Hitachi, Ltd.

Akira Shimura

Isao Sato

Fumiyuki Hirose

Hiraku Ikeda

Haruo Urushidani

Osamu Arai

Seiichi Kirikami

Kazuhiko Kumata

Minoru Takaba

Michio Kuroda

Nobuyuki Iizuka

Shoei Takahashi

Hiroshi Inose

Takeshi Iwamiya

Tetsuo Sasada

Koji Takahashi

Katsukuni Hisano

Yoji Ishibashi

Yasutaka Komatsu

Nobuo Shimizu

Tsuguaki Koga

Yasuhiko Otawara

Seisaku Takihana

Hideaki Kaneda

Yoshiharu Nakayama

Tomoyoshi Endo

Naohiko Iwata

Tomo Sato

Takeshi Ishida

Tadashi Kurokawa

Takumi Yamanobe

A control method of a gas turbine which is provided with a multi can type combustor consisting of a plurality of unit combustors, each of which has a first stage combustion section for diffusion combustion and a second stage combustion section for premix combustion. Combustion states in the first and second stage combustion sections are monitored to take in quantities representative of the combustion conditions as control factors. The combustion in the second stage combustion section is assumed to be abnormal when the taken in quantities exceed an allowable limit and the combustion in the first and second stage combustion sections is changed to independent combustion only in the first stage combustion section when the number of unit combustors, each of which is assumed to be abnormal, exceeds a predetermined number of the unit combustors.

Gas turbine and a gas turbine control method

A gas turbine engine control method and apparatus as disclosed for optimizing fuel/air mixture, especially during decreasing load conditions. In a large capacity gas turbine engine system used for generation of electric power, the system is designed to operate at a relatively constant rotational speed of the turbine which drives an electric generator unit. The load of the turbine engine varies throughout the day due to changes in electrical power demands. During normal rated load conditions, the control of the fuel/air mixture is by way of changes in fuel supply, corrected to return the turbine exhaust temperature to a desired rated temperature. During this mode of operation, the compressor inlet guide vanes are maintained in a substantially constant open position. For accommodating decreasing load conditions where the temperature drops below a predetermined temperature level below the rated temperature operation, the system is switched to an inlet guide vane control mode of operation. During the guide vane control mode of operation, the inlet guide vanes are controlled at a more precise temperature correction sensitivity than is the case for normal load operations. This more precise inlet guide vane control during decreasing load conditions assures improved fuel/air mixture during decreasing load and consequent improved efficiency and minimal NO.sub.x compound emissions, especially during changing ambient temperature conditions where cold air would otherwise increase the air supply.

Gas turbine control method and apparatus

A gas turbine apparatus has a gas turbine and a plurality of burners for providing combustion gas to drive the turbine. A flow control means of each burner for fuel or combustion air is adjusted by control means to control each said burner individually in dependence on a predetermined combustion characteristic of the respective burner. Sensed quantities relating to the combustion performance of the burners are input to the control means which adjusts the flow control means of each burner in dependence on the sensed quantities and the predetermined combustion characteristic of the respective burner.

Gas turbine apparatus and method of control thereof

A method for controlling a gas turbine combustor which comprises nozzles for injecting fuel into a combustor and which serves to combust the fuel with air in a combustion chamber so as to rotatively drive a gas turbine by combustion gas compressed as a result of combustion of a fuel, wherein the ratio of a flow rate of fuel supplied into the combustor to a flow rate of air supplied into the combustor is changed in accordance with at least one of the states of fuel, air and rotational frequency of the turbine.

Method for controlling gas turbine combustor

To provide a combustion apparatus and a controlling method therefor which are capable of preventing the flame-out and backfire of the flame of a premix burner and the increase of the NOx concentration attributable to the change of the calorific value of the fuel, the amount of air supplied to the premix burner is so controlled as to achieve a low NOx within the range in which the premix burner effects a stable combustion in accordance with the calorie of the fuel supplied to the combustion apparatus, and a change of the output of the combustion apparatus attributable to this control of the amount of air is compensated by the control of the amount of the fuel supplied to the diffusion burner.

Combustion apparatus and control method therefor

A fuel supply amount is controlled while the load of a gas turbine is changed so that the fuel supply amount is shifted to a fuel supply amount in accordance with the changed load. A fuel supply control valve is operated at high speed during an initial stage and operated at a lower speed as the fuel supply amount necessary for the changed load is reached. Therefore flameout of a combustor is prevented without increasing the number of revolutions of the gas turbine over a certain upper limit.

Method and apparatus for controlling the supply of fuel to a gas turbine

A gas turbine combustor and a method of operating the gas turbine combustor, with the gas turbine combustor comprising a combustion sleeve, a combustion sub-chamber disposed at an upstream side of the combustion sleeve and having an air and fuel supply system, and a combustion main chamber disposed on a downstream side of the sub-chamber and having an air and fuel supply system. The combustion sub-chamber and combustion main chamber are formed in such a manner that the start-up of the gas turbine is effected by the hot combustion gas generated in the sub-chamber. The combustion sub-chamber is provided with an inner sleeve protruding from a side wall of the sub-chamber such that a tip of the inner sleeve is located in the vicinity of a downstream end of the sub-chamber, and a fuel nozzle is provided in a tip of the inner sleeve for increasing the fuel-to-air ratio during an initiating period of an increase in the gas turbine rotation speed.

Gas turbine combustor and methodd of operating the same

A method for detecting combustion conditions in a plurality of combustors in a gas-turbine apparatus which includes the combustors and a gas turbine driven by combustion gas from the combustors, comprises a step for measuring concentration of unburnt component in the combustion gas by means of a plurality of sensors disposed on the downstream side of the gas turbine, a step for obtaining a distribution pattern of the measured concentration, and a step for investigating the distribution pattern to detect combustion conditions in the combustors.

Method for detecting combustion conditions in combustors

A device for detecting combustion conditions in a plurality of combustors in a gas-turbine apparatus which includes the combustors and a gas turbine driven by combustion gas from the combustors, comprises a plurality of sensors for measuring concentration of unburnt component in the combustion gas, which is disposed on the downstream side of the gas turbine, a unit for obtaining a distribution pattern of the measured concentration and for investigating the obtained distribution pattern to detect combustion conditions in the combustors.

Device for detecting combustion conditions in combustors

Growing community of inventors

Hitachi, Japan

Akira Shimura