Gas turbine engine variable geometry flow component

A variable geometry mechanism suitable for use in a gas turbine engine is disclosed in which movable vane segments which are coupled to a rotatable ring, or rings, are used to change an aerodynamic property of a working fluid flowing through the gas turbine engine. The movable vane segments can be rotated through the ring, or rings, between a first position associated with the first vane and a second position associated with a second vane to place the movable vane segments in proximity to one or the other of the first and second vanes of the gas turbine engine. The movable vane segments can be used to alter, among other things, camber, exit flow area, and can be used to influence and/or accommodate such properties as incidence angle, and swirl angle.

Engine liquid injection

A device capable of collecting a condensate from a working fluid is disclosed. The condensate can take the form of a liquid and can be injected into a flow path of an engine. In one form the engine is a gas turbine engine and the liquid is injected upstream of a combustor. The liquid can be produced using a component that cools the working fluid to condense a vapor within it. In one non-limiting form the component is part of a refrigeration system. In addition to producing condensate, the refrigeration system can cool the working fluid to be used as cooled cooling air to a turbine of a gas turbine engine. In another non-limiting embodiment a liquid derived from a blackwater containing waste from an organism can be delivered in whole or in part to a flow path of the engine.

Gas turbine engine having configurable bypass passage

A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible.

Air particle separator

A gas turbine engine is disclosed having a particle separator and an ejector disposed downstream of the particle separator and structured to entrain a dirty flow from the separator. A container of working fluid can be placed in flow communication with the ejector to provide an ejector flow to entrain the dirty flow from the particle separator. Alternatively and/or additionally, the ejector can be configured to use a flow of working fluid from the gas turbine engine as an ejector flow.

AIR INLET DUCT HAVING A PARTICLE SEPARATOR AND AN AGGLOMERATOR FOR A GAS TURBINE ENGINE

An air-inlet duct includes a particle separator and an agglomerator. The particle separator is configured to receive atmospheric air laden with particles and to direct the particles into a scavenge passageway while allowing the atmospheric air to move into a compressor passageway thereby reducing the number of particles that enter the compressor passageway. The agglomerator is configured to cause the particles to be attracted to one another and cluster together. 1. An air-inlet duct for a gas turbine engine , the air-inlet duct comprisinga particle separator formed to include an inlet passageway for receiving a stream of air, a compressor passageway that extends downstream from the inlet passageway, and a scavenge passageway that extends downstream from the inlet passageway and that is positioned radially outward of the compressor passageway, the particle separator configured to receive atmospheric air laden with fine particles and large particles and to direct the large particles into the scavenge passageway while allowing the atmospheric air to move into the compressor passageway thereby reducing the number of large particles that enter the compressor passageway, andan agglomerator configured to emit an electro-magnetic field into the inlet passageway to charge the fine particles in the inlet passageway to cause the fine particles to be attracted to one another and cluster together to form large particles directed into the scavenge passageway by the particle separator to reduce the number of fine particles directed into the compressor passageway.2. The air-inlet duct of claim 1 , wherein the particle separator includes an outer wall spaced apart from an engine rotation axis claim 1 , an inner wall located between the outer wall and the engine rotation axis claim 1 , the inner wall and the outer wall defining the inlet passageway therebetween claim 1 , and a splitter located between the outer wall and the inner wall and including an outer splitter surface that ...

ENGINE LIQUID INJECTION

A device capable of collecting a condensate from a working fluid is disclosed. The condensate can take the form of a liquid and can be injected into a flow path of an engine. In one form the engine is a gas turbine engine and the liquid is injected upstream of a combustor. The liquid can be produced using a component that cools the working fluid to condense a vapor within it. In one non-limiting form the component is part of a refrigeration system. In addition to producing condensate, the refrigeration system can cool the working fluid to be used as cooled cooling air to a turbine of a gas turbine engine. In another non-limiting embodiment a liquid derived from a blackwater containing waste from an organism can be delivered in whole or in part to a flow path of the engine. 1. An apparatus comprising:a vehicle having an internal combustion engine and a fluid flow path leading from an intake to a combustion chamber and to an exhaust;a cooling system having a heat exchange member structured to cool a working fluid in a passage, the working fluid including a vapor; anda liquid flow path in communication with the fluid flow path of the internal combustion engine and structured to convey a liquid condensed from the working fluid via the heat exchange member and route the liquid into the fluid flow path of the internal combustion engine.2. The apparatus of claim 1 , wherein the working fluid in the passage is in fluid communication with the fluid flow path claim 1 , wherein the liquid flow path is structured to deliver the liquid upstream of the combustion chamber claim 1 , the liquid includes water claim 1 , and the water injection alters a thermodynamic cycle of the internal combustion engine.3. The apparatus of claim 1 , which further includes a container for collecting the liquid condensed from the working fluid claim 1 , the liquid flow path downstream of the container.4. The apparatus of claim 3 , wherein the combustion chamber is a combustor of a gas turbine engine. ...

GAS TURBINE ENGINE HAVING CONFIGURABLE BYPASS PASSAGE

A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible. 1. An apparatus comprising:a gas turbine engine having a core flow path and a bypass duct structured to bypass a working flow around a combustor of the gas turbine engine; anda moveable component associated with the bypass duct and structured to change a flow area by moving between a first position and a second position, the moveable component actuated to the second position such that a geometry of the duct forms a resonance space tuned to attenuate a noise.2. The apparatus of claim 1 , which further includes an actuator coupled to the moveable component and energized by a controller.3. The apparatus of claim 2 , which further includes a sensor structured to detect a noise information claim 2 , the sensor in communication with the controller claim 2 , wherein the controller is structured to operate upon the noise information when energizing the controller.4. The apparatus of claim 1 , wherein the bypass duct includes a plurality of bypass ducts claim 1 , and wherein various of the plurality of bypass ducts can form resonance spaces.5. The apparatus of claim 1 , wherein the resonance space includes a first portion forward of the moveable component and a second portion aft of the moveable component claim 1 , each of the first portion and second portion capable of generating a noise.6. The apparatus of claim 1 , wherein the resonance space ...

Bearing race cooling

A cooling architecture can include a longitudinally extending radially inner shaft, a radially outer support, and a bearing assembly. The longitudinally extending radially inner shaft can include an inner race. The inner race can define an inner circumferential chamber configured to carry an inner working fluid. The radially outer support can include an outer race. The bearing assembly can include a plurality of roller bearings disposed radially between the inner race and the outer race. The bearing assembly can be configured to radially align the inner shaft with respect to the outer support.

Bearing race cooling in a geared turbofan engine

A cooling architecture in a geared turbofan engine can include a longitudinally extending radially inner shaft, a radially outer support, and a bearing assembly. The longitudinally extending radially inner shaft can include an inner race. The inner race can define an inner circumferential chamber configured to carry an inner working fluid. The radially outer support can include an outer race. The bearing assembly can include a plurality of roller bearings disposed radially between the inner race and the outer race. The bearing assembly can be configured to radially align the inner shaft with respect to the outer support.

BEARING RACE COOLING

A cooling architecture can include a longitudinally extending radially inner shaft, a radially outer support, and a bearing assembly. The longitudinally extending radially inner shaft can include an inner race. The inner race can define an inner circumferential chamber configured to carry an inner working fluid. The radially outer support can include an outer race. The bearing assembly can include a plurality of roller bearings disposed radially between the inner race and the outer race. The bearing assembly can be configured to radially align the inner shaft with respect to the outer support. 1. A rolling bearing system comprising:a rotatable shaft defining an axis;a support member positioned radially outward of said shaft;an annular inner race coupled to said shaft;an annular outer race coupled to said support member and axially aligned with said inner race;a bearing assembly comprising a plurality of roller bearings circumferentially spaced and radially disposed between said inner and outer races,wherein one or more of said inner and outer races defines an interior chamber bound at least in part by a circumferential bearing facing wall, said bearing facing wall defining a plurality of outlet passages providing fluid communication between the interior chamber and the exterior of the race.2. The rolling bearing system of wherein said inner race defines an interior chamber bound at least in part by a circumferential bearing facing wall claim 1 , said bearing facing wall defining a plurality of passages providing fluid communication between the interior chamber and the exterior of the race.3. The rolling bearing system of wherein said outer race defines an interior chamber bound at least in part by a circumferential bearing facing wall claim 2 , said bearing facing wall defining a plurality of passages providing fluid communication between the interior chamber and the exterior of the race.4. The rolling bearing system of wherein said outer race defines an interior ...

SPLIT AXIAL-CENTRIFUGAL COMPRESSOR

A gas turbine engine including a compressor, a turbine, and a variable-ratio unit is disclosed. The turbine is coupled to the compressor to drive rotation of multiple stages of the compressor. The variable-ratio unit is configured to transmit rotational power from the turbine to at least one stage of the compressor to drive rotation of the at least one stage of the compressor. 1. A gas turbine engine comprisinga compressor including an axial compression stage and a centrifugal compression stage arranged aft of the axial compression stage along an engine axis,a turbine arranged aft of the centrifugal compression stage and coupled to the compressor to drive rotation of the axial compression stage and the centrifugal compression stage about the engine axis, anda variable-ratio unit coupled to the turbine and the compressor, the variable-ratio unit configured to transmit rotational power generated by the turbine about the engine axis to at least one of the axial compression stage and the centrifugal compression stage to drive rotation of the at least one of the axial compression stage and the centrifugal compression stage at various speeds offset from a turbine speed,wherein the axial compression stage has an outlet radius and the centrifugal compression stage has an inlet radius that is about equal to the outlet radius of the axial compression stage to facilitate a smooth transition of air from the axial compression stage to the centrifugal compression stage.2. The gas turbine engine of claim 1 , wherein the variable-ratio unit is included in an infinitely variable transmission.3. The gas turbine engine of claim 2 , wherein the variable-ratio unit includes one of a toroidal variator and a planetary-type ball variator.4. The gas turbine engine of claim 1 , wherein (i) the centrifugal compression stage is coupled to the turbine for common rotation therewith about the engine axis claim 1 , and (ii) the axial compression stage is coupled to the turbine through the variable ...

SYSTEMS AND METHODS OF REDUCING DISTORTIONS OF THE INLET AIRFLOW TO A TURBOMACHINE

Systems and methods of conditioning inlet air flow in a turbine engine. Where distortions in uniformity of inlet air flow are caused at least in part by the interaction of the air flow with the air inlet duct, a method of adaptively removing the distortions prior to the compressor stage comprises determining the distortion in the airflow; exposing the airflow to a plurality of correction vanes; and positioning the plurality of correction vanes based at least upon the determined distortion. An inlet conditioner system comprises an adaptable conditioning grid located within an air passage; a sensor suite configured to sense a characteristic of the airflow within the air passage; and a control system operably connected to the sensor suite and the adaptable conditioning grid. The control system may be adapted to configure the adaptable conditioning grid based on a sensed characteristic. 1. In a turbine engine having an air inlet duct prior to the compressor stage , wherein airflow distortions are caused at least in part by the interaction of the air flow with the air inlet duct , a method of adaptively removing the distortions prior to the compressor stage comprising the steps of:determining the distortion in the airflow;positioning a plurality of correction vanes based at least upon the determined distortion; andexposing the airflow to the plurality of correction vanes.2. The method of claim 1 , wherein the plurality of correction vanes comprises a plurality of shape memory materials.3. The method of claim 2 , wherein the step of positioning the plurality of correction vanes comprises applying an electrical current to at least one respective correction vane of the plurality of correction vanes claim 2 , wherein the application of electrical current transitions the respective correction vane of the plurality of correction vanes from a first state to a second state.4. The method of claim 2 , wherein the step of determining the distortion comprises predetermining the ...

GAS TURBINE ENGINE VARIABLE GEOMETRY FLOW COMPONENT

A variable geometry mechanism suitable for use in a gas turbine engine is disclosed in which movable vane segments which are coupled to a rotatable ring, or rings, are used to change an aerodynamic property of a working fluid flowing through the gas turbine engine. The movable vane segments can be rotated through the ring, or rings, between a first position associated with the first vane and a second position associated with a second vane to place the movable vane segments in proximity to one or the other of the first and second vanes of the gas turbine engine. The movable vane segments can be used to alter, among other things, camber, exit flow area, and can be used to influence and/or accommodate such properties as incidence angle, and swirl angle. 1. An apparatus comprising:a gas turbine engine component having a plurality of fixed airfoil members distributed circumferentially about a reference axis;a movable airfoil extension structured for use in a flow path of a gas turbine engine and positioned intermediate a first one of the plurality of fixed airfoil members and a second one of the plurality of fixed airfoil members, the movable airfoil extension configured to be moved between a first operating position adjacent a first one of the plurality of fixed airfoil members and a second operating position adjacent a second fixed airfoil member, wherein at transition positions intermediate the first operating position and the second operating position the movable airfoil extension is free of interfacing contact with the first and second one of the plurality of airfoil members; andwherein movement of the movable airfoil extension between the first operating position and the second operating position alters a flow path characteristic of both the first one of the plurality of fixed airfoil members and the second one of the plurality of fixed airfoil members.2. The apparatus of claim 1 , wherein the fixed airfoil members are gas turbine engine vanes and the gas turbine ...

COMBINED CYCLE POWER PLANT

A combined cycle engine is used to provide power to a vehicle. In one form the combined cycle engine includes two engines coupled through a gearbox. The engines can include a gas turbine engine, reciprocating engine, and a rotary engine. In one embodiment the combined cycle engine includes a gas turbine engine coupled to a gearbox along with either a reciprocating or rotary engine also coupled to the gearbox. One or more clutches can be provided to selectively couple the gas turbine engine and the reciprocating or rotary engine to the vehicle through the gearbox. In one embodiment the diesel engine can provide power to the vehicle during an idle condition and then also provide power to the gas turbine engine to assist the starting of the gas turbine engine. 1. An apparatus comprising:a gas turbine engine operable to rotate a first shaft in response to an operation of the gas turbine engine;a variable volume combustion chamber engine operable to rotate a second shaft in response to an operation of the variable volume combustion chamber engine; anda gearbox having a first input connected with the first shaft, a second input connected to the second shaft, and an output selectively coupled with one of the first shaft and the second shaft;wherein the output provides power from the gas turbine engine at a first power output condition, the output provides power from the variable volume combustion chamber engine at a second power output condition; andwherein power from the variable volume combustion chamber engine is used to start the gas turbine engine through the gearbox.2. The apparatus of claim 1 , wherein the first power output condition is greater than the second power output condition claim 1 , wherein the gas turbine engine provides motive power to a ground based vehicle claim 1 , and wherein the variable volume combustion chamber engine provides idle power to the ground based vehicle.3. The apparatus of claim 1 , wherein the variable volume combustion chamber ...

AIR PARTICLE SEPARATOR

A gas turbine engine is disclosed having a particle separator and an ejector disposed downstream of the particle separator and structured to entrain a dirty flow from the separator. A container of working fluid can be placed in flow communication with the ejector to provide an ejector flow to entrain the dirty flow from the particle separator. Alternatively and/or additionally, the ejector can be configured to use a flow of working fluid from the gas turbine engine as an ejector flow. 1. An apparatus comprising:a gas turbine engine having an inlet structured to capture an inlet flow stream and deliver it to rotating turbomachinery components of the gas turbine engine;a particle separator having a dirty flow path and a clean flow path, the dirty flow path oriented to withdraw particles from the inlet flow stream, the clean flow path in flow communication with the rotating turbomachinery components;a pressure source separate from the rotating turbomachinery components of the gas turbine engine and capable of producing a flow of pressurized fluid, the pressure source in flow communication with a conduit; andan ejector structured to receive the conduit and the dirty flow path, wherein the pressurized fluid flowing in the conduit is entrained with a dirty flow conveyed in the dirty flow path.2. The apparatus of wherein the pressure source is a pressure vessel capable of being charged.3. The apparatus of claim 2 , further comprising a valve disposed between the pressure vessel and the ejector claim 2 , the valve operable to close off a flow from the pressure vessel to the ejector.4. The apparatus of claim 3 , further comprising a controller operable to control the valve claim 3 , the controller configured to open the valve and permit a flow of pressurized fluid from the pressure vessel during a start of the gas turbine engine.5. The apparatus of claim 1 , further comprising a vehicle coupled with and capable of receiving power from the gas turbine engine claim 1 , and ...

WIRELESS BATTERY CHARGING SYSTEM

An inductive battery charger is incorporated with a power source that in one embodiment is a genset. A charging surface can be provided that in some forms is hinged, separable, or includes a pocket. In some forms resonant inductive coupling can be used to charge a battery through inductive charging. A battery can be charged within an area such as a perimeter of a military post (e.g. an observation post) using techniques described herein. A battery can also be charged remotely by inductive techniques such as through the use of a passing vehicle, etc.

FREQUENCY SPECTRUM SYSTEM SECURITY

A system may include a receiver configured to receive a communications signal from a transmitter and processing circuitry configured to: determine at least one frequency characteristic of the communications signal and compare the at least one frequency characteristic to at least one verified frequency characteristic stored by a memory associated with the processing circuitry to determine whether the transmitter is a verified transmitter. In some examples, the transmitter, receiver and communications signal are an optical transmitter, and optical receiver, and an optical signal, respectively. 1. A method comprising:receiving, by a receiver, from a transmitter, a communications signal, wherein the receiver and a verified transmitter are keyed to each other based on at least one frequency characteristic of the communication signal;determining, by processing circuitry, the at least one frequency characteristic of the communications signal; anddetermining, by the processing circuitry, whether the transmitter is the verified transmitter keyed to the receiver based on the at least one frequency characteristic and at least one verified frequency characteristic stored by a memory associated with the processing circuitry.2. The method of claim 1 , wherein:the receiver comprises an optical receiver;the transmitter comprises an optical transmitter;the communications signal comprises an optical signal; andthe optical signal encodes data.3. The method of claim 1 , wherein the at least one frequency characteristic comprises an actual carrier frequency of the communications signal.4. The method of claim 1 , wherein the at least one frequency characteristic comprises a phase modulation sideband frequency of the communications signal.5. The method of claim 1 , wherein the at least one frequency characteristic comprises an amplitude of the optical signal at an actual carrier frequency of the communications signal.6. The method of claim 1 , wherein the at least one frequency ...

ADJUSTABLE TURBINE VANE COOLING

A turbine vane cooling system operably coupling a cooling fluid source to a turbine vane assembly is disclosed herein. A plurality of turbine vanes having an airfoil shaped surface forming a substantially hollow body is connected to the turbine vane assembly. An inlet can be operably connected to each turbine vane to form a fluid communication path between a cooling fluid source and an interior of the hollow body of each turbine vane. At least one outlet fluidly communicating with the interior of said hollow body can be formed in the vane. A regulating member can variably block a portion of an inlet of each of the turbine vanes in response to a temperature of each turbine vane. 1. A turbine vane cooling system comprising:a cooling fluid system operably coupling a cooling fluid source and a turbine vane assembly;a plurality of turbine vanes having an airfoil shaped surface forming a substantially hollow body connected to the turbine vane assembly;an inlet operably connected to each turbine vane forming a fluid communication path between with the cooling fluid source and an interior of the hollow body of each turbine vane;at least one outlet fluidly communicating with the interior of said hollow body of each turbine vane; anda regulating member positioned proximate each inlet operable for blocking a variable portion of each inlet of each turbine vane.2. The turbine vane cooling system of claim 1 , wherein said regulating member is formed from a material having a higher coefficient of thermal expansion than a material forming said hollow body.3. The turbine vane cooling system of claim 1 , wherein said regulating member includes an aperture in fluid communication with said inlet.4. The turbine vane cooling system of claim 3 , wherein said aperture defines a substantially round orifice that expands and contracts with an increase or decrease claim 3 , respectively claim 3 , in temperature.5. The turbine vane cooling system of further comprising: a biasing member engaged ...

SPLIT AXIAL-CENTRIFUGAL COMPRESSOR

A gas turbine engine including a compressor, a turbine, and a transmission is disclosed. The turbine is coupled to the compressor to drive rotation of multiple stages of the compressor. The transmission is configured to transmit rotational power from the turbine to at least one stage of the compressor to drive rotation of the at least one stage of the compressor. 1. A gas turbine engine comprisinga compressor including an axial compression stage and a centrifugal compression stage arranged aft of the axial compression stage along an engine axis,a turbine arranged aft of the centrifugal compression stage and coupled to the compressor to drive rotation of the axial compression stage and the centrifugal compression stage about the engine axis, anda transmission coupled to the turbine and the compressor, the transmission configured to transmit rotational power generated by the turbine about the engine axis to at least one of the axial compression stage and the centrifugal compression stage to drive rotation of at least one of the axial compression stage and the centrifugal compression stage at a first speed offset from a turbine speed,wherein the axial compression stage has an outlet radius and the centrifugal compression stage has an inlet radius that is about equal to the outlet radius of the axial compression stage to facilitate a smooth transition of air from the axial compression stage to the centrifugal compression stage.2. The gas turbine engine of claim 1 , wherein (i) the centrifugal compression stage is coupled to the turbine for common rotation therewith about the engine axis claim 1 , and (ii) the axial compression stage is coupled to the turbine through the transmission for rotation about the engine axis at the first speed offset from the turbine speed.3. The gas turbine engine of claim 2 , wherein the transmission comprises a first planetary gear set arranged forward of the axial compression stage about the engine axis.4. The gas turbine engine of claim 3 ...

Method and process for blockchain implementation with third party devices

A method for controlling an engine having a control module and smart nodes. The method includes maintaining a block chain ledger, which includes an information block from at least a preceding engine start, may be at the control module of the aircraft engine. The method also includes maintaining a hash of at least a digital certificate and data at one of the smart nodes; transmitting a message including the hash to the control module; receiving the message at the control module; determining a control hash based upon the information from at least a preceding engine start at the control module; module comparing the hash to the control hash at the control; and based upon the comparison, starting the engine and updating the block chain ledger as a function of the received message.

Secure engine communication

A method of communication, within a processing system of a gas turbine engine, between a first electronic component and a second electronic component, comprising: generating by the first electronic component, a request, comprising a digital certificate, intern comprising a first host public key and a first client public key, signed with a first host private key, to initiate a trusted communication session with a second electronic component; encrypting at the first electronic component, at least a portion of the request with a first client private key; transmitting the request to the second electronic component; the first host private key and the first host public key defining a first asymmetric keypair and the first client private key and the first client public key defining a second asymmetric keypair.

Turbine based combined cycle integrated power and thermal system

A hybrid propulsion system is provided. The system may comprise a gas turbine engine and a secondary engine, an inlet, an exhaust, a pressurized tank, and an expansion valve. The inlet may be in fluid communication with the ambient environment. The gas turbine engine may have a core passage including a compressor, a combustion chamber, and a turbine. The core passage may be in selective fluid communication with the inlet. The exhaust may be in fluid communication with the ambient environment and the core passage. The pressurized tank may be located upstream of the core passage. The pressurized tank may contain a cooling fluid. The expansion valve may be in fluid communication with the pressurized tank and the core passage. The pressurized tank may provide cooling fluid to the core passage to cool the gas turbine engine during operation of the secondary engine.

Systems and methods of reducing distortions of the inlet airflow to a turbomachine

Systems and methods of conditioning inlet air flow in a turbine engine. Where distortions in uniformity of inlet air flow are caused at least in part by the interaction of the air flow with the air inlet duct, a method of adaptively removing the distortions prior to the compressor stage comprises determining the distortion in the airflow; exposing the airflow to a plurality of correction vanes; and positioning the plurality of correction vanes based at least upon the determined distortion. An inlet conditioner system comprises an adaptable conditioning grid located within an air passage; a sensor suite configured to sense a characteristic of the airflow within the air passage; and a control system operably connected to the sensor suite and the adaptable conditioning grid. The control system may be adapted to configure the adaptable conditioning grid based on a sensed characteristic.

Gas turbine engine having configurable bypass passage

Power augmentation system for an engine powered air vehicle

One embodiment of the present invention is a unique augmented gas turbine engine propulsion system. Another embodiment is a gas turbine engine power augmentation system. Yet another embodiment is a system for augmenting power in an engine powered air vehicle. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for fluid driven actuation systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Radiant electromagnetic energy management

A device provides a radiant electromagnetic energy output. During standby operation of the device, the output is provided at one or more frequencies selected to dissipate excess power through atmospheric absorption. Circuitry is included to tune the output of the device to a second frequency different than the first frequency for various directed energy applications that make use of the excess power. The circuitry can be arranged to further utilize frequency agility for power dissipation, to provide different operating modes involving a radiant output, or the like.

Air-inlet duct having a particle separator and an agglomerator for a gas turbine engine

An air-inlet duct includes a particle separator and an agglomerator. The particle separator is configured to receive atmospheric air laden with particles and to direct the particles into a scavenge passageway while allowing the atmospheric air to move into a compressor passageway thereby reducing the number of particles that enter the compressor passageway. The agglomerator is configured to cause the particles to be attracted to one another and cluster together.

Air-provisioning system with ejectors

A propulsion system includes two gas turbine engines and an air-provisioning system. The air-provisioning system includes a first ejector, a second ejector, a plenum fluidically connected with the first ejector and the second ejector, and a first propulsor. The air-provisioning system is configured to bleed and mix air from each gas turbine engine in the ejectors so as to provide selectively a flow of plenum air from the plenum to the first propulsor at a desired pressure and a desired flow rate to power the first propulsor.

Secure engine communication

A method of communication, within a processing system of a gas turbine engine, between a first electronic component and a second electronic component, comprising: generating by the first electronic component, a request, comprising a digital certificate, intern comprising a first host public key and a first client public key, signed with a first host private key, to initiate a trusted communication session with a second electronic component; encrypting at the first electronic component, at least a portion of the request with a first client private key; transmitting the request to the second electronic component; the first host private key and the first host public key defining a first asymmetric keypair and the first client private key and the first client public key defining a second asymmetric keypair

Engine liquid injection

A device capable of collecting a condensate from a working fluid is disclosed. The condensate can take the form of a liquid and can be injected into a flow path of an engine. In one form the engine is a gas turbine engine and the liquid is injected upstream of a combustor. The liquid can be produced using a component that cools the working fluid to condense a vapor within it. In one non- limiting form the component is part of a refrigeration system. In addition to producing condensate, the refrigeration system can cool the working fluid to be used as cooled cooling air to a turbine of a gas turbine engine. In another non- limiting embodiment a liquid derived from a blackwater containing waste from an organism can be delivered in whole or in part to a flow path of the engine.

A method and process for blockchain implementation with third party devices

A method for controlling an engine having a control module and smart nodes. The method includes maintaining a block chain ledger, which includes an information block from at least a preceding engine start, may be at the control module of the aircraft engine. The method also includes maintaining a hash of at least a digital certificate and data at one of the smart nodes; transmitting a message including the hash to the control module; receiving the message at the control module; determining a control hash based upon the information from at least a preceding engine start at the control module; module comparing the hash to the control hash at the control; and based upon the comparison, starting the engine and updating the block chain ledger as a function of the received message.

Engine liquid injection

Engine liquid injection

A device capable of collecting a condensate from a working fluid is disclosed. The condensate can take the form of a liquid and can be injected into a flow path of an engine. In one form the engine is a gas turbine engine and the liquid is injected upstream of a combustor. The liquid can be produced using a component that cools the working fluid to condense a vapor within it. In one non- limiting form the component is part of a refrigeration system. In addition to producing condensate, the refrigeration system can cool the working fluid to be used as cooled cooling air to a turbine of a gas turbine engine. In another non- limiting embodiment a liquid derived from a blackwater containing waste from an organism can be delivered in whole or in part to a flow path of the engine.

Engine liquid injection

Split axial-centrifugal compressor

A gas turbine engine including a compressor, a turbine, and a transmission is disclosed. The turbine is coupled to the compressor to drive rotation of multiple stages of the compressor. The transmission is configured to transmit rotational power from the turbine to at least one stage of the compressor to drive rotation of the at least one stage of the compressor.