Abstract: A combustion control system for a turbine engine is disclosed. The combustion control system includes a fuel injector having a main fuel supply and pilot fuel supply coupled to a combustor of the turbine engine. The combustion control system also includes a sensor coupled to a transfer tube. The transfer tube is fluidly coupled to the combustor, and the sensor is configured to detect a pressure pulse in the combustor. A semi-infinite coil is also coupled to the transfer tube. The combustion control system also includes a controller electrically connected to the sensor. The controller is configured to compare an amplitude of the pressure pulse within a frequency range to a threshold amplitude, and adjust the pilot fuel supply in response to the comparison.

Abstract: A system and method for modifying the supply of fuel to injectors to attenuate combustion oscillations in a gas turbine engine. The gas turbine engine may comprise a combustor, a plurality of injectors and a manifold. The plurality of injectors may be operable to provide fuel to the combustor. The manifold may be configured to supply fuel to all of the plurality of injectors or to only a portion of the plurality of injectors in reaction to a determination of an existence of combustion oscillations.

Abstract: A computer-implemented method is provided for determining a corrective action. The method may include obtaining diagnostic data and calculating, using the diagnostic data, a prognostic. The method may also include retrieving, when the prognostic is above an alarm level, historical records and calculating a Bayesian posterior probability using the diagnostic data and the historical records. Further, the method may include calculating a prognostic prescience metric using the diagnostic data and the historical records and determining, based on the Bayesian posterior probability, the prognostic prescience metric, and an economic calculation, the corrective action.

Abstract: An exhaust treatment system is provided. The system may include a particulate trap configured to remove one or more types of particulate matter from an exhaust flow, the exhaust flow including at least a portion of a totality of exhaust gases produced by an engine. The system may further include a burner assembly configured to increase a temperature of gases in the exhaust flow at a location upstream from the particulate trap. The burner assembly may include an exhaust inlet oriented in a direction along a first axis and configured to direct the exhaust flow into the burner assembly and an exhaust outlet oriented in a direction along a second axis at an angle relative to the first axis, the exhaust outlet being configured to direct the exhaust flow out of the burner assembly toward the particulate trap.

Abstract: A combustor liner assembly includes a liner assembly, including a hot dome, a hot wall, and an impingement shield. The liner assembly further includes a convector assembly. The combustor liner assembly further includes an impingement dome assembly, including a ring-shaped portion defining a plurality of apertures configured to receive a plurality of fuel injectors, and a face. The ring-shaped portion and the face define an annular passage, and the face defines a plurality of apertures and a plurality of orifices. The convector assembly and the impingement dome assembly are operably coupled to one another, and the plurality of orifices of the face are configured such that the hot dome is exposed to air flowing in the annular passage of the impingement dome assembly. The combustor liner assembly is configured to provide flow communication between the annular passage of the impingement dome assembly and the plurality of fuel injectors.

Abstract: A power system includes a gas turbine engine. The gas turbine engine may include a first portion, a second portion, and a longitudinal axis. The power system may also include a first moveable support engaged to the first portion of the gas turbine engine. The first moveable support may be operable to at least partially constrain movement of the first portion of the gas turbine engine during operation of the gas turbine engine. Additionally, the first moveable support may be operable to at least partially support the first portion of the gas turbine engine as the first portion of the gas turbine engine is moved away from the longitudinal axis independently of the second portion of the gas turbine engine.

Abstract: A combustor includes a first wall, a second wall, an injector grommet, a combustor longitudinal axis, and a connection assembly indirectly connecting the first wall to the second wall. A portion of the injector grommet is disposed within a groove of the connection assembly.

Abstract: A method of correlating thermal sensors data with temperature sensor data is disclosed. The method may include generating one or more temperature sensor data points and receiving the one or more temperature sensor data points at a remote location. The method may also include generating one or more thermal sensor data points or images and receiving the one or more thermal sensor data points or images at the remote location. Additionally, the method may include correlating the one or more thermal sensor data points or images based on the one or more temperature sensor data points and generating a notification when a temperature of one or more correlated thermal sensor data points or images fails to maintain a determined relationship with a preset limit in one or more locations other than the location of one or more temperature sensor data point.

Abstract: A splash plate dome assembly for a combustion liner of a turbine engine is disclosed. The splash plate may include an outer periphery having a plurality of corners and an inner periphery defining an aperture and an annular flange. The splash plate may include a plurality of first flow guides extending from the outer periphery to the inner periphery. The splash plate may further include a plurality of second flow guides extending from the outer periphery to a location intermediate the inner periphery and the outer periphery. The splash plate, annular flange, first flow guides, and second flow guides may be integrally formed by casting. The splash plate may be mounted to a combustion dome having a plurality of distributed through holes for forming impingement jets on an upstream face of the splash plate.

Abstract: A fuel nozzle for a turbine engine is disclosed. The fuel nozzle has a common axis, a body portion disposed about the common axis, a barrel portion located radially outward from the body portion. The fuel nozzle also has at least one swirler vane disposed between the body portion and the barrel portion and a liquid fuel jet disposed within the at least one swirler vane. The at least one swirler vane is configured to radially redirect an axial flow of air. The liquid fuel jet is configured to inject liquid fuel in a radial direction relative to the common axis.

Abstract: A method of attaching an air duct to a recuperator core may include welding a pair of butterpasses along a length of each of a plurality of core portions, connecting the plurality of core portions to one another to form the recuperator core and a pair of butterpasses extending along a length of the recuperator core, and attaching the air duct to the recuperator core along at least a portion of the pair of butterpasses. The method may also include controllably moving a welding torch into the air duct and along substantially the length of the recuperator core and controllably welding each butterpass to the air duct along substantially the length of the recuperator core without adding metal to the weld.

Abstract: A recuperator core has a plurality of passages sealingly formed therein. In use, a fluid passes through a respective one of the plurality of passages under pressure. The recuperator core must be tested to determine an operational efficiency or leakage within the respective plurality of passages. A pair of sealing mechanisms are positioned at a respective one a pair of ends of the respective one of the plurality of passages. A pressure or a vacuum is pulled across the respective ones of plurality of passages and a rate of leakage or decay rate is monitored to define an operational recuperator core and a failed recuperator core.

Abstract: A primary surface recuperator is made from a plurality of components, one of such components being a primary surface sheets. The primary surface sheet is used to transfers heat from a donor fluid to a recipient fluid. A first sheet portion of the primary surface sheet has a pair of sides and has a preestablished thermal deformation characteristic including a resistance to high temperature deformation and a high temperature resistance to corrosion. A second sheet portion has a pair of sides and has a preestablished thermal deformation characteristic being less than the resistance to high temperature deformation and the high temperature resistance to corrosion of the first sheet portion. The first sheet and the second sheet are attached at a respective one of the pair of sides of the first sheet portion and the second sheet portion forming an axis. The axis is positioned at an angle to the pair of sides.

Abstract: An apparatus for manufacturing a cell of a recuperator wherein the cell includes a plurality of primary surface sheets, a plurality of spacer bars and a pair of guide vanes. A fixture has a top portion and a bottom portion. The top portion is pivotably movable between an open or loading position and a closed or welding position. A plurality of the spacer bars, plurality of primary surface sheets and a pair of guide vanes are positioned in the fixture in a preestablished relationship and are fixedly attached one to another by a tack welding machine. A controller operative controls the tack welding machine.

Abstract: An inspection fixture and line is used to accurately determine the geometry and dimensional accuracy of a circular recuperator core. With the fixture and line inspection of a length, an inner diameter and an outer diameter of the circular recuperator core are completed. The method of using the fixture and the line further insures the concentricity of a donor inlet duct and a donor outlet duct.

Abstract: A system is disclosed to manufacture a recuperator core. The core is made up of a plurality of cells and an inner sealing member. A manufacturing system has an input end, an assembly station having a lower or inner chucking portion and an upper portion, and a welding station. The lower or inner chucking portion is movable between a lower position and an upper position and has a retracted position and an expanded position. The upper portion is movable between a loading position and a clamping position and is rotatable between a first position and a second position. The welding station performs a tack welding operation and a lineal welding operation.

Abstract: A method for aligning a circular core. The method has a work station which defines an inner chucking portion being movable between a lower position and an upper position and a retracted position and an expanded position. The work station defines an upper portion being movable between a first position and a second position and a loading position and a clamping position. The clamping position has a plurality of positions. The circular core being aligned during at least a portion of the plurality of positions. And, the work station having a welding station.

Abstract: Internal combustion engines produce a number of emissions including oxides of nitrogen, NOx. One manner of reducing NOx production used in gas turbine engines is through the use of catalytic reactors. Catalytic reactors reduce the ignition temperatures required for complete combustion of a fuel air mixture. However, high temperatures present in catalytic reactors cause sintering of the substrate, vaporization of the catalyst, and sintering of catalyst and metal substrate. The present invention is directed at controlling the temperature of a catalytic reactor in an internal combustion engine. An exothermic catalyst coats a first side of a substrate in the catalytic reactor. An endothermic catalyst coats a second side of the substrate.

Abstract: An assembly line for economically and efficiently assembling a core into a recuperator. The assembly line has an inlet end, an assembly station, a welding station, a control station and an outlet end. The inlet end has a plurality of the cores to be used for assembly thereat. The core is positioned within the assembly station and an assembly fixture locates a ducting structure in a preestablished relationship to the core. The control station using a plurality of sensors sends an input to a controller and the welding station performs a weld fixedly securing the ducting structure to the core.

Abstract: A fin folding machine has a base, a pair of vertical side support members extending from the base. A top support member is spaced from the base and is attached to the pair of vertical side support members. The base, pair of vertical side support members, and the top support member defining an opening therebetween. A plurality of tools are movably positioned within the opening. A bar has a plurality of sensors positioned therein abut a plurality of sides. The sensors send corresponding signals to a controller which monitors the position of the plurality of tools relative to a preestablished position. And, the plurality of tools are moved to the preestablished position. The sensors monitor the preestablished position of a depth and taper of a plurality of deep serpentine upper grooves and a plurality of deep serpentine lower grooves.