Hitachi, Ltd.

Fumiyuki Hirose

Isao Sato

Motoaki Utamura

Isao Takehara

Nobuyuki Iizuka

Tetsuo Sasada

Hidetaro Murata

Yasuhiro Katoh

Takaaki Kuwahara

Nobuyuki Horii

Akira Shimura

Osamu Arai

Hiroshi Inose

Katsukuni Hisano

Yoji Ishibashi

Hiraku Ikeda

Seiichi Kirikami

Katsuo Wada

Michio Kuroda

Minoru Takaba

Yoshihiro Uchiyama

Haruo Urushidani

Shoei Takahashi

Yoshitaka Kojima

Naotatsu Asahi

Kazuhiko Kumata

Ryoichiro Oshima

Yasutaka Komatsu

Yasuhiko Otawara

Yoshiharu Nakayama

Tomoyoshi Endo

Naohiko Iwata

Takeshi Iwamiya

Takeshi Ishida

Masashi Kunihiro

Takumi Yamanobe

Osamu Sakuda

A gas turbine comprises a compressor for compressing a gas supplied therein and discharging the compressed gas, a combustor in which the discharged gas from the compressor and a fuel are combusted, a turbine to be driven by a combustion gas from the combustor, and a water injection unit which injects water into the gas to be supplied to the compressor, thereby lowering the temperature of the gas to be introduced into the compressor to a temperature lower than the atmospheric temperature, and causing water droplets having been injected in the gas and within the compressor to be vaporized while flowing down therein, wherein the quantity of water spray injection is controlled while monitoring operational conditions of the gas turbine.

Gas turbine having water injection unit

Gas turbine with water injection

Gas turbine having water spray injection control

Gas turbine

Gas turbine having water droplet injector

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

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

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Hitachi, Japan

Fumiyuki Hirose