PROPULSION SYSTEM FOR AN AIRCRAFT

A hybrid-electric propulsion system includes a propulsor, a turbomachine, and an electrical system having an electric machine coupled to the turbomachine. A method for operating the propulsion system includes operating, by one or more computing devices, the turbomachine to rotate the propulsor and generate thrust for the aircraft; receiving, by the one or more computing devices, data indicative of an un-commanded loss of the thrust generated from the turbomachine rotating the propulsor; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine, the propulsor, or both in response to receiving the data indicative of the un-commanded loss of thrust.

HYBRID-ELECTRIC PROPULSION SYSTEM FOR AN AIRCRAFT

A computer-implemented method of assessing a health of a gas turbine engine of a hybrid-electric propulsion system for an aircraft includes receiving, by one or more computing devices, data indicative of an amount of electrical power provided to, or extracted from, an electric machine. The method also includes receiving, by the one or more computing devices, data indicative of an operating parameter of the hybrid-electric propulsion system. The method also includes assessing, by the one or more computing devices, a health of the gas turbine engine based at least in part on the received data indicative of the amount of electrical power provided to, or extracted from, the electric machine and the received data indicative of the operating parameter of the hybrid electric propulsion system. The method also includes providing, by the one or more computing devices, information to a user indicative of the health of the gas turbine engine. 1. A computer-implemented method of assessing a health of a gas turbine engine of a hybrid-electric propulsion system for an aircraft , the hybrid-electric propulsion system comprising an electric machine rotatable with the gas turbine engine , the method comprising:receiving, by one or more computing devices, data indicative of an amount of electrical power provided to, or extracted from, the electric machine;receiving, by the one or more computing devices, data indicative of an operating parameter of the hybrid-electric propulsion system;assessing, by the one or more computing devices, a health of the gas turbine engine based at least in part on the received data indicative of the amount of electrical power provided to, or extracted from, the electric machine and the received data indicative of the operating parameter of the hybrid electric propulsion system; andproviding, by the one or more computing devices, information to a user indicative of the health of the gas turbine engine.2. The method of claim 1 , wherein receiving claim 1 , ...

Constant density heat exchanger and system for energy conversion

A constant density heat exchanger and method of operating are provided. The constant density heat exchanger includes a housing extending between a first end and a second end and defining a chamber having an inlet and an outlet. A first plate is positioned at the first end of the housing and rotatable about an axis of rotation such that the first plate selectively allows a working fluid to flow into the inlet of the chamber. A second plate is positioned at the second end of the housing and rotatable about the axis of rotation such that the second plate selectively allows the working fluid to flow out of the outlet of the chamber. The first plate and the second plate are rotatable about the axis of rotation so as to hold a volume of the working fluid at constant density as a heat source imparts thermal energy thereto.

PROPULSION SYSTEM FOR AN AIRCRAFT

A hybrid-electric propulsion system for an aircraft is provided herein that can include a propulsor and a turbomachine comprising a high pressure turbine drivingly coupled to a high pressure compressor through a high pressure spool. An auxiliary power unit can be operably coupled with a starter motor. An electrical system can comprise a first electric machine coupled to the turbomachine. The first electric machine can be separate from the starter motor. A controller can be configured to provide electrical power from an electric power source to the first electric machine to drive the first electric machine to start, or assist with starting, the turbomachine.

ENERGY CONVERSION APPARATUS AND CONTROL SYSTEM

A system including a closed cycle engine having a piston body defining a hot side and a cold side and having a piston assembly movable within the piston body. An electric machine is operatively coupled with the piston assembly. A control system includes one or more sensors operable to detect a piston movement characteristic of the piston assembly movable within the piston body. A controller is communicatively coupled with the one or more sensors and a controllable device. The controller is configured to determine a control command based at least in part on data received from the one or more sensors. The control command is selected based at least in part to cause the electric machine operatively coupled with the piston assembly to generate a preselected electrical power output. The controller provides the determined control command to the controllable device. The controllable device is operable to control an input to an engine working fluid disposed within the piston body. 1. A system for energy conversion , comprising:a closed cycle engine having a piston body defining a hot side and a cold side and having a piston assembly movable within the piston body;an electric machine operatively coupled with the piston assembly, wherein the electric machine is operable to generate electrical power when the piston assembly is moved within the piston chamber; and one or more sensors operable to detect a piston movement characteristic of the piston assembly movable within the piston body;', 'a controllable device; and', determine a control command based at least in part on data received from the one or more sensors, the control command selected based at least in part to cause the electric machine operatively coupled with the piston assembly to generate a preselected electrical power output; and', 'provide the determined control command to the controllable device, the controllable device operable to control an input to an engine working fluid disposed within the piston body, ...

PROPULSION SYSTEM FOR AN AIRCRAFT

A hybrid-electric propulsion system for an aircraft includes a propulsor and a turbomachine. The turbomachine includes a high pressure turbine drivingly coupled to a high pressure compressor through a high pressure spool. The hybrid electric propulsion system further includes an electrical system including a first electric machine, a second electric machine, and an electric energy storage unit electrically connectable to the first and second electric machines. The first electric machine is coupled to the high pressure spool of the turbomachine and the second electric machine is coupled to the propulsor for driving the propulsor to provide a propulsive benefit for the aircraft. The hybrid electric propulsion system also includes a controller configured to provide electrical power from an electric power source to the first electric machine to drive the first electric machine to start, or assist with starting, the turbomachine. 1. A hybrid-electric propulsion system for an aircraft comprising:a propulsor;a turbomachine comprising a high pressure turbine drivingly coupled to a high pressure compressor through a high pressure spool;an electrical system comprising a first electric machine, a second electric machine, and an electric energy storage unit electrically connectable to the first and second electric machines, the first electric machine coupled to the high pressure spool of the turbomachine and the second electric machine coupled to the propulsor for driving the propulsor to provide a propulsive benefit for the aircraft; anda controller configured to provide electrical power from an electric power source to the first electric machine to drive the first electric machine to start, or assist with starting, the turbomachine.2. The hybrid-electric propulsion system of claim 1 , wherein the turbomachine is configured as part of a first turbofan engine claim 1 , and wherein the propulsor is configured as part of a second turbofan engine.3. The hybrid-electric propulsion ...

SYSTEM AND APPARATUS FOR ENERGY CONVERSION

A system for energy conversion including a closed cycle engine containing a volume of working fluid is provided. The engine includes a double-ended piston assembly including a pair of pistons coupled to a connection member. An expansion chamber is separated from a compression chamber by the piston. The engine defines an outer end and an inner end relative to a lateral extension of the piston assembly. A heater body is positioned thermally proximal to the expansion chamber and thermally distal to the compression chamber, and the heater body is positioned at the outer end of the engine. A load device is operably coupled to the piston assembly at the inner end of the engine. The load device is positioned between the pair of pistons of the piston assembly.

Constant density heat exchanger and system for energy conversion

A constant density heat exchanger is provided. The constant density heat exchanger includes a housing extending between a first end and a second end and defining a chamber having an inlet and an outlet. A first flow control device is positioned at the inlet of the chamber and movable between an open position in which a working fluid is permitted into the chamber and a closed position in which the working fluid is prevented from entering the chamber. A second flow control device is positioned at the outlet of the chamber and movable between an open position in which the working fluid is permitted to exit the chamber and a closed position in which the working fluid is prevented from exiting the chamber. A heat exchange fluid imparts thermal energy to the volume of working fluid held at constant density within the chamber by the first and second control devices.

Hybrid-electric propulsion system for an aircraft

A hybrid-electric propulsion system for an aircraft includes a turbomachine, the turbomachine including a first spool and a second spool. A method for operating the hybrid electric propulsion system includes operating, by one or more computing devices, the turbomachine such that the first spool mechanically drives a prime propulsor of the hybrid-electric propulsion system; and modifying, by the one or more computing devices, a speed relationship parameter defined between the first spool and second spool by providing electrical power to, or drawing electrical power from, an electric machine mechanically coupled to the first spool, the second spool, or both.

PROPULSION SYSTEM FOR AN AIRCRAFT

A hybrid-electric propulsion system includes a propulsor, a turbomachine, and an electrical system having an electric machine coupled to the turbomachine. A method for operating the propulsion system includes operating, by one or more computing devices, the turbomachine to rotate the propulsor and generate thrust for the aircraft; receiving, by the one or more computing devices, data indicative of an un-commanded loss of the thrust generated from the turbomachine rotating the propulsor; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine, the propulsor, or both in response to receiving the data indicative of the un-commanded loss of thrust. 1. A method for operating a turbomachine of a hybrid-electric propulsion system of an aircraft , the hybrid-electric propulsion system comprising a propulsor , a turbomachine , and an electrical system having an electric machine coupled to the turbomachine , the method comprising:operating, by one or more computing devices, the turbomachine to rotate the propulsor and generate thrust for the aircraft;receiving, by the one or more computing devices, data indicative of an un-commanded loss of the thrust generated from the turbomachine rotating the propulsor; andproviding, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine, the propulsor, or both in response to receiving the data indicative of the un-commanded loss of thrust.2. The method of claim 1 , wherein the electrical system further comprises an electric energy storage unit claim 1 , and wherein providing claim 1 , by the one or more computing devices claim 1 , electrical power to the electric machine comprises providing claim 1 , by the one or more computing devices claim 1 , electrical power to the electric machine from the electric energy storage unit.3. The method of claim 1 , wherein the turbomachine is a first turbomachine claim 1 , ...

IRRADIATION DEVICES WITH OPTICAL MODULATORS FOR ADDITIVELY MANUFACTURING THREE-DIMENSIONAL OBJECTS

An irradiation device for additively manufacturing three-dimensional objects may include a beam generation device configured to generate an energy beam, an optical modulator including a micromirror array disposed downstream from the beam generation device, and a focusing lens assembly disposed downstream from the optical modulator. The micromirror array may include a plurality of micromirror elements configured to reflect a corresponding plurality of beam segment of the energy beam along a beam path incident upon the focusing lens assembly. The focusing lens assembly may include one or more lenses configured to focus the plurality of beam segments such that for respective ones of a plurality of modulation groups including a subset of micromirror elements, a corresponding subset of beam segments are focused to at least partially overlap with one another at a combination zone corresponding to the respective modulation group.

ENGINE APPARATUS AND METHOD FOR OPERATION

A system for energy conversion, the system including a closed cycle engine containing a volume of working fluid, the engine comprising a first chamber defining an expansion chamber and a second chamber defining a compression chamber each separated by a piston attached to a connection member of a piston assembly, and wherein the engine comprises a heater body in thermal communication with the first chamber, and further wherein the engine comprises a cold side heat exchanger in thermal communication with the second chamber, and wherein a third chamber is defined within the piston, wherein the third chamber is in selective flow communication with the first chamber, the second chamber, or both.

PROPULSION SYSTEM FOR AN AIRCRAFT

A hybrid-electric propulsion system includes a propulsor, a turbomachine, and an electrical system, the electrical system including an electric machine coupled to the turbomachine. A method for operating the propulsion system includes operating, by one or more computing devices, the turbomachine in a steady-state flight operating condition, the turbomachine rotating the propulsor when operated in the steady-state flight operating condition; receiving, by the one or more computing devices, a command to accelerate the turbomachine while operating the turbomachine in the steady-state flight operating condition; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine, the propulsor, or both in response to the received command to accelerate the turbomachine. 1. A method for operating a turbomachine of a hybrid-electric propulsion system of an aircraft , the hybrid-electric propulsion system comprising a propulsor , a turbomachine , and an electrical system , the electrical system comprising an electric machine coupled to the turbomachine , the method comprising:operating, by one or more computing devices, the turbomachine in a steady-state flight operating condition, the turbomachine rotating the propulsor when operated in the steady-state flight operating condition;receiving, by the one or more computing devices, a command to accelerate the turbomachine while operating the turbomachine in the steady-state flight operating condition; andproviding, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine, the propulsor, or both in response to the received command to accelerate the turbomachine.2. The method of claim 1 , further comprising:maintaining, by the one or more computing devices, a fuel flow to a combustion section of the turbomachine substantially constant for an initial time period in response to the received command to accelerate the ...

Irradiation devices with optical modulators for additively manufacturing three-dimensional objects

An irradiation device for additively manufacturing three-dimensional objects may include a beam generation device configured to generate an energy beam, an optical modulator including a micromirror array disposed downstream from the beam generation device, and a focusing lens assembly disposed downstream from the optical modulator. The micromirror array may include a plurality of micromirror elements configured to reflect a corresponding plurality of beam segment of the energy beam along a beam path incident upon the focusing lens assembly. The focusing lens assembly may include one or more lenses configured to focus the plurality of beam segments such that for respective ones of a plurality of modulation groups including a subset of micromirror elements, a corresponding subset of beam segments are focused to at least partially overlap with one another at a combination zone corresponding to the respective modulation group.

INTERLACE SCANNING STRATEGIES AND USES THEREOF

A method, apparatus, and program for additive manufacturing. In one aspect, the method comprises: forming an at least partially solidified portion within a first scan region (), wherein the solidified portion within the first scan region () is formed by irradiating a build material along a first irradiation path (). A second portion of a build material may be irradiated along a second irradiation path (), wherein the second scan region () is offset with respect to the first scan region () thereby defining an offset region (). The offset region () is at least partially solidified by the first irradiation path () and the second irradiation path () and a reference line () intersects the first irradiation path () and the second irradiation path () within the offset region (), wherein the reference line () is substantially parallel to a side () of the first scan region (). 1. A method for forming an object comprising:{'b': 830', '801', '811, 'irradiating a first portion of build material () within a first scan region () along a first irradiation path ();'}{'b': 803', '813', '803', '801', '802', '802', '811', '813', '819', '811', '813', '802', '819', '810', '801, 'irradiating a second portion of build material within a second scan region () along a second irradiation path (), wherein the second scan region () is offset with respect to the first scan region () thereby defining an offset region (), wherein the offset region () is at least partially solidified by the first irradiation path () and the second irradiation path () and a reference line () intersects the first irradiation path () and the second irradiation path () within the offset region (), wherein the reference line () is substantially parallel to a side () of the first scan region ().'}2830801400803400. The method of forming an object of claim 1 , wherein the first portion of build material () is irradiated within the first scan region () when a build unit () is at a first location with respect to the object ...

Energy conversion apparatus and control system

A system including a closed cycle engine having a piston body defining a hot side and a cold side and having a piston assembly movable within the piston body. An electric machine is operatively coupled with the piston assembly. A control system includes one or more sensors operable to detect a piston movement characteristic of the piston assembly movable within the piston body. A controller is communicatively coupled with the one or more sensors and a controllable device. The controller is configured to determine a control command based at least in part on data received from the one or more sensors. The control command is selected based at least in part to cause the electric machine operatively coupled with the piston assembly to generate a preselected electrical power output. The controller provides the determined control command to the controllable device. The controllable device is operable to control an input to an engine working fluid disposed within the piston body.

Shaft feedback sensor error detection

Methods and apparatus for detecting a sensor angle error in a system in which a measured quantity is determined on the basis of a phase of a signal. A signal derived from the measurement of multiple sensors is ascribed to a vector in a two-dimensional space, and a norm is calculated characterizing that vector. A value is calculated characterizing variation of that norm over a specified period of time and that value is compared with a threshold in order to identify a sensor fault.

ENERGY CONVERSION APPARATUS

An energy conversion apparatus may include an engine assembly, such as a monolithic engine assembly, that includes a first heater body and a first engine body. The first heater body may define a first portion of a first monolithic body or at least a portion of a first monolithic body-segment. The first engine body may define a second portion of the first monolithic body or at least a portion of a second monolithic body-segment operably coupled or operably couplable to the first heater body. The engine assembly may include a second heater body and/or a second engine body. The second heater body may define a portion of a second monolithic body or a third monolithic body-segment. The second engine body may define a portion of the second monolithic body or a fourth monolithic body-segment operably coupled or operably couplable to the second heater body and/or the first engine body. 1. An engine assembly , comprising:a first heater body, the first heater body defining a first portion of a first monolithic body or at least a portion of a first monolithic body-segment; anda first engine body, the first engine body defining a second portion of the first monolithic body or at least a portion of a second monolithic body-segment operably coupled or operably couplable to the first heater body.2. The engine assembly of claim 1 , wherein the first engine body comprises:a first piston body, the first piston body defining a third portion of the first monolithic body or at least a portion of the second monolithic body-segment operably coupled or operably couplable to the first heater body; and/ora first machine body, the first machine body defining a fourth portion of the first monolithic body or a third monolithic body-segment operably coupled or operably couplable to the first piston body and/or to the second monolithic body segment.3. The engine assembly of claim 1 , wherein the first heater body and/or the first engine body comprises a first regenerator body claim 1 , the first ...

PROPULSION SYSTEM FOR AN AIRCRAFT

A propulsion system for an includes a combustion engine, a propulsor, and an electric machine configured to either be driven by the combustion engine or configured to drive the propulsor. The electric machine defines an axis. The electric machine includes a rotor extending along and rotatable about the axis, and a stator having a plurality of winding assemblies, the plurality of winding assemblies spaced along the axis of the electric machine, each winding assembly operable with the rotor independently of an adjacent winding assembly during operation of the electric machine. 1. A propulsion system for an aircraft , the propulsion system comprising:a combustion engine;a propulsor; and a rotor extending along and rotatable about the axis; and', 'a stator comprising a plurality of winding assemblies, the plurality of winding assemblies spaced along the axis of the electric machine, each winding assembly operable with the rotor independently of an adjacent winding assembly during operation of the electric machine., 'an electric machine configured to either be driven by the combustion engine or configured to drive the propulsor, the electric machine defining an axis and comprising'}2. The propulsion system of claim 1 , wherein the plurality of winding assemblies includes a first winding assembly and a second winding assembly spaced along the axis of the electric machine claim 1 , and wherein the rotor extends continuously between the first winding assembly and the second winding assembly.3. The propulsion system of claim 2 , wherein the rotor comprises a plurality of permanent magnets claim 2 , and wherein the plurality of permanent magnets extend continuously between the first winding assembly and the second assembly along the axis.4. The propulsion system of claim 1 , wherein the stator comprises at least three winding assemblies and up to thirty winding assemblies.5. The propulsion system of claim 1 , wherein the rotor comprises a plurality of permanent magnets.6. The ...

Propulsion system for an aircraft

A hybrid-electric propulsion system for an aircraft includes a propulsor and a turbomachine. The turbomachine includes a high pressure turbine drivingly coupled to a high pressure compressor through a high pressure spool. The hybrid electric propulsion system further includes an electrical system including a first electric machine, a second electric machine, and an electric energy storage unit electrically connectable to the first and second electric machines. The first electric machine is coupled to the high pressure spool of the turbomachine and the second electric machine is coupled to the propulsor for driving the propulsor to provide a propulsive benefit for the aircraft. The hybrid electric propulsion system also includes a controller configured to provide electrical power from an electric power source to the first electric machine to drive the first electric machine to start, or assist with starting, the turbomachine.

PROPULSION SYSTEM FOR AN AIRCRAFT

A hybrid-electric propulsion system includes a propulsor, a turbomachine, and an electrical system. The electrical system includes a first electric machine coupled to the turbomachine and an electric energy storage unit. A method for operating the propulsion system includes operating the hybrid electric propulsion system in a flight operation mode. The method also includes operating the hybrid electric propulsion system in a maintenance operation mode, wherein operating the hybrid electric propulsion system in the maintenance operation mode includes providing electrical power from an electrical power source to the first electric machine such that the first electric machine rotates a compressor and a turbine of the turbomachine during a borescope inspection of the turbomachine. 1. A method for operating a hybrid-electric propulsion system of an aircraft , the hybrid-electric propulsion system comprising a propulsor , a turbomachine , and an electrical system , the electrical system comprising a first electric machine coupled to the turbomachine and an electric energy storage unit , the method comprising:operating the hybrid electric propulsion system in a flight operation mode, wherein operating the hybrid electric propulsion system in the flight operation mode comprises rotating the first electric machine with the turbomachine to generate electrical power and provide at least a portion of such electrical power to the electric energy storage unit; andoperating the hybrid electric propulsion system in a maintenance operation mode, wherein operating the hybrid electric propulsion system in the maintenance operation mode comprises providing electrical power from an electrical power source to the first electric machine such that the first electric machine rotates a compressor and a turbine of the turbomachine during a borescope inspection of the turbomachine.2. The method of claim 1 , wherein the hybrid electric propulsion system further comprises a propulsor claim 1 , ...

PROPULSION SYSTEM FOR AN AIRCRAFT

A hybrid-electric propulsion system includes a propulsor, a turbomachine, and an electrical system, the electrical system including an electric machine coupled to the turbomachine. A method for operating the propulsion system includes operating, by one or more computing devices, the turbomachine such that the turbomachine rotates the propulsor; receiving, by the one or more computing devices, a command to accelerate the turbomachine while operating the turbomachine; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine, the propulsor, or both in response to the received command to accelerate the turbomachine.

ENERGY CONVERSION APPARATUS

An engine body may include a piston body comprising a piston chamber and a regenerator body comprising a regenerator conduit. An engine body may include a working-fluid heat exchanger body comprising a plurality of working-fluid pathways fluidly communicating between the piston chamber and the regenerator conduit. Additionally, or alternatively, an engine body may include a heater body comprising a plurality of heating fluid pathways and the plurality of working-fluid pathways. The heating fluid pathways may have a heat transfer relationship with the working fluid pathways. The working-fluid pathways may fluidly communicate between the piston chamber and the regenerator conduit. The engine body may include a monolithic body defined at least in part by the piston body, the regenerator body, and the working-fluid heat exchanger body, and/or defined at least in part by the piston body, the regenerator body, and the heater body. 120-. (canceled)21. An engine body , comprising:a piston body comprising a piston chamber;a regenerator body comprising a regenerator conduit; anda working-fluid heat exchanger body comprising a plurality of working-fluid pathways fluidly communicating between the piston chamber and the regenerator conduit;wherein the engine body comprises a monolithic body defined at least in part by the piston body, the regenerator body, and the working-fluid heat exchanger body.22. The engine body of claim 21 , comprising:a heater body comprising a plurality of heating fluid pathways having a heat transfer relationship with the plurality of working fluid pathways.23. The engine body of claim 22 , wherein the heater body defines at least a portion of a monolithic body-segment coupled to the engine body.24. The engine body of claim 22 , wherein the heater body defines a portion of the monolithic body.25. The engine body of claim 21 , comprising:a combustor body defining a combustion chamber.26. The engine body of claim 25 , wherein the combustor body defines at ...

Hybrid-electric propulsion system for an aircraft

A method of operating a hybrid-electric propulsion system for an aircraft includes determining a flight phase parameter for the aircraft is equal to a first value, and operating the hybrid-electric propulsion system in an electric charge mode in response to determining the flight phase parameter for the aircraft is equal to the first value. The method also includes determining the flight phase parameter for the aircraft is equal to a second value different from the first value, and operating the hybrid-electric propulsion system in an electric discharge mode in response to determining the flight phase parameter for the aircraft is equal to the second value.

Propulsion system for an aircraft

A hybrid-electric propulsion system includes a turbomachine, a propulsor coupled to the turbomachine, and an electrical system, the electrical system including an electric machine coupled to the turbomachine. A method for operating a hybrid-electric propulsion system includes operating, by one or more computing devices, the turbomachine in an idle operating condition; receiving, by the one or more computing devices, a command to accelerate the turbomachine while operating the turbomachine in the idle operating condition; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine and increase an acceleration of the turbomachine in response to the received command to accelerate the turbomachine.

SYSTEM FOR ANTICIPATING LOAD CHANGES

Systems and methods for converting energy are provided. In one aspect, the system includes a closed cycle engine having a piston body and a piston assembly movable within the piston body. An electric machine is operatively coupled with the piston assembly and operable to generate electrical power. An electrical device is in communication with the electric machine. The system includes a control system having sensors, a controllable device, and a controller. The controller is configured to determine whether a load change on the electric machine is anticipated based at least in part on received data indicative of a load state of the electrical device; in response to whether the load change is anticipated, determine a control command for adjusting an output of at least one of the engine and the electric machine; and cause the controllable device to adjust the output based at least in part on the control command.

ENGINE AND ELECTRICAL MACHINE HEALTH MONITORING

Systems and methods for estimating engine and electrical machine health are provided. The systems and methods therefore include features that provide for improved health estimates of one or more engines and/or electrical machines of one or more engines having an electrical machine embedded therein or coupled thereto. In particular, the systems and methods therefore include features for utilizing sensed or measured operating parameters of the electrical machines and/or operating parameters of the prime mover to estimate the health of the prime mover and/or the electrical machines embedded therein or coupled thereto. 1. A method for monitoring the health of at least one of a prime mover and an electrical machine coupled with the prime mover , the method comprising:measuring a response to a change in torque on the electrical machine, the response indicative of a change in one or more operating parameters of at least one of the prime mover and the electrical machine; anddetermining a health estimate of at least one of the electrical machine and the prime mover based at least in part on the response.2. The method of claim 1 , wherein prior to measuring the response claim 1 , the method further comprises:pulsing the electrical machine for a predetermined time to induce the change in torque on the electrical machine.3. The method of claim 1 , wherein during determining claim 1 , the method further comprises:comparing the response to a baseline response; anddetermining a delta between the response and the baseline response;wherein the health estimate is based at least in part on the delta between the response and the baseline response.4. The method of claim 1 , wherein the change in the one or more operating parameters is indicative of a change in a power output of the prime mover.5. The method of claim 1 , wherein the response is a fuel flow response indicative of a change in fuel flow of the prime mover.6. The method of claim 1 , wherein the prime mover is a gas turbine ...

HYBRID-ELECTRIC PROPULSION SYSTEM FOR AN AIRCRAFT

A method of operating a hybrid-electric propulsion system for an aircraft includes determining a flight phase parameter for the aircraft is equal to a first value, and operating the hybrid-electric propulsion system in an electric charge mode in response to determining the flight phase parameter for the aircraft is equal to the first value. The method also includes determining the flight phase parameter for the aircraft is equal to a second value different from the first value, and operating the hybrid-electric propulsion system in an electric discharge mode in response to determining the flight phase parameter for the aircraft is equal to the second value. 1. A method of operating a hybrid-electric propulsion system for an aircraft , the method comprising:determining a flight phase parameter for the aircraft is equal to a first value;operating the hybrid-electric propulsion system in an electric charge mode in response to determining the flight phase parameter for the aircraft is equal to the first value, wherein operating the hybrid-electric propulsion system in the electric charge mode comprises driving the electric machine with a combustion engine to generate electrical power, driving a prime propulsor with the combustion engine to generate thrust, and charging an energy storage unit with at least a portion of the electrical power generated;determining the flight phase parameter for the aircraft is equal to a second value different from the first value; andoperating the hybrid-electric propulsion system in an electric discharge mode in response to determining the flight phase parameter for the aircraft is equal to the second value, wherein operating the hybrid-electric propulsion system in the electric discharge mode comprising providing electrical power from the energy storage unit to at least one of an electric propulsor assembly to drive the electric propulsor assembly or to the electric machine to drive one or more components of the combustion engine.2. The ...

Propulsion system for an aircraft

A hybrid-electric propulsion system includes a turbomachine and an electric machine coupled to the turbomachine. A method for operating the hybrid-electric propulsion system includes receiving information indicative of an operability parameter of the turbomachine; determining the turbomachine is operating within a predetermined operability range based at least in part of the received information indicative of the operability parameter of the turbomachine; and operating the hybrid electric propulsion system in an electric generation mode to generate electric power with the electric machine in response to determining the turbomachine is operating within the predetermined operability range.

Propulsion system for an aircraft

A hybrid-electric propulsion system includes a propulsor, a turbomachine, and an electrical system, the electrical system including an electric machine coupled to the turbomachine. A method for operating the propulsion system includes operating, by one or more computing devices, the turbomachine such that the turbomachine rotates the propulsor; receiving, by the one or more computing devices, a command to accelerate the turbomachine while operating the turbomachine; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine, the propulsor, or both in response to the received command to accelerate the turbomachine.

CONSTANT DENSITY HEAT EXCHANGER AND SYSTEM FOR ENERGY CONVERSION

A constant density heat exchanger and system for energy conversion is provided. The constant density heat exchanger includes a housing extending between a first end and a second end and defining a chamber having an inlet and an outlet. A first flow control device is positioned at the inlet of the chamber and movable between an open position in which a working fluid is permitted into the chamber and a closed position in which the working fluid is prevented from entering the chamber. A second flow control device is positioned at the outlet of the chamber and movable between an open position in which the working fluid is permitted to exit the chamber and a closed position in which the working fluid is prevented from exiting the chamber. A heat exchange fluid imparts thermal energy to the volume of working fluid as the first flow control device and the second flow control device hold the volume of working fluid at constant density within the chamber. 1. A constant density heat exchanger , comprising:a housing extending between a first end and a second end and defining a chamber having an inlet and an outlet;a first flow control device positioned at the inlet of the chamber and movable between an open position in which a working fluid is permitted into the chamber and a closed position in which the working fluid is prevented from entering the chamber;a second flow control device positioned at the outlet of the chamber and movable between an open position in which the working fluid is permitted to exit the chamber and a closed position in which the working fluid is prevented from exiting the chamber, andwherein a heat exchange fluid imparts thermal energy to the volume of working fluid as the first flow control device and the second flow control device hold the volume of working fluid at constant density within the chamber.2. The constant density heat exchanger of claim 1 , wherein the first flow control device comprises a first valve positioned upstream of the inlet of ...

Energy conversion apparatus

An energy conversion apparatus may include an engine assembly, such as a monolithic engine assembly, that includes a first heater body and a first engine body. The first heater body may define a first portion of a first monolithic body or at least a portion of a first monolithic body-segment. The first engine body may define a second portion of the first monolithic body or at least a portion of a second monolithic body-segment operably coupled or operably couplable to the first heater body. The engine assembly may include a second heater body and/or a second engine body. The second heater body may define a portion of a second monolithic body or a third monolithic body-segment. The second engine body may define a portion of the second monolithic body or a fourth monolithic body-segment operably coupled or operably couplable to the second heater body and/or the first engine body.

Engine and electrical machine health monitoring

Systems and methods for estimating engine and electrical machine health are provided. The systems and methods therefore include features that provide for improved health estimates of one or more engines and/or electrical machines of one or more engines having an electrical machine embedded therein or coupled thereto. In particular, the systems and methods therefore include features for utilizing sensed or measured operating parameters of the electrical machines and/or operating parameters of the prime mover to estimate the health of the prime mover and/or the electrical machines embedded therein or coupled thereto.

Interlace scanning strategies and uses thereof

A method, apparatus, and program for additive manufacturing. In one aspect, the method comprises: forming an at least partially solidified portion within a first scan region (801), wherein the solidified portion within the first scan region (801) is formed by irradiating a build material along a first irradiation path (811). A second portion of a build material may be irradiated along a second irradiation path (813), wherein the second scan region (803) is offset with respect to the first scan region (801) thereby defining an offset region (802). The offset region (802) is at least partially solidified by the first irradiation path (811) and the second irradiation path (813) and a reference line (819) intersects the first irradiation path (811) and the second irradiation path (813) within the offset region (802), wherein the reference line (819) is substantially parallel to a side (810) of the first scan region (801).

Propulsion system for an aircraft

A hybrid-electric propulsion system includes a turbomachine and an electrical system, the electrical system including an electric machine coupled to the turbomachine. A method for operating the propulsion system includes receiving, by one or more computing devices, a command to accelerate the turbomachine to provide a desired thrust output; receiving, by the one or more computing devices, data indicative of a temperature parameter approaching or exceeding an upper threshold; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine to provide, or assist with providing, the desired thrust output in response to receiving the command to accelerate the turbomachine and receiving the data indicative of the temperature parameter approaching or exceeding the upper threshold.

Constant density heat exchanger and system for energy conversion

A constant density heat exchanger is provided. The constant density heat exchanger includes a housing extending between a first end and a second end and defining a chamber having an inlet and an outlet. A first flow control device is positioned at the inlet of the chamber and movable between an open position in which a working fluid is permitted into the chamber and a closed position in which the working fluid is prevented from entering the chamber. A second flow control device is positioned at the outlet of the chamber and movable between an open position in which the working fluid is permitted to exit the chamber and a closed position in which the working fluid is prevented from exiting the chamber. A heat exchange fluid imparts thermal energy to the volume of working fluid held at constant density within the chamber by the first and second control devices.

System for anticipating load changes

Systems and methods for converting energy are provided. In one aspect, the system includes a closed cycle engine having a piston body and a piston assembly movable within the piston body. An electric machine is operatively coupled with the piston assembly and operable to generate electrical power. An electrical device is in communication with the electric machine. The system includes a control system having sensors, a controllable device, and a controller. The controller is configured to determine whether a load change on the electric machine is anticipated based at least in part on received data indicative of a load state of the electrical device; in response to whether the load change is anticipated, determine a control command for adjusting an output of at least one of the engine and the electric machine; and cause the controllable device to adjust the output based at least in part on the control command.

Hybrid-electric propulsion system for an aircraft

A computer-implemented method of assessing a health of a gas turbine engine of a hybrid-electric propulsion system for an aircraft includes receiving, by one or more computing devices, data indicative of an amount of electrical power provided to, or extracted from, an electric machine. The method also includes receiving, by the one or more computing devices, data indicative of an operating parameter of the hybrid-electric propulsion system. The method also includes assessing, by the one or more computing devices, a health of the gas turbine engine based at least in part on the received data indicative of the amount of electrical power provided to, or extracted from, the electric machine and the received data indicative of the operating parameter of the hybrid electric propulsion system. The method also includes providing, by the one or more computing devices, information to a user indicative of the health of the gas turbine engine.

Energy conversion apparatus

An engine body may include a piston body comprising a piston chamber and a regenerator body comprising a regenerator conduit. An engine body may include a working-fluid heat exchanger body comprising a plurality of working-fluid pathways fluidly communicating between the piston chamber and the regenerator conduit. Additionally, or alternatively, an engine body may include a heater body comprising a plurality of heating fluid pathways and the plurality of working-fluid pathways. The heating fluid pathways may have a heat transfer relationship with the working fluid pathways. The working-fluid pathways may fluidly communicate between the piston chamber and the regenerator conduit. The engine body may include a monolithic body defined at least in part by the piston body, the regenerator body, and the working-fluid heat exchanger body, and/or defined at least in part by the piston body, the regenerator body, and the heater body.

CONSTANT DENSITY HEAT EXCHANGER AND SYSTEM FOR ENERGY CONVERSION

A constant density heat exchanger and system for energy conversion is provided. The constant density heat exchanger includes a housing extending between a first end and a second end and defining a chamber having an inlet and an outlet. A first flow control device is positioned at the inlet of the chamber and movable between an open position in which a working fluid is permitted into the chamber and a closed position in which the working fluid is prevented from entering the chamber. A second flow control device is positioned at the outlet of the chamber and movable between an open position in which the working fluid is permitted to exit the chamber and a closed position in which the working fluid is prevented from exiting the chamber. A heat exchange fluid imparts thermal energy to the volume of working fluid as the first flow control device and the second flow control device hold the volume of working fluid at constant density within the chamber.

PROPULSION SYSTEM FOR AN AIRCRAFT

A hybrid-electric propulsion system includes a turbomachine and an electrical system, the electrical system including an electric machine coupled to the turbomachine. A method for operating the propulsion system includes receiving, by one or more computing devices, a command to accelerate the turbomachine to provide a desired thrust output; receiving, by the one or more computing devices, data indicative of a temperature parameter approaching or exceeding an upper threshold; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine to provide, or assist with providing, the desired thrust output in response to receiving the command to accelerate the turbomachine and receiving the data indicative of the temperature parameter approaching or exceeding the upper threshold. 1. A method for operating a turbomachine of a hybrid-electric propulsion system of an aircraft , the hybrid-electric propulsion system comprising a turbomachine and an electrical system , the electrical system comprising an electric machine coupled to the turbomachine , the method comprising:receiving, by one or more computing devices, a command to accelerate the turbomachine to provide a desired thrust output;receiving, by the one or more computing devices, data indicative of a temperature parameter approaching or exceeding an upper threshold; andproviding, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine to provide, or assist with providing, the desired thrust output in response to receiving the command to accelerate the turbomachine and receiving the data indicative of the temperature parameter approaching or exceeding the upper threshold.2. The method of claim 1 , wherein receiving claim 1 , by one or more computing devices claim 1 , the command to accelerate the turbomachine to provide the desired thrust output comprises receiving claim 1 , by one or more computing ...

PROPULSION SYSTEM FOR AN AIRCRAFT

A hybrid-electric propulsion system includes a turbomachine and an electric machine coupled to the turbomachine. A method for operating the hybrid-electric propulsion system includes receiving information indicative of an operability parameter of the turbomachine; determining the turbomachine is operating within a predetermined operability range based at least in part of the received information indicative of the operability parameter of the turbomachine; and operating the hybrid electric propulsion system in an electric generation mode to generate electric power with the electric machine in response to determining the turbomachine is operating within the predetermined operability range. 1. A method for operating a hybrid-electric propulsion system of an aircraft , the hybrid-electric propulsion system comprising a turbomachine and an electric machine coupled to the turbomachine , the method comprising:receiving information indicative of an operability parameter of the turbomachine;determining the turbomachine is operating within a predetermined operability range based at least in part of the received information indicative of the operability parameter of the turbomachine; andoperating the hybrid electric propulsion system in an electric generation mode to generate electric power with the electric machine in response to determining the turbomachine is operating within the predetermined operability range.2. The method of claim 1 , wherein receiving information indicative of the operability parameter of the turbomachine comprises receiving information indicative of an exhaust gas temperature of the turbomachine claim 1 , and wherein determining the turbomachine is operating within the predetermined operability range comprises determining the exhaust gas temperature of the turbomachine is below an exhaust gas temperature threshold.3. The method of claim 1 , wherein receiving information indicative of the operability parameter of the turbomachine comprises receiving ...

Energy conversion apparatus

A monolithic engine assembly may include an engine body that includes a regenerator body. The engine body and the regenerator body may respectively define at least a portion of a monolithic body, or the engine body may define at least a portion of a first monolithic body-segment and the regenerator body may define at least a portion of a second monolithic body-segment operably coupled or operably couplable to the first monolithic body-segment. The regenerator body may include a regenerator conduit, and a plurality of fin arrays adjacently disposed within the regenerator conduit and respectively supported by the regenerator conduit in spaced relation to one another. The spaced relation of the plurality of fin arrays may define a gap longitudinally separating adjacent ones of the plurality of fin arrays.

PROPULSION SYSTEM FOR AN AIRCRAFT

A hybrid-electric propulsion system includes a turbomachine, a propulsor coupled to the turbomachine, and an electrical system, the electrical system including an electric machine coupled to the turbomachine. A method for operating a hybrid-electric propulsion system includes operating, by one or more computing devices, the turbomachine in an idle operating condition; receiving, by the one or more computing devices, a command to accelerate the turbomachine while operating the turbomachine in the idle operating condition; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine and increase an acceleration of the turbomachine in response to the received command to accelerate the turbomachine.

POWDER RECLAMATION AND CLEANING SYSTEM FOR AN ADDITIVE MANUFACTURING MACHINE

An additive manufacturing machine () includes a build unit () comprising a powder dispenser () including a hopper () for receiving a volume of additive powder (). A powder supply system () includes a powder supply source () for providing additive powder () into the hopper () during a refill process. A powder reclamation system () includes a vacuum pump () coupled to a vacuum duct () defining a suction inlet () positioned for collecting misdirected additive powder () dispensed during the refill process. A return duct () includes a filter mechanism () may filter and return the collected additive powder () back to the powder supply source () for reuse. 1910910. An additive manufacturing machine () defining a vertical direction (V) , the additive manufacturing machine () comprising:{'b': 920', '906', '1004', '1006, 'a build unit () comprising a powder dispenser () including a hopper () for receiving a volume of additive powder ();'}{'b': 1000', '1010', '1006', '1004, 'a powder supply system () comprising a powder supply source () for providing additive powder () into the hopper () during a refill process; and'}{'b': '1002', 'claim-text': [{'b': '1030', 'a vacuum pump () for generating a vacuum; and'}, {'b': 1034', '1036', '1030', '1040', '1040', '1006, 'a vacuum duct (, ) extending from the vacuum pump () to a suction inlet (), the suction inlet () being positioned for collecting misdirected additive powder () dispensed during the refill process.'}], 'a powder reclamation system () comprising291010001014100610101004101610141004. The additive manufacturing machine () of claim 1 , wherein the powder supply system () further comprises a conveyor () that transports additive powder () dispensed from the powder supply source () to the hopper () claim 1 , a discharge () of the conveyor () being positioned over the hopper () along the vertical direction (V).391010401016101410061004. The additive manufacturing machine () of claim 2 , wherein the suction inlet () is positioned ...

ENERGY CONVERSION APPARATUS

An energy conversion apparatus may include an engine assembly, such as a monolithic engine assembly. The engine assembly may include a first monolithic body segment and a plurality of second monolithic body segments directly coupled or directly couplable to the first monolithic body segment. The first monolithic body segment may define a combustion chamber and a recirculation pathway in fluid communication with the combustion chamber. The recirculation pathway may be configured to recirculate combustion gas through the combustion chamber. The plurality of second monolithic body segments may respectively define at least a portion of a piston chamber and a plurality of working-fluid pathways fluidly communicating with the piston chamber.

ENERGY CONVERSION APPARATUS

A monolithic engine assembly may include an engine body that includes a regenerator body. The engine body and the regenerator body may respectively define at least a portion of a monolithic body, or the engine body may define at least a portion of a first monolithic body-segment and the regenerator body may define at least a portion of a second monolithic body-segment operably coupled or operably couplable to the first monolithic body-segment. The regenerator body may include a regenerator conduit, and a plurality of fin arrays adjacently disposed within the regenerator conduit and respectively supported by the regenerator conduit in spaced relation to one another. The spaced relation of the plurality of fin arrays may define a gap longitudinally separating adjacent ones of the plurality of fin arrays. 1. A monolithic engine assembly , comprising:an engine body comprising a regenerator body, wherein the engine body and the regenerator body respectively define at least a portion of a monolithic body, or wherein the engine body defines at least a portion of a first monolithic body-segment and the regenerator body defines at least a portion of a second monolithic body-segment operably coupled or operably couplable to the first monolithic body-segment.2. The monolithic engine assembly of claim 1 , comprising:a piston body, wherein the piston body defines at least a portion of the engine body, or wherein the piston body defines a third monolithic body-segment operably coupled or operably couplable to the engine body; andwherein the regenerator body defines a portion of the piston body, or wherein the regenerator body is operably coupled or operably couplable to the piston body.3. The monolithic engine assembly of claim 2 , comprising:a working-fluid heat exchanger body, the working-fluid heat exchanger body comprising a plurality of working-fluid pathways fluidly communicating between a piston chamber defined by the piston body and a regenerator conduit defined by the ...

Propulsion system for an aircraft

A propulsion system for an includes a combustion engine, a propulsor, and an electric machine configured to either be driven by the combustion engine or configured to drive the propulsor. The electric machine defines an axis. The electric machine includes a rotor extending along and rotatable about the axis, and a stator having a plurality of winding assemblies, the plurality of winding assemblies spaced along the axis of the electric machine, each winding assembly operable with the rotor independently of an adjacent winding assembly during operation of the electric machine.

IRRADIATION DEVICES WITH OPTICAL MODULATORS FOR ADDITIVELY MANUFACTURING THREE-DIMENSIONAL OBJECTS

An irradiation device for additively manufacturing three-dimensional objects may include a beam generation device configured to generate an energy beam, an optical modulator including a micromirror array disposed downstream from the beam generation device, and a focusing lens assembly disposed downstream from the optical modulator. The micromirror array may include a plurality of micromirror elements configured to reflect a corresponding plurality of beam segment of the energy beam along a beam path incident upon the focusing lens assembly. The focusing lens assembly may include one or more lenses configured to focus the plurality of beam segments such that for respective ones of a plurality of modulation groups including a subset of micromirror elements, a corresponding subset of beam segments are focused to at least partially overlap with one another at a combination zone corresponding to the respective modulation group.

Energy conversion apparatus

An energy conversion apparatus may include an engine assembly, such as a monolithic engine assembly. The engine assembly may include a first monolithic body segment and a plurality of second monolithic body segments directly coupled or directly couplable to the first monolithic body segment. The first monolithic body segment may define a combustion chamber and a recirculation pathway in fluid communication with the combustion chamber. The recirculation pathway may be configured to recirculate combustion gas through the combustion chamber. The plurality of second monolithic body segments may respectively define at least a portion of a piston chamber and a plurality of working-fluid pathways fluidly communicating with the piston chamber.

IRRADIATION DEVICES WITH OPTICAL MODULATORS FOR ADDITIVELY MANUFACTURING THREE-DIMENSIONAL OBJECTS

An irradiation device for additively manufacturing three-dimensional objects may include a beam generation device configured to generate an energy beam, an optical modulator including a micromirror array disposed downstream from the beam generation device, and a focusing lens assembly disposed downstream from the optical modulator. The micromirror array may include a plurality of micromirror elements configured to reflect a corresponding plurality of beam segment of the energy beam along a beam path incident upon the focusing lens assembly. The focusing lens assembly may include one or more lenses configured to focus the plurality of beam segments such that for respective ones of a plurality of modulation groups including a subset of micromirror elements, a corresponding subset of beam segments are focused to at least partially overlap with one another at a combination zone corresponding to the respective modulation group.

System for anticipating load changes

Systems and methods for converting energy are provided. In one aspect, the system includes a closed cycle engine having a piston body and a piston assembly movable within the piston body. An electric machine is operatively coupled with the piston assembly and operable to generate electrical power. An electrical device is in communication with the electric machine. The system includes a control system having sensors, a controllable device, and a controller. The controller is configured to determine whether a load change on the electric machine is anticipated based at least in part on received data indicative of a load state of the electrical device; in response to whether the load change is anticipated, determine a control command for adjusting an output of at least one of the engine and the electric machine; and cause the controllable device to adjust the output based at least in part on the control command.

System and apparatus for energy conversion

An aspect of the present disclosure is directed to a system for energy conversion. The system includes a closed cycle engine containing a volume of working fluid. The engine includes an expansion chamber and a compression chamber each separated by a piston attached to a connection member of a piston assembly. The engine further includes a plurality of heater conduits extended from the expansion chamber. The engine includes a plurality of chiller conduits extended from the compression chamber. The expansion chamber and heater conduits are fluidly connected to the compression chamber and chiller conduits via a walled conduit.

Propulsion system for an aircraft

A hybrid-electric propulsion system includes a propulsor, a turbomachine, and an electrical system, the electrical system including an electric machine coupled to the turbomachine. A method for operating the propulsion system includes operating, by one or more computing devices, the turbomachine in a steady-state flight operating condition, the turbomachine rotating the propulsor when operated in the steady-state flight operating condition; receiving, by the one or more computing devices, a command to accelerate the turbomachine while operating the turbomachine in the steady-state flight operating condition; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine, the propulsor, or both in response to the received command to accelerate the turbomachine.

HYBRID-ELECTRIC PROPULSION SYSTEM FOR AN AIRCRAFT

A hybrid-electric propulsion system for an aircraft includes a turbomachine, the turbomachine including a first spool and a second spool. A method for operating the hybrid electric propulsion system includes operating, by one or more computing devices, the turbomachine such that the first spool mechanically drives a prime propulsor of the hybrid-electric propulsion system; and modifying, by the one or more computing devices, a speed relationship parameter defined between the first spool and second spool by providing electrical power to, or drawing electrical power from, an electric machine mechanically coupled to the first spool, the second spool, or both. 1. A method of operating a hybrid-electric propulsion system for an aircraft having a turbomachine , the turbomachine including a first spool and a second spool , the method comprising:operating, by one or more computing devices, the turbomachine such that the first spool mechanically drives a prime propulsor of the hybrid-electric propulsion system; andmodifying, by the one or more computing devices, a speed relationship parameter defined between the first spool and second spool by providing electrical power to, or drawing electrical power from, an electric machine mechanically coupled to the first spool, the second spool, or both.2. The method of claim 1 , wherein modifying claim 1 , by the one or more computing devices claim 1 , the speed relationship parameter defined between the first spool and second spool comprises:receiving, by the one or more computing devices, data indicative of a rotational speed of the first spool;receiving, by the one or more computing devices, data indicative of a rotational speed of the second spool;determining, by the one or more computing devices, the speed relationship parameter is outside a desired speed relationship parameter range; andproviding, by the one or more computing devices, electrical power to, or drawing, by the one or more computing devices, electrical power from, ...

PROPULSION SYSTEM FOR AN AIRCRAFT

A hybrid-electric propulsion system includes an electric machine coupled to a rotating system of the turbomachine and an electric energy storage unit, the electric machine electrically coupled to an electric power source. A method for operating the turbomachine of a hybrid-electric propulsion system includes providing electrical power from the electric machine to the electric energy storage unit during a flight operation mode of the turbomachine, the turbomachine rotating the electric machine to generate electrical power during the flight operating mode; determining the turbomachine is in a post flight operation mode or in a pre-flight operation mode; and providing electrical power from the electric power source to the electric machine such that the electric machine rotates the rotating system of the turbomachine to prevent or correct a bowed rotor condition. 1. A method for operating a turbomachine of a hybrid-electric propulsion system of an aircraft , the hybrid-electric propulsion system comprising an electric machine coupled to a rotating system of the turbomachine , the electric machine electrically coupled to an electric power source , the method comprising:rotating the electric machine with the turbomachine to generate electrical power during a flight operation mode of the turbomachine;rotating a propulsor of the hybrid electric propulsion system utilizing at least in part the electrical power generated from the rotating of the electric machine with the turbomachine to provide a propulsive benefit for the aircraft during the flight operation mode of the turbomachine;determining the turbomachine is in a post flight operation mode or in a pre-flight operation mode; andproviding electrical power from the electric power source to the electric machine such that the electric machine rotates the rotating system of the turbomachine to prevent or correct a bowed rotor condition.2. The method of claim 1 , wherein determining the turbomachine is in the post flight ...

Closed cycle engine with bottoming-cycle system

Systems and methods for converting energy are provided. In one aspect, the system includes a closed cycle engine defining a cold side. The system also includes a bottoming-cycle loop. A pump is operable to move a working fluid along the bottoming-cycle loop. A cold side heat exchanger is positioned along the bottoming-cycle loop in a heat exchange relationship with the cold side of the closed cycle engine. A constant density heat exchanger is positioned along the bottoming-cycle loop downstream of the cold side heat exchanger and upstream of an expansion device. The constant density heat exchanger is operable to hold a volume of the working fluid flowing therethrough at constant density while increasing, via a heat source, the temperature and pressure of the working fluid. The expansion device receives the working fluid at elevated temperature and pressure and extracts thermal energy from the working fluid to produce work.

Propulsion system for an aircraft

Engine apparatus and method for operation

A system for energy conversion, the system including a closed cycle engine containing a volume of working fluid, the engine comprising a first chamber defining an expansion chamber and a second chamber defining a compression chamber each separated by a piston attached to a connection member of a piston assembly, and wherein the engine comprises a heater body in thermal communication with the first chamber, and further wherein the engine comprises a cold side heat exchanger in thermal communication with the second chamber, and wherein a third chamber is defined within the piston, wherein the third chamber is in selective flow communication with the first chamber, the second chamber, or both.

Method for health monitoring and gas turbine engine

Propulsion system for an aircraft

A hybrid-electric propulsion system includes a turbomachine, a propulsor coupled to the turbomachine, and an electrical system, the electrical system including an electric machine coupled to the turbomachine. A method for operating a hybrid-electric propulsion system includes operating, by one or more computing devices, the turbomachine in an idle operating condition; receiving, by the one or more computing devices, a command to accelerate the turbomachine while operating the turbomachine in the idle operating condition; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine and increase an acceleration of the turbomachine in response to the received command to accelerate the turbomachine.

Propulsion system for an aircraft

A hybrid-electric propulsion system includes a turbomachine, a propulsor coupled to the turbomachine, and an electrical system, the electrical system including an electric machine coupled to the turbomachine. A method for operating a hybrid-electric propulsion system includes operating, by one or more computing devices, the turbomachine in an idle operating condition; receiving, by the one or more computing devices, a command to accelerate the turbomachine while operating the turbomachine in the idle operating condition; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine and increase an acceleration of the turbomachine in response to the received command to accelerate the turbomachine.

Hybrid-electric propulsion system for an aircraft

A method of operating a hybrid-electric propulsion system for an aircraft includes determining a flight phase parameter for the aircraft is equal to a first value, and operating the hybrid-electric propulsion system in an electric charge mode in response to determining the flight phase parameter for the aircraft is equal to the first value. The method also includes determining the flight phase parameter for the aircraft is equal to a second value different from the first value, and operating the hybrid-electric propulsion system in an electric discharge mode in response to determining the flight phase parameter for the aircraft is equal to the second value.

Propulsion system for an aircraft

A hybrid-electric propulsion system includes a propulsor, a turbomachine, and an electrical system. The electrical system includes a first electric machine coupled to the turbomachine and an electric energy storage unit. A method for operating the propulsion system includes operating the hybrid electric propulsion system in a flight operation mode. The method also includes operating the hybrid electric propulsion system in a maintenance operation mode, wherein operating the hybrid electric propulsion system in the maintenance operation mode includes providing electrical power from an electrical power source to the first electric machine such that the first electric machine rotates a compressor and a turbine of the turbomachine during a borescope inspection of the turbomachine.

Propulsion system for an aircraft

A hybrid-electric propulsion system includes a propulsor, a turbomachine, and an electrical system having an electric machine coupled to the turbomachine. A method for operating the propulsion system includes operating, by one or more computing devices, the turbomachine to rotate the propulsor and generate thrust for the aircraft; receiving, by the one or more computing devices, data indicative of an un-commanded loss of the thrust generated from the turbomachine rotating the propulsor; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine, the propulsor, or both in response to receiving the data indicative of the un-commanded loss of thrust.

Propulsion system for an aircraft

A hybrid-electric propulsion system includes a turbomachine and an electrical system, the electrical system including an electric machine coupled to the turbomachine. A method for operating the propulsion system includes receiving, by one or more computing devices, a command to accelerate the turbomachine to provide a desired thrust output; receiving, by the one or more computing devices, data indicative of a temperature parameter approaching or exceeding an upper threshold; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine to provide, or assist with providing, the desired thrust output in response to receiving the command to accelerate the turbomachine and receiving the data indicative of the temperature parameter approaching or exceeding the upper threshold.

Energy conversion apparatus

An energy conversion apparatus may include an engine assembly (c900), such as a monolithic engine assembly (c900), that includes a first heater body (c902) and a first engine body (c904). The first heater body (c902) may define a first portion of a first monolithic body (c908) or at least a portion of a first monolithic body-segment (c912). The first engine body (c904) may define a second portion of the first monolithic body (c908) or at least a portion of a second monolithic body-segment (c914) operably coupled or operably couplable to the first heater body (c902). The engine assembly (c900) may include a second heater body (c930) and/or a second engine body. The second heater body (c930) may define a portion of a second monolithic body (c936) or a fourth monolithic body-segment (c940). The second engine body (c942) may define a portion of the second monolithic body (c936) or a fifth monolithic body-segment (c942) operably coupled or operably couplable to the second heater body (c930) and/or the first engine body (c904).

Propulsion system for an aircraft

A hybrid-electric propulsion system includes a propulsor, a turbomachine, and an electrical system, the electrical system including an electric machine coupled to the turbomachine. A method for operating the propulsion system includes operating, by one or more computing devices, the turbomachine such that the turbomachine rotates the propulsor; receiving, by the one or more computing devices, a command to accelerate the turbomachine while operating the turbomachine; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine, the propulsor, or both in response to the received command to accelerate the turbomachine.

Proplusion system for an aircraft

Energy conversion apparatus

A monolithic engine assembly (c900) may include an engine body (c050) that includes a regenerator body (c800). The engine body (c050) and the regenerator body (c800) may respectively define at least a portion of a monolithic body, or the engine body (c050) may define at least a portion of a first monolithic body-segment and the regenerator body (c800) may define at least a portion of a second monolithic body-segment operably coupled or operably couplable to the first monolithic body-segment. The regenerator body (c800) may include a regenerator conduit (c1000), and a plurality of fin arrays (c1016) adjacently disposed within the regenerator conduit (c1000) and respectively supported by the regenerator conduit (c1000) in spaced relation to one another. The spaced relation of the plurality of fin arrays (c1016) may define a gap (c1018) longitudinally separating adjacent ones of the plurality of fin arrays (c1016).

Energy conversion apparatus and control system

A system including a closed cycle engine having a piston body defining a hot side and a cold side and having a piston assembly movable within the piston body. An electric machine is operatively coupled with the piston assembly. A control system includes one or more sensors operable to detect a piston movement characteristic of the piston assembly movable within the piston body. A controller is communicatively coupled with the one or more sensors and a controllable device. The controller is configured to determine a control command based at least in part on data received from the one or more sensors. The control command is selected based at least in part to cause the electric machine operatively coupled with the piston assembly to generate a preselected electrical power output. The controller provides the determined control command to the controllable device. The controllable device is operable to control an input to an engine working fluid disposed within the piston body.

Propulsion system for an aircraft

A hybrid-electric propulsion system for an aircraft includes a propulsor and a turbomachine. The turbomachine includes a high pressure turbine drivingly coupled to a high pressure compressor through a high pressure spool. The hybrid electric propulsion system further includes an electrical system including a first electric machine, a second electric machine, and an electric energy storage unit electrically connectable to the first and second electric machines. The first electric machine is coupled to the high pressure spool of the turbomachine and the second electric machine is coupled to the propulsor for driving the propulsor to provide a propulsive benefit for the aircraft. The hybrid electric propulsion system also includes a controller configured to provide electrical power from an electric power source to the first electric machine to drive the first electric machine to start, or assist with starting, the turbomachine.

Propulsion system for an aircraft

Engine apparatus and method for operation

An engine apparatus including at least four piston assemblies is provided. Each piston assembly includes a piston attached to a connection member at a first end and a second end. Each piston of the piston assembly defines a first chamber and a second chamber separated by the piston. The first chamber and the second chamber are each defined at the first end and at the second end. Each first chamber of one piston assembly is fluidly connected to the second chamber at a different piston assembly. At least one first chamber at the first end is fluidly connected to a respective second chamber at the second end. At least one first chamber at the second end is fluidly connected to a respective second chamber at the first end. At least one first chamber at one end is fluidly connected to a respective second chamber at the same end.

System and apparatus for energy conversion

A system and apparatus for energy conversion.

System and apparatus for energy conversion

Propulsion system for an aircraft

Propulsion system for an aircraft

A propulsion system includes a combustion engine, a propulsor, and an electric machine configured to either be driven by the combustion engine or configured to drive the propulsor. The electric machine defines an axis. The electric machine includes a rotor extending along and rotatable about the axis, and a stator having a plurality of winding assemblies, the plurality of winding assemblies spaced along the axis of the electric machine, each winding assembly operable with the rotor independently of an adjacent winding assembly during operation of the electric machine.

Propulsion system for an aircraft

A hybrid-electric propulsion system (50) for an aircraft (10) includes a propulsor (104) and a turbomachine (102). The turbomachine (102) includes a high pressure turbine (116) drivingly coupled to a high pressure compressor (112) through a high pressure spool (122). The hybrid electric propulsion system (50) further includes an electrical system including a first electric machine, a second electric machine, and an electric energy storage unit (55) electrically connectable to the first and second electric machines. The first electric machine is coupled to the high pressure spool (122) of the turbomachine (102) and the second electric machine is coupled to the propulsor (104) for driving the propulsor (104) to provide a propulsive benefit for the aircraft (10). The hybrid electric propulsion system (50) also includes a controller configured to provide electrical power from an electric power source to the first electric machine to drive the first electric machine to start, or assist with starting, the turbomachine (102).

航空機用推進システム

【課題】ハイブリッド電気航空機推進システムの電気エネルギー蓄積ユニットを充電するための方法を提供する。 【解決手段】ハイブリッド電気推進システム（５０）は、ターボ機械（１０２）と、ターボ機械（１０２）に連結された電気機械（５６）とを含む。ハイブリッド電気推進システム（５０）を動作させるための方法は、ターボ機械（１０２）の動作可能性パラメータを示す情報を受信するステップと、ターボ機械（１０２）の動作可能性パラメータを示す受信した情報の少なくとも一部に基づいて、ターボ機械（１０２）が所定の動作可能性範囲内で動作していることを判定するステップと、ターボ機械（１０２）が所定の動作可能性範囲内で動作していると判定したことに応答して、電気機械（５６）を用いて電力を発生させるためにハイブリッド電気推進システム（５０）を発電モードで動作させるステップとを含む方法。 【選択図】図４

System and apparatus for energy conversion

An aspect of the present disclosure is directed to a system for energy conversion. The system includes a closed cycle engine containing a volume of working fluid. The engine includes an expansion chamber and a compression chamber each separated by a piston attached to a connection member of a piston assembly. The engine further includes a plurality of heater conduits extended from the expansion chamber. The engine includes a plurality of chiller conduits extended from the compression chamber. The expansion chamber and heater conduits are fluidly connected to the compression chamber and chiller conduits via a walled conduit.

Propulsion system for an aircraft

A hybrid-electric propulsion system 50 includes a turbomachine 102 and an electric machine 56 coupled to the turbomachine 102. A method for operating the hybrid-electric propulsion system 50 includes receiving information indicative of an operability parameter of the turbomachine 102; determining the turbomachine 102 is operating within a predetermined operability range based at least in part of the received information indicative of the operability parameter of the turbomachine 102; and operating the hybrid electric propulsion system 50 in an electric generation mode to generate electric power with the electric machine 56 in response to determining the turbomachine 102 is operating within the predetermined operability range.

Irradiation devices with optical modulators for additively manufacturing three-dimensional objects

An irradiation device for additively manufacturing three-dimensional objects may include a beam generation device configured to generate an energy beam, an optical modulator including a micromirror array disposed downstream from the beam generation device, and a focusing lens assembly disposed downstream from the optical modulator. The micromirror array may include a plurality of micromirror elements configured to reflect a corresponding plurality of beam segment of the energy beam along a beam path incident upon the focusing lens assembly. The focusing lens assembly may include one or more lenses configured to focus the plurality of beam segments such that for respective ones of a plurality of modulation groups including a subset of micromirror elements, a corresponding subset of beam segments are focused to at least partially overlap with one another at a combination zone corresponding to the respective modulation group.

Irradiation devices with optical modulators for additively manufacturing three-dimensional objects

An irradiation device for additively manufacturing three-dimensional objects may include a beam generation device configured to generate an energy beam, an optical modulator including a micromirror array disposed downstream from the beam generation device, and a focusing lens assembly disposed downstream from the optical modulator. The micromirror array may include a plurality of micromirror elements configured to reflect a corresponding plurality of beam segment of the energy beam along a beam path incident upon the focusing lens assembly. The focusing lens assembly may include one or more lenses configured to focus the plurality of beam segments such that for respective ones of a plurality of modulation groups including a subset of micromirror elements, a corresponding subset of beam segments are focused to at least partially overlap with one another at a combination zone corresponding to the respective modulation group.

Propulsion system for an aircraft

A hybrid-electric propulsion system (50) for an aircraft (10) includes a propulsor (104) and a turbomachine (102). The turbomachine (102) includes a high pressure turbine (116) drivingly coupled to a high pressure compressor (112) through a high pressure spool (122). The hybrid electric propulsion system (50) further includes an electrical system including a first electric machine, a second electric machine, and an electric energy storage unit (55) electrically connectable to the first and second electric machines. The first electric machine is coupled to the high pressure spool (122) of the turbomachine (102) and the second electric machine is coupled to the propulsor (104) for driving the propulsor (104) to provide a propulsive benefit for the aircraft (10). The hybrid electric propulsion system (50) also includes a controller configured to provide electrical power from an electric power source to the first electric machine to drive the first electric machine to start, or assist with starting, the turbomachine (102).

Hybrid propulsion system for use during uncommanded thrust loss and method of operating

A hybrid-electric propulsion system includes a propulsor, a turbomachine, and an electrical system having an electric machine coupled to the turbomachine. A method for operating the propulsion system includes operating, by one or more computing devices, the turbomachine to rotate the propulsor and generate thrust for the aircraft; receiving, by the one or more computing devices, data indicative of an un-commanded loss of the thrust generated from the turbomachine rotating the propulsor; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine, the propulsor, or both in response to receiving the data indicative of the un-commanded loss of thrust.

System and apparatus for energy conversion

A system and apparatus for energy conversion.

Engine apparatus and method for operation

Irradiation devices with optical modulators for additively manufacturing three-dimensional objects

An irradiation device for additively manufacturing three-dimensional objects may include a beam generation device configured to generate an energy beam, an optical modulator including a micromirror array disposed downstream from the beam generation device, and a focusing lens assembly disposed downstream from the optical modulator. The micromirror array may include a plurality of micromirror elements configured to reflect a corresponding plurality of beam segment of the energy beam along a beam path incident upon the focusing lens assembly. The focusing lens assembly may include one or more lenses configured to focus the plurality of beam segments such that for respective ones of a plurality of modulation groups including a subset of micromirror elements, a corresponding subset of beam segments are focused to at least partially overlap with one another at a combination zone corresponding to the respective modulation group.

Engine apparatus and method for operation

A system for energy conversion, the system including a closed cycle engine containing a volume of working fluid, the engine comprising a first chamber defining an expansion chamber and a second chamber defining a compression chamber each separated by a piston attached to a connection member of a piston assembly, and wherein the engine comprises a heater body in thermal communication with the first chamber, and further wherein the engine comprises a cold side heat exchanger in thermal communication with the second chamber, and wherein a third chamber is defined within the piston, wherein the third chamber is in selective flow communication with the first chamber, the second chamber, or both.

Engine apparatus and method for operation

Propulsion system for an aircraft

A hybrid-electric propulsion system includes a propulsor, a turbomachine, and an electrical system having an electric machine coupled to the turbomachine. A method for operating the propulsion system includes operating, by one or more computing devices, the turbomachine to rotate the propulsor and generate thrust for the aircraft; receiving, by the one or more computing devices, data indicative of an un-commanded loss of the thrust generated from the turbomachine rotating the propulsor; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine, the propulsor, or both in response to receiving the data indicative of the un-commanded loss of thrust.