Patent application number | Description | Published |
20080289316 | COMBINED-CYCLE POWER PLANT AND STEAM THERMAL POWER PLANT - A combined-cycle power plant, a steam thermal power plant, and a method for operating the power plant, which are capable of effectively utilizing raw fuel produced from medium- or small-scaled gas fields and oil fields. Raw fuel produced from a gas field is separated into a gas component and a liquid component by a separator. The gas component is burnt in a combustor of a gas turbine, and resulting motive power is converted to electricity by a power generator. The liquid component separated by the separator is burnt in a steam generator to generate steam that is supplied to a steam turbine. Resulting motive power of the steam turbine is converted to electricity by a power generator. Since the electricity generated by the power generators is AC power, the AC power is converted by a converter to DC power that is transferred from the vicinity of the gas field to a consuming area via a cable. | 11-27-2008 |
20080289337 | COMBINED-CYCLE POWER PLANT AND STEAM THERMAL POWER PLANT - A combined-cycle power plant, a steam thermal power plant, and a method for operating the power plant, which are capable of effectively utilizing raw fuel produced from medium- or small-scaled gas fields and oil fields. Raw fuel produced from a gas field is separated into a gas component and a liquid component by a separator. The gas component is burnt in a combustor of a gas turbine, and resulting motive power is converted to electricity by a power generator. The liquid component separated by the separator is burnt in a steam generator to generate steam that is supplied to a steam turbine. Resulting motive power of the steam turbine is converted to electricity by a power generator. Since the electricity generated by the power generators is AC power, the AC power is converted by a converter to DC power that is transferred from the vicinity of the gas field to a consuming area via a cable. | 11-27-2008 |
20090185896 | GAS TURBINE AND GAS TURBINE COOLING METHOD - A gas turbine includes a nozzle vane and a sealing unit engaged with the nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel. The nozzle vane and the sealing unit are disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path. A plurality of engagement portions between the sealing unit and the nozzle vane are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, and a downstream one of the plurality of engagement portions has a contact interface formed in a direction across a turbine rotary shaft. A reduction in the thermal efficiency of the gas turbine can be suppressed. | 07-23-2009 |
20090196738 | GAS TURBINE AND GAS TURBINE COOLING METHOD - A gas turbine includes a nozzle vane and a sealing unit engaged with the nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel. The nozzle vane and the sealing unit are disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path. A plurality of engagement portions between the sealing unit and the nozzle vane are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, and a downstream one of the plurality of engagement portions has a contact interface formed in a direction across a turbine rotary shaft. A reduction in the thermal efficiency of the gas turbine can be suppressed. | 08-06-2009 |
20090282837 | Gas turbine unit and its cooling method - It is the object of the present invention to feed cooling air suitable for cooling the high-temperature part of the gas turbine. | 11-19-2009 |
20090293493 | ADVANCED HUMID AIR TURBINE POWER PLANT - An advanced humid air turbine power plant capable of suppressing condensation of moisture in a cooling channel, which is provided to cool a high-temperature component of a gas turbine, in a start up stage, a coast down stage, and a load varying state of the gas turbine. In the advanced humid air turbine power plant comprising a compressed air supply line for supplying compressed air generated by a compressor to the high-temperature component of the gas turbine, and a humidified air supply line for supplying humidified air generated in a humidifying tower to the high-temperature component of the gas turbine, the power plant further comprises valves capable of adjusting respective air flow rates in the compressed air supply line and the humidified air supply line. A coolant is switched over from the compressed air to the humidified air in the start up stage and the load increasing stage of the gas turbine, and from the humidified air to the compressed air in the load decreasing stage and the coast down stage, as well as in the event of an abnormality in a humidifying line. | 12-03-2009 |
20090320438 | TWO-SHAFT GAS TURBINE - Provided is a two-shaft gas turbine with improved reliability that improves output power and efficiency and is stably operated by establishing a balance between the driving force of a compressor and the output power of a high-pressure turbine in the case where the two-shaft gas turbine is applied to a system in which the flow rate of fluid flowing into a combustor is increased compared with a simple cycle gas turbine. | 12-31-2009 |
20110162369 | Gas Turbine, Exhaust Diffuser, and Method of Modifying Gas Turbine Plant - A method of modifying a gas turbine plant which is provided with a one-shaft gas turbine having a compressor for compressing air, a combustor for generating a combustion gas from the air compressed by the compressor and a fuel, and a one-shaft turbine driven by the combustion gas generated by the combustor and supported by a rotational axis common to the compressor, and an electric generator for generating electric power by driving force of the one-shaft turbine, wherein: the one-shaft turbine is replaced with a two-shaft gas turbine including a compressor for compressing air, a combustor for generating a combustion gas from the air compressed by the compressor and a fuel, and a high-pressure turbine driven by the combustion gas generated by the combustor and supported by a first rotational axis common to the compressor, and a low-pressure turbine driven by the combustion gas used to drive the high-pressure turbine and supported by a second rotational axis, which is different from the axis for the high-pressure turbine. | 07-07-2011 |
20110200449 | MEMBER HAVING INTERNAL COOLING PASSAGE - Provided is a member having an internal cooling passage | 08-18-2011 |
20120060509 | Inner Bleed Structure of 2-Shaft Gas Turbine and a Method to Determine the Stagger Angle of Last Stage Stator of Compressor for 2-Shaft Gas Turbine - An inner bleed structure of the 2-shaft gas turbine includes a slit for leading part of compressed air to a cavity is formed between a wall surface of a rotor wheel of the compressor equipped with a last stage rotor of the compressor which is connected to a first rotating shaft and end of an inner casing, and a bleed hole for leading part of compressed air after flowing down the last stage of the compressor to a cavity formed in the inner side of the inner casing at the downstream side of the last stage of the compressor. | 03-15-2012 |
20130259668 | Transonic Blade - The present invention provides a transonic blade that concurrently achieves reduction in shock loss at a design point and improvement in stall margin in blades operating in a flow field of transonic speed or higher in an axial-flow rotating machine. A cross-sectional surface at each of spanwise positions of the blade is shifted parallel to a stagger line connecting a leading edge with a trailing edge of the blade. A stacking line is shifted toward an upstream side of working fluid. The stacking line connects together respective gravity center positions of blade cross-sectional surfaces at spanwise positions in a range from a hub cross-sectional surface joined to a rotating shaft or an outer circumferential side casing of a rotating machine to a tip cross-sectional surface lying at a position most remote from the hub cross-sectional surface in a spanwise direction. | 10-03-2013 |