amount of a set value of fuel flow rate or air flow rate based on the value detected by the sensor, a third generator for setting a modification amount of the correction amount while taking account of the target load, a first multiplier for operating a modified correction amount from a correction amount set by the second generator and a modification amount set by the third generator, and a second multiplier for calculating the flow rate of fuel or air being supplied to a combustor by adding the modified correction amount to the set value of fuel flow rate or air flow rate.

Gas turbine control device

A gas turbine control apparatus, etc. are provided by which combustion fluctuation, even if arising in plural frequency bands, can be effectively suppressed. If the combustion fluctuation arises in plural frequency bands, corresponding to a predetermined priority order, adjustment is done so that the combustion fluctuation of the frequency band of a high priority order is suppressed. If the gas turbine state changes after the adjustment, this is reflected on a data base. If no sufficient data is stored yet in the data basefor any the reason, such as immediately after installation of the gas turbine, correction is made using data of countermeasures based on data of another same type gas turbine contained in a basic data base 31 and data of countermeasures based on experiences of skilled adjusting operators contained in a knowledge data base. Also, in a stabilized operation, operation condition may be varied so that an optimal operation condition is automatically searched.

Growing community of inventors

Tokyo, Japan

Tomo Kawakami