Abstract: A cross-sectional area (Dout) of a transition piece outlet is set within a range of 0.79£DoutDin£0.9, relative to a cross-sectional area (Din) of a transition piece inlet of a combustor, and in a first stage turbine nozzle of a turbine connected to the transition piece outlet, a size (Hin) in a radial direction between upstream ends of the inner shroud and the outer shroud has a same dimension as a size (a) in a radial direction of the transition piece outlet. In a combustor transition piece that is included in the combustor having a center line (S) arranged with an angle to an axial center (R) of a rotor of a gas turbine and that guides combustion gas to the turbine, a cross-sectional area is monotonously reduced from the transition piece inlet in which the combustion gas flows to the transition piece outlet from which the combustion gas flows out.

Abstract: Provided is a gas turbine combustor capable of reducing the size of a low-temperature air layer of pilot air formed between a pilot flame and a premixed flame and of improving the flame stability of the premixed flame. A gas turbine combustor, which is provided with a pilot burner that is provided at the center portion of a combustor main body formed in a cylindrical shape to form a pilot flame, and a plurality of main burners arranged so as to surround the outer periphery of the pilot burner to form a premixed flame, includes, as the ignition improving part, a channel blocking member that reduces the size of the low-temperature air layer of the pilot air formed between the pilot flame and the premixed flame.

Abstract: Provided is a gas turbine combustor capable of reducing the size of a low-temperature air layer of pilot air formed between a pilot flame and a premixed flame and of improving the flame stability of the premixed flame. A gas turbine combustor, which is provided with a pilot burner that is provided at the center portion of a combustor main body formed in a cylindrical shape to form a pilot flame, and a plurality of main burners arranged so as to surround the outer periphery of the pilot burner to form a premixed flame, includes, as the ignition improving part, a channel blocking member that reduces the size of the low-temperature air layer of the pilot air formed between the pilot flame and the premixed flame.

Abstract: In a gas-turbine combustion burner which is provided, at a distal end thereof, with a fuel spraying hole that sprays fuel into a combustion region formed inside a combustion cylinder of a gas-turbine combustor and in which a fuel flow path that guides the fuel, which is supplied from a fuel source, to the fuel spraying hole is formed in the interior thereof, the impedance of a fuel supply system that guides the fuel from the fuel source to the fuel spraying hole is set so that propagation of pressure fluctuations from the combustion region to the fuel supply system becomes an allowable level or less.

Abstract: A pilot nozzle, a gas turbine combustor and a gas turbine are provided with a nozzle main body having a fuel passage, a cover ring arranged at an outside of a front end-outer peripheral portion of the nozzle main body at a predetermined interval to form an inner air passage and capable of injecting air toward a front side of the nozzle main body, a plurality of nozzle tips that includes a fuel injection nozzle attached to a front end portion of the cover ring at a predetermined interval in a circumferential direction to communicate with the fuel passage and is able to inject fuel toward an outside of injection air from the inner air passage, and a swirling force application unit that applies a swirling force to air injected through the inner air passage.

Abstract: An object is to reduce a fluctuation in the gas-turbine output in a nozzle switching period. In the nozzle switching period during which a first nozzle group that has been used is switched to a second nozzle group that is going to be used, the amounts of fuel supplied through the first nozzle group and the second nozzle group are adjusted by using at least one adjustment parameter registered in advance, the adjustment parameter registered in advance is updated according to the operating condition of the gas turbine, and the updated adjustment parameter is registered as an adjustment parameter to be used next.

Abstract: Provided is a gas turbine combustor capable of reducing the size of a low-temperature air layer of pilot air formed between a pilot flame and a premixed flame and of improving the flame stability of the premixed flame. A gas turbine combustor, which is provided with a pilot burner that is provided at the center portion of a combustor main body formed in a cylindrical shape to form a pilot flame, and a plurality of main burners arranged so as to surround the outer periphery of the pilot burner to form a premixed flame, includes, as the ignition improving part, a channel blocking member that reduces the size of the low-temperature air layer of the pilot air formed between the pilot flame and the premixed flame.

Abstract: A fuel control method for a gas turbine with a combustor being formed of at least two groups of a pluralities of main nozzles for supplying fuel, and that supplies fuel from the main nozzles of all groups upon ignition of the combustor (S1), and supplies fuel from three main nozzles of a group A during subsequent acceleration of the gas turbine (S3). Because fuel is injected from a small number of the main nozzles during acceleration, the fuel flow rate per one main nozzle is increased, thereby increasing the fuel-air ratio (fuel flow rate/air flow rate) in a combustion region and improving the combustion characteristics. Accordingly, the generation of carbon monoxide and unburned hydrocarbon is reduced, whereby no bypass valve is required and manufacturing costs are reduced.

Abstract: A transition piece of a combustor which is sustainable even under conditions of more severe thermal environments is provided in the present invention. A transition piece of a combustor is provided with a cylindrical trunk main body, a cylindrical exit trunk part which is joined to the downstream end of the trunk main body and which cooperates with the trunk main body to constitute a trunk part, and an inner flange which extends from the downstream end part of the exit trunk part toward the outer periphery side of the exit trunk part. The exit trunk part and the inner flange are of an one-piece product. On the exit trunk part, there is formed a groove, and there is formed a cooling fluid passage which opens at the groove.

Abstract: A fuel control method for a gas turbine with a combustor being formed of at least two groups of a pluralities of main nozzles for supplying fuel, and that supplies fuel from the main nozzles of all groups upon ignition of the combustor (S1), and supplies fuel from three main nozzles of a group A during subsequent acceleration of the gas turbine (S3). Because fuel is injected from a small number of the main nozzles during acceleration, the fuel flow rate per one main nozzle is increased, thereby increasing the fuel-air ratio (fuel flow rate/air flow rate) in a combustion region and improving the combustion characteristics. Accordingly, the generation of carbon monoxide and unburned hydrocarbon is reduced, whereby no bypass valve is required and manufacturing costs are reduced.

Abstract: A pilot nozzle, a gas turbine combustor and a gas turbine are provided with a nozzle main body having a fuel passage, a cover ring arranged at an outside of a front end-outer peripheral portion of the nozzle main body at a predetermined interval to form an inner air passage and capable of injecting air toward a front side of the nozzle main body, a plurality of nozzle tips that includes a fuel injection nozzle attached to a front end portion of the cover ring at a predetermined interval in a circumferential direction to communicate with the fuel passage and is able to inject fuel toward an outside of injection air from the inner air passage, and a swirling force application unit that applies a swirling force to air injected through the inner air passage.

Abstract: A combustor-transition-piece guide jig is constituted by two rails, a fixing member, and a holding member. The fixing member is provided at one ends of the rails and attached to a combustor attachment port. The rails are inserted from the combustor attachment port toward inside of the combustor casing and fixed to the combustor attachment port by the fixing member. The rails come into contact with a combustor-transition-piece guiding part provided on a combustor transition piece to guide a movement of the combustor transition piece in one direction.

Abstract: The combustor of the present invention is provided with a combustor basket to which air A is supplied from outside, first nozzles which are installed in a plural number annularly along an inner circumference of the combustor basket to individually supply premixed gas M of the air (A) with a fuel (f) into the combustor basket, and a transition piece, a base end of which is connected to the combustor basket, and which burns the premixed gas (M) supplied from the first nozzles to form a flame front (F) which spreads to an outer circumference toward the leading end in an axial direction. Each of the first nozzles supplies the premixed gas (M) by changing the fuel concentration around the center axis of the first nozzle so that the flame front (F) is made uniform in temperature in the axial direction.

Abstract: An object is to provide a combustor that requires a small mounting space for an acoustic damper, that can achieve size reduction, and that can improve the ease of maintenance. A combustor (5) of the present invention includes a combustion cylinder (19) that defines a combustion area (23) therein and an acoustic damper (31) that has a damper cover having an acoustic-damper resonance space communicating with the combustion area (23). The damper cover is provided along the combustion cylinder (19) so as to extend in a direction intersecting an axial direction (L) of the combustion cylinder (19).

Abstract: Provided is a combustor connection structure in which a cross-sectional area (Dout) of a transition piece outlet is set within a range of 0.79?Dout/Din?0.9, relative to a cross-sectional area (Din) of a transition piece inlet of a combustor, and in a first stage turbine nozzle of a turbine connected to the transition piece outlet, a size (Hin) in a radial direction between upstream ends of the inner shroud and the outer shroud has a same dimension as a size (a) in a radial direction of the transition piece outlet. In a combustor transition piece that is included in the combustor having a center line (S) arranged with an angle to an axial center (R) of a rotor of a gas turbine and that guides combustion gas to the turbine, a cross-sectional area is monotonously reduced from the transition piece inlet in which the combustion gas flows to the transition piece outlet from which the combustion gas flows out.

Abstract: In order to reduce a manufacturing cost and a running cost, casings each housing a combustion oscillation detecting device are attached in an alternating manner to cross-flame tubes by which a plurality of combustors arranged annularly in a combustor casing are connected to each other.

Abstract: A transition piece of a combustor which is sustainable even under conditions of more severe thermal environments is provided in the present invention. A transition piece of a combustor is provided with a cylindrical trunk main body, a cylindrical exit trunk part which is joined to the downstream end of the trunk main body and which cooperates with the trunk main body to constitute a trunk part, and an inner flange which extends from the downstream end part of the exit trunk part toward the outer periphery side of the exit trunk part. The exit trunk part and the inner flange are of an one-piece product. On the exit trunk part, there is formed a groove, and there is formed a cooling fluid passage which opens at the groove.

Abstract: In a gas-turbine combustion burner which is provided, at a distal end thereof, with a fuel spraying hole that sprays fuel into a combustion region formed inside a combustion cylinder of a gas-turbine combustor and in which a fuel flow path that guides the fuel, which is supplied from a fuel source, to the fuel spraying hole is formed in the interior thereof, the impedance of a fuel supply system that guides the fuel from the fuel source to the fuel spraying hole is set so that propagation of pressure fluctuations from the combustion region to the fuel supply system becomes an allowable level or less.

Abstract: A gas turbine includes a combustor, a combustor casing formed in a cylindrical shape to house the combustor therein, and a combustor insertion hole, which is a hole formed on a side periphery of the combustor casing, where a size thereof in a direction orthogonal to a circumferential direction of the combustor casing is formed larger than that in the circumferential direction of the combustor casing, and when the combustor inserted into the hole, a member moved together with the combustor, and the hole are viewed from a moving direction of the combustor, the hole includes an entire external form of the combustor and the member moved together with the combustor.

Abstract: In a communicating structure between combustors that generates combustion gas inside pipe pieces and a turbine portion that generates a rotational driving force by making the combustion gas sequentially pass through a turbine stage formed of turbine stator vanes and turbine rotor blades, at least some of the first-stage turbine stator vanes closest to the combustor among the turbine stator vanes are disposed downstream of sidewalls of one pipe piece and another pipe piece that are adjacent to each other, and the distance from leading edges of the first-stage turbine stator vanes disposed downstream of the sidewalls of the pipe pieces to end portions of the sidewalls closer to the turbine portion is equal to or less than a spacing between an internal surface of the sidewall of the one pipe piece and an internal surface of the sidewall of the other pipe piece.