Abstract: An adaptor for a tungsten inert gas (TIG) welding gas block may include an adaptor body having a first end and a second end, wherein the first end includes a pair of parallel members separated by a receiving slot; the second end comprises a male twist lock post; the first end is configured to securely engage with the TIG gas block; and the second end is configured to engage with a welding lead.

Abstract: An assembly for a turbine engine having a longitudinal axis includes a first structural element and a nut device, the first structural element having a first hole and a second hole, and the nut device having a retainer fixed to an inner face of the first structural element, the retainer comprising at least a first recess and a second recess connected to one another by a connecting element, the first recess and the second recess each retaining a nut respectively aligned with the first hole and the second hole which are formed through the first structural element, the connecting element being, in whole or in part, adapted to compensate for a greater thermal expansion of the retainer than the thermal expansion of the first structural element.

Abstract: A turbomachinery installation for an offshore platform is disclosed. The turbomachinery installation comprises a train system having at least one preassembled power module, and a torque tube baseplate, on which the train system is installed. A supporting baseplate of the power module is coupled with the torque tube baseplate. Also disclosed is a method of assembling a turbomachinery installation.

Abstract: The BTT probe fixing apparatus includes a cooling sleeve inserted into a fixing hole formed in a vane carrier, the cooling sleeve accommodating a BTT probe measuring vibration of a blade therein, and the cooling sleeve having a lower end thereof fastened to the fixing hole. Furthermore, the BTT probe fixing apparatus includes a probe holder having a lower end fastened to a penetration hole formed in a casing and having an inner portion where the cooling sleeve penetrates therethrough and is inserted thereinto such that the cooling sleeve is capable of being slid in the probe holder, the probe holder being configured to move according to thermal expansion of the casing while maintaining the cooling sleeve and the BTT probe in a fixed position relative to the vane carrier.

Abstract: A misting nozzle assembly that includes a manifold having a fluid entry point and a plurality of ports formed therein each of which is fluidly connected to the fluid entry point. A plurality of nozzle is each adapted for attachment within a respective of the plurality of ports.

Abstract: A system for bleeding air from a compressor of an aircraft engine, the system comprises a bleed off valve and a plenum for receiving bleed air from the compressor via the bleed off valve. The plenum has a first outlet for discharging the bleed air from the plenum into the atmosphere, and a second outlet fluidly connected to the compressor for reinjecting a portion of the bleed air into an air intake portion of the compressor. A backflow valve is provided for selectively closing the first outlet of the plenum. The backflow valve has an actuator operable to displace a closure from a closed position to an open position upon a fluid pressure inside the plenum reaching a pressure threshold.

Abstract: An exhaust cone for an aircraft turbomachine, extending along a longitudinal axis and having a radially internal annular wall and a radially external skin delimiting a primary flow path for hot gases and surrounding the internal annular wall, and partitions mounted radially between the external skin and the internal annular wall and intersecting them in a manner that together with the skin and wall delimits acoustic chambers. The exhaust cone can further include at least one seal arranged between a radial end of one of the partitions and at least one among the internal annular wall and the external skin.

Abstract: An aircraft hybrid electrical propulsion (HEP) system includes an electrical system configured to deliver power to a plurality of electrical loads, a propulsion system configured to generate thrust in response to an input power, and an HEP controller in signal communication with the electrical system and the propulsion system. The HEP controller is configured to monitor a load demand of at least one electrical load among the plurality of electrical loads and to actively control the input power to actively control the thrust in response to changes in the load demand.

Abstract: A combustion engine including at least one combustion chamber, a first bleed air supply fluidly coupled to a portion of the combustion engine upstream the combustion chamber, a second bleed air supply fluidly coupled to a portion of the combustion engine downstream the combustion chamber, and a turbomachine comprising a first compressor, a second compressor, and a first turbine mounted to a common shaft, with the first and second compressors in serial flow arrangement. The turbomachine, further comprising an intercooler serially fluidly coupling a portion of the first compressor to a portion of the second compressor.

Abstract: A combustion system for a vehicle having an engine includes a hydrogen fuel system having a fuel source providing a hydrogen fuel, a combustor operable to combust the hydrogen fuel to generate combustion gases, and a fuel delivery assembly operable to deliver the hydrogen fuel from the fuel source to the combustor. A first control system has a first update rate and is operable to control one or more operational aspects of the turbine engine. A second control system is in communication with the first control system and the hydrogen fuel system and has a second update rate faster than the first update rate. The second control system is operable to monitor at least one parameter associated with the hydrogen fuel system and output at least one control signal to the hydrogen fuel system to control the delivery or the combustion of the hydrogen fuel.

Abstract: A turbine engine assembly includes a turbine section including at plurality of turbine stages through which the gas flow expands to generate a mechanical power output. An inter-turbine burner between at least two of the plurality of turbine stages reheats the gas flow. A condenser extracts water from the gas flow exhausted from the turbine section, and an evaporator heats the water extracted by the condenser to generate a steam flow with the steam flow communicated to the inter-turbine burner and added to the gas flow expanded through the turbine section.

Abstract: The present disclosure is direct to a system for regulating a velocity of gases in a turbomachine. The system includes an exhaust section of the turbomachine. The system also includes a damper having an actuator and a restriction. The damper is positioned within the exhaust section and is operable to adjust the velocity of the gases based on a position of the restriction. The system further includes a controller communicatively coupled to the damper. The controller is configured to control the position of the restriction to regulate the velocity of the gases relative to a predetermined velocity range.

Abstract: An assembly is provided for a turbine engine. This assembly includes a housing, a combustor and a steam injector. The housing includes an air plenum. The combustor is disposed within the air plenum. The combustor includes a combustor wall and a combustion chamber. The combustor wall is disposed between the combustion chamber and the air plenum. The combustor wall includes a quench aperture that extends through the combustor wall from the air plenum to the combustion chamber. The steam injector projects partially into or through the quench aperture.

Abstract: A hybrid electric propulsion (HEP) system of an aircraft includes a gas turbine engine configured to generate rotational power, and an electric propulsion system configured to generate at least one of thrust or lift for operation of the aircraft. The propulsion system includes a propulsor and an electric motor configured to drive the propulsor. A controller is in signal communication with the gas turbine engine and the electric propulsion system. The controller operates the gas turbine engine based on an on-board engine model (OEM), monitors electrical parameters of the electric propulsion system, and updates the OEM in response to changes to the electrical parameters.

Abstract: The invention relates to a combined thermal power plant for generating electrical energy with a gas turbine and a hot-air turbine. The hot-air turbine comprises a closed gas circuit for conducting process gas. Heat is transferred from the exhaust gases of the gas turbine to the process gas of the hot air-turbine via a heat exchanger.

Abstract: A system is provided for an aircraft. This aircraft system includes a propulsor, a powerplant and a control system. The powerplant is configured to output mechanical power to drive rotation of the propulsor. The powerplant includes a heat engine and an electric machine. The heat engine is configured to provide a first portion of the mechanical power. The electric machine is configured to provide a second portion of the mechanical power. The control system is configured to operate the powerplant to control a rotational speed of the propulsor by adjusting the second portion of the mechanical power.

Abstract: A turbine engine includes a turbo-engine, a fan, a frame, and a lubrication system. The turbo-engine includes a core air flowpath. The fan is drivingly coupled to the turbo-engine. The frame supports the core air flowpath and includes a plurality of lubricant struts that extend through the core air flowpath. The lubrication system includes a sump having a lubricant therein, a scavenge reservoir, and a lubricant strut flowpath disposed through each of the plurality of lubricant struts. The lubricant strut flowpath is in fluid communication with the sump and the scavenge reservoir. The lubricant strut flowpath of each of the plurality of lubricant struts directs the lubricant from the sump to the scavenge reservoir.

Abstract: A gas turbine engine includes a compressor section having a downstream most location and more upstream locations. A compressor housing surrounds the compressor rotors. A combustor is downstream of the compressor and a turbine section is downstream of the combustor. At least one bleed inlet passage bleeds air compressed from the compressor section, and delivers the air for use on an associated aircraft. A baffle plate is intermediate the at least one bleed inlet passage and a bleed exit port from the gas turbine engine. The baffle plate has a plurality of holes for allowing the air to flow from the bleed inlet passage to the bleed exit port, with an area of the holes increasing from a location adjacent the at least one bleed inlet passage and in a circumferential direction away from the at least one bleed inlet passage. An aircraft air supply system and an aircraft are also disclosed.

Abstract: A system for an aircraft includes a fan rotor, an engine core, a fan case, a core case, a bifurcation, an inner electrical system, an outer electrical system and multiple electrical lines electrically coupling the inner electrical system to the outer electrical system. The engine core is configured to drive rotation of the fan rotor about an axis. The fan case houses the fan rotor. The core case houses the engine core. The bifurcation radially crosses a bypass flowpath. The bypass flowpath is downstream of the fan rotor and located radially between the fan case and the core case. The inner electrical system is arranged with the engine core. The outer electrical system is mounted to the fan case. The electrical lines extend between and electrically couple the inner electrical system to the outer electrical system. The electrical lines run in parallel along one another radially through the bifurcation.

Abstract: An engine component assembly with a first substrate having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface, with the cooling surface being different than the hot surface, a second substrate having a first surface in fluid communication with a cooling fluid supply and a second surface, different from the first surface, facing and spaced from the cooling surface to define at least one interior cavity. At least one cavity is provided within the first substrate defining a cavity surface where at least a portion of the cavity surface is directly opposite the second surface. At least one cooling aperture extending through the second substrate from the first surface to the second surface, and defining a streamline along which a cooling fluid passes from the cooling fluid supply to the at least one interior cavity.