Hitachi, Ltd.

Petroleum Energy Center

Mitsubishi Hitachi Power Systems, Ltd.

Mitsubishi Power, Ltd.

Osami Yokota

Hirokazu Takahashi

Akinori Hayashi

Nobuyuki Hokari

Shohei Numata

Shinichi Inage

Tetsuma Tatsumi

Masahiko Yamagishi

Koji Nishida

Shinsuke Kokubo

Tomomi Koganezawa

Shohei Yoshida

Tetsuo Sasada

Toshifumi Sasao

Tsunemasa Nishijima

Shin-ichi Inage

Masataka Hidaka

Youji Ishibashi

Kouji Nishida

Testuma Tatsumi

Disclosed is a heat-transfer device adapted to enhance uniformity of cooling characteristics to be given to a heat transfer object, and thereby to extend a life of the heat transfer object. The heat-transfer device for facilitating heat exchange between combustion air (heat transfer medium) flowing along an outer surface of a combustor liner (heat transfer object), and the combustor liner, the heat-transfer device including at least one longitudinal vortex generating device protruding toward a annular passage (flow passage) of the combustion air and formed to generate a longitudinal vortex E with a central axis in a flow direction of the combustion air, and stir the combustion air flowing in the annular passage; and at least one radiator fin provided in a region A on the outer surface of the combustor liner, the region A being where a flow of the vortex E, on a swirling plane thereof, that are generated by the vortex generating device is directed from a side of the combustor liner, toward a side of a flow sleeve, the fin exchanging heat with the combustion air stirred by the vortex generating device.

Heat-transfer device and gas turbine combustor with same

A gas turbine combustor includes a combustor liner, a flow sleeve in which the combustor liner is provided and an annular flow passage formed between the combustor liner and the flow sleeve, through which compressed air flows. The flow sleeve includes an internal-diameter changing portion diagonally connected to the flow sleeve and an internal-diameter reducing portion connected to the internal-diameter changing portion and extending along the flow direction of the compressed air. The combustor liner includes an annular protruding portion annularly formed on an outer wall of the combustor liner and protruding toward the flow sleeve. The annular protruding portion is located at a position on the outer wall of the combustion liner, the position facing a connection position between the flow sleeve and the internal-diameter changing portion or being at an upstream side of the position facing the connection position in the flow direction of the compressed air.

Gas turbine combustor

A gas turbine combustor achieves improved product reliability and a reduced increase in pressure loss through improvements made on a cooling characteristic and structural intensity. The structure of the gas turbine combustor includes a plurality of circularity recesses formed on a side of an annular passage on a partial area of a combustion liner that requires cooling. Each of the circularity recesses has a rectangular surface forming a convex at a right angle with respect to a flowing direction of combustion air. The circularity recesses form a rectangular triangle having an oblique surface facing upstream of the flowing direction of the combustion air.

Gas turbine combustion liner with triangular heat transfer element

A gas turbine combustor is provided in which product reliability and heat transfer promotion are compatible while suppressing an increase in pressure loss. In a gas turbine combustor comprising a combustor liner, an outer tube provided around an outer periphery of the combustor liner, and an annular flow passage in which a cooling medium (cooling air) flows and which is formed between an outer surface of the combustor liner and an inner surface of the outer tube, the outer tube includes an inner diameter reduced portion and a taper portion smoothly connecting the inner diameter reduced portion and an inner peripheral portion on an upstream side, and is provided at an inner surface of the taper portion with longitudinal vortex generating means generating a vortex that has a central rotation axis in a flowing direction of the cooling medium (cooling air).

Cooling structure for gas turbine combustor liner

An object of the present invention is to provide a gas turbine combustor that can suppress an increase in pressure loss while improving product reliability. The gas turbine combustor includes a combustor liner, an air transfer casing installed on the outer circumference of the combustor liner, the combustor liner and the air transfer casing defining an annular passage therebetween adapted to allow a heat-transfer medium to flow therethrough, and a plurality of vortex generating devices disposed on an inside surface of the air transfer casing, the vortex generating devices generating longitudinal vortices each having a rotational axis extending in a flow direction of a heat-transfer medium. The plurality of vortex generating devices are arranged in paired manner, with each pair of devices generating vortices having rotational directions opposed to each other.

Gas turbine combustor equipped with heat-transfer device

The present invention provides a reformed-fuel-burning gas turbine system that constantly generates good-quality reformed fuel even when heavy fuel has a different composition. The reformed-fuel-burning gas turbine system according to the present invention comprises a heavy oil heater; a water heater; a reformer vessel for mixing high-temperature, high-pressure water with high-temperature, high-pressure heavy oil to cause a hydrothermal reaction and producing reformed fuel from heavy oil; and a gas turbine which operates on the reformed fuel. The reformed-fuel-burning gas turbine system according to the present invention further comprises a detector for detecting the static dielectric constants or solubility of high-temperature, high-pressure heavy oil heated by the heavy oil heater and high-temperature, high-pressure water heated by the water heater; a first temperature regulating valve for adjusting the thermal dose of the heavy oil heater; a second temperature regulating valve for adjusting the thermal dose of the water heater; and a control device for adjusting the first temperature regulating valve and the second temperature regulating valve in accordance with the static dielectric constants or solubility of the heavy oil and water, which are detected by the detector, in order to control the static dielectric constants or solubility of the high-temperature, high-pressure heavy oil and high-temperature, high-pressure water, which are to be supplied to the reformer vessel.

Reformed-fuel-burning gas turbine system and method of operating the same

A gas turbine system burning heavy-oil modified fuel and a method of operating the gas turbine system, which covers from a stage of modifying heavy oil and producing gas turbine fuel to a stage of operating a gas turbine, including startup, ordinary shutdown and emergency shutdown of the gas turbine. The gas turbine system burning heavy-oil modified fuel comprises a reactor for mixing heavy oil and water to cause reaction, thereby separating and removing a heavy component from the heavy oil, a gas-liquid separator for separating hydrocarbon gas and modified oil obtained in the reactor from each other, a gas turbine combustor for burning the hydrocarbon gas supplied from the gas-liquid separator, and a gas turbine driven by combustion gas produced in the gas turbine combustor. The system further comprises another line for extracting the hydrocarbon gas externally of a relevant system region. The other line is branched from a line for supplying the hydrocarbon gas from the gas-liquid separator to the gas turbine combustor.

Gas turbine system burning heavy-oil modified fuel and method of operating same

A heavy oil reforming system includes a reforming preheater raising the temperature of a mixed fluid comprising a high pressure heavy oil and high pressure steam up to a temperature for reforming reaction. The mixed fluid having been heated up to the temperature for reforming reaction is introduced into a reformer kept at the temperature for reforming reaction and thereby the heavy oil is reformed. This reforming system allows the attainment of a residence time of 1 to 10 min necessary for reforming in a uniform or nearly uniform temperature field, thereby implementing the manufacturing of reformed fuels from a large volume of heavy oil.

System for reforming heavy oil, method therefor, and combined cycle power system

In a method for producing gas turbine fuel through the step of modifying heavy fuel oil with the use of an asphaltene-insoluble solvent, the utilization factor of the heavy fuel oil usable as gas turbine fuel is increased by making asphaltene selectively removable. A solvent having a specific inductive capacity in the range of 1.4 to 2.0 is used as the asphaltene-insoluble solvent. In particular, water controlled in temperature and pressure so as to have a specific inductive capacity in the above range is used as the asphaltene-insoluble solvent. By using such a solvent, an asphaltene component contained in the heavy fuel oil can be selectively removed and power generation can be performed while utilizing 95% or more of the heavy fuel oil.

Method for producing gas turbine fuel, and method and system for generating electric power by gas turbine

A gas turbine which can be easily employed in an area where it is hard to obtain a sufficient amount of water, such as an isolated island. Heated and pressurized heavy oil and water in a supercritical state are mixed with each other in a modifying unit to produce fuel-purpose modified oil. The fuel-purpose modified oil is depressurized by a depressurizing valve. Due to a temperature fall caused by adiabatic expansion with the depressurization, the fuel-purpose modified oil is brought into a two-phase state where moisture is in a gas phase (steam) and modified oil is in a liquid phase. The fuel-purpose modified oil is separated into the steam and the modified oil by a gas-liquid separator. The separated steam is condensed to water in a condenser and returned to a water supply line. The modified oil in the liquid phase is supplied to a combustor, thereby driving a gas turbine.

Modified fuel burning gas turbine

The invention is intended to produce high-pressure light fuel gas with good combustibility by contacting and reacting high-temperature, high-pressure water and heavy oil with each other in a contact-reaction unit to extract light oil components from the heavy oil and to remove metals. The high-temperature, high-pressure water and the heavy oil are introduced to the contact-reaction unit for contact and reaction with each other therein. Heavy oil components not dissolved in the high-temperature, high-pressure water are separated by precipitation from hydrocarbon gases and light oil components which are dissolved in the high-temperature, high-pressure water. The separated heavy oil components are burnt or incinerated without any further modification.

Growing community of inventors

Hitachinaka, Japan

Osami Yokota