Abstract: A turbine or turbine system includes a compressor, a combustor, a turbine section, a diffuser with a parting line between two components, and a seal along the parting line. The seal includes a protrusion, a recess, and a flexible portion between the protrusion and the recess. The flexible portion has a bent cross-section perpendicular to the parting line. An outer surface of the bent cross-section contacts an inner surface of the recess. An inner surface of the bent cross-section contacts an outer surface of the protrusion. Sealing a parting line between two parts of a diffuser in a gas turbine system includes disposing a flexible portion between a protrusion and a recess of the two parts, contacting an outer surface of the bent cross-section with an inner surface of the recess, contacting an inner surface of the bent cross-section with an outer surface of the protrusion, and pressurizing the diffuser.

Abstract: A fuel injector for a gas turbine combustor includes side wall fuel injection bodies extending between opposite end walls. Each side wall fuel injection body defines a fuel plenum and includes an outer surface defining fuel injection ports in communication with the fuel plenum. One or more fuel injection bodies extending between the end walls are positioned between the side wall fuel injection bodies. Each fuel injection body defines a fuel plenum and includes an outer surface defining fuel injection ports in fluid communication with the fuel plenum. A conduit fitting coupled to the frame is fluidly connected to the respective fuel plenums. The fuel injection ports fluidly communicate with air flow paths defined between the fuel injection bodies and the side wall fuel injection bodies. A combustor for a gas turbine includes a liner and an axial fuel staging system with the present fuel injector.

Abstract: The present disclosure is directed to an end cover assembly for a combustor of a turbomachine. The end cover assembly includes an end cover and a bundled tube fuel nozzle assembly positioned downstream from the end cover. The bundled tube fuel nozzle assembly includes a plurality of fuel nozzle tubes. A flame detector sight tube couples to the end cover. The flame detector sight tube is aligned with one of the fuel nozzle tubes.

Abstract: A sealing arrangement for sealing between a first stage nozzle and a plurality of aft frames includes a first inner seal and a second inner seal which are circumferentially oriented and circumferentially aligned. A side seal is radially disposed between the first inner seal and the second inner seal. The side seal includes a first portion that is axially offset from the first inner seal and the second inner seal and a second portion abutting the first inner seal and the second inner seal. Also disclosed is an aft frame having a forward face and an aft face. The aft frame includes at least one side seal slot that extends along a side portion. A first portion of the side seal slot is axially offset from the aft face. A second portion of the side seal slot is axially and radially offset from the first portion.

Abstract: A thrust reverser for a turbojet engine nacelle includes movable cowls which move backward relative to a front frame under the action of an actuation system, thereby making flaps tilt, via a control mechanism, so as to substantially close the annular cold air flow path, and by opening cascades disposed around this flow path and which receive the cold air flow and return it forward. When the thrust reverser is closed, the cascades are partially integrated in the cowls, and the thrust reverser includes an actuation system which makes the cascades move backward along a stroke which is shorter than the stroke of the cowl.

Abstract: A flow conditioner in a combustor of a gas turbine comprises a body and a flow conditioning portion configured to be placed in an air path providing air flow to a combustion chamber, the flow conditioning portion including a plurality of holes tuned to a damping frequency to dampen a pressure fluctuation caused by combustion dynamics from the combustion chamber.

Abstract: Embodiments of emission reduction system including various embodiments of an emission filters for a power plant including a gas turbine are disclosed. The system includes: an emission filter; and a retraction system operably coupled to an exhaust passage of the gas turbine. The exhaust passage defines an exhaust path of exhaust from the gas turbine. The retraction system selectively moves the emission filter between a first location within the exhaust path and a second location out of the exhaust path. In a combined cycle power plant, the first location is upstream of a heat recovery steam generator (HRSG). The systems and filters described allow for temporary positioning of emission filter(s) just downstream of a gas turbine exhaust outlet, or upstream of an HRSG, where provided, for emission reduction at low loads or startup conditions, and removal of the emission filter(s) once operations move to higher loads.

Abstract: Embodiments of emission reduction system including various embodiments of an emission filters for a power plant including a gas turbine are disclosed. The system includes: an emission filter; and a retraction system operably coupled to an exhaust passage of the gas turbine. The exhaust passage defines an exhaust path of exhaust from the gas turbine. The retraction system selectively moves the emission filter between a first location within the exhaust path and a second location out of the exhaust path. In a combined cycle power plant, the first location is upstream of a heat recovery steam generator (HRSG). The systems and filters described allow for temporary positioning of emission filter(s) just downstream of a gas turbine exhaust outlet, or upstream of an HRSG, where provided, for emission reduction at low loads or startup conditions, and removal of the emission filter(s) once operations move to higher loads.

Abstract: Embodiments of emission reduction system including various embodiments of an emission filters for a power plant including a gas turbine are disclosed. The system includes: an emission filter; and a retraction system operably coupled to an exhaust passage of the gas turbine. The exhaust passage defines an exhaust path of exhaust from the gas turbine. The retraction system selectively moves the emission filter between a first location within the exhaust path and a second location out of the exhaust path. In a combined cycle power plant, the first location is upstream of a heat recovery steam generator (HRSG). The systems and filters described allow for temporary positioning of emission filter(s) just downstream of a gas turbine exhaust outlet, or upstream of an HRSG, where provided, for emission reduction at low loads or startup conditions, and removal of the emission filter(s) once operations move to higher loads.

Abstract: Embodiments of emission reduction system including various embodiments of an emission filters for a power plant including a gas turbine are disclosed. The system includes: an emission filter; and a retraction system operably coupled to an exhaust passage of the gas turbine. The exhaust passage defines an exhaust path of exhaust from the gas turbine. The retraction system selectively moves the emission filter between a first location within the exhaust path and a second location out of the exhaust path. In a combined cycle power plant, the first location is upstream of a heat recovery steam generator (HRSG). The systems and filters described allow for temporary positioning of emission filter(s) just downstream of a gas turbine exhaust outlet, or upstream of an HRSG, where provided, for emission reduction at low loads or startup conditions, and removal of the emission filter(s) once operations move to higher loads.

Abstract: Embodiments of emission reduction system including various embodiments of an emission filters for a power plant including a gas turbine are disclosed. The system includes: an emission filter; and a retraction system operably coupled to an exhaust passage of the gas turbine. The exhaust passage defines an exhaust path of exhaust from the gas turbine. The retraction system selectively moves the emission filter between a first location within the exhaust path and a second location out of the exhaust path. In a combined cycle power plant, the first location is upstream of a heat recovery steam generator (HRSG). The systems and filters described allow for temporary positioning of emission filter(s) just downstream of a gas turbine exhaust outlet, or upstream of an HRSG, where provided, for emission reduction at low loads or startup conditions, and removal of the emission filter(s) once operations move to higher loads.

Abstract: A gas turbine engine comprises a compressor driven by a shaft, and a reference starting schedule, the compressor having a reference stability boundary, with the reference starting schedule defining a reference working line. A method of starting the gas turbine engine is described in which the method comprises the steps of: (i) accelerating the rotational speed of the shaft towards an engine idle speed; (ii) defining for the compressor, as the rotational speed increases, an operational working line; and (iii) modifying at least one operating parameter of the gas turbine engine as the rotational speed increases such that for a rotational speed, an operational working line is closer to the reference stability boundary than the reference working line is to the reference stability boundary.

Abstract: A gas turbine engine includes a platform that has a gas path side, a non-gas path side, a first mate face, and a second mate face. The second mate face has a beveled edge sloping towards the first mate face. The gas turbine engine also includes a coverplate that includes a first bend, a flat portion substantially parallel to the first mate face and a first wing substantially parallel to the second mate face.

Abstract: A gas turbine combustor assembly includes a primary combustion chamber in fluid communication with a primary fuel injector and a primary air inlet. A torch igniter is carried by the primary combustion chamber, and includes an auxiliary combustion chamber housing comprising a mixing chamber and a throat region converging downstream of the mixing chamber. An air swirler including a plurality of swirl openings surrounding an outlet of an auxiliary fuel injector is coupled to the auxiliary combustion chamber proximate the mixing chamber. An ignition source projects into the mixing chamber of the auxiliary combustion chamber.

Abstract: Systems and methods for regulating fuel flow to a gas turbine engine are provided. Power for the engine is governed using a control structure having an inner control loop and an outer control loop, the outer control loop comprising a feedback controller that outputs a feedback command based on a power error determined as a function of a shaft horsepower, the feedback command used to determine a gas generator speed error, the gas generator speed error used by the inner control loop for outputting a fuel flow command. The shaft horsepower is determined from a torque measurement of the engine using a torque pressure transducer. When a momentary loss of the torque measurement from the torque pressure transducer is detected, power fluctuations due to the loss of torque measurement are limited by maintaining the feedback command from the feedback controller constant during the momentary loss of torque measurement.

Abstract: A combustor including a combustor main body having a transition piece that defines a flow channel therein, and a combustor basket inserted in the transition piece from an upstream side of the flow channel that defines a gap through which a film air is sent with an inner peripheral surface of the transition piece; a connecting pipe disposed upstream of an outlet of the gap that connects to the combustor main body from an outer peripheral side and communicates with the flow channel via a connection hole; and a flow guide disposed at an identical position to the outlet of the gap on a downstream side of a connecting portion of the connecting pipe and the combustor main body that guides a compressed air introduced from outside the connecting pipe so that a flow rate distribution is made uniform in a circumferential direction of the combustor main body.

Abstract: A fuel injector (10) such as an injector for an annular combustion chamber of a turbine engine, comprising a downstream head (16) having a central outlet (22) and an annular peripheral outlet (24) surrounding the central outlet (22), and an injector arm (12) upstream of the head (16) comprising coaxial central channel (18) and annular channel (20), characterised in that the central channel (18) is in fluid communication with the peripheral outlet (24) and the annular channel (20) is in fluid communication with the central outlet (22).

Abstract: A retention device includes a retention block including an opening extending through the retention block in a first direction. A tab also extends from the retention block in the first direction. A fastener extends through the opening and includes a head configured to engage the retention block. A clinch nut is coupled to the fastener with an interface surface of the clinch nut configured to engage the tab of the retention block.

Abstract: A combustor according to the present invention is provided with: a pilot burner (15) disposed along an axis (P); a plurality of premixing burners (16), each of which has a premixing swirler cylinder (19) and a premixing nozzle (20) disposed inside the premixing swirler cylinder (19) and that are disposed about the axis (P) in the circumferential direction so as to surround the periphery of the pilot burner (15); a substrate (23) through which the pilot burner (15) and the premixing swirler cylinders (19) are individually inserted so as to be supported therein; and stagnation eliminating blocks (27) that are provided so as to fill spaces between the premixing swirler cylinders (19) on a surface of the substrate (23) on the downstream side, wherein air film supplying ports (38) that form air films A on surfaces of the stagnation eliminating blocks (27) are formed in the stagnation eliminating blocks (27).

Abstract: A control device is configured to control a gas turbine that is configured to compress a suctioned air with a compressor to obtain compressed air, mix a fuel supplied from a combustor with the compressed air to burn the fuel and the compressed air to generate a combustion gas, operate a turbine with the combustion gas to rotate a rotor, and discharge the combustion gas that has operated the turbine as a flue gas. The compressor includes an inlet guide vane which is capable of adjusting a degree of opening and is on an air-suction side, and the control device is configured to execute temperature adjustment control to control the degree of opening of the inlet guide vane along a temperature adjustment line indicating an upper limit temperature of a flue gas temperature defined according to a load of the gas turbine.