Abstract: A gas turbine plant comprises an air compressor, gas turbine including at least one high temperature section, a driven equipment, which are operatively connected in series, a gas turbine combustor arranged between the air compressor and the gas turbine, a fuel system disposed for supplying a fuel to the gas turbine combustor, and a heat exchange section for heating the fuel from the fuel by means of a high pressure air as a heating medium fed from the air compressor.

Abstract: Automated systems for performing integrated analyses. In one embodiment, an integrated analysis system can be used to comprehensively evaluate the effects of changes in hardware configuration or operating conditions on gas turbine power plant performance and economics. The system evaluates these changes by concurrently analyzing a number of different aspects of the power plant while ensuring that the data used in each of the different analyses is consistent. These analyses can include turbine and compressor aerodynamic analysis, cooling and leakage flow analysis, heat transfer analysis, part life analysis, heat balance analysis, cost analysis and overall power plant performance and economic analysis.

Abstract: It is the object of the present invention to feed cooling air suitable for cooling the high-temperature part of the gas turbine. The present invention comprises a compressor, a combustor, and a turbine. Further, a turbine-cooling system to feed the gas from the compressor to the turbine is provided, and the turbine-cooling system comprises a heat exchanger to cool the gas compressed by the compressor, and a means for separating liquid from the gas cooled by the heat exchanger. Thus, according to the present invention, it becomes possible to feed cooling air suitable for cooling the high-temperature part of the gas turbine and to achieve higher reliability of the gas turbine unit.

Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

Abstract: A gas turbine blade ring is cooled by steam whose temperature, pressure and flow rate are controlled so that a clearance between a moving blade tip and blade ring is maintained appropriately. Steam from a steam turbine bottoming cycle (10) flows into a blade ring cooling passage (8) of a gas turbine (1) via piping (12) for cooling the blade ring. The steam, having cooled the blade ring, is supplied into a transition piece cooling passage (9) of a combustor (3) for cooling the transition piece, and is then recovered into the steam turbine bottoming cycle (10) via piping (14). While the steam cools the blade ring, the temperature, pressure and flow rate of the steam are controlled so that thermal elongation of the blade ring is adjusted and the clearance at the moving blade tip is controlled so as to approach a target value. Thus, the clearance is maintained as small as possible in operation and the gas turbine performance is enhanced.

Abstract: Bleeding is operated by annularly providing plural stationary blades at an interior side of a vehicle; annularly providing plural moving blades around rotor disk adjacent to stationary blades; providing plural stage units comprising the stationary and moving blades; introducing bleed air into each stage unit from a compressor; supplying bleed air extracted from a final stage of the compressor into a first stage unit; and supplying bleed air extracted from compressed air which has not yet arrived at a final stage unit of the compressor.

Abstract: A gas turbine combustor transition piece outlet structure enabling a reduction in the temperature difference of a flange formed at the transition piece outlet. A flange is formed with a cooling medium channel along the inner circumference, cooling medium channels along the left and right side surfaces, and heating medium channels along the top and bottom surfaces. By cooling the inner circumference or the side surfaces of the flange by a cooling medium or heating the top and bottom surfaces of the flange by a heating medium, the temperature difference of the flange is reduced. Note that as the cooling medium, it is possible to use compressed air, low temperature steam, or fuel, while as the heating medium, it is possible to use high temperature steam or combustion gas.

Abstract: A gas turbine has a cooling air system supplying air for cooling a high temperature part of the gas turbine and a spray air system supplying air for spraying fuel into a combustor and is formed so that a part of high-pressure air compressed by a gas turbine compressor is used as air of the cooling air system and spray air system, wherein a heat exchanger and a boost compressor are arranged downstream of the outlet of compressed air of the gas turbine compressor, and the boost compressor is composed of a parallel connection of a compressor driven by the turbine shaft and ae compressor driven by a driven source other than the turbine shaft, and pressurized air from the boost compressor is used as air for the cooling air system and the spray air system.

Abstract: A device and method for recuperating a gas turbine engine comprises a compressor being configured to receive a coolant fluid stream, to compress the coolant fluid stream and to discharge the compressed coolant fluid stream to a turbine in fluid communication with the compressor. The compressed coolant fluid stream undergoing thermal exchange within the turbine, exit the turbine thereafter. A source of a working fluid stream is in fluid communication with the turbine. The working fluid stream is fluidly isolated from a portion of the coolant fluid stream and undergoing thermodynamic expansion through the turbine to extract energy therefrom. Where desired, the entire coolant fluid stream is fluidly isolated from the working fluid stream. At least a portion of the coolant fluid stream is channeled downstream of the turbine to supply a preheated process fluid stream to an adjacent system.

Abstract: A gas turbine includes at least one compressor 1 and at least one turbine 2, wherein one portion of the air leaving the compressor 1 is delivered to a combustion chamber 3 and a further portion is extracted as cooling air, wherein at least one portion of the cooling air flow 4 is directed through a secondary air turbine 5, for extracting energy.

Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

Abstract: A turbine blade and assembly for use in a gas turbine engine are provided. The turbine blade has a root portion adapted for mounting to a rotor, and an airfoil portion extending from the root portion. A cooling air inlet duct is provided and adapted to communicate with the cooling air plenum when installed to the rotor. The air inlet duct has an inlet scoop portion adapted to extend into the cooling air plenum and an inlet scoop aperture oriented and adapted to capture cooling air from the cooling air plenum as a consequence of turbine rotation when the blade is mounted to the rotor. Scooped air is provided to a cooling air channel defined in an airfoil portion of the blade for the purpose of cooling the blade. The engine optionally includes a bearing gallery cooling air jacket in communication with the low pressure compressor stage for the purpose of cooling.

Abstract: The invention relates to a turbine 1, in particular a gas turbine, which along a swivel-mounted rotationally symmetrical rotor 2 has a compressor 3, a combustion chamber 5 and a turbine section 7 formed of a plurality of turbine stages 15, in which each turbine stage 15 contains mutually interacting blades 17 and vanes 16 which a hot working fluid 13 can flow around, with a coolant provided by the compressor 3 for cooling the blades 16, 17, which can flow in a channel along the rotor 2 from the compressor 3 to the turbine section 7 and into which a liquid can be introduced for cooling. In order to specify a turbine in which less wear occurs and in which the lifetime of the components is increased, it is proposed that the channel extends outside the rotor 2 and that the liquid can be introduced at the end of the channel which faces the compressor 2.

Abstract: The invention relates to method for cooling a gas turbine according to which compressed air is extracted from a compressor connected upstream from the gas turbine for feeding said gas turbine and is used as cooling air. Cooling efficiency and yield are increased by means of cooling the compressed air through heat exchange with an air stream and feeding the gas turbine with cooled compressed air for cooling it. The invention also relates to a gas turbine installation comprising a gas turbine and a compressor connected upstream from said gas turbine, with at least one cooling air duct extending from the compressor. The primary side of a heat exchanger is connected to the air cooling duct and its secondary side is connected to a duct through which an air stream flows for supplying the heat exchanger.

Abstract: The compressor discharge air that normally leaks from the high pressure compressor hub and a portion of the compressor discharge air that is utilized for component cooling, is re-routed to by-pass the engine's TOBI to flow into a manifold defined by the stator support structure and a foot of the first turbine vane to the inner diameter platform of the first turbine vane of the high pressure turbine section to cool the aft end thereof before being discharged into the engine's main gaseous stream.

Abstract: A turbine component having a surface provided with a heat transfer enhancement feature formed therein that includes at least one linear surface concavity comprised of plural overlapped surface concavities.

Abstract: A combined cycle gas turbine system is improved to enhance a gas turbine efficiency and a combined efficiency by effecting steam-cooling of a combustor transition piece and a turbine blade. The combined cycle system has a gas turbine (8) having a generator (1), a compressor (2), a combustor (3), a blade cooling air cooler (4) and a turbine (6), a steam turbine (29) having a high pressure turbine (21), an intermediate pressure turbine (22) and a low pressure turbine (23), and a waste heat recovery boiler (9). Saturated water of a high pressure pump (27) is partially led into a demineralizer (118) and a water sprayer (116) for cooling steam to be supplied into a moving blade (52). The steam, after being used for cooling, is recovered into a reheater (20). Outlet steam of the high pressure turbine (21) is led into a stationary blade (53) for cooling thereof and the steam is then recovered into an inlet of the intermediate pressure turbine (22).

Abstract: A gas turbine with reheat in the turbine section includes a fuel injection device for the injection of fuel in to a combustion air flow in the direction of flow before a cooling air flow branching. By way of the early mixing of fuel in the combustion air flow and concomitant additional use of the cooling air flow as combustion air, the specific output and the efficiency of the gas turbine are improved.

Abstract: A gas turbine engine rotor has a body and blades, which are attached to the rotor by a root portion, for receiving a hot fluid flow and a compressed fluid from a compressor. Each blade has a base portion, an external airfoil surface, a blade flow portion of the airfoil, and a passage system communicating with the compressor and with the blade flow portion to create a thermal insulating boundary between the heated fluid and the external airfoil surface. The rotor has a substantially planar platform member, extending substantially transversally to the body of the blade and having an upstream portion protruding in the direction toward the combustion zone. The platform member has at least a pair of openings on either side of the airfoil, the openings being positioned in series along the blade flow portion. One opening of the pair defines an inclined passage in the platform member, and the other opening is separated by a partition from the first opening.

Abstract: A gas turbine (5) according to the invention, which comprises a main combustion chamber (10), a cooling system for air cooling of at least the guide vanes (26, 29) and guide rings (28, 38) of various stages (25, 27) of the gas turbine (5), and a main gas passage, also includes a further combustion chamber (34), which is arranged downstream of the main combustion chamber (10) as seen in the hot-gas main direction (H). The cooling air (15) used to cool a stage (25) of the gas turbine which is arranged upstream of the further combustion chamber (34) is fed into this further combustion chamber (34). In this context, it is particularly advantageous for the cooling air (15) used to cool the various stages (25, 27) of the gas turbine (5) to be fed for combustion. This makes it possible, inter alia, to increase the output of the gas turbine (5) without having to increase the supply of fuel.

Abstract: A combined cycle gas turbine system is improved to enhance a gas turbine efficiency and a combined efficiency by effecting steam-cooling of a combustor transition piece and a turbine blade. The combined cycle system has a gas turbine (8) having a generator (1), a compressor (2), a combustor (3), a blade cooling air cooler (4) and a turbine (6), a steam turbine (29) having a high pressure turbine (21), an intermediate pressure turbine (22) and a low pressure turbine (23), and a waste heat recovery boiler (9). Saturated water of a high pressure pump (27) is partially led into a demineralizer (118) and a water sprayer (116) for cooling steam to be supplied into a moving blade (52). The steam, after being used for cooling, is recovered into a reheater (20). Outlet steam of the high pressure turbine (21) is led into a stationary blade (53) for cooling thereof and the steam is then recovered into an inlet of the intermediate pressure turbine (22).

Abstract: A gas turbine plant comprises an air compressor, gas turbine turbine including at least one high temperature section, a driven equipment, which are operatively connected in series, a gas turbine combustor arranged between the air compressor and the gas turbine, a fuel system disposed for supplying a fuel to the gas turbine combustor, and a heat exchange section for heating the fuel from the fuel by means of a high pressure air as a heating medium fed from the air compressor.

Abstract: Air intake temperature in a gas turbine is regulated by a heat exchange fluid having a low viscosity at low temperatures. The circulated heat transfer fluid preferably comprises an alkali metal formate, most preferably potassium formate. The potassium formate may be blended with other alkali metal formate(s), with alcohol, glycols, salt brines, or any combination of glycols, alcohols, Sodium Nitrite, Sodium Nitrates, Potassium Chloride, Sodium Chloride, water and/or or other salt brines.

Abstract: Combined cycle gas turbine system is improved to enhance a gas turbine efficiency and a combined efficiency by effecting steam-cooling of a combustor transition piece and a turbine blade. In a combined cycle system comprising; a gas turbine (8) having a generator (1), a compressor (2), a combustor (3), a blade cooling air cooler (4) and a turbine (6); a steam turbine (29) having a high pressure turbine (21), an intermediate pressure turbine (22) and a low pressure turbine (23); and a waste heat recovery boiler (9), saturated water of a high pressure pump (27) is partially led into a demineralizer (118) and a water sprayer (116) for cooling steam to be supplied into a moving blade (52) and the steam, after used for the cooling, is recovered into a reheater (20). Outlet steam of the high pressure turbine (21) is led into a stationary blade (53) for cooling thereof and the steam is then recovered into an inlet of the intermediate pressure turbine (22).

Abstract: Cooling systems with liquid for gas turbine engines use the relative motion of the engine stator with respect to the rotor for actuating the coolant pump. The cooling system is completely encapsulated within the engine rotor. The cooling system includes a tank containing the cooling liquid, a coolant pump coupled to the tank to extract the cooling liquid from the tank, a system of ducts and channels extending in the rotor shaft, and rotor disks and rotor blades, where the heat exchanger is positioned either in the compressor drum, or in the end of compressor section.

Abstract: In a turbine (1) having a moving-blade row which has a moving blade (12) on a turbine shaft (8), and having a guide blade (14) which has a guide-blade row, an especially high efficiency is to be achieved with simple means with the turbine blades (12, 14) being cooled in a reliable manner. To this end, the cooling-medium passage inside the guide blade (14), according to the invention, is split up into a first and a second partial-flow passage, the cooling medium flowing in the first partial-flow passage being used for cooling the guide blade (14), and the cooling medium flowing in the second partial-flow passage being passed on more or less free of losses.

Abstract: A gas turbine engine cooling system for providing cooling air to engine components includes a core engine and, in downstream serial flow relationship, a high pressure compressor, a combustor, and high pressure turbine. A first flowing system is used for flowing a portion of the pressurized air to a heat exchanger to cool the pressurized air and provide the cooling air and a second flowing system is used for flowing a first portion of the cooling air to a compressor impeller operably connected to a compressor disk of the high pressure compressor for boosting pressure of the first portion of the cooling air. A second portion of the cooling air is supplied to turbine cooling. The heat exchanger may be a fuel to air heat exchanger for cooling the portion of the pressurized air from the first flowing means with fuel.

Abstract: A combined cycle system includes a gas turbine (8) having a generator (1), a compressor (2), a combustor (3), a blade cooling air cooler (4), a fan (5), and a turbine (6); a steam turbine (29) having a high pressure turbine (21), an intermediate pressure turbine (22), and a low pressure turbine (23); and a waste heat recovery boiler (9). Saturated water from a high pressure pump (27) is partially led into a heat exchanger (110) for cooling steam to be supplied into a moving blade (52) and a stationary blade (53). Also, outlet steam from the high pressure turbine (21) is led into the moving blade (52), the stationary blade (53), and the combustor transition piece (54) for cooling thereof, and the steam is then supplied to an inlet of the intermediate pressure turbine (22). Further, the outlet steam from the high pressure turbine (21) is led into the turbine (6) for cooling blades thereof.

Abstract: This invention relates to an arrangement for the cooling of the casing 1 of an aircraft gas turbine with a bypass duct 2 and at least one cooling air tube 3, this cooling air tube 3 having its inlet 4 arranged in the bypass duct 2 and entering at least one cooling air chamber 5 for the supply of cooling air to the casing 1, characterized in that a movable air deflector 6 is arranged in the bypass duct 2 upstream of the inlet 4 of the cooling air tube 3.

Abstract: An operation method for a combined plant can simplify the steam lines and also decrease the cost for manufacturing combined plants as well. The combined plant comprises a gas turbine plant and a steam turbine plant; the steam turbine plant comprising a steam drum for generating steam and supplying the steam into a steam turbine, a condenser for condensing steam passing through the steam turbine, a steam turbine bypass line for connecting the upstream of the steam turbine and the condenser and bypassing the steam turbine; and a gas turbine steam cooling portion for cooling a hot portion of the gas turbine plant by steam supplied from the steam drum, and which is provided parallel to a pipe connecting the upstream of the steam turbine bypass line and the steam drum, wherein when the combined plant is in a normal operation mode, an amount of steam passing through the gas turbine steam cooling portion is adjusted by a valve which is provided in the steam turbine bypass line.

Abstract: A gas turbine having a rotor driver by a shaft with a cooling medium passageway therein has a heat shield pipe portion mounted inside the passageway which forms an air layer with a wall of the passageway to protect a bearing member metal supporting the shaft from the heat of a cooling medium and a seal shaft portion for forming a labyrinth seal to prevent leakage of the cooling medium are formed as one piece and constitute a heat shied seal pipe.

Abstract: An apparatus and method for steam cooling a gas turbine. An intermediate-pressure drum 106 of a recovery boiler supplies outlet steam, as a cooling steam, to a combustor 117 through a steam channel 116. The flow rate of steam guided into the combustor 117 is adjusted through opening or closing of a first flow control valve 120 by a controller 125 such that the pressure of the intermediate-pressure drum 106 becomes a set value set according to a load status of a gas turbine 101. A required amount of steam according to the load status of the gas turbine 101 is fed to the combustor 117. Thus, the flow rate of steam guided into the combustor 117 is controlled by adjustment of the existing first flow control valve 120 for maintaining the pressure of the intermediate-pressure drum 106 in a predetermined state, without the need to provide an expensive valve device in the steam channel 116.

Abstract: A gas turbine comprising a compressor, combustor and turbine further comprises (1) a cooling air system for supplying part of air compressed by a compressor to the high temperature section of the turbine, (2) a heater exchanger for exchanging heat of part of air compressed by the compressor, this heater being mounted on the cooling air system, and (3) a system for adjusting the air temperature downstream from the heater exchanger in conformity to the operation period of the turbine.

Abstract: An Advanced Cheng Combined Cycle engine is a combination of the Cheng Cycle or the Advanced Cheng Cycle and a combined cycle, and serves to further enhance the power generation capability of either the Cheng Cycle, the Advanced Cheng Cycle, or the combined cycle alone. A gas turbine is provided, having a turbine generating power, a compressor receiving power from the turbine, and a combustion chamber to which is input compressed air from the compressor along with fuel and combustion products for producing energy to drive the turbine, the gas turbine producing a hot stream gas. A heat recovery steam generator receives hot stream gas produced by the gas turbine and generates high-pressure steam therefrom. A steam turbine receives and is driven by high-pressure steam generated by the heat recovery steam generator. The steam turbine bleeds intermediate-pressure steam for cooling the turbine and for injection back into the combustion chamber of the gas turbine.

Abstract: A gas turbo set (1, 2, 3) is equipped with at least a cooling air system (20,21). Throttle points (22, 23) are arranged as throttling points in the cooling air flowpath, for the purpose of defining the cooling air mass flow. Said manifolds are bypassed by bypass lines (24). Means (25) are arranged in said bypass lines for adjusting the bypass mass flow. Thus, the cooling air mass flow can be varied without acting on the main cooling air flow as such.

Abstract: A gas turbine engine including in-line intercooling wherein compressor intercooling is achieved without removing the compressor main flow airstream from the compressor flowpath is described. In an exemplary embodiment, a gas turbine engine suitable for use in connection with in-line intercooling includes a low pressure compressor, a high pressure compressor, and a combustor. The engine also includes a high pressure turbine, a low pressure turbine, and a power turbine. For intercooling, fins are located in an exterior surface of the compressor struts in the compressor flowpath between the outlet of the low pressure compressor and the inlet of the high pressure compressor. Coolant flowpaths are provided in the compressor struts, and such flowpaths are in flow communication with a heat exchanger. In operation, air flows through the low pressure compressor, and compressed air is supplied from the low pressure compressor to the high pressure compressor.

Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

Abstract: The compressor discharge air that normally leaks from the high pressure compressor hub and a portion of the compressor discharge air that is utilized for component cooling, is re-routed to by-pass the engine's TOBI to flow into a manifold defined by the stator support structure and a foot of the first turbine vane to the inner diameter platform of the first turbine vane of the high pressure turbine section to cool the aft end thereof before being discharged into the engine's main gaseous stream.

Abstract: Cooling air system for reducing the thermal load on components in the turbine high-pressure region of gas turbines, having blades/vanes which respectively have a plurality of separate flow chambers for different airflows, and having cooling air guidance from the high-pressure region of the compressor into the blading of the high-pressure region of the turbine. Each of the highly loaded blades/vanes has a front flow chamber, at least one central flow chamber and a rear flow chamber. The cooling guidance includes at least one heat exchanger for a part of the cooling air and a flow connection from the heat exchanger to the front and to the rear flow chambers of each blade/vane, with the cooling air guidance to the central flow chamber of each blade/vane bypassing the heat exchanger.

Abstract: A combined cycle system includes a gas turbine (8) having a generator (1), a compressor (2), a combustor (3), a blade cooling air cooler (4), a fan (5), and a turbine (6); a steam turbine (29) having a high pressure turbine (21), an intermediate pressure turbine (22), and a low pressure turbine (23); and a waste heat recovery boiler (9). Saturated water from a high pressure pump (27) is partially led into a heat exchanger (110) for cooling steam to be supplied into a moving blade (52) and a stationary blade (53). Also, outlet steam from the high pressure turbine (21) is led into the moving blade (52), the stationary blade (53), and the combustor transition piece (54) for cooling thereof, and the steam is then supplied to an inlet of the intermediate pressure turbine (22). Further, the outlet steam from the high pressure turbine (21) is led into the turbine (6) for cooling blades thereof.

Abstract: The temperature and flow rate of steam introduced to a gas turbine and a combustor is controlled properly through mixing intermediate-pressure steam and high-pressure steam. Thus, two different requirements, i.e., adjustment of steam temperature and securing of a sufficient steam flow rate, can be satisfied simultaneously. As a result, it becomes possible to simultaneously achieve control of the clearance of the blade ring of the gas turbine by means of steam and cooling of the combustor by means of steam.

Abstract: A cooling air cooling system is selectively operable to reduce fuel gum deposits within the cooling system during gas turbine engine operations. The cooling system includes a recirculating loop that includes at least three heat exchangers in fluid communication with the recirculating loop. A first heat exchanger cools cooling air supplied to the gas turbine engine. A second heat exchanger cools fluid exiting the first of the heat exchangers with fan discharge air prior to the fluid entering the third heat exchanger. A third heat exchanger uses combustor main fuel flow to cool the fluid circulating in the recirculating loop.

Abstract: A cooling air cooling system operable to reduce fuel gum deposits within the cooling system when a gas turbine engine operates above a predefined percentage of rated engine power. The cooling system includes a recirculating loop including a plurality of heat exchanges in fluid communication with the recirculating loop. A first head exchange uses heat transfer fluid to cool cooling air used by the gas turbine engine. A second head exchange is a fluid-fuel head exchanger that uses combustor main fuel flow to cool the head transfer fluid circulating in the recirculating loop.

Abstract: A combined cycle power plant including a gas turbine plant, a heat recovery steam generator, and a steam turbine plant. The heat recovery steam generator includes a main stream side steam piping, a bypass side steam piping, a steam branching to branch a steam flowing from a former stage in the heat recovery steam generator into two steams, one as a main stream side steam and another as a de-superheating steam, and a steam merging portion to merge the main stream side steam superheated by the high pressure superheater and the de-superheating steam passed through the bypass side steam piping. The heat recovery steam generator is provided with a blocking prevention function to prevent blocking of the main stream side steam piping and the bypass side steam piping and a thermal stress generation protection function.

Abstract: Cooling air passages are formed in the wall of an exhaust casing connected to a turbine casing of a gas turbine. Low pressure air extracted from the low pressure stage of an air compressor of the gas turbine is supplied to the cooling air passage from the portion near the downstream end of the exhaust casing. Cooling air flows through the cooling air passage toward the upstream end of the exhaust casing and then flows into an annular cavity formed in the turbine casing near the portion corresponding to the last turbine stage. Therefore, the metal temperature of the exhaust casing near the upstream end (near the joint between the exhaust casing and the turbine casing) is lowered by the cooling air and, as cooling air of a relatively high temperature is supplied to the cavity in the turbine casing, the metal temperature of the turbine casing near the downstream end becomes higher than that provided by a conventional cooling system.

Abstract: A gas turbo set (1, 2, 3) is equipped with at least a cooling air system (20,21). Manifolds (22,23) are arranged as throttling points in the cooling air flowpath, for the purpose of defining the cooling air mass flow. Said manifolds are bypassed by bypass lines (24). Means (25) are arranged in said bypass lines for adjusting the bypass mass flow. Thus, the cooling air mass flow can be varied without acting on the main cooling air flow as such.

Abstract: A gas turbine for power generation operated at a turbine nozzle inlet temperature ranging from 1200 to 1650° C., which is improved to obtain a high heat efficiency by making disk blades and nozzles arranged in first to final stages from optimum materials and optimally cooling these disk blades and nozzles, and to obtain a combined power generation system using the gas turbine. The combined power generation system includes a highly efficient gas turbine operated at a turbine nozzle inlet combustion gas temperature ranging from 1200 to 1650° C., and a high pressure-intermediate pressure-low pressure integral type steam turbine operated at a steam inlet temperature of 530° C. or more, wherein the gas turbine is configured such that turbine blades, nozzles and disks are each cooled, and the blades and nozzles are each made from an Ni-based alloy having a single crystal or columnar crystal structure and disks are made from a martensite steel.

Abstract: A gas turbine has a cooling air system supplying air for cooling a high temperature part of the gas turbine and a spray air system supplying air for spraying fuel into a combustor and is formed so that a part of high-pressure air compressed by a gas turbine compressor is used as air of the cooling air system and spray air system, wherein a heat exchanger and a boost compressor are arranged downstream of the outlet of compressed air of the gas turbine compressor, and the boost compressor is composed of a parallel connection of a compressor driven by the turbine shaft and ae compressor driven by a driven source other than the turbine shaft, and pressurized air from the boost compressor is used as air for the cooling air system and the spray air system.

Abstract: A tube-type vortex reducer for the conduction of cooling air in a compressor 1 of a gas turbine with at least one radial secondary air tube 2 arranged in a disk interspace 3, includes a deflector arranged in a discharge area of the secondary air tube for the deflection of the secondary air flow into an axial direction or away from an axial direction.

Abstract: A gas turbine engine having a housing and an axially extending shaft journaled to the housing by two axially spaced apart bearings. The bearings are located along the shaft so as to define an overhung shaft portion. A rotating component such as a turbine wheel or compressor wheel is mounted on the overhung shaft portion and is concentric about the centerline (50) of the engine. An annular shroud (40) that is part of the housing is disposed about the rotating component, the annular shroud (40) being concentric about a centerline (60) radially offset from the engine (50).