Abstract: A cyclonic separator for a gas turbine engine includes a housing, a fluid inlet, a first fluid outlet, a second fluid outlet, and a particle separator. The housing includes a first end, a second end, and an outer wall extending between the first end and the second end. The fluid inlet is disposed at the first end of the housing. The first fluid outlet is disposed at the second end of the housing. The second fluid outlet is disposed in the outer wall downstream of the first end of the housing and extends outward at least partially in the radial direction. The particle separator is disposed in the housing between the first end and the second end inward of the outer wall in the radial direction and extends in the circumferential direction. The particle separator defines a plurality of openings extending in the radial direction.

Abstract: An integral guide vane combustor assembly for a gas turbine engine comprises an annular array of radially extending guide vane combustors. The gas turbine engine comprises, in axial flow sequence, a compressor assembly, the integral guide vane combustor assembly, a turbine assembly, and an exhaust assembly. Each of the guide vane combustors comprises, in axial flow sequence, a guide vane portion, and a combustor body portion. The guide vane portion is formed integrally with the combustor body portion, and the guide vane portion is configured to direct a gas flow exiting the compressor assembly into the combustor body portion.

Abstract: Methods, apparatuses and systems for measuring a fire spread rate by a controller component are provided. The method includes: monitoring a field of view of a first sensor, where the first sensor is a long wavelength infrared (LWIR) camera configured to detect one or more fire by products; determining that a fire event occurs based on a detection of at least one particle in the field of view of the first sensor; determining a fire spread rate in an instance that the fire event occurs; and triggering an extinguisher system according to the fire spread rate and a distance between the first sensor and the extinguisher system.

Abstract: An accessible debris separator for a gas turbine engine is provided. The accessible debris separator including a chamber formed by a entrance wall, an exit wall, an inner wall, and an outer wall; a plurality of inlet openings in the entrance wall; a plurality of outlet openings in the exit wall; and a component within the chamber, the component forcing cooling air with debris particulates entering the chamber via an inlet opening of the plurality of inlet openings to take a circuitous path thereby separating the debris particulates from the cooling air prior to the cooling air exiting the chamber via an outlet opening of the plurality of outlet openings.

Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct; a primary fan driven by the turbomachine; and a secondary fan located downstream of the primary fan within the inlet duct. The gas turbine engine defines a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10, wherein the thrust to power airflow ratio is a ratio of an airflow through a bypass passage over the turbomachine plus an airflow through the fan duct to an airflow through the core duct, and wherein the core bypass ratio is a ratio of the airflow through the fan duct to the airflow through the core duct.

Abstract: An aircraft propulsion system includes a core engine and a heat exchanger assembly that is operable in a heat exchanger configuration where the exhaust gas flow is in thermal communication with a working fluid flow and a bypass configuration where the exhaust gas flow passes through the heat exchanger assembly without thermal communication with the working fluid flow.

Abstract: Shower head structure and shower device includes shower head body, water distributing disc, ratchet wheel, key, connecting rod and reset elastic member. Shower head body includes shell assembly and flow dividing assembly, where multiple groups of water inlets are disposed in and water distributing disc is rotationally mounted on. Water passing holes communicated with one group of water inlets every time are disposed on water distributing disc. Ratchet wheel is fixedly connected to side of water distributing disc away from flow dividing assembly. Key has first end hinged to shell assembly and second end telescopically disposed relative to one side of shell assembly. Connecting rod is slidably disposed in shell assembly and in transmission connection between second end and ratchet wheel. Key drives connecting rod. Reset elastic member has one end connected to shower head body and other end acting on connecting rod. Reset elastic member drives connecting rod.

Abstract: A gas turbine engine for an aircraft. The gas turbine engine comprising: a rich burn, quick quench, lean burn (RQL) combustor having a number of fuel spray nozzles in the range of 14-22 or a number of fuel spray nozzles per unit engine core size in the range 2 to 6. An MTO nvPM emissions index ratio is defined as: EI maxTO , SAF EI maxTO , FF where: EImaxTO,SAF is the system loss corrected nvPM emissions index in mg/kg of the gas turbine engine when operating at around 100% available thrust for given operating conditions if a fuel provided to the fuel spray nozzles comprises a sustainable aviation fuel (SAF); and EImaxTO,FF is the system loss corrected nvPM emissions index in mg/kg of the gas turbine engine when operating at around 100% available thrust for the given operating conditions if a fuel provided to the fuel spray nozzles is a fossil-based hydrocarbon fuel. The MTO nvPM emissions index ratio of the gas turbine engine is less than 1.

Abstract: A gas turbine engine includes: a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct; a primary fan driven by the turbomachine; and a secondary fan located downstream of the primary fan within the inlet duct, the gas turbine engine defining a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10, wherein the thrust to power airflow ratio is a ratio of an airflow through a bypass passage over the turbomachine plus an airflow through the fan duct to an airflow through the core duct, wherein the core bypass ratio is a ratio of the airflow through the fan duct to the airflow through the core duct.

Abstract: An injector head for a fuel injector of an engine includes an injector body configured to be coupled with a fuel stem of the fuel injector. The injector body extends orthogonally relative to the fuel stem. The injector body extends axially along a central axis and circumferentially about the central axis. The injector head also includes a central fuel assembly. The central fuel assembly includes a tip portion disposed proximal to a downstream end of the injector body. The tip portion includes an end portion, an intermediate portion, a plurality of support pins extending between the end portion and the intermediate portion, and a plurality of fins extending radially-outward and from the intermediate portion along the central axis. The injector head is formed by additive layer manufacturing. The plurality of support pins and the plurality of fins provide support for forming the injector head by additive layer manufacturing.

Abstract: An air handling transport includes a base frame and a combustion air module mounted to the base frame. The combustion air module includes a combustion air plenum for providing filtered combustion air to a turbine mounted on a separate transport. The transport further includes a ventilation air module mounted to the base frame. The ventilation air module provides filtered ventilation air to an enclosure for the turbine mounted on the separate transport. The ventilation air module includes a ventilation air compartment, a ventilation air duct, and a ventilation air plenum. The ventilation air duct is in the base frame and extends below the ventilation air compartment, the combustion air module, and the ventilation air plenum. The ventilation air duct couples the ventilation air compartment to the ventilation air plenum.

Abstract: A system is provided for an aircraft. This aircraft system includes a turbine engine and an air system. The turbine engine includes a flowpath, a compressor section, a combustor section and a turbine section. The flowpath extends through the compressor section, the combustor section and the turbine section from an airflow inlet into the flowpath to a combustion products exhaust from the flowpath. The air system includes an air circuit, a first boost compressor, a second boost compressor and a heat exchanger. A circuit inlet into the air circuit is fluidly coupled to the flowpath upstream of the combustor section. The air circuit projects out from the circuit inlet and extends through the first boost compressor, the second boost compressor and the heat exchanger.

Abstract: A shower (1) for a sanitary faucet, comprising: a body (2) having at least one inflow duct (3) for a liquid; a plurality of spray plates (4.1, 4.2, 4.3); and an actuator (5), which can be adjusted along an actuating distance (6) for supplying the liquid to at least one of the spray plates (4.1, 4.2, 4.3), and wherein the actuator (5) has at least one snap position (7.1, 7.2) along the actuating distance (6), in which the liquid can be delivered by at least two spray plates (4.1, 4.2, 4.3).

Abstract: A combustor comprising a dome wall, a combustor liner extending from the dome wall, and a combustion chamber at least partially defined by the dome wall and the combustor liner. A set of fuel cups are arranged along the dome wall. A set of dilution passages extend through the dome wall or the combustor liner to direct air into the combustion chamber, wherein a dilution passage of the set of dilution passages includes an inlet, an outlet, and a passageway.

Abstract: A gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct; a primary fan driven by the turbomachine; a nacelle surrounding the primary fan; and a secondary fan located downstream of the primary fan within the inlet duct. The gas turbine engine is characterized by a thrust to power airflow ratio, a core bypass ratio, a blade effective acoustic length, an acoustic spacing length, and an inlet-to-nacelle ratio.

Abstract: A splitter between a primary flow and a secondary flow of a dual flow turbomachine includes a single-piece structure including an outer annular wall, an inner annular wall, a radial annular wall and an inner annular baffle, defining a first cavity between the outer annular wall and the inner annular baffle, and a second cavity between the inner annular wall, the radial annular wall and the inner annular baffle.

Abstract: A firefighting vehicle includes a chassis that houses an electric drivetrain for driving wheels of the vehicle. A conduit extends within the chassis from back to front for conveying firefighting fluid. Within the chassis, a first motor and a first battery pack are disposed on a first side of the conduit and a second motor and a second battery pack are disposed on a second side of the conduit. The first motor is configured to drive a first wheel on a first side of the vehicle, and the second motor is configured to drive a second wheel on a second side of the vehicle. The conduit is configured to provide firefighting fluid to a monitor mounted at the front of the chassis, where the fluid can be discharged toward a target, such as a fire.

Abstract: A gas turbine engine is provided. The gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct; a primary fan driven by the turbomachine; and a secondary fan located downstream of the primary fan within the inlet duct. The gas turbine engine defines a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10, wherein the thrust to power airflow ratio is a ratio of an airflow through a bypass passage over the turbomachine plus an airflow through the fan duct to an airflow through the core duct, and wherein the core bypass ratio is a ratio of the airflow through the fan duct to the airflow through the core duct.

Abstract: A battery flooding system includes a flood port and an elongated connector. The flood port is configured to be fluidly coupled to a battery housing of an electrified vehicle. The elongated connector is configured to interface with the flood port to facilitate providing a fluid to the flood port from a fluid source such that the fluid is provided within the battery housing.

Abstract: Disclosed is an apparatus, system, and method, by which a difference in the thermal energies, and/or temperatures, of two bodies, materials, gases, liquids, solids, objects, and/or other groups or collections of matter, may be harnessed to provide mechanical energy to a rotary engine and/or shaft. Also disclosed is an apparatus, system, and method, by which mechanical energy (e.g., the rotation of a shaft) may be used to produce and/or amplify a difference in the thermal energies, and/or temperatures of, and/or between, two bodies, materials, gases, liquids, solids, objects, and/or other groups or collections of matter. The disclosed thermal-to-mechanical energy conversion apparatus, as well as the complementary mechanical-to-thermal energy conversion apparatus, lacks moving parts and therefore satisfies a previously unmet need for a simple, robust, and efficient heat engine.