Abstract: A gas turbine engine includes a gas turbine and a plurality of combustors each in fluid communication with the gas turbine. The gas turbine engine includes a first seal disposed between the gas turbine and the plurality of turbine combustors. The first seal is configured to sealingly engage with the gas turbine and at least two of the plurality of turbine combustors. The gas turbine engine also includes a second seal disposed between the gas turbine and the plurality of turbine combustors. The second seal is configured to sealingly engage with the gas turbine and at least two of the plurality of turbine combustors.

Abstract: A method of starting a turbine engine, including a re-try performed if a main injector has not ignited when a shaft has reached a first predetermined speed value, the re-try including: a stopping during which a starter and the ignitor device are stopped; a second ignition during which fuel is injected into the combustion chamber, the ignitor device being actuated, the second ignition being performed when a speed of rotation of the shaft reaches a second predetermined speed value; and a second starting during which the starter is actuated once more to drive the shaft in rotation.

Abstract: A heat transfer assembly for controlling heat transfer of a turbine engine is provided. The turbine engine includes a housing and includes a compressor, a combustor and a turbine located within the housing. The heat transfer assembly includes a flow control device having a sidewall coupled to the turbine, the sidewall is in flow communication with a compressor vane. The sidewall is configured to define a first flow path from the compressor vane to a turbine vane and a second flow path from the compressor vane to a turbine blade. A heat exchanger is coupled to the housing and located between the compressor and the turbine, wherein the heat exchanger is in flow communication with at least one of the first flow path and the second flow path. A fluid supply device is coupled to the housing and in flow communication with the heat exchanger.

Abstract: A turbine engine includes a compressor section, a combustor section in fluid communication with the compressor section, a high pressure turbine in fluid communication with the combustor, a low pressure turbine in fluid communication with the high pressure turbine, and a mid turbine frame located axially between the high pressure turbine and the low pressure turbine. The mid turbine frame includes an outer frame case, an inner frame case, and a plurality of hollow spokes that distribute loads from the inner frame case to the outer frame case. The spokes are hollow to allow cooling airflow to be supplied through the spokes to the inner frame case.

Abstract: An end-wall component of the mainstream gas annulus of a gas turbine engine has a cooling arrangement including one or more circumferentially extending rows of ballistic cooling holes through which, in use, dilution cooling air is jetted into the mainstream gas to reduce the mainstream gas temperature adjacent the end-wall. A portion of the cooling holes are first cooling holes angled such that the direction of the dilution cooling air jetted therethrough has, on entry into the mainstream gas annulus, a component in one tangential direction. A portion of the cooling holes are second cooling holes angled such that the direction of the dilution cooling air jetted therethrough has, on entry into the mainstream gas annulus, a component in the opposite tangential direction. The first and second cooling holes are arranged such that the cooling air from jets having entry components in opposing tangential directions collide and coalesce.

Abstract: An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity.

Abstract: A fuel leak detection system for use in a turbine enclosure is provided. The system includes a ventilation duct extending through an interior cavity of the turbine enclosure such that an extended portion of the ventilation duct is positioned within a bottom portion of the turbine enclosure. The ventilation duct includes a plurality of openings configured to allow air from within the turbine enclosure to be drawn into the ventilation duct through the plurality of openings. The system also includes a sensor system coupled in flow communication with the air drawn into the ventilation duct, the sensor system configured to detect fuel in the air.

Abstract: Provided is a gas turbine including: a first compressor which compresses air; a mixer which adds the compressed air from the first compressor to fuel and generates a fuel mixture; a combustor which combusts the generated fuel mixture from the mixer; a plurality of flow meters which adjusts an amount of the air or the fuel injected into the mixer; and a control unit which maintains the Wobbe Index of the fuel mixture within a predetermined Wobbe Index range.

Abstract: A turbine engine includes a first fan including a plurality of fan blades rotatable about an axis and a reverse flow core engine section including a core turbine axially forward of a combustor and compressor. The core turbine drives the compressor about the axis and a transmission system. A geared architecture is driven by the transmission system to drive the first fan at a speed less than that of the core turbine. A second fan is disposed axially aft of the first fan and forwarded of the core engine and a second turbine is disposed between the second fan and the core engine for driving the second fan when not coupled to the transmission.

Abstract: A gas turbine including a compressor and a combustor, an SOFC including an air electrode (cathode) and a fuel electrode (anode), a first compressed air supply line adapted to supply a compressed air compressed by the compressor to the combustor, a second compressed air gas supply line adapted to supply a part of a compressed air compressed by the compressor to the air electrode (cathode), a first fuel gas supply line adapted to supply a fuel gas to the combustor, a second fuel gas supply line adapted to supply a fuel gas to the fuel electrode (anode), a fuel gas recirculation line adapted to return an exhausted fuel gas discharged from the fuel electrode (anode) to the fuel electrode (anode), a cooler provided in the fuel gas recirculation line are provided.

Abstract: An example gas turbine engine includes a turbine and first and second spools coaxial with one another. The first spool is arranged within the second spool and extends between forward and aft ends. The aft end extends axially beyond the second spool and supports the turbine. A housing is arranged downstream from the turbine. First and second bearings are mounted to the aft end of the first spool and supported by the housing portion.

Abstract: The present application and the resultant patent provide a gas turbine engine system. The gas turbine engine system may include a gas turbine engine, a water wash system, and a system controller. The gas turbine engine may include a compressor, a combustor in communication with the compressor, and a turbine in communication with the combustor. The water wash system may be in communication with the gas turbine engine and configured to remove contaminants therefrom. The water wash system may include a number of valves configured to control flows through the water wash system, and a number of sensors configured to measure operating parameters of the water wash system. The system controller may be in communication with the valves and the sensors and operable to automatically control the valves upon receiving operating parameter signals from the sensors in order to perform a wash of the gas turbine engine.

Abstract: Embodiments may include an actuation system for an exhaust nozzle of a gas turbine engine. The actuation system may comprise a plurality of flap assemblies including a plurality of convergent flaps movable between first and second convergent positions and a plurality of divergent flaps movable between first and second divergent positions. Each of the plurality of divergent flaps may extend from a respective one of the plurality of convergent flaps. The system may further include a first sync ring rotatably carried by an engine body and configured to synchronously move the divergent flaps between the first and second divergent positions and a second sync ring rotatably carried by the engine body and configured to synchronously move the convergent flaps between the first and second convergent positions. A method may translate rotation of the sync ring to movement of a vehicle surface between radially outward and inward positions.

Abstract: The burner includes a swirl chamber. The swirl chamber has a substantially conical shape defining a central axis. The swirl chamber is defined by a plurality of wall elements. A combination of nozzles at the pressure, suction side and trailing edge of the wall element are placed for fuel injection. The wall elements define slots between each other. The slots have different widths (w) in consecutive planes in the axial direction, wherein said planes are perpendicular to the central axis.

Abstract: An assembly includes a suspension pylon and a thrust reverser which has vanes for deflecting flow and a cowl able to move between an open position and a closed position by an actuator. The thrust reverser further includes rails able to slide in slideways. In particular, the actuator is disposed in line with a corresponding rail. The actuator may be an actuator having a rotating nut connected to an endless screw or an actuator suitable for pulling on the corresponding rail or on the corresponding slideway.

Abstract: The present application discloses a common purpose apparatus for carrying out physical and chemical reactions of carbonaceous materials with oxygen bearing gases and preheated gases that is used for carrying out thermo chemical transformation of carbonaceous materials into gaseous and liquid fuels, and for combusting carbonaceous fuels and to recover energy there from, and for remediating hydrocarbon-contaminated materials, and further for producing bio-chars from biomass.

Abstract: A combustor (10) includes a liner (12) that defines a combustion chamber (18) first pre-mix chamber (14) is upstream of the combustion chamber, and a fuel plenum (40) in fluid communication with the first pre-mix chamber surrounds a least a portion of the first pre-mix chamber. A method of supplying a fuel to combustor includes flowing the fuel over an outer surface of a first pre-mix chamber and into the first pre-mix chamber.

Abstract: An improved fastening system and method overcomes traditional thermal mismatch that occurs with standard fastener systems that are employed in extreme temperature environments. The fastening system could employ a metallic fastener that is combined with metallic spacer, each of which having a differing thermal growth coefficient. This arrangement may reduce thermal expansion by several orders of magnitude over the range of temperatures where the thermal fastener can be applied. Such an improved fastening system may be employed in gas turbine machines and in other locations where it is desirable to improve fastening of objects in extreme temperature environments.

Abstract: A borescope assembly includes a first borescope plug comprising a first perimeter geometry portion. Also included is a second borescope plug comprising a second perimeter geometry portion distinct from the first perimeter geometry portion. Further included is a first borescope hole comprising a first hole geometry portion corresponding to the first perimeter geometry portion of the first borescope plug. Yet further included is a second borescope hole comprising a second hole geometry portion corresponding to the second perimeter geometry portion of the second borescope plug.

Abstract: A heat recovery steam generator has a plurality of heat exchangers, including superheaters 28, 30, an evaporator 32 and an economizer 34, disposed in a duct 27 along the flow direction of an exhaust gas 25 from a gas turbine 14, and generates steam by utilizing the exhaust gas 25 from the gas turbine 14. The heat recovery steam generator includes: auxiliary combustors 50, 52, each disposed upstream of one of the heat exchangers, for heating the exhaust gas by means of burners; and an air supply device for supplying air to the burners of the auxiliary combustor 52 from the outside of the duct.