Abstract: A combustor component of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat shield panel. The heat shield panel defines a bend and a microcircuit flow path within a thickness of the heat shield panel. The microcircuit flow path includes an inlet and an outlet radially outward of the inlet. The microcircuit flow path at the bend is positioned radially between the inlet and the outlet, and the microcircuit flow path follows the bend. A method of cooling a combustor of a gas turbine engine is also disclosed.

Abstract: The present disclosure is directed to a retention assembly for a stationary gas turbine component. The retention assembly includes a first stationary gas turbine wall having a first surface. A retention boss extends outwardly from the first surface. The retention assembly includes a second stationary gas turbine wall having a second surface. A retainer is positioned between the first and the second surfaces. The retainer includes a base wall positioned adjacent to the retention boss. A first sidewall extends outwardly from the base wall, and a second sidewall extends outwardly from the base wall. A first arm extends outwardly from the first sidewall, and a second arm extends outwardly from the second sidewall. Each of the first arm and the second arm includes a plurality of convolutions. At least one of the plurality of convolutions is in contact with the second surface.

Abstract: A liner panel for use in a gas turbine engine. The liner panel has a hot side and a cold side. The liner panel includes a rail extending from the cold side and a multiple of studs extending from the cold side. At least one of the multiple of studs extends from, in part, the rail.

Abstract: Aspects of the disclosure are directed to a system of an aircraft, comprising: at least one fairing, a liner, and an actuator configured to cause the at least one fairing to be translated relative to the liner in order to obtain a modulation of a metering area between the liner and the at least one fairing.

Abstract: A fan for a gas turbine engine is provided. The fan includes a plurality of fan blades, a disk, and a trunnion mechanism for attaching the fan blades to the disk. The disk can be formed of a plurality of individual disk segments, with the trunnion mechanism attaching one of the plurality of fan blades to a respective disk segment. A retention member is also provided. The retention member includes a means for catching a portion of the trunnion mechanism should a primary attachment system of the trunnion mechanism fail.

Abstract: A buffer air cooler system for gas turbine engines disposed in a bypass duct of the engine, includes a housing for containing the buffer air cooler therein and an inlet portion attached to the housing. In one embodiment, the inlet portion has a double-skin configuration in at least one region of a top, bottom and sides of the inlet portion.

Abstract: An apparatus for injecting premixed fuel and air through a center body and into the combustion zone of a gas turbine includes a fuel injector nozzle with a premix pilot nozzle having a plurality of premix passages in fluid communication with an air supply and a fuel supply that premixes air and fuel within the premix passages. The apparatus has either an active or passive fuel feed control. Fuel can be fed to the apparatus either conventionally or as a breech load circuit integrated into the oil cartridge. Fuel can be supplied passively via a fuel channel connecting the swozzle fuel plenum to the premix passages. Alternatively, fuel can be injected from the oil cartridge into the premix passages.

Abstract: An apparatus for discriminating ignition in a gas-turbine aeroengine is configured to discriminate that ignition occurred in a combustion chamber upon discriminating that a calculated high-pressure turbine rotational speed change rate at a detected high-pressure turbine rotational speed equal to or greater than a predetermined rotational speed threshold is equal to or greater than a predetermined rotational speed change rate threshold and that the change rate has been equal to or greater than the predetermined rotational speed change rate threshold continuously for a predetermined time period or longer, whereby whether or not ignition of an air-fuel mixture occurred in a combustion chamber can be accurately discriminated or determined without using a dedicated sensor or detector even when an EGT sensor or detector fails.

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a turbine engine component and a lubrication system. The lubrication system directs lubricant through the turbine engine component. The lubrication system includes a wash flow filter.

Abstract: The invention relates to a method for operation of a combined-cycle power plant with cogeneration, in which method combustion air is inducted in at least one gas turbine, and in which method the exhaust gas emerging from the at least one turbine is passed through a heat recovery steam generator (HRSG) in order to generate steam. The electricity production can be decoupled from the steam production in order to restrict the electricity production while the heat provided by steam extraction remains at a constant level. A portion of the inducted combustion air can be passed through at least one turbine to the HRSG without being involved in the combustion of the fuel in the gas turbine. This portion of the combustion air can be used to operate at least one supplementary firing in the heat recovery steam generator.

Abstract: Carbon dioxide is separated from natural gas using a single stage membrane separation system to produce a retentate gas that typically meets the specification for pipeline distribution of natural gas, and a permeate gas comprising methane that is combusted to generate power and/or heat, e.g. for use in providing the utility requirements of the process itself or for export to an integrated process. Advantages include an overall reduction in power consumption and improvement in process efficiency.

Abstract: A thrust reverser includes: a thrust-reversing element movable between a stowed position and a deployed position; at least one hydraulic actuator operably coupled to move the thrust-reversing element between the stowed and deployed positions; at least one hydraulic primary lock configured to transition, in response to a first activation pressure, between an engaged state, where movement of the thrust-reversing element is inhibited, and a released state, where movement of the thrust-reversing element is uninhibited; and a directional control unit fluidly coupled to the hydraulic actuator and the hydraulic primary lock, the directional control unit configured to transition from a first stage to a second stage in response to a second activation pressure that is greater than the first activation pressure, and where a transition from the first stage to the second stage by the directional control unit causes the hydraulic actuator to move the thrust-reversing element to the deployed position.

Abstract: A combustion chamber of a gas turbine having a head plate and a combustion chamber head, where the head plate is connected to the combustion chamber, and where several heat shields arranged in the interior of the combustion chamber are bolted to the head plate, characterized in that each heat shield and the combustion chamber head are fastened to the head plate by means of joint bolted connections.

Abstract: A method of managing a gas turbine engine includes the steps of detecting an airspeed and detecting a fan speed. A parameter relationship is referenced related to a desired variable area fan nozzle position based upon at least airspeed and fan speed. The detected airspeed and detected fan speed is compared to the parameter relationship to determine a target variable area fan nozzle position. An actual variable area fan nozzle position is adjusted in response to the determination of the target area fan nozzle position and at least one threshold.

Abstract: An air supply and conditioning system for an inlet system of a gas turbine includes an air processing unit having an inlet configured to receive compressed air from a compressor of the gas turbine. The air processing unit includes a heat exchanger that is downstream from the inlet. A vortex cooler is disposed downstream from the inlet of the air processing unit. The vortex cooler is in fluid communication with the heat exchanger and with an outlet of the air processing unit. The system further includes a self-cleaning filter that is disposed within a duct of the inlet system. The self-cleaning filter is in fluid communication with at least one of the outlet of the air processing unit or an outlet of the vortex cooler.

Abstract: The present disclosure concerns a thrust reverser for an aircraft turbojet engine nacelle including at least one movable thrust reverser cowling, a means for locking the cowling, an outlet nozzle having a variable cross-section that is arranged in the downstream extension of said cowling and that is movable, and at least one actuator that includes an actuating rod capable of moving the variable nozzle and the movable cowling, remarkable in that the reverser is provided with a passive coupler.

Abstract: A bearing assembly for a turbine engine includes a first gas bearing configured to receive a load from a rotating shaft of the turbine engine, a transmission disk configured to receive the load from the first gas bearing, and a damping member coupled to a casing of a combustor section of the turbine engine. The transmission disk includes a gas delivery disk, which includes an axial opening configured to facilitate an axial flow through the gas delivery disk and a duct configured to facilitate a radial flow through the gas delivery disk to form the first gas bearing. The damping member is configured to receive the load from the transmission disk.

Abstract: A fuel injector for a gas turbine engine may include a center body disposed about a longitudinal axis, and a premix barrel positioned radially outwardly from the center body to define an annular passageway between the center body and the premix barrel. The annular passageway may extend from an upstream end that is configured to be fluidly coupled to a compressor to a downstream end that is configured to be fluidly coupled to a combustor. The premix barrel may include a first portion at the upstream end and a second portion at the downstream end. The first portion may include a stainless steel material, and the second portion may include a nickel based superalloy material. The second portion may be coupled to the first portion by a laser clad coupling.

Abstract: A propulsive force imparted to an object is vectored using rotatable members arranged in one or more arrays disposed in the path of a fluid ejected by a fluid accelerator unit, such as air ejected by a fan driven by a gas turbine engine. The propulsive force is vectored by changing the rotation of one or more of the rotatable members.

Abstract: A thrust reverser of a turbofan engine has a translating structure and a blocker door device capable of diverting a bypass flowpath for reversing propulsion direction. The translating structure moves axially between a forward position and a rearward position and thereby drives a compound motion of a blocker door of the blocker door device that moves between respective stowed and deployed states. A passive linkage of the blocker door device is orientated between a stationary structure and the blocker door and may be utilized in combination with an extendable linkage that may be orientated between the blocker door and the stationary structure.