Abstract: The present disclose provides a method of manufacturing a turbine component for a gas turbine engine, comprising: forming, by a casting process, a primary component; forming, by an additive manufacturing process, a secondary component, wherein the secondary component comprises a main air passageway extending therethrough; assembling the primary component and the secondary component together to form the turbine component, wherein the main air passageway of the secondary component forms part of an internal air flow path through the turbine component.

Abstract: A turbine shroud segment, e.g. for a gas turbine engine, which is coolable by a supply of cooling air, e.g. from a gas turbine engine compressor. The turbine shroud segment has a segment casing that has a radially outer surface and a radially inner surface. The segment casing houses a main plenum, a first layer of impingement chambers, a second layer of impingement chambers, and a plurality of effusion passages. The first layer of impingement chambers fluidly communicates with the main plenum via transfer passages that are formed in the segment casing. The second layer of impingement chambers fluidly communicates with the first layer of impingement chambers via impingement passages that are formed in the segment casing. The effusion passages run between impingement chamber core surface, which is a radially inner surface of an impingement chamber, and the radially inner surface of the segment casing.

Abstract: A method for operating a generator set includes: operating the generator set in synchronized manner to a power grid, which includes: synchronizing a generator voltage with a grid voltage; matching a generator voltage frequency and/or a generator voltage phase with a grid frequency and/or a grid voltage phase; operating generator set in synchronization mode to synchronize the generator voltage phase with the grid voltage phase; operating an engine in a phase control mode with adjustment of an engine phase to change the generator voltage phase; transmitting the grid voltage phase to a phase regulator; regulating, by the phase regulator, the engine phase to a phase difference, which is created by a difference between the generator voltage phase and the grid voltage phase; and setting a phase parameter formed as the combustion control variable for torque-forming combustion setting of the engine, to adjust the engine phase subject to the phase difference.

Abstract: A method for operating a generator set includes: providing the generator set includes an internal combustion engine and a generator connected to an engine of the internal combustion engine in a torque-transmitting manner; specifying a generator set frequency and a generator set phase of a voltage of a power produced by the generator; adapting a torque-forming combustion control variable for the engine; operating the engine in a phase controlled mode by regulating an engine phase via a phase regulator to change a generator set phase, the engine phase being in a predetermined phase relationship with the generator set phase; setting the variable for adapting the engine phase to a target engine phase; determining an engine target phase by a target phase generator upstream of the phase regulator, subject to a calculated rotational reference system that describes a rotary motion of a fictitious inertia-increasing mass with a virtual stabilization speed.

Abstract: Disclosed is a fuel system for a gas turbine engine having a core exhaust and a combustion section. The system comprises a fuel pump for fluid communication with a fuel reservoir; a driving turbine for driving the fuel pump; and an air feed to drive the driving turbine, the air feed being fluidly connectable to the core exhaust of the gas turbine engine. Also disclosed is a fuel system comprising: a fuel pump for fluid communication with a fuel reservoir; a fuel line from the fuel pump for fluid communication with the combustion section of the gas turbine engine; and an air feed to a heat exchanger, the air feed being fluidly connectable to the core exhaust of the gas turbine engine, wherein the fuel line is in thermal communication with the air feed within a heat exchanger.

Abstract: An example stator tube assembly includes a hollow body defining a cavity and having a longitudinal length and a radial thickness. The hollow body is configured to be disposed within a stator housing and to separate the cavity from a stator cavity within the stator housing. The hollow body comprises a first radial thickness along a first portion of its longitudinal length and a second radial thickness along a second portion of its longitudinal length, the second radial thickness being greater than the first radial thickness.

Abstract: A method of electropolishing an internal passageway of a component, wherein the passageway has an inlet and an outlet; including: providing an electrode assembly including a flexible electrode, a shuttle and a guide cable extending between the flexible electrode and the shuttle; inserting the shuttle into the inlet; causing fluid to flow through the passageway to transport the shuttle through the passageway from the inlet towards the outlet; pulling the guide cable through the passageway to position the electrode in the passageway adjacent to a region of the passageway to be polished; and electropolishing the passageway using the electrode while moving the electrode within the passageway. Also, an electrode assembly for electropolishing an internal passageway of a component, including: a flexible electrode, a shuttle, and a guide cable extending between the flexible electrode and the shuttle.

Abstract: In some examples, systems and techniques for repairing or otherwise forming a blade of a bladed disk. In one example, a method including positioning a shield member around a perimeter of a partial blade extending from a rotor disk of a bladed disk, the shield member being positioned adjacent to a build surface of the partial blade; and depositing, with the shield member around the perimeter of the partial blade, a material on the build surface using an additive manufacturing technique to form a repaired portion on the build surface of the partial blade.

Abstract: A bleed air control system is configured to vary the air pressure at the inlet of a gas turbine engine. The bleed air control system includes a first gas turbine engine configured to provide bleed air, a second gas turbine engine acting as an auxiliary power unit, and a bleed air control system configured to selectively provide bleed air from the first gas turbine engine to the second gas turbine engine.

Abstract: A thermal management system for an aircraft comprises a first gas turbine engine, a first thermal bus, a first heat exchanger, and a chiller. The first thermal bus comprises a first heat transfer fluid, with the first heat transfer fluid being in fluid communication, in a closed loop flow sequence, between the first gas turbine engine, the first heat exchanger, and the chiller. Waste heat energy generated by the first gas turbine engine, is transferred to the first heat transfer fluid. The chiller is configured to lower a temperature of the first heat transfer fluid prior to the first heat transfer fluid being circulated through the gas turbine engine. The first heat exchanger is configured to transfer the waste heat energy from the first heat transfer fluid to a dissipation medium.

Abstract: A vane adjustment assembly includes a plurality of vanes, an annular ring coupled to the vanes, and a ring adjustment assembly. The ring adjustment assembly includes a first inclined plate and a second inclined plate, the first inclined plate having an inclined surface facing a first inclined surface of the second inclined plate. A roller pin is coupled to a second inclined surface of the second inclined plate opposite the first inclined surface. The second inclined plate is adjustable in the circumferential direction such that the inclined surface of the first inclined plate and the first inclined surface of the second inclined plate slide against each other during adjustment of the second inclined plate so as to adjust an axial position and a circumferential position of the roller pin relative to the annular ring.

Abstract: An inner cowl arrangement for a gas turbine engine includes a first hinge and a second hinge pivotally connecting a first cowl member and a second cowl member, respectively, to a mounting structure. The inner cowl arrangement further includes a latch detachably securing the first and second cowl members. At least one of the first hinge, the second hinge, and the latch includes a pressure relief component that deforms or breaks when an applied load on the pressure relief component due to a pressure within an engine core is greater a normal operating load, causing at least one of the first cowl member and the second cowl member to move relative to the engine core, and forming an opening.

Abstract: A rotary assembly for driving spool rotation includes a rotor and a flow modifier. The rotor is mechanically coupled to a spool of a gas turbine engine. The flow modifier receives flow from and/or direct flow to the rotor. The rotary assembly permits relative movement between the rotor and the flow modifier to move between: a turbine configuration wherein the rotor receives air from an external air source to drive the spool to rotate; and a compressor configuration wherein the rotor is driven to rotate by the spool and to receive and compress air from the gas turbine engine, and discharge the compressed air for supply to the airframe system. The rotary assembly also includes controller to control relative movement between the rotor and the flow modifier through a range of turbine positions of the turbine configuration to vary a torque applied to the rotor for driving the spool.

Abstract: A micromanipulator for mounting on the end of a macromanipulator, the micromanipulator comprising: a connection plate with a at least a first and second motor connected to a rigidly mounted base section, a first rotational section connected to the base section about a pivotable axis, the first rotational section being further connected to a slider rod which is connected to the first motor, and a second rotational section connected to the first rotational section about a pivotable axis, the second rotational section being further connected to a slider rod which is connected to the second motor and wherein the rotational joints between the base section and first joint section and the rotational joint between the first and second rotational sections are offset by 90°.

Abstract: A rotor assembly includes a first component, a second component, and a splined balance weight. The first component is arranged circumferentially around a central axis. The second component is arranged circumferentially around the central axis. The splined balance weight is located radially between the first component and the second component.

Abstract: A gas turbine engine for an aircraft comprises, in axial flow sequence, a compressor module, a combustor module, and a turbine module, with a first electric machine being rotationally connected to the turbine module. The first electrical machine is configured to generate a maximum electrical power PEM1 (W), and the gas turbine engine is configured to generate a maximum dry thrust T (N); and a ratio S of: S = ( Maximum ? Electrical ? Power ? Generated = P E ? M ? 1 ) ( Maximum ? Dry ? Thrust = T ) is in a range of between 2.0 and 10.0.

Abstract: In general, techniques are described for fused filament fabrication of abradable coatings. An additive manufacturing system comprising a substrate defining a major surface, a filament delivery device, and a computing device may be configured to perform various aspects of the techniques. The computing device may be configured to control the filament delivery device to deposit a filament on the substrate, the filament including a powder and a binder, wherein the binder is configured to be substantially removed from the filament and the powder includes a metal or alloy configured to be sintered to form an abradable layer.

Abstract: An article may include a substrate including a ceramic matrix composite (CMC); a composite coating layer including a first coating material that includes a rare-earth disilicate and a second coating material that includes at least one of a rare-earth monosilicate, a CMAS-resistant material, or a high-temperature dislocating material, where the second coating material forms a substantially continuous phase in the composite coating layer.

Abstract: In some examples, an electrical power system includes a solid state power converter including a first set of switches on a source side of the solid state power converter and a second set of switches on a load side of the solid state power converter. The electrical power system also includes a power source connected to the source side of the solid state power converter and also includes a differential bus connected to the load side of the solid state power converter. The electrical power system further includes a controller configured to receive a first signal indicating a current at the source side and receive a second signal indicating a current at the load side. The controller is further configured to detect, based on a time derivative of the first signal and a time derivative of the second signal, a fault in the electrical power system.

Abstract: The coil winding has an electrical conductor for an electrical machine and includes at least two layers. The electrical conductor, following its longitudinal extension, runs inwardly wound in a first of the at least two layers, and then extends to a second of the at least two layers and runs outwardly wound in the second layer. The electrical machine includes at least one such coil winding. The hybrid electric aircraft is in particular an airplane and includes such an electrical machine and/or at least one such coil winding.