Hitachi, Ltd.

Mitsubishi Hitachi Power Systems, Ltd.

Mitsubishi Heavy Industries Limited

Hidetaro Murata

Isao Takehara

Motoaki Utamura

Tetsuo Sasada

Fumiyuki Hirose

Yasuhiro Katoh

Takaaki Kuwahara

Nobuyuki Horii

Kenji Nanataki

Nobuaki Kizuka

Hidetoshi Kuroki

Hiromi Koizumi

Nozomi Saito

Atsushi Sano

Ryo Kawai

Hiroshi Inoue

Akinori Hayashi

Tomohiro Asai

Shinichi Hoizumi

Katsuo Wada

Kazuyuki Ito

Hironori Tsukidate

Toshifumi Sasao

Takeo Saito

Shinichi Inage

Tsunemasa Nishijima

Mitsuo Teranishi

Tsunemasa Nishijama

A twin-shaft gas turbine can be used for 50 and 60 Hz power generation without using a reducer. A gas generator includes a compressor that generates compressed air, a burner that burns a fuel mixed with the compressed air received from the compressor so as to generate combustion gas, and a high-pressure turbine that is rotationally driven by the combustion gas received from the burner and generates driving force for the compressor. An output turbine includes a low-pressure turbine that is driven by exhaust gas received from the high-pressure turbine and a power generator that is driven by the low-pressure turbine. A control device reduces opening degree of IGV of the compressor and thereby reduces power of the compressor, and the rotational frequency of the gas generator is increased in a full-speed no-load operating state of the power generator.

Twin-shaft gas turbine for multiple frequency power generation

It is an object of the present invention to provide a compressor that has a simple structure, produces a damping effect and improves aerodynamic performance. In a compressor including stator bladescircumferentially mounted to an inner circumferential surface side of a casingforming a annular path; and an inner barrelsupported by the casing and arranged on the radially inside of the stator blade as a partition wall on the radial side of the annular path; the stator blade includes an outer shroudmounted to an inner circumferential surface of the casing at a position facing the inner barrel, and an inner shroudsupporting a blade portion at an inner diameter side, the inner shroud being disposed in an annular groove formed in an outer circumferential surface of the inner barrel facing the inner shroud. The stator blade including the outer shroud, the inner shroudand the blade portionsare formed in a monolithic structure by milling.

Compressor

A two-shaft gas turbine is capable of starting premixed combustion without extinguishing a flame. The two-shaft gas turbine includes a combustor and a gas generator controller. The combustor has a premix burner that includes combustion regions in which premixed combustion is to be carried out individually. The gas generator controller controls the combustor. In a method for starting the premixed combustion in the combustor, the gas generator controller selects at least one of the combustion regions in which the premixed combustion is to be carried out, on the basis of a fuel-air ratio, and starts premix combustion in the selected combustion region or separately in each of the selected combustion regions. Further, as the fuel-air ratio is increased, the controller increases the number of the selected region in which the premixed combustion is carried out.

Method for starting premixed combustion in combustor for two-shaft gas turbine

An airfoil profile is formed such that a passage width ratio, represented in a dimensionless manner, of an inter-blade passage width of vane root cross-section to an outlet throat width substantially monotonously decreases from a blade inlet toward a blade outlet. The blade has a blade airfoil profile shape in an envelope within a range of .+&#x2212;.2.0 mm in a direction normal to any surface location of an airfoil profile portion. The airfoil profile portion has a reference airfoil contour represented in Cartesian coordinates wherein Z is a distance representing a sectional height from a root of the airfoil profile portion. The contours represented by X and Y at each section Z are joined smoothly with one another in a blade height direction to form a complete shape of the airfoil profile portion.

Turbine blade

A twin-shaft gas turbine, which has a gas generatorincluding a compressor, a combustor, and a high-pressure turbine, is configured to make a first control mode and a second control mode selectively useable for control of the gas generator. In addition, in the first control mode, an IGV angle in the compressor is controlled in accordance with a corrected shaft rotation speed of the gas generator, and in the second control mode, the IGV angle is controlled to maintain a constant gas generator shaft rotation speed. Furthermore, the first control mode is used to start, to stop, and to operate the turbine under fixed or lower load conditions, and that the second control mode is used under operational states other than those to which the first control mode is applied.

Twin-shaft gas turbine including a control system for adjusting the compressor inlet guide vane angle to optimize engine transient response

A combustor includes two upstream parts of fuel supply system supplying gaseous fuels of two types having different heating values from each other, a three-way fuel transfer valve merging the two upstream parts of fuel supply system with each other, a plurality of gaseous fuel supply subsystems supplying a combustion chamber with the gaseous fuels supplied through the three-way fuel transfer valve and branched, and a plurality of burners injecting, corresponding to each of the gaseous fuel supply subsystems, the gaseous fuel supplied from the gaseous fuel supply subsystem into the combustion chamber.

Gas turbine combustor and gaseous fuel supply method for gas turbine combustor

A twin-shaft gas turbine, which has a gas generatorincluding a compressor, a combustor, and a high-pressure turbine, is configured to make a first control mode and a second control mode selectively usable for control of the gas generator. In addition, in the first control mode, an IGV angle in the compressor is controlled in accordance with a corrected shaft rotation speed of the gas generator, and in the second control mode, the IGV angle is controlled to maintain a constant gas generator shaft rotation speed. Furthermore, the first control mode is used to start, to stop, and to operate the turbine under fixed or lower load conditions, and that the second control mode is used under operational states other than those to which the first control mode is applied.

The temperature rise of a wheel space between a high-pressure turbine and a low-pressure turbine is suppressed. Cooling air is led from outside a casingto a wheel space via a low-pressure turbine initial stage stator bladeand a diaphragm. An upstream side space seal portionis adapted to restrict and divide the upstream side space into an outer circumferential portionand an inner circumferential portionand to allow cooling air to the upstream side space outer circumferential portionto blow out into the upstream side space outer circumferential portion. Also, a downstream side space seal portionis adapted to restrict and divide the downstream side space into an outer circumferential portionand an inner circumferential portionand to allow cooling air to blow out into the downstream side space outer circumferential portion

Two-shaft gas turbine

A gas turbine combustor comprises a premixed combustion burner disposed on the periphery of a pilot burner, an approximately cylindrical combustor liner disposed on the downstream side of the premixed combustion burner, which defines a combustion chamber in the liner. The gas turbine combustor is characterized by further comprising flame stabilizers radially disposed at the exit of the premixed combustion burner, and a fuel injection means with which the pilot burner is provided injects at least one of gas fuel and liquid fuel, in which a plurality of air nozzles are provided which are located outside the pilot burner and inside the premixed combustion burner, and which spout out air into the combustion chamber. Adequate combustion can be accomplished with a combustor which is capable of using gas fuel and liquid fuel, and at the same time, NOx can be reduced.

Gas turbine combustor, combustion method of the gas turbine combustor, and method of remodeling a gas turbine combustor

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

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Hitachi, Japan

Hidetaro Murata