Abstract: A propeller blade comprises a composite blade spar and at least one cover shell section adhesively bonded to the blade spar by a thermoplastic adhesive.

Abstract: A steam turbine blade includes a blade body (7) including blade surfaces (70) extending in a blade height direction. The blade body (7) includes a first suction port (74) extending in the blade height direction and opening in the blade surface (70), a first drain flow path (75) internally extending in the blade height direction, and first communication passages (76) internally provided away from one another in the blade height direction and independently of one another and making the first drain port (74) and the first drain flow path (75) in communication with each other.

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section extending from a first platform section. The airfoil section defines an internal core cavity for conveying a fluid flow, and a baffle assembly that has a first baffle and a second baffle. The first baffle includes a first baffle body extending in the internal core cavity. The first baffle body defines an internal baffle cavity. The second baffle includes a second baffle body dimensioned to extend from the platform section into the internal baffle cavity such that an outer periphery surface of the second baffle body and an external wall of the airfoil section cooperate to define a first cooling passage that directs cooling flow into the internal baffle cavity.

Abstract: A component for a gas turbine engine that separates a cooling air plenum from a heated gas environment. The component defines a hot section surface adjacent to the heated gas environment having a plurality of cooling apertures fluidically connecting the cooling air plenum to the heated gas environment to allow a cooling air to flow from the cooling air plenum to the heated gas environment through the plurality of cooling apertures. The plurality of cooling apertures each have an aperture diameter of less than about 3 millimeters (mm) and an average surface roughness of less than about 1 micrometer (1 ?m).

Abstract: A gas turbine component includes a substrate and a corrosion resistant layer coupled to the substrate. The corrosion resistant layer includes zirconium silicate and is configured to protect the substrate from exposure to a vanadium corrodent.

Abstract: An inter-compressor case for a gas turbine engine is disclosed. The inter-compressor case comprises: an outer casing and an inner casing radially spaced apart relative to a longitudinal axis; a gas path extending from a plurality of radial inlets arranged in a circumferentially spaced apart array around the outer casing to an annular outlet defined by an axially extending downstream portion of the outer casing and an axially extending downstream portion of the inner casing; a plurality of struts having a gas path surface extending across the gas path between the outer casing and the inner casing; and a plurality of flow separators extending from the adjacent radial inlets. The flow separators have trailing edges disposed upstream of the annular outlet and include a plurality of full length flow separators and a plurality of truncated flow separators.

Abstract: A gas turbine engine includes a platform that has a gas path side, a non-gas path side, a first mate face, and a second mate face. The second mate face has a beveled edge sloping towards the first mate face. The gas turbine engine also includes a coverplate that includes a first bend, a flat portion substantially parallel to the first mate face and a first wing substantially parallel to the second mate face.

Abstract: The gas turbine engine rotor assembly includes a rotor disc with a plurality of sealing tabs projecting radially out from a peripheral surface of the rotor disc in the rear end portion thereof. A said sealing tab is disposed at a tip portion of a fixing member of the disc, formed between pairs of blade root slots, adjacent a trailing edge of the rotor disc. The sealing tabs help to reduce the leakage of secondary air out the back of a blade pocket defined between adjacent blades mounted on the rotor disc.

Abstract: An axial flow rotating machinery includes: a rotor; a casing; a rotating-blade stage including rotating blades and a radially-outer side rotating blade ring continuing to radially outer ends of the rotating blades; and a rotating-blade side seal device configured to seal a gap between the radially-outer side rotating blade ring and the casing. The rotating-blade side seal device includes: a seal fin having an annular shape and extending toward an outer peripheral surface of the radially-outer side rotating blade ring from the casing; and a swirl brake fixed to the casing in a cavity formed at an upstream side of the seal fin. The swirl brake includes: a first plate-shaped member having a surface along a radial direction of the rotor; and a second plate-shaped member or a third plate-shaped member having a surface oblique to the radial direction of the rotor.

Abstract: A hydrostatic advanced low leakage seal configured to be disposed relatively rotatable components includes a base. The seal also includes a shoe extending circumferentially. The seal further includes a beam operatively coupling the shoe to the base, the beam having a beam length that is substantially equal to or greater than a circumferential pitch of the shoe.

Abstract: A method of manufacturing a hydrostatic advanced low leakage seal configured to be disposed between relatively rotatable components is provided. The method includes manufacturing a plurality of separate, independent components of the seal. The method also includes assembling the plurality of separate, independent components to form the seal.

Abstract: A hydrostatic advanced low leakage seal configured to be disposed between relatively rotatable components. The seal includes a base. The seal also includes a shoe extending circumferentially. The seal further includes a first beam operatively coupling the shoe to the base, the first beam having a first thickness. The seal yet further includes a second beam operatively coupling the shoe to the base, the second beam having at least a portion thereof with a second thickness that is less than the first thickness.

Abstract: A hydrostatic advanced low leakage seal configured to be disposed between relatively rotatable components. The seal includes a base. The seal also includes a shoe extending circumferentially. The seal further includes a radially outer beam operatively coupling the shoe to the base. The seal yet further includes a radially inner beam operatively coupling the shoe to the base, wherein one of the radially inner beam and the radially outer beam is oriented to be angled relative to the other of the radially inner and outer beam.

Abstract: A blade outer air seal includes a seal body that has a channel on a radially inner side that defines a first height portion outside of the channel and a second height portion within the channel. A first cavity is in the first height portion and a second cavity is in the second height portion. An abradable coating is over the radially inner side and fills the first and second cavities.

Abstract: Systems and methods for controlling tip clearance in a gas turbine engine are provided. The system may include a distribution manifold positioned along the engine case for a turbine of a gas turbine engine. The distribution manifold may include a passageway for a thermal fluid, an inlet configured to direct the thermal fluid into the passageway, an inner surface extending along and facing the outer surface of the engine case, and a plurality of outlets configured to direct the thermal fluid onto the outer surface of the engine case. The thermal fluid may include bypass air. A component may add kinetic energy to the thermal fluid.

Abstract: A method for determining an arrival-time of a rotor blade that includes attaching an RF reader to a stationary surface and an RF tag to the rotor blade. Time-of-flight data points are collected via an RF monitoring process that includes: emitting an RF signal from the RF reader and recording a first time; receiving the RF signal at the RF tag and emitting a return RF signal by the RF tag in response thereto; receiving the return RF signal at the RF reader and recording a second time; and determining the time-of-flight data point as being the duration occurring between the first time and the second time. The RF monitoring process is repeated until multiple time-of-flight data points are collected. A minimum time-of-flight is determined from the multiple time-of-flight data points, and the arrival-time for the rotor blade is determined as being a time that corresponds to the minimum time-of-flight.

Abstract: A ventilation flow path for guiding a compressed gas flowing between two blade rows adjacent in an axial direction to an interior of a compressor rotor shaft is formed in the compressor rotor shaft. The ventilation flow path has an introduction part, a plurality of branch parts, and a collection part. The introduction part guides the compressed gas flowing between the two blade rows into the compressor rotor shaft. The plurality of branch parts branch out from the introduction part, and are formed in mutually different positions in the axial direction. The collection part is connected to each of the plurality of branch parts. The compressed gas flows into the collection part after passing through the plurality of branch parts, and then, the compressed gas that has flowed in flows outside through the collection part.

Abstract: A containment system for a gas turbine engine includes an outer containment ring having a first projection that extends radially inward and an inner containment ring having at least a second projection that extends radially outward toward the outer containment ring. The second projection is offset and spaced apart from the first projection to define a chamber in a first state. The containment system includes a lattice defined within the chamber that spans the chamber, and the lattice is integrally formed with each of the outer containment ring and the inner containment ring. The second projection is configured to interlock with the first projection in a second state.

Abstract: A fan containment arrangement for a gas turbine engine comprises: a fan containment casing; and a fan track liner radially within the fan containment casing and extending radially inwardly from the fan containment casing to a gas-washed surface delimiting a gas path for a fan. The fan track liner comprises an impact resistant layer formed from titanium or titanium alloy. No greater than about 20% of the radial thickness of the fan track liner is formed from titanium or titanium alloy. The fan track liner comprises first and second cellular impact structures separated from one another by a first septum layer, the first cellular impact structure being the impact resistant layer formed from titanium or titanium alloy, or the impact resistant layer formed from titanium or titanium alloy is a septum layer, separating the first and second cellular impact structures. (FIG.

Abstract: A gear-box casing in a gas turbine engine, in particular an aircraft engine, characterized in that the gear-box casing has partially a region including fiber reinforced plastic, the fibers in this region being arranged only in an angular range of +/?40° to 50°, in particular of +/?42° to 48°, most particularly +/?45°, in relation to the main axis of rotation of the gear-box casing. The invention also concerns a method for producing a gear-box casing and a gas turbine engine.

Abstract: A fan rotor module for a gas turbine engine, the fan rotor module comprising a drive arm, a fan disc and a windage shield attached at one or more points to a rear portion of the fan disc, wherein the fan rotor module comprises at least one balancing weight disposed at one or more of the points where the windage shield is attached to the rear portion of the fan disc.

Abstract: A power system is configured to generate mechanical energy from supercritical carbon dioxide in a closed loop. The power system includes a compressor that yields a high pressure supercritical carbon dioxide. A heat exchanger is operatively connected to the compressor and yields a high enthalpy supercritical carbon dioxide. A rotary engine is operatively connected to the heat exchanger and configured to convert thermal energy from the high enthalpy supercritical carbon dioxide into mechanical energy and an output supercritical carbon dioxide. A pressure differential orifice is operatively coupled to the rotary engine and to the heat exchanger and configured to decrease the temperature and the pressure of the output supercritical carbon dioxide resulting in a low pressure low temperature supercritical carbon dioxide. The low pressure low temperature supercritical carbon dioxide is heated in the heat exchanger and the renters the compressor completing the closed loop.

Abstract: A valve mechanism includes a valve, a camshaft, a fixed support, an intermediate swing arm and a supporting base. The fixed support is provided with a connecting-portion via hole running from top to bottom, two oil passages are defined in a connecting portion, and each of the oil passages is connected with the connecting-portion via hole and a corresponding intermediate swing arm shaft hole. The supporting base defines first and second oil feeding passages therein, the first supporting-base oil feeding passage is communicated with the connecting-portion via hole, and an upper end of the second supporting-base oil feeding passage extends to a base-body camshaft supporting portion of the supporting base. An engine and a vehicle are also provided.

Abstract: An electrically-actuated VCT device cascaded controller, comprises: a system processing device configured to receive inputs from one or more sensors and generate an output signal that is communicated to an electric phaser motor; the system processing device: receives data indicating an angular position of a camshaft relative to an angular position of a crankshaft at a primary control loop; receives data indicating an angular velocity of the crankshaft at a secondary control loop; and generates the output signal that controls the electric phaser motor using the primary control loop and the secondary control loop.

Abstract: A variable camshaft timing (VCT) assembly for controlling angular positions of concentric camshafts. The VCT assembly includes an independent VCT device and a dependent VCT device. The independent VCT device is hydraulically- or electrically-actuated. The independent VCT device is coupled with a first concentric camshaft and has a first component that rotates during phasing movements. The first component has a first set of slots therein. The dependent VCT device is coupled with a second concentric camshaft. The dependent VCT device has a second component that lacks rotation during phasing movements, and has multiple phase lugs. The second component has a second set of slots therein. The phase lugs are received in the first set of slots and are received in the second set of slots.

Abstract: The relates to an electromechanical camshaft adjuster comprising an electric motor and an adjusting gear, which has a housing two housing parts, that are sealed off with respect to each other by means of a static seal and with respect to the electric motor and a cylinder head by means of two dynamic seals. A first housing part of the adjusting gear a pot shape that tapers in a stepped manner towards a housing bottom of the housing part, said pot shape having three different inner diameter regions. In the region closest to the bottom with the smallest inner diameter, a stop plate that acts in the circumferential direction is held. In the region with the middle inner diameter, an output ring gear is mounted with play, and in the region with the largest inner diameter, an input ring gear is secured.

Abstract: Provided are a valve guide made of an iron-based sintered alloy excellent in wear resistance and thermal conductivity, and a method of producing the same. Specifically, provided are a method of producing a valve guide made of an iron-based sintered alloy, the method including the steps of: molding raw material powder including diffusion-alloyed powder including core iron powder and Cu bonded to the core iron powder through diffusion to obtain a molded body; and sintering the molded body, to thereby produce a valve guide made of an iron-based sintered alloy, and a valve guide produced by the production method.

Abstract: A method of operating an electromagnetic latch assembly of a type that includes an electromagnet and a latch pin that is stable independently from the electromagnet in both first and second positions includes energizing the electromagnet systematically over a period in a manner that enhances the functionality of the electromagnetic latch assembly without causing the latch pin to move between the first and second positions. The period may be a period over which the electromagnetic latch assembly is too cold and the electromagnet may be energized in a manner that is effective for heating. Alternatively, the period may be one over which the electromagnetic latch assembly is subject to high inertial forces and the electromagnet may be energized in a manner that is effective to enhance latch pin retention.

Abstract: Disclosed herein are particulate filtration systems comprising a fuel source, a fuel burner, and a porous ceramic structure, the fuel source comprising at least one fuel additive capable of producing ash upon combustion. The resulting ash can be deposited on the porous ceramic structure in an amount sufficient to improve the filtration efficiency of the structure over a relatively short period of time or relatively short driving distances. Vehicles comprising such particulate filtration systems and methods for filtering particulate matter from a fluid stream are also disclosed herein. Further disclosed herein are methods for conditioning a particulate filter to improve the initial filtration efficiency.

Abstract: The invention relates to an exhaust after treatment system with a passive NOx adsorber and a heatable SCR catalytic converter. The exhaust gas after treatment system according to the invention for an internal combustion engine comprises an exhaust pipe, a passive NOx adsorber arranged in the exhaust pipe, an injector arranged in the exhaust pipe, a mixer arranged in the exhaust pipe, an SCR catalytic converter arranged in the exhaust pipe and a heating device arranged in the exhaust pipe, wherein the heating device is set up in such a way that at exhaust gas temperatures below a start-up temperature of the SCR catalytic converter, the temperature in the SCR catalytic converter can be brought to a temperature above the start-up temperature within a period of time by means of the heating device.

Abstract: A method and a corresponding apparatus are provided for preconditioning an exhaust gas system (100) for discharging and purifying combustion exhaust gases of an internal combustion engine (1), in particular an internal combustion engine (1) of a motor vehicle (200). The method includes operating, air being heated by a heating element (8) in the exhaust gas system (100) to heat air in the exhaust gas system (100), operating a fan in the exhaust gas system (100) for producing a hot air stream with the heated air, using the hot air stream for heating a first catalytic converter (7) of the exhaust gas system (100) to a minimum operating temperature.

Abstract: An exhaust after-treatment system that is configured to treat an exhaust produced by an engine, and includes a bypass passage including an inlet for receiving an amount of the exhaust from an exhaust passage. A first exhaust treatment component is located within the bypass passage, and a valve is located proximate the bypass passage that is configured to control the amount of the exhaust that enters the inlet of the bypass passage. A second exhaust treatment component is located in the exhaust passage downstream from the inlet of the bypass passage, wherein an outlet of the bypass passage communicates the exhaust treated by the first exhaust treatment component back to the exhaust passage at a location that is downstream from the second exhaust treatment component such that the exhaust treated by the first exhaust treatment component does not interact with the second exhaust treatment component.

Abstract: The invention relates to a method for detecting a blocked pressure line in an SCR system of an internal combustion engine. The SCR system comprises a feed pump, a dosing module and a pressure sensor. The method comprises the following steps: a reference signal of a pressure (p) in the pressure line is measured over a measuring time (tM) if a reducing agent solution is not dosed by the dosing module, and a signal energy of the reference signal is then calculated. A pressure signal is measured over the measuring time (tM) during the dosing of a dosing mass of the reducing agent solution by the dosing module, and a signal energy of the pressure signal is then calculated. Finally, a ratio of the signal energies of the pressure signal to the signal energy of the reference signal is calculated. The blocked pressure line is detected if the ratio falls short of a first pre-definable threshold value.

Abstract: A vehicle exhaust system includes an exhaust component having an inner wall to define an internal cavity that provides an engine exhaust gas flow path from an inlet to an outlet. An injector is configured to spray a fluid into the internal cavity to mix with engine exhaust gas. An inlet baffle is mounted to the exhaust component adjacent the inlet and includes at least one scoop having a scoop length that is greater than a scoop width. The scoop includes a scoop opening that directs engine exhaust gas toward the inner wall of the internal cavity at a location that is upstream of spray injected by the injector.

Abstract: An exhaust after-treatment system includes a first set of exhaust after-treatment components, a second set of exhaust after-treatment components, an inlet to the exhaust after-treatment system, an outlet from the exhaust after-treatment system, and a valve and conduit arrangement configurable in a plurality of modes, in a first mode, exhaust gas entering the inlet flows through the second set of exhaust after-treatment components, then through the first set of exhaust after-treatment components, and then through the outlet. In a second mode, exhaust gas entering the inlet flows through the second set of exhaust after-treatment components without flowing through the first set of exhaust after-treatment components, and then through the outlet in a third mode, exhaust gas entering the inlet flows through the first set of exhaust after-treatment components, then through the second set of exhaust after-treatment components, and then through the outlet.

Abstract: Certain embodiments of the present disclosure provide an acoustic inlet barrel of an engine. The acoustic inlet barrel may include an inner barrel configured to provide a boundary for directing airflow through the engine. The inner barrel may include an inner face sheet separated from an outer face sheet by an acoustic core. The inner barrel may include a plurality of elongated, non-circular perforations formed through the inner face sheet.

Abstract: A process for manufacturing an exhaust system, especially for an internal combustion engine of a vehicle, includes providing an exhaust gas-guiding component (26) with a wall (38) made of a metallic material and providing a sensor-mounting connector (22), to be fixed at the wall. The sensor-mounting connector includes a sensor-mounting area (28) to be positioned outside the exhaust gas-guiding component, and a connection area (34), which is to be positioned such that the connection area meshes with the wall. The connection area is pressed against an outer surface (40) of the wall of the exhaust gas-guiding component in a fastening area (39) of the wall, and at the same time rotated about a longitudinal axis (A) of the connector to penetrate into the material forming the wall and a connection in substance is established between the metallic material of the wall and the metallic material of the sensor-mounting connector.

Abstract: A water jacket of an engine may include: a block-side water jacket formed in a cylinder block of the engine and surrounding a cylinder of the cylinder block; and a head-side water jacket formed in a cylinder head of the engine and surrounding a combustion chamber and an exhaust port of the cylinder head. In particular, the head-side water jacket includes: a first coolant passage surrounding the combustion chamber of the cylinder head, and a second coolant passage surrounding the exhaust port of the cylinder head, and the second coolant passage is fluidly separated from the first coolant passage.

Abstract: An oil supply element for supplying oil into a cooling channel of a piston in an internal combustion engine, may include a channel having a lateral opening with an oil discharge element and may be configured to direct a partial oil flow via the oil discharge element and the lateral opening to at least one of an underside of a piston crown, a hub, and a piston interior.

Abstract: A general purpose engine includes: a crankcase to support an engine rotary shaft; a cylinder unit extending from the crankcase in a direction perpendicular to an axis of the engine rotary shaft; a cooling fan fixed to one of opposite ends of the engine rotary shaft; and a fan housing configured to have an air induction opening defined therein for the cooling fan and to cover the crankcase and the cylinder unit from one side of the engine rotary shaft. At a position of the fan housing which is opposed to the cooling fin of the cylinder unit, a cleaning access window is defined. The cleaning access window is covered by a debris covering that is capable of being selectively opened and closed. The debris covering has one end portion engaged with the fan housing and the other end portion removably mounted on the fan housing by a magnetic body.

Abstract: In some embodiments, a vehicle includes a temperature monitoring controller. The temperature monitoring controller is a processor, control module, or other suitable hardware that is configured to receive temperature sensor values from an engine control module (ECM) when an ignition bus is in a powered on state, and to decide when the engine should be automatically started in order to maintain a temperature above a low temperature threshold. The temperature monitoring controller periodically causes an ignition bus of the vehicle to be placed in the powered on state when the engine is shut down in order to collect temperature sensor values. The temperature monitoring controller determines whether to automatically start the engine, and if not, determines how long to wait before collecting temperature sensor values again based on a rate of change of the temperature sensor values.

Abstract: A cylinder head (3) is formed with a pre-chamber (12) surrounded by a thin pre-chamber wall (11) sticking out from the inside wall surface of the cylinder head (3) to the inside of the main combustion chamber (5). Inside of the pre-chamber (12), the electrode of a spark plug (15) is arranged. When the spark plug (15) is used to burn the air-fuel mixture in the pre-chamber (12), jet flames are ejected from the communication holes (13) to the main combustion chamber (5). The thin pre-chamber wall (11) is formed from a metal material while the overall outer circumferential surface around the communication holes (13) passing through the thin pre-chamber wall (11) is formed by a material with a lower heat conductivity than the thin pre-chamber wall (11).

Abstract: A pre-chamber is formed between the front end of a spark plug (15) attached to the cylinder head (3) and a thin pre-chamber wall (11) sticking out from the inside wall surface of the cylinder head (3) to the inside of a main combustion chamber (5). The communication holes (13) communicating the inside of the sub chamber (12) and the inside of the main combustion chamber (5) are formed inside the thin pre-chamber wall (11). The thin pre-chamber wall (11) is formed into a shape with a cross-sectional area gradually decreasing from the inside wall surface of the cylinder head (3) toward the inside of the main combustion chamber (5) such as a conical shape, frustoconical shape, polygonal conical shape, or polygonal frustoconical shape.

Abstract: A cylinder head (3) is formed with a pre-chamber (12) surrounded by a thin pre-chamber wall (11) sticking out from the inside wall surface of the cylinder head (3) to the inside of a main combustion chamber (5). Inside the pre-chamber (12), the electrode of a spark plug (15) is arranged. When the spark plug (15) is used to burn the air-fuel mixture inside the pre-chamber (12), jet flames are ejected from the communication holes (13) to the main combustion chamber (5). The thin pre-chamber wall (11) is formed into a two-layer structure of an outside wall (11a) facing the main combustion chamber (5) and an inside wall (11b) facing the pre-chamber (12). The inside wall (11b) is formed by a material with a higher heat conductivity than the outside wall (11a).

Abstract: A direct-injected compression ignition internal combustion engine includes an engine housing having a cylinder and a piston movable within the cylinder and including a piston end face forming a combustion bowl. The piston end face has an annular piston rim with a rounded inner rim surface that extends radially inward and axially downward from a planar outer rim surface to a combustion bowl edge. An antebowl is defined by the rounded inner rim surface and has an antebowl volume that is about 0.8% or greater of a total volume of the combustion bowl and the antebowl together. A configuration and dimensional attributes of the antebowl is associated with reduced smoke production during operation, particularly for low to mid-load transients.

Abstract: An air cooling device includes a first inlet surge tank, a first heat exchanger to cool air introduced from the first surge tank, a second inlet surge tank, a second heat exchanger to cool air introduced from the second surge tank, and an outlet surge tank. The outlet surge tank receives both of airs introduced from the first heat exchanger and the second heat exchanger and the airs flows from the outlet surge tank toward an internal combustion engine. The outlet surge tank includes a merging space and a fixing hole. The merging space is where the airs introduced from the first heat exchanger and the second heat exchanger merge with each other. A fastening member to fasten the outlet surge tank passes through the fixing hole from an outer surface of the outlet surge tank away from the merging space toward the internal combustion engine.

Abstract: Methods and systems are provided for a compressor coolant chamber. In one example, a system comprising dividing the coolant chamber into two portions, a first portion adapted to couple to a second portion and shape a coolant chamber therebetween.

Abstract: An assembly may include an actuator. The actuator may include an actuator housing delimiting an actuator housing interior space and a ventilation line disposed within the actuator housing. The ventilation line may be guided from the actuator housing interior space to an outside and opening out in a ventilation opening arranged on an outer side of a housing wall of the actuator housing. The assembly may also include a housing including a housing flange. The ventilation line may be closed via an air-permeable and liquid-impermeable membrane. The actuator may further include a positioning dome arranged on the ventilation opening and projecting outward from the actuator housing. The positioning dome disposed integrally on the actuator housing. When the actuator is mounted on the housing, the positioning dome may engage a recess disposed on the housing flange facilitating positioning the actuator housing relative to the housing flange.

Abstract: A pumped heat energy storage (PHES) system (100) including a charging circuit and a discharging circuit effective to balance or split a total heat rejection of the PHES system between the charging circuit and the discharging circuit. The charging circuit may include thermal storage vessels (102, 104) to store thermal energy generated from a first compressor (110). A first heat rejection system (128) is fluidly coupled with the thermal storage vessels to remove thermal energy from the charging circuit. The discharging circuit may include a first turbine (146) fluidly coupled with the thermal storage vessels to extract thermal energy stored in the thermal storage vessels and convert the thermal energy to mechanical energy via an expansion of a second working fluid. A second heat rejection system (156) is fluidly coupled with the thermal storage vessels and the first turbine to remove thermal energy from the discharging circuit.

Abstract: There is disclosed a fan assembly including a fan rotor including a hub and fan blades. The fan blades have a leading edge and a trailing edge. A fan stator downstream of the fan rotor relative to a direction of an airflow through the fan assembly. The fan stator includes vanes extending between radially inner ends and radially outer ends. A flow recirculation circuit has an inlet downstream of the vanes of the fan stator and an outlet upstream of the vanes. A recirculation rotor has a plurality of airfoils circumferentially distributed around the axis and located in the flow recirculation circuit. The recirculation rotor is rotatable about the axis within the recirculation circuit. A method of operating the fan assembly is also disclosed.