Abstract: A combustor with axially staged fuel injection includes a plurality of nozzle segments annularly arranged about a center fuel nozzle. Each nozzle segment includes a fuel plenum partially defined between a forward plate and an aft plate and a plurality of tubes that extends through the fuel plenum and the aft plate. A panel fuel injector extends axially downstream from the aft plate and includes an outer wall, an inner wall, a plurality of outlets defined along at least one of the outer wall and the inner wall and a plurality of premix channels defined between the outer wall and the inner wall. Each premix channel is in fluid communication with a fuel supply, a compressed air supply and a respective outlet of the plurality of outlets.

Abstract: An exhaust system for reducing infrared emissions of a rotary wing aircraft includes a duct assembly having an inlet portion and an outlet portion; the inlet portion configured to receive exhaust from an engine of the aircraft; and the outlet portion coupled to the inlet portion, the outlet portion having an outlet duct with an outlet opening, the outlet duct configured expel an emission containing engine exhaust proximate to a tail fairing of the rotary wing aircraft.

Abstract: A solar chemically recuperated gas turbine system includes an exhaust-gas reformer, a solar reformer and a gas turbine unit with a combustion chamber. The reaction outlet of the exhaust-gas reformer is connected to the inlet of the solar reformer, the flue gas side inlet of the exhaust-gas reformer is connected to the exhaust-gas outlet of the gas turbine. The solar reformer outlet is connected to the combustion chamber inlet. Combustion gas drives the gas turbine after fuel burns in the combustion chamber, and the exhaust gas enters the exhaust-gas reformer. Fuel and steam are mixed and enter the reaction side of the exhaust-gas reformer through a fuel inlet. A reforming reaction between the fuel and steam under heating of the exhaust gas generates syngas. A further reforming reaction occurs by absorbing concentrated solar energy after the syngas enters the solar reformer, and the reactant is provided to combustion chamber.

Abstract: An assembly is provided for a turbofan engine. This turbofan engine assembly includes a cowling, a door and an actuation mechanism configured to actuate movement of the door in response to receiving a control signal. The cowling is configured to form a compartment at least partially around a case of the turbofan engine. The cowling includes an exhaust port that is fluidly coupled with the compartment. The door is configured to at least partially open and close the exhaust port. This variable exhaust port may be opened in case increased airflow is needed through the compartment, such as when increased cooling airflow is needed through an environmental air precooler that cools compressed air for the aircraft cabin and the precooler exhausts its cooling air into the compartment.

Abstract: The invention relates to a combustion chamber for a turbomachine, such as an aircraft turbojet engine or turboprop engine, comprising an internal annular shroud and an external annular shroud which at their upstream ends are connected by an annular chamber end wall (48), said chamber comprising deflectors (50) mounted upstream of the annular chamber end wall (48). Injectors (19) are mounted in sleeves (44) at least one of which comprises a radially annular flange (66) which is designed to slide radially between the chamber end wall (48) and the deflector (50) and which is blocked axially between the chamber end wall (48) and the deflector (50).

Abstract: A bulkhead assembly for a combustor of a gas turbine engine includes a bulkhead support shell with a multiple of swirler openings. Each of the multiple of swirler openings is surrounded by a first multiple of cooling impingement passages that define an angle ? with respect to a hot side of the bulkhead support shell and a second multiple of cooling impingement passages that define an angle ? with respect to the hot side of the bulkhead support shell. The angle ? is different than the angle ?.

Abstract: A gas turbine system includes a turbine combustor. The turbine combustor includes one or more first fuel injectors coupled to a head end of the turbine combustor and configured to deliver a first portion of a fuel to a first axial position of a combustion section of the turbine combustor. The turbine combustor also includes one or more second fuel injectors coupled to the turbine combustor axially downstream of the head end and configured to deliver a second portion of the fuel to a second axial position of the combustion section of the turbine combustor, the second axial position being downstream of the first axial position. The gas turbine system also includes a controller configured to deliver the first and the second portions of the fuel such that combustion of the fuel and oxidant within the overall combustion section of the turbine combustor is at a defined equivalence ratio.

Abstract: A method of actuating a hydraulic latch and a fan duct includes providing a pressurized fluid for actuating a latch, providing a valve to control flow of pressurized fluid to the latch and the fan duct, and selectively opening the valve, whereby the pressurized fluid opens the fan duct. A gas turbine engine includes a fan duct with an inner structure surrounding an engine core, a fan case surrounding a fan, and at least one latch. The at least one latch secures a first portion of the fan duct inner structure to a core engine fame or to a second portion of the fan duct inner structure. The at least one latch is also configured to secure the second portion of the fan duct inner structure to the core engine fame or to the first portion of the fan duct inner structure.

Abstract: A gas turbine engine includes a rotor section proximate to a combustor section, where the rotor section is subject to bowing effects due to thermal differences and heat transfer at engine shutdown. The gas turbine engine also includes a heat pipe system. The heat pipe system includes one or more heat pipes installed between an upper portion of the rotor section and a lower portion of the rotor section. The heat pipe system is operable to accept heat at a hot side of the heat pipe system at the upper portion, flow heat from the hot side to a cold side of the heat pipe system, and reject heat from the cold side of the heat pipe system at the lower portion to reduce a thermal differential between the upper portion and the lower portion at engine shutdown.

Abstract: An interface arrangement includes two annular components that extend along an axis and are in contact with one another and a third component that is positioned radially inward from at least one of the two components. There is an anti-rotation feature on one of the three components that engages an anti-rotation feature on an annular seal member. The seal member is in contact with the first two components and is positioned between the third component and at least one of the first two components.

Abstract: A fuel burner system (10) configured to inject a liquid fuel and a gas fuel into a combustor (12) of a turbine engine (14) such that the engine (14) may operate on the combustion of both fuel sources (20, 24) is disclosed. The fuel burner system (10) may be formed from a nozzle cap (16) including one or more first fuel injection ports (18) in fluid communication with a first fuel source (20) of syngas and one or more second fuel injection ports (22) in fluid communication with a second fuel source (24) of natural gas. The fuel burner system (10) may also include an oil lance (26) with one or more oil injection passages (28) that is in fluid communication with at least one oil source (30) and is configured to emit oil into the combustor (12). The oil lance (26) may include one or more fluid injection passages (32) configured to emit air to break up the oil spray and water to cool the combustor (12), or both.

Abstract: A turbine airfoil segment includes inner and outer platforms that are joined by at least one airfoil. The airfoil includes leading and trailing edges that are joined by spaced apart first and second sides to provide an exterior airfoil surface. At least one of the inner and outer platforms includes film cooling holes that have external breakout points that are located in substantial conformance with the Cartesian coordinates set forth in Table 1 for the inner platform or Table 2 for the outer platform. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate. The film cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.20 inches (5.0 mm).

Abstract: A staged fuel injector comprises a pilot inner air swirler arranged along a centre axis of the injector, a pilot fuel swirler arranged radially outboard of the pilot inner air swirler, a main inner air swirler arranged radially outboard of the pilot fuel swirler and a main fuel swirler arranged radially outboard of the pilot fuel swirler. A fuel feed arm is arranged in fluid communication with the pilot fuel swirler and the main fuel swirler for delivering fuel to the pilot fuel swirler and the main fuel swirler and a heat protective casing enclosing the fuel feed arm, the pilot fuel swirler and the main fuel swirler.

Abstract: A gas turbine engine includes a case having a wall that provides a cavity. The wall includes an aperture and a bore. A tube assembly with a flange provides a fluid passage aligned with the aperture. A flow diverter is arranged in the cavity and includes a plate with a hole. An insert has a body and a head. The body is received in the hole and press-fit in the bore. The head captures the plate against the wall. A fastener secures the flange to the insert and clamps the flow diverter to the case.

Abstract: The present disclosure relates to systems and methods useful for power production. In particular, a power production cycle utilizing CO2 as a working fluid may be combined with a second cycle wherein a compressed CO2 stream from the power production cycle can be heated and expanded to produce additional power and to provide additional heating to the power production cycle.

Abstract: Provided is an integrated coal gasification combined cycle equipped with: a gasifier that generates combustible gas from pulverized coal; a gas cooler; gas turbine equipment; an auxiliary fuel supply unit that supplies an auxiliary fuel to the gas turbine equipment; a heat recovery steam generator; steam turbine equipment; generators; and a circulation line unit that circulates cooling water. The heat recovery steam generator has a first medium-pressure coal economizer and a second medium-pressure coal economizer. When the combustible gas generated from the pulverized coal is burned, a serial heat exchange line is formed wherein cooling water passes through the first medium-pressure coal economizer, the second medium-pressure coal economizer, and the gas cooler. When the auxiliary fuel is burned, separate heat exchange lines are formed, wherein the cooling water separately passes through the first medium-pressure coal economizer and the second medium-pressure coal economizer.

Abstract: A combustion burner includes a nozzle, a swirl vane having a fuel injection hole, the swirl vane being disposed in an air flow passage of an annular shape extending along an axial direction of the nozzle around the nozzle, and a partition plate having an annular shape and partitioning at least a region of the air flow passage in a radial direction of the nozzle, so as to divide at least the region into an inner flow passage facing an outer peripheral surface of the nozzle and an outer flow passage disposed on an outer side of the inner flow passage with respect to the radial direction. The fuel injection hole is disposed in the outer flow passage of the air flow passage. An end portion on an upstream side of the partition plate is disposed upstream of the fuel injection hole in the axial direction.

Abstract: A combustion chamber assembly includes a combustion chamber casing, a combustion chamber, a plurality of fuel injectors and respective seals. The axis of each fuel injector head is arranged at an angle to the axis of the combustion chamber casing and parallel to the center line of the combustion chamber. Each seal is positioned between a fuel injector head and an aperture in an upstream wall of the combustion chamber. Each seal has an aperture extending through the seal which is arranged parallel to the axis of the combustion chamber casing or the flange of the fuel injector. Each fuel injector head has a part spherical surface located in a seal. The assembly provides a clearance required to engage, or disengage, a fuel injector head while minimizing the amount of material removed from the between the apertures in the upstream wall of the combustion chamber.

Abstract: In an embodiment of the invention, a dual-wall casing for a combustor comprises an outer wall and an inner wall defining a channel therebetween. The walls are fastened together by a bolt which extends from the inner wall and across the channel. In use, the inner wall is exposed to combustion products. Cooling is provided by a primary inlet hole extending through the outer wall and arranged upstream (with respect to the direction of flow of coolant in the channel) of the bolt and an array of effusion holes extending through the inner wall and positioned with their inlet in line of sight of the primary inlet hole. The primary inlet hole is sized with respect to the array of effusion holes such that it has a flow area which causes locally negligible flow restriction.

Abstract: A combustor is capable of ignition and flame propagation at low fuel concentrations for gas or liquid fuel. Combustors are disposed annularly along an outer peripheral portion of a casing of a turbine. A combustion chamber burns fuel and air to generate a combustion gas. A diffusion burner is disposed upstream of the combustion chamber; and a plurality of premix burners are disposed around the diffusion burner. Cross fire tubes provide communication between combustion chambers of combustors adjacent to each other. A cross fire tube connected to a combustor adjacent to a first side in the circumferential direction of the casing is disposed so as to have a central axis passing over a premix burner as viewed from the combustion chamber and another cross fire tube connected to the combustor adjacent to a second side is disposed so as to have a central axis passing between two premix burners.