Abstract: Provided is a combustor connection structure in which a cross-sectional area (Dout) of a transition piece outlet (222) is set within a range of 0.79?Dout/Din?0.9, relative to a cross-sectional area (Din) of a transition piece inlet (221) of a combustor (2), and in a first stage turbine nozzle (321) of a turbine (3) connected to the transition piece outlet (222), a size (Hin) in a radial direction of an upstream opening is matched with a size (a) in a radial direction of the transition piece outlet (222). In a combustor transition piece (22) that is included in the combustor (2) having a center line (S) arranged with an angle to an axial center (R) of a rotor (4) of a gas turbine and that guides combustion gas to the turbine (3), a cross-sectional area is monotonously reduced from the transition piece inlet (221) in which the combustion gas flows to the transition piece outlet (222) from which the combustion gas flows out.

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: 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 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: 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: 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 that generates rotational power by supplying fuel to compressed air compressed by a compressor and burning the fuel in a combustor and supplying resultant combustion gas to a turbine, a circumferential distance starting from a leading edge of a turbine first stage nozzle toward a trailing edge side of the first stage nozzle and ending at center of transition pieces of such combustors that are adjacent in a circumferential direction is set relative to a circumferential pitch of such first stage nozzles within a range of 0.05?S/P?0.15, and an axial distance between a leading edge of the first stage nozzle and a transition piece rear end of the combustor is set relative to the circumferential pitch of the first stage nozzles within a range of 0.00?L/P?0.13. By improving the relative position of a transition piece of the combustor and the first stage nozzle, both suppression of inner pressure fluctuations of the combustor and enhancement in aerodynamic efficiency can be achieved.

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: A gas turbine combustor includes a fuel supplying section and a combustion tube. The fuel supplying section supplies fuel to a combustion zone inside the combustion tube. The combustion tube passes combustion gas to the turbine. The combustion tube is provided with a first region where an air passage for cooling air is formed and a second region where a steam passage for cooling steam is formed. The second region is located downstream of the first region in a direction of a mainstream flow of the combustion gas.

Abstract: In order to reduce a manufacturing cost and a running cost, casings (22) each housing a combustion oscillation detecting device (21) are attached in an alternating manner to cross-flame tubes (17) by which a plurality of combustors arranged annularly in a combustor casing are connected to each other.