Abstract: A hybrid interchangeable battery evaluation tool (HIBET) is provided. HIBET determines an amount of electrical energy and an amount of jet fuel necessary for a hybrid electric aircraft to complete a flight based on a range of the flight, a payload of the hybrid electric aircraft, an indication of a battery mass limitation of the hybrid electric aircraft, and an optimization of an energy split between the electrical energy and the jet fuel. HIBET causes an indication of the amount of electrical energy to be displayed in a graphical user interface and/or to be otherwise outputted.

Abstract: A turbofan engine has a fan portion in fluid communication with a core stream and a bypass stream of air separated by splitters disposed both upstream and downstream of the fan portion. A blade splitter (shroud) on the fan partially spans the fan blade thus separating the core and bypass streams downstream while leaving a gap upstream for communication between the flows. The communication gap expands the operational range of the fan over fans without the communication gap.

Abstract: A system includes a flow battery and a temperature control system. The flow battery is configured to thermally manage a thermal load. In some embodiments, the flow battery is also configured to electrically power the thermal load. The temperature control system is configured to cool electrolyte in the flow battery in response to the thermal load being inactive.

Abstract: An endwall assembly disposed at one end of a vane assembly may comprise an endwall spar that includes an cold side, an hot side, a leading edge, a trailing edge, and an axis extending from the leading edge to the trailing edge perpendicular to the leading edge. The endwall assembly may include a coversheet on the hot side of the endwall spar and a cooling channel that includes a cooling fluid inlet disposed in the endwall spar, and a cooling fluid outlet. The endwall assembly may include a structure protruding from the cold side of the endwall spar, wherein the structure is located between the cooling fluid inlet and the cooling fluid outlet along the axis; and a cooling fluid source cavity on the cold side of the wall, the cooling fluid source cavity in fluid communication with the cooling fluid channel via the cooling fluid inlet.

Abstract: A heat transfer system for controlling two or more heat loads, including a high transient heat load, is provided. The heat transfer system may include sensible-heat thermal energy storage. A method of transferring heat from two or more heat loads to an ambient environment is further provided.

Abstract: Fuel injectors having a fuel-air heat exchange system and methods thereof for use in a gas turbine engine. The fuel-air heat exchanger allows heat transfer between a flow of cooling air used to cool components of the engine and a flow of fuel used to drive the engine to transfer heat to the flow of fuel and cool the cooling air.

Abstract: A turbine vane comprising ceramic matrix composite materials includes a vane support core, an airfoil, and an end wall that at least partially defines a gas path. The turbine vane is formed from a plurality of ceramic plies or preforms that are infiltrated with ceramic matrix material to form a one-piece ceramic matrix composite turbine vane.

Abstract: A rotor assembly includes a plurality of wheels and a tie bolt that extends through the plurality of wheels and applies a compressive force to the plurality of wheels. The tie bolt includes a first segment with a first stiffness and a second segment with a second stiffness to allow for thermal growth of the plurality of wheels.

Abstract: Systems and methods are disclosed for controlling surge margin in the compressor section of a gas turbine engine. A first compressor section and a second compressor section are in fluid communication with a bypass conduit. An auxiliary turbine and discharge conduit are positioned in the bypass conduit. Fluid flow from the compressor sections into the bypass conduit is controlled by bypass control valves.

Abstract: Vehicles, such as aircraft, may include turbine-based combined cycle power plants (TBCC) for power to achieve high-mach speeds. An anti-unstart configuration provides control for transitioning between the amount of air directed to either engine during operation of gas turbine engine and scramjet engines, to avoid unstart during operation above sonic speeds.

Abstract: An example high-performance system includes an example high-performance component including a substrate and a multilayer abradable track adjacent to the substrate. The abradable track includes a plurality of alternating layers along a thickness of the abradable track. The plurality of alternating layers includes at least one relatively porous abradable layer and at least one relatively dense layer. A porosity of the relatively dense layer is lower than that of the at least one relatively porous abradable layer. The example high-performance system may include a rotating component configured to contact and abrade the multilayer abradable track. An example technique for forming the multilayer abradable track includes thermal spraying a first precursor composition toward the substrate to form a relatively porous abradable layer of a layer pair of a plurality of layer pairs of the multilayer abradable track, and a second precursor composition to form a relatively dense layer of the pair.

Abstract: A power generation system for a nuclear reactor includes an externally-heated turbine engine, a reactor heat exchanger, and a heat recuperating system. The externally-heated turbine engine produces compressed air that is heated by the reactor heat exchanger. The heat recuperating system includes a heat exchanger thermally connected to the externally-heated turbine engine to transfer heat to the compressed air to supplement the reactor heat exchanger.

Abstract: Cooling systems and methods of operation are provided. The cooling system may comprise a two-phase pumped loop (TPPL). The two-phase pumped loop may include, a receiver, a pump downstream from the receiver, a heat load downstream from the pump, a TPPL tee downstream from the heat load, a TPPL check valve downstream from the TPPL tee, and a heat exchanger downstream from the TPPL check valve and upstream from the receiver. The cooling system may further include a vapor cycle system (VCS) loop. The vapor cycle system loop may include the receiver, a compressor downstream from a vapor outlet of the receiver, a compressor check valve downstream from the compressor and upstream of the heat exchanger, the heat exchanger, and the heat load downstream from a liquid outlet of the receiver.

Abstract: An electronics cabinet cooling system may include multiple cabinet heat exchangers mounted at an air discharge of respective different electronic cabinets. Heat from a flow of air heated by electronic components in the electronic cabinets may be received by respective cabinet heat exchangers. A liquid refrigerant flowing through the heat exchangers in parallel may be at least partially changed from liquid to gas and absorb the heat from the flow of air. A three-way tee in a common outlet header downstream from the cabinet heat exchangers may direct the gas refrigerant to a condenser and the liquid refrigerant to a receiver. The condenser may condense the gas refrigerant to liquid refrigerant, which may be routed to the receiver.

Abstract: A turbine wheel for a gas turbine engine including a compressor impeller and a radial inflow turbine integral to or attached to the compressor impeller is provided. A compressor turbine wheel including features to increase surface area of a surface of the compressor impeller and/or the radial inflow turbine and/or a passage to flow air between the compressor impeller and the radial inflow turbine is further provided. Methods for cooling radial inflow turbines integral to compressor impellers are further provided.

Abstract: A system is presented for directing the flow of cooling fluid in a rotational machine having co-axial rotatable shafts. The system comprises a first shaft rotatable about an axis, a second shaft rotatable about the axis and having a portion axially overlapping with the first shaft, and a fluid catcher. The fluid catcher is coupled between the first shaft and the second shaft. The fluid catcher comprises a first interface region interfacing with the first shaft, a second interface region interfacing with the second shaft, a fluid retention lip at least partly defining an oil capture region; and a body. The body is coupled to the oil retention lip and defines a channel in fluid communication with the oil capture region. The channel is positioned to direct fluid to one of the first interface region or the second interface region.

Abstract: An anti-rotation device for a pair of threaded components includes a pair of ratchet interfaces and a spring element. A first ratchet interface and the spring element are movably disposed within a first threaded component, and a second ratchet interface is disposed at a mating end of a second threaded component. During relative rotation of the pair of threaded components, the ratchet interfaces engage, providing a resistance to the threaded components loosening that is greater than a resistance that the ratchet interfaces provide to the threaded components tightening. The anti-rotation device engages automatically upon relative rotation of the threaded components, and not as a separate step occurring after rotation. Additionally, the anti-rotation device may be especially useful in systems where various types of movement can cause the threaded components to loosen, and where visual access to the anti-rotation device is impeded.

Abstract: A seal system may include a static housing, a carbon seal positioned in the static housing, a runner having a sealing surface aligned with the carbon seal, a number of electromagnets positioned in the static housing, and a controller circuitry. The controller circuitry may control a variable flow of electric current to control an electromagnetic field respectively generated by each of the electromagnets. The controller circuitry may variably apply the electromagnetic field to move at least one of the carbon seal or the runner and correspondingly adjust an applied force loading of an interface of the carbon seal and the sealing surface of the runner.

Abstract: A bearing lubrication system includes a bearing assembly comprising a duplex bearing including an outer ring, an inner ring positioned radially inward from the outer ring, and two sets of circumferentially distributed rolling elements between the inner and outer rings. The bearing assembly further includes a housing radially surrounding the duplex bearing and including a lubricant flow passage in fluid communication with a source of lubricant. A flow orifice is located downstream of the lubricant flow passage for jetting the lubricant into the duplex bearing. The flow orifice has an axial location between the two sets of rolling elements.

Abstract: A shroud assembly adapted for use with a gas turbine engine includes a seal segment, a carrier, and a mount system. The seal segment extends circumferentially at least partway around an axis to define a gas path boundary of the shroud assembly. The carrier is configured to support the seal segment in position radially relative to the axis. The mount system couples the seal segment with the carrier.