Mitsubishi Heavy Industries Limited

Mitsubishi Hitachi Power Systems, Ltd.

Wataru Akizuki

Katsunori Tanaka

Shigemi Mandai

Yoshifumi Iwasaki

Koichi Nishida

Keijirou Saitoh

Keisuke Yamamoto

Shinichi Yoshioka

Takashi Sonoda

Akihiko Saito

Ryuji Takenaka

Fuminori Fujii

Hideki Haruta

Hisashi Nakahara

Koji Takaoka

Ryoichi Haga

Yuji Komagome

Isamu Matsumi

Sadao Minagawa

Noriyoshi Uyama

Naohiro Sumimura

Shinji Akamatsu

Kuniaki Aoyama

Masataka Ohta

Masaaki Matsuura

Masahito Kataoka

Yoshikuni Kasai

Teruya Tachibana

Hisanari Nakajima

Jyunji Hashimura

A fuel control device includes a combustion temperature estimation value calculation unit that calculates a temperature estimation value when a mixture of fuel and inflow air is burned using an atmospheric condition, an opening degree command value of a valve that controls the amount of air that is mixed with the fuel and burned, and an output prediction value calculated on the basis of a fuel control signal command value used for calculation of a total fuel flow rate flowing through a plurality of fuel supply systems, a fuel distribution command value calculation unit that calculates a fuel distribution command value indicating a distribution of fuel output from the fuel supply systems based on the temperature estimation value, and outputs the fuel distribution command value, and a valve opening degree calculation unit that calculates each valve opening degree of a fuel flow rate control valve of the fuel supply systems.

Fuel control device, combustor, gas turbine, control method, and non-transitory computer-readable medium

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

A combustion control device is installed in a gas turbine including a compressor, a combustor, a turbine, a turbine bypass pipe through which compressed air from a casing is discharged to a turbine downstream part so as to bypass the turbine, and a turbine bypass valve that regulates a turbine bypass flow rate of the compressed air. The combustion control device includes: a fuel distribution setting unit that sets a turbine inlet temperature or a turbine inlet temperature-equivalent control variable on the basis of input data, and sets fuel distribution ratios on the basis of the turbine inlet temperature or the turbine inlet temperature-equivalent control variable; and a fuel valve opening setting section that sets the valve openings of fuel regulating valves. The fuel distribution setting unit includes correction means for modifying the fuel distribution ratios.

Gas turbine combustion control device and combustion control method and program therefor

A combustion control device () is installed in a gas turbine including a compressor (), combustors (), a turbine (), a bleed air pipe () through which bleed air is returned to an inlet of an air intake facility (), and an air bleed valve () that regulates the amount of bleed air extracted. The combustion control device () includes: a fuel distribution setting unit () that sets a turbine inlet temperature or a turbine inlet temperature-equivalent control variable on the basis of input data, and sets fuel distribution ratios on the basis of the turbine inlet temperature or the turbine inlet temperature-equivalent control variable; and a fuel valve opening setting section () that sets the valve openings of fuel regulating valves. The fuel distribution setting unit () includes correction means for modifying the fuel distribution ratios.

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 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

A gas turbine combustor is provided with a nozzle extension tube having an inclination outward in a diameter direction of a combustor inner cylinder and in a peripheral direction of the combustor inner cylinder. As a result, the premixed gas is transformed to a spiral flow passing into a combustion chamber while turning, i.e., an outward turning flow, thereby sufficiently mixing the premixed gas while the premixed gas is flowing in the combustion chamber.

A pilot nozzle diffusion-injects a fuel. A pilot swirler swirls a pilot air around the pilot nozzle. An air guide is arranged between the outer surface of the pilot nozzle and the pilot swirler. The air guide extends from the pilot swirler to a tip of the pilot nozzle. The air guide has a tip that protrudes beyond the tip of the pilot nozzle and this the tip of the air guide is bent away from a center of the pilot nozzle.

Pilot burner, premixing combustor, and gas turbine

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Hyogo, Japan

Wataru Akizuki