SYSTEM AND METHOD FOR COMPRESSOR INTERCOOLER

A method includes compressing an air flow to a first pressure, transferring heat from the air flow to a liquefaction fluid via an intercooler heat exchanger, compressing the air flow to a second pressure greater than the first pressure, combusting the air flow and a fuel to generate a combustion product flow, and driving a turbine with the combustion product flow. The turbine is configured to drive machinery of a liquefaction system. The liquefaction fluid includes at least one of a pre-cooling fluid, a refrigerant, and a liquefied product of the liquefaction system. 1. A system comprising: a first compressor stage configured to compress an air flow to a first pressure;', 'a second compressor stage configured to compress the air flow to a second pressure greater than the first pressure; and', 'a turbine disposed along an axis of the gas turbine system;, 'a gas turbine system comprising a body comprising a plurality of channels configured to receive a cooling fluid; and', 'a plurality of fins extending from the body, wherein the air flow is configured to flow over the plurality of fins, and the intercooler heat exchanger is configured to transfer heat from the air flow to the cooling fluid; and, 'an intercooler heat exchanger disposed between the first compressor stage and the second compressor stage, wherein the intercooler comprisesa liquefaction system indirectly coupled to the intercooler heat exchanger, wherein the liquefaction system comprises a liquefaction fluid, and the liquefaction fluid is configured to receive heat from the cooling fluid.2. The system of claim 1 , comprising a working fluid system coupled to the intercooler heat exchanger and to the liquefaction system claim 1 , wherein the working fluid system comprises a working fluid heat exchanger and a pumping system claim 1 , the pumping system is configured to circulate the cooling fluid from the intercooler heat exchanger to the working fluid heat exchanger claim 1 , and the working fluid heat ...

Variable geometry heat exchanger apparatus

A heat exchanger apparatus including a surface cooler and a passive automatic retraction and extension system coupled to the surface cooler. The surface cooler having disposed therein one or more fluid flow channels configured for the passage therethrough of a heat transfer fluid to be cooled. The heat transfer fluid in a heat transfer relation on an interior side of said one or more fluid flow channels. The surface cooler including a plurality of fins projecting from an outer surface thereof. The passive automatic retraction and extension system including a thermal actuation component responsive to a change in temperature of at least one of the heat transfer fluid and a cooling fluid flow so as to actuate a change in a geometry of the surface cooler. Further disclosed is an engine including the heat exchanger apparatus.

Heat exchanger assembly for a gas turbine engine

A heat exchanger assembly (130) for a gas turbine engine (10) including a fan assembly (12), a fan casing (42) substantially circumscribing the fan assembly, a core gas turbine engine (13), and a splitter (44) substantially circumscribing the core gas turbine engine such that a bypass duct (40) is defined between the fan casing and the splitter, the heat exchanger including an arcuate radially inner plate (360), an arcuate radially outer plate (270) coupled to the radially inner plate such that a cavity (364) is defined therebetween, and an arcuate heat exchanger (300) coupled at least partially within the cavity such that the heat exchanger is coupled to a fan casing and such that the heat exchanger is positioned upstream or downstream from the fan assembly.

Heat exchanger assembly for a gas turbine engine

A heat exchanger assembly (130) for a gas turbine engine (10) including a fan assembly (12), a fan casing (42) substantially circumscribing the fan assembly, a core gas turbine engine (13), and a splitter (44) substantially circumscribing the core gas turbine engine such that a bypass duct (40) is defined between the fan casing and the splitter, the heat exchanger including an arcuate radially inner plate (360), an arcuate radially outer plate (270) coupled to the radially inner plate such that a cavity (364) is defined therebetween, and an arcuate heat exchanger (300) coupled at least partially within the cavity such that the heat exchanger is coupled to a fan casing and such that the heat exchanger is positioned upstream or downstream from the fan assembly.

Method and apparatus for decongealing a lubricating fluid in a heat exchanger apparatus

A decongealing channel for use in a heat exchanger apparatus, including a supersaturated solution contained therein and an actuation component in fluid communication with a lubricating fluid coupled to the decongealing channel. The actuation component is responsive to a change in pressure exerted thereon by the lubricating fluid so as to actuate an exothermic response in the supersaturated solution. The heat exchanger apparatus is disposed in a bypass fan duct of an aircraft engine. The heat exchanger apparatus including a manifold portion, one or more flow through openings extending therethrough the manifold portion to define one or more flow through channels having contained therein the lubricating fluid. In addition, the manifold portion including one or more additional openings extending therethrough to define one or more decongealing channels. Further disclosed is an engine including the heat exchanger apparatus and a method of decongealing a lubricating fluid in the heat exchanger apparatus.

Gas turbine engine heat exchangers and methods of assembling the same

A heat exchanger assembly comprises a heat exchanger body including a first fluid circuit and a second fluid circuit. The first circuit includes a first bypass valve in flow communication with a first fluid circuit inlet channel. The first fluid circuit also includes a plurality of cooling channels in flow communication with the first bypass valve. The first bypass valve is configured to channel a first fluid to the plurality of cooling channels during a first mode of operation to facilitate reducing a temperature of the first fluid. The second fluid circuit includes a second bypass valve configured to facilitate a flow of a second fluid through at least a portion of the heat exchanger body during the first mode of operation.

Aviation bypass valve including a shape memory alloy material

An aviation bypass valve for use in a heat exchanger apparatus, including a shape memory alloy material. The heat exchanger apparatus further including an air-cooled oil cooler disposed in a bypass fan duct of an aircraft engine. The heat exchanger apparatus including a bypass valve in fluid communication with the air cooled oil cooler. The bypass valve including a valve body, a piston disposed in the valve body and moveable therein and an actuation component. The actuation component including a shape memory alloy. The actuation component responsive to a change in at least one of a thermal condition and a pressure exerted thereon so as to move the piston, thereby opening and closing the bypass valve.

Methods of skiving metal and forming a fin in a heat exchanger

Methods of skiving metal using a skiving blade to form a shaving and methods of forming fins in a heat exchanger by skiving using a skiving blade. Where the metal body used to form the shaving or fin is made from a metal material having a hardness greater than that of aluminum.

Heat Exchanger for an Intercooler and Water Extraction Apparatus

A heat exchanger assembly is provided which may be modularly constructed for inline or off engine installation. A water extraction device is also provided which may be used independently or with the heat exchanger to remove water from a fluid flowpath. 1. An heat exchanger assembly , comprising:an axially forward face, an axially aft face and a passageway extending from said forward face to said rearward face, a plurality of circumferential segments disposed about said passageway between said forward face and said rearward face;each of said plurality of segments formed of a single piece of material having internal flow paths extending in a circumferential direction;said each segment having a plurality of fins formed by skiving said single piece of material thereby precluding a brazed connection of said fins;said plurality of segments stacked in a radially outwardly extending arrangement;said segments disposed adjacent one another in an axial arrangement;wherein said flow paths of said circumferentially adjacent segments are aligned in the circumferential direction.2. The assembly of claim 1 , said fins extending in one of radial or axial direction.3. The assembly of claim 1 , said fins extending at least one of radially inwardly or radially outwardly.4. The assembly of wherein an axial forward end of at least an axial forward said segment has an aerodynamically tailored leading edge.5. The assembly of wherein said forward face has a geometric shape.6. The assembly of wherein said forward face has one of tapered claim 5 , curved or flat.7. The assembly of further comprising bifurcations allowing for thermal expansion in a radial and axial direction.8. The assembly of wherein said assembly is modular.9. The assembly of wherein said modular assembly may be split in half.10. The assembly of wherein said modular assembly may be split in quadrants.11. The assembly of further comprising a turbine shaft extending through said passageway.12. The assembly of wherein said in ...

GAS TURBINE ENGINE HEAT EXCHANGERS AND METHODS OF ASSEMBLING THE SAME

A heat exchanger assembly for use in a gas turbine engine includes a bypass valve and at least one body portion. The body portion includes at least one de-congealing inlet channel in flow communication with the bypass valve, a plurality of cooling channels in flow communication with the bypass valve and the at least one de-congealing inlet channel, and at least one de-congealing outlet channel in flow communication with the bypass valve and the at least one de-congealing inlet channel. The bypass valve is configured to deliver a fluid between the at least one de-congealing inlet channel and the plurality of cooling channels during a first mode of operation to facilitate reducing a temperature of the fluid. The bypass valve is further configured to deliver the fluid between the at least one de-congealing inlet channel and the at least one de-congealing outlet channel during a second mode of operation. 1. A heat exchanger assembly for use in a gas turbine engine including a core gas turbine engine having an axis of rotation , a splitter circumscribing the core gas turbine engine , a fan assembly positioned upstream of the core gas turbine engine , a fan casing substantially circumscribing the fan assembly , and a bypass duct that is defined between the fan casing and the splitter , said heat exchanger assembly comprising:a bypass valve; and at least one de-congealing inlet channel in flow communication with said bypass valve;', 'a plurality of cooling channels in flow communication with said bypass valve and said at least one de-congealing inlet channel, wherein said bypass valve is configured to deliver a fluid between said at least one de-congealing inlet channel and said plurality of cooling channels during a first mode of operation to facilitate reducing a temperature of the fluid; and', 'at least one de-congealing outlet channel in flow communication with said bypass valve and said at least one de-congealing inlet channel, wherein said bypass valve is configured ...

DUCT ASSEMBLY AND METHOD OF FORMING

Duct assembly and method of forming a duct assembly, the method including providing a duct having an outer surface and an inner surface, the outer surface defining a periphery and the inner surface defining a first fluid passageway, covering at least a portion of the outer surface with at least a portion of a sacrificial body, depositing a metal layer over an exposed surface of the sacrificial body, and removing the sacrificial body. 1. A method of forming a duct assembly , the method comprising:providing a duct having an outer surface and an inner surface, the outer surface defining a periphery and the inner surface defining a first fluid passageway;covering at least a portion of the outer surface with at least a portion of a sacrificial body;depositing a metal layer over exposed surface of the sacrificial body; andremoving the sacrificial body to define at least one additional fluid passageway between the metal layer and the at least a portion of the outer surface.2. The method of wherein the depositing further comprises depositing the metal layer over a second exposed surface of the duct.3. The method of wherein the depositing the metal layer further comprises electroforming the metal layer.4. The method of wherein providing the duct further comprises forming the duct.5. The method of wherein the forming the duct further comprises drawing a metal tube to form the duct.6. The method of wherein forming the duct further comprises coupling an end of the duct to a flange.7. The method of further comprising covering at least a portion of the flange with another portion of the sacrificial body.8. The method of wherein the covering the at least a portion of the flange comprises injection molding a sacrificial material into a seat on the flange.9. The method of wherein the depositing further comprises depositing the metal layer over a portion of the flange.10. The method of wherein the covering further comprises covering a first portion of the outer surface with a first ...

THERMAL MANAGEMENT SYSTEM

A method and assembly for conveying heat from a heat exchanger having a housing defining a fluid pathway including at least one fluid passageway leading from an inlet port of the heat exchanger to an outlet port of the heat exchanger, the housing have a first side and a second side, opposite the first side where the housing includes at least one aperture extending through the housing from the first side to the second side and where the aperture is fluidly separate from the fluid pathway and heat from liquid flowing through the fluid pathway is transferred via at least one of conduction or convection to the housing. 1. Avionics control assembly , comprising:an engine control device having an avionics housing defining an exterior and an interior, with at least one connector extending from the exterior of the avionics housing and at least one sensor located within the interior; anda heat exchanger having a heat exchanger housing defining a fluid pathway including at least one fluid passageway leading from an inlet port of the heat exchanger to an outlet port of the heat exchanger, the heat exchanger housing have a first side and a second side, opposite the first side where the heat exchanger housing includes at least one aperture extending through the heat exchanger housing from the first side to the second side and where the aperture is fluidly separate from the fluid pathway, where the heat exchanger is operably coupled to the exterior of the avionics housing with the at least one connector located within the aperture and heat from liquid flowing through the fluid pathway is transferred via at least one of conduction or convection to the avionics housing.2. The avionics control assembly of wherein at least a portion of the heat exchanger is spaced from the exterior of the avionics housing and the heat is transferred via both conduction and convection to the avionics housing.3. The avionics control assembly of claim 2 , further comprising a backing plate mounted to ...

AVIATION BYPASS VALVE INCLUDING A SHAPE MEMORY ALLOY MATERIAL

An aviation bypass valve for use in a heat exchanger apparatus, including a shape memory alloy material. The heat exchanger apparatus further including an air-cooled oil cooler disposed in a bypass fan duct of an aircraft engine. The heat exchanger apparatus including a bypass valve in fluid communication with the air cooled oil cooler. The bypass valve including a valve body, a piston disposed in the valve body and moveable therein and an actuation component. The actuation component including a shape memory alloy. The actuation component responsive to a change in at least one of a thermal condition and a pressure exerted thereon so as to move the piston, thereby opening and closing the bypass valve. 1. A bypass valve comprising:a valve body;a piston disposed in the valve body, and moveable therein; andan actuation component, wherein the actuation component includes a shape memory alloy (SMA), the actuation component responsive to a change in at least one of a thermal condition and a pressure exerted thereon so as to move the piston, thereby opening and closing the bypass valve.2. The bypass valve of claim 1 , wherein the actuation component is configured to move the piston to a closed position in response to a predetermined temperature exerted thereon.3. The bypass valve of claim 2 , wherein shape memory alloy component is configured to move the piston to an open position in response to a predetermined temperature exerted thereon.4. The bypass valve of claim 1 , wherein the actuation component is a linearly configured shape memory alloy component.5. The bypass valve of claim 1 , wherein the actuation component is a shape memory alloy spring.6. The bypass valve of claim 1 , wherein the actuation component is configured to include a linearly configured shape memory alloy component and a shape memory alloy spring.7. The bypass valve of claim 1 , wherein the bypass valve is configured for use in an aerospace application.8. The bypass valve of claim 1 , wherein the ...

METHOD AND APPARATUS FOR DECONGEALING A LUBRICATING FLUID IN A HEAT EXCHANGER APPARATUS

A decongealing channel for use in a heat exchanger apparatus, including a supersaturated solution contained therein and an actuation component in fluid communication with a lubricating fluid coupled to the decongealing channel. The actuation component is responsive to a change in pressure exerted thereon by the lubricating fluid so as to actuate an exothermic response in the supersaturated solution. The heat exchanger apparatus is disposed in a bypass fan duct of an aircraft engine. The heat exchanger apparatus including a manifold portion, one or more flow through openings extending therethrough the manifold portion to define one or more flow through channels having contained therein the lubricating fluid. In addition, the manifold portion including one or more additional openings extending therethrough to define one or more decongealing channels. Further disclosed is an engine including the heat exchanger apparatus and a method of decongealing a lubricating fluid in the heat exchanger apparatus. 1. A decongealing channel for use in a heat exchanger apparatus comprising:a decongealing channel body enclosing therein a supersaturated solution;an actuation component coupled to the decongealing channel body and in fluid communication with a lubricating fluid, the actuation component responsive to a change in a fluid pressure exerted thereon by the lubricating fluid so as to actuate an exothermic response in the supersaturated solution.2. The decongealing channel of claim 1 , wherein the actuation component includes a linearly configured piston drive and a deformable disk.3. The decongealing channel of claim 2 , wherein the piston drive includes a piston and a spring claim 2 , and wherein the actuation component is configured to linearly move the piston to deform the deformable disk in response to a fluid pressure exerted thereon by the lubricating fluid.4. The decongealing channel of claim 3 , wherein the deformable disk is configured to deform relative to the ...

DUAL SEATED BY-PASS VALVE FOR SURFACE COOLERS

A dual seated by-pass valve is provided for a surface heat exchanger. The valve provides a power element and at least two seats and two poppets which are spring biased and responsive to movement of the power element to open and close pathways to core cooling channels and de-congealing channels. 1. A heat exchanger circuit , comprising:a heat exchanger for heat exchange having a body including:a plurality of cooling fins for said heat exchanger;a first plurality of core cooling channels within said body arranged closer to said plurality of cooling fins;said first plurality of core cooling channels having at least one cooling inlet connection in flow communication with hot engine fluid conduit and a cooling outlet connection;a second plurality of de-congealing channels in fluid communication with said at least one cooling inlet connection and said at least one cooling outlet connection, said de-congealing channels having at least one de-congealing inlet and a de-congealing outlet;a by-pass valve in receiving fluid communication with said cooling inlet connection and said at least one de-congealing inlet and output fluid communication with said de-congealing outlet and said at least one cooling outlet connection, said by-pass valve further comprising;a valve body;a power element extending through said valve body;a de-congealing flow path passing through said valve body;a core cooling flow path passing through said valve body;a de-congealing poppet in fluid communication with said de-congealing flow path and operably connected to said power element, said de-congealing poppet being movable between a first closed position and a second open position;a core cooling poppet in fluid communication with said core cooling flow path, said core cooling poppet being operably connected to said power element;wherein said de-congealing poppet and said core cooling poppet allow for engine fluid flow through two paths within said by-pass valve.2. The heat exchanger circuit of claim 1 , ...

Conformal surface heat exchanger for aircraft

A heat exchanger is described which conforms to external surface contours of an aircraft, such as an airplane or a helicopter, having a turbo-prop assembly. The heat exchanger is provided to cool engine fluids, which rise in temperature during engine operation.

GAS TURBINE ENGINE HEAT EXCHANGERS AND METHODS OF ASSEMBLING THE SAME

A heat exchanger assembly comprises a heat exchanger body including a first fluid circuit and a second fluid circuit. The first circuit includes a first bypass valve in flow communication with a first fluid circuit inlet channel. The first fluid circuit also includes a plurality of cooling channels in flow communication with the first bypass valve. The first bypass valve is configured to channel a first fluid to the plurality of cooling channels during a first mode of operation to facilitate reducing a temperature of the first fluid. The second fluid circuit includes a second bypass valve configured to facilitate a flow of a second fluid through at least a portion of the heat exchanger body during the first mode of operation. 1. A heat exchanger assembly for use in a gas turbine engine including a core gas turbine engine having an axis of rotation and a fan casing substantially circumscribing the core gas turbine engine , said heat exchanger assembly comprising: [ a first bypass valve;', 'a first fluid circuit inlet channel in flow communication with said first bypass valve; and', 'a plurality of cooling channels in flow communication with said first bypass valve, wherein said first bypass valve is configured to channel a first fluid to said plurality of cooling channels during a first mode of operation to facilitate reducing a temperature of said first fluid; and, 'a first fluid circuit comprising, 'a second fluid circuit including a second bypass valve, wherein said second bypass valve is configured to facilitate a flow of a second fluid through at least a portion of said heat exchanger body during the first mode of operation., 'a heat exchanger body including2. The heat exchanger assembly in accordance with claim 1 , wherein said first fluid circuit includes a first fluid circuit outlet channel in flow communication with said first bypass valve claim 1 , wherein said first bypass valve is configured to channel said first fluid to said first fluid circuit outlet ...

VARIABLE GEOMETRY HEAT EXCHANGER APPARATUS

A heat exchanger apparatus including a surface cooler and a passive automatic retraction and extension system coupled to the surface cooler. The surface cooler having disposed therein one or more fluid flow channels configured for the passage therethrough of a heat transfer fluid to be cooled. The heat transfer fluid in a heat transfer relation on an interior side of said one or more fluid flow channels. The surface cooler including a plurality of fins projecting from an outer surface thereof. The passive automatic retraction and extension system including a thermal actuation component responsive to a change in temperature of at least one of the heat transfer fluid and a cooling fluid flow so as to actuate a change in a geometry of the surface cooler. Further disclosed is an engine including the heat exchanger apparatus. 1. A heat exchanger apparatus comprising:a surface cooler having disposed therein one or more fluid flow channels configured for the passage therethrough of a heat transfer fluid to be cooled, the heat transfer fluid in a heat transfer relation on an interior side of said one or more fluid flow channels, the surface cooler including a plurality of fins projecting from an outer surface thereof; and 'a thermal actuation component responsive to a change in temperature of at least one of the heat transfer fluid and a cooling fluid flow so as to actuate a change in a geometry of the surface cooler.', 'a passive automatic retraction and extension system coupled to the surface cooler, the passive automatic retraction and extension system comprising2. The heat exchanger apparatus of claim 1 , wherein the thermal actuation component includes a shape memory alloy.3. The heat exchanger apparatus of claim 1 , wherein the thermal actuation component is a shape memory alloy wire.4. The heat exchanger apparatus of claim 1 , wherein the thermal actuation component provides passive claim 1 , automatic retraction of the plurality of fins away from the cooling fluid ...

ADDITIVE HEAT EXCHANGER AND METHOD OF FORMING

A method of electroforming can be used to prepare a heat exchanger by electroforming the heat exchanger on a mandrel having a smooth and conductive surface. The mandrel is in the shape of at least part of the heat exchanger, and is removed from the electroformed heat exchanger. 1. A method of electroforming a heat exchanger , the method comprising:polishing a conductive surface of a mandrel shaped as at least a portion of the heat exchanger;electroforming the heat exchanger onto the conductive surface of the mandrel; andremoving the mandrel from the electroformed heat exchanger.2. The method of wherein polishing the conductive surface smooths the conductive surface roughness (rms) to less than 32 microinches (0.81 micrometers).3. The method of wherein electroforming the heat exchanger further includes electroforming the heat exchanger to have a wall thickness that is less than 4 mils (0.01 centimeters).4. The method of further comprising activating the conductive surface for electroforming.5. The method of wherein activating includes treating the conductive surface to remove contaminants.6. The method of wherein the electroformed heat exchanger is treated along inner surfaces that are exposed when the mandrel is removed.7. The method of wherein treating the heat exchanger includes treating the inner surfaces with an etchant.8. The method of further comprising attaching a manifold component to the mandrel.9. The method of further comprising metalizing the mandrel to form the conductive surface prior to polishing the conductive surface.10. The method of further comprising forming the mandrel to shape to at least the portion of the heat exchanger prior to metalizing the mandrel.11. A method of electroforming a component claim 9 , the method comprising:polishing a conductive surface of a mandrel shaped as the component;electroforming the component onto the conductive surface of the mandrel; andremoving the mandrel from the component to expose a new surface of the ...

DUAL SEATED BY-PASS VALVE FOR SURFACE COOLERS

A dual seated by-pass valve is provided for a surface heat exchanger. The valve provides a power element and at least two seats and two poppets which are spring biased and responsive to movement of the power element to open and close pathways to core cooling channels and de-congealing channels. 1. A by-pass valve for a heat exchanger , comprising:a valve body;a power element extending through said valve body;a de-congealing flow path passing through said valve body;a core cooling flow path passing through said valve body;a de-congealing poppet in fluid communication with said de-congealing flow path and operably connected to said power element, said de-congealing poppet being movable between a first closed position and a second open position;a core cooling poppet in fluid communication with said core cooling flow path, said core cooling poppet being operably connected to said power element.2. The by-pass valve for a heat exchanger of claim 1 , wherein said power element is biased by a return spring.3. The by-pass valve for a heat exchanger of claim 2 , further comprising an overpressure spring engaging said de-congealing poppet.4. The by-pass valve for a heat exchanger of claim 3 , said de-congealing poppet being spring biased.5. The by-pass valve for a heat exchanger of further comprising an overpressure poppet disposed between said decongealing flow path and said core cooling flow path.6. The by-pass valve for a heat exchanger of claim 5 , said overpressure spring engaging said overpressure poppet.7. The by-pass valve for a heat exchanger of claim 1 , said power element having a wax capsule.8. The by-pass valve for a heat exchanger of claim 7 , said wax capsule having wax pellets therein.9. The by-pass valve for a heat exchanger of claim 8 , said wax capsule changing state based on temperature of said cooling fluid passing therethrough.10. The by-pass valve for a heat exchanger of wherein when said cooling fluid is relatively cold claim 1 , said core cooling ...

TUBULAR COOLER WITH INTEGRATED FAN

A tubular fin heat exchanger is provided with an integrated fan within the confines of a duct assembly. The tubular heat exchanger provides a structure and pathway to minimize space and weight of the integrated heat exchanger into the gas turbine engine. 1. A tubular cooler with integrated fan assembly , comprising:a duct having an inlet end and an outlet end;a heat exchanger disposed within said duct;said heat exchanger having an annular shape and extending axially at least partially between said first end and said second end of said duct;a fan disposed in flow communication with said duct, said fan forcing airflow through said heat exchanger;said heat exchanger including:an extrusion core body having a fluid inlet and a fluid outlet; and,a plurality of fins extending from and integrally formed with said extrusion core body and positioned within said duct.2. The tubular cooler with integrated fan assembly of claim 1 , said extrusion core body having a plurality of circumferentially extending channels therein.3. The tubular cooler with integrated fan assembly of further comprising fins extending from one side of said extrusion core body.4. The tubular cooler with integrated fan assembly of further comprising fins extending from two sides of said extrusion core body.5. The tubular cooler with integrated fan assembly of further comprising an outer flow and an inner flow corresponding to said fins extending from said two sides of said extrusion core body.6. The tubular cooler with integrated fan assembly of claim 1 , said fan being disposed in said duct.7. The tubular cooler with integrated fan assembly of claim 1 , said fan being connected to said duct.8. The tubular cooler with integrated fan assembly of claim 7 , said fan being connected to one of said inlet end or said outlet end.9. The tubular cooler with integrated fan assembly of claim 8 , said fan being disposed intermediate to said inlet and said outlet.10. The tubular cooler with integrated fan assembly of ...

AIRCRAFT SURFACE COOLER ASSEMBLY

A surface cooler having a first cooling passage section configured to be operably coupled to a fan casing of an aircraft engine, the cooling passage section having a heat exchanger body defining a first distal end and a second distal end and having a set of fluid passages internal to the heat exchanger body and a first set of fins located on a first exterior surface of the heat exchanger body and a manifold operably coupled to a first distal end of the cooling passage section and wherein the manifold includes a manifold body having an interior fluidly coupled to at least one of the set of fluid passages and a second set of fins located on the manifold body to define a finned manifold and a method for forming same. 1. A fan casing assembly , comprising:an annular fan casing having peripheral wall; a first cooling passage section configured to be operably coupled to the annular fan casing of an aircraft engine, the first cooling passage section having a heat exchanger body defining a first distal end and a second distal end and having a set of fluid passages internal to the heat exchanger body and a first set of fins located on a first exterior surface of the heat exchanger body; and', 'a manifold operably coupled to the first distal end of the first cooling passage section and wherein the manifold includes a manifold body having an interior fluidly coupled to at least one of the set of fluid passages and a second set of fins located on the manifold body to define a finned manifold., 'an annular surface cooler operably coupled to the annular fan casing and having a first surface confronting the peripheral wall and a second surface opposite the first surface, the annular surface cooler, comprising2. The fan casing assembly of claim 1 , further comprising a second manifold operably coupled to the second distal end of the first cooling passage section and wherein the second manifold includes a second manifold body having a second interior fluidly coupled to at least one ...

Mounting assembly and fan casing assembly

A fan casing assembly for a turbine engine including a fan casing having a peripheral wall, a surface cooler having a first surface confronting the peripheral wall and a mounting assembly having a lower portion generally retained between the first surface of the annular surface cooler and the peripheral wall and having a floating body extending through the set of fan casing fastener openings and an upper portion located radially exterior of the annular fan casing and operably coupled to the lower portion.

AVIONICS HEAT EXCHANGER

Aircraft turbine engines are controlled by complex electronic devices such as FADEC and PSS units. These devices can be adversely impacted by the engine environment including the condensing of evaporated water. Aspects of the present disclosure include unique heat exchangers to control the temperature of these electronic devices to assure their proper operation. 1. Avionics control assembly , comprising:an engine control device having an avionics housing defining an exterior and an interior, with at least one connector extending from the exterior of the avionics housing and at least one sensor located within the interior; anda heat exchanger including a duct defining a fluid pathway including at least one fluid passageway leading from an inlet port of the heat exchanger to an outlet port of the heat exchanger, the duct defining a length with a rearmost face and when the duct is operably coupled to the exterior of the avionics housing, at least one first portion of the rearmost face is spaced from the exterior of the avionics housing and at least one second portion of the rearmost face is in contact with the exterior of the avionics housing and heat from liquid flowing through the fluid pathway is transferred to the avionics housing.2. The avionics control assembly of wherein the at least one second portion is formed by an extension protruding from the duct.3. The avionics control assembly of wherein the exterior of the avionics housing includes a surface feature and the rearmost face of the at least one second portion is complementary in profile to the surface feature.4. The avionics control assembly of wherein the at least one first portion comprises multiple first portions forming multiple airgaps between the duct and the avionics housing.5. The avionics control assembly of wherein the fluid passageway does not extend into the extension.6. The avionics control assembly of wherein the duct comprises a non-constant cross-section between the at least one first ...

ANNULAR SURFACE COOLER AND METHOD OF FORMING MULTIPLE FINS IN A HEAT EXCHANGER

A method of forming fins in a heat exchanger includes using a stacked slit saw with multiple saw blades to simultaneously cut multiple fins into a metal body of the heat exchanger, with each fin having a body extending from an upper surface of the metal body and terminating in a tip. 1. A method of forming multiple fins in a heat exchanger , the method comprising:providing a metal body having an upper surface and where the metal body includes fluid cooling passages and a layer of metal along the upper surface and spaced from the fluid cooling passages; andcutting the layer of metal to simultaneously form a plurality of fins, with each fin having a body extending from the upper surface and terminating in a tip.2. The method of wherein the body extends substantially along a width of the metal body.3. The method of wherein simultaneously forming the plurality of fins comprises creating the plurality of fins with a single machining pass.4. The method of wherein the single machining pass is accomplished via a single advancing motion of a stacked slit slaw along a lengthwise direction of the metal body.5. The method of wherein the stacked slit saw comprises stacked slit saw blades in a horizontal mill.6. The method of wherein the stacked slit saw blades provide support to the plurality of fins during the single machining pass.7. The method of wherein cutting the layer of metal to simultaneously form a plurality of fins comprises controlling a feed rate of the metal body and a rotational speed of the stacked slit saw.8. The method of wherein the single machining pass is over a section of the heat exchanger that is more than five feet in length.9. The method of wherein the single machining pass creates a plurality of fins that are completely spaced from each other.10. The method of wherein a space between two adjacent of the plurality of fins comprises a square base.11. The method of wherein the plurality of fins are at a 90 degree angle with respect to the upper surface.12 ...

METHODS OF FORMING A HEAT EXCHANGER

An aspect of a method of forming a heat exchanger includes providing a metal body, removing material from the metal body to partially create a set of cooling passages, filling the partially created set of cooling passages with sacrificial material, forming a remainder of the set of cooling passages such that a set of fully formed cooling passages for the heat exchanger are defined, and removing the sacrificial material from the cooling passages. 1. A method of forming a heat exchanger , the method comprising:providing a metal body having a first surface and a second surface opposite and spaced from the first surface;removing material from the first surface of the metal body to partially create a set of cooling passages having open faces within the metal body;filling the partially created set of cooling passages via the open faces with sacrificial material such that the sacrificial material forms an exposed surface;forming a remainder of the set of cooling passages such that the exposed surface is covered and the open faces are closed and a set of fully formed cooling passages for the heat exchanger are defined; andremoving the sacrificial material from the set of fully formed cooling passages;wherein the heat exchanger is configured to operate in a high pressure environment of 0.7 MPa or more and a high temperature environment of 150° C. or more.2. The method of wherein removing material from the metal body comprises machining the metal body to partially create the set of cooling passages within the metal body.3. The method of wherein multiple walls of a cooling passage of the set of cooling passages are created by removing material from the metal body.4. The method of wherein material is removed from the metal body along the partially created cooling passage in a non-uniform fashion such that at least one heat transfer augmentation structure is formed along at least a portion of at least one of the multiple walls.5. The method of wherein the at least one heat ...

Dual seated by-pass valve for surface coolers

A heat exchanger circuit can include a heat exchanger having a body with a plurality of cooling fins for the heat exchanger, a plurality of core cooling channels within the body, a plurality of de-congealing channels in fluid communication with the plurality of core cooling channels, and a by-pass valve in fluid communication with the plurality of core cooling channels and the plurality of de-congealing channels.

Avionics Heat Exchanger

Les moteurs à turbine d'avion sont commandés par des dispositifs électroniques complexes tels que le FADEC et les unités PSS. Ces dispositifs peuvent être affectés par l'environnement du moteur, y compris la condensation de l'eau évaporée. Les aspects de la présente divulgation comprennent des échangeurs de chaleur uniques destinés à contrôler la température de ces appareils électroniques afin d'assurer leur bon fonctionnement. La présente invention propose un ensemble de commande avionique qui comprend un dispositif de commande de moteur comportant un boîtier avionique définissant un extérieur et un intérieur, avec au moins un connecteur (60), s'étendant depuis l'extérieur du boîtier avionique, et au moins un capteur (62) situé à l'intérieur. L’ensemble de commande avionique comprend également un échangeur de chaleur (52) comportant un conduit (64) définissant une voie de circulation de fluide avec au moins un passage de fluide menant d'un orifice d'entrée (68) de l'échangeur de chaleur (52) à un orifice de sortie (70) de l'échangeur de chaleur (52). Le conduit (64) définit une longueur avec une face arrière, et lorsque le conduit (64) est relié sur le plan fonctionnel à l'extérieur du boîtier avionique, au moins une première partie de la face arrière est espacée de l'extérieur du boîtier avionique, et au moins une deuxième partie de la face arrière est en contact avec l'extérieur du boîtier avionique, et la chaleur du liquide s’écoulant dans la voie de circulation de fluide est transmise au boîtier avionique. Figure pour l’abrégé : Fig 2

Dual seated by-pass valve for surface coolers

A dual seated by -pass valve (136) is provided for a surface heat exchanger (50, 150). The valve provides a power element (716) and at least two seats and two poppets (724, 734) which are spring biased and responsive to movement of the power element to open and close pathways (704, 706) to core cooling channels (232) and de-congealing channels (248, 250).

Aviation bypass valve including a shape memory alloy material

An aviation bypass valve for use in a heat exchanger apparatus, including a shape memory alloy material. The heat exchanger apparatus further including an air-cooled oil cooler disposed in a bypass fan duct of an aircraft engine. The heat exchanger apparatus including a bypass valve in fluid communication with the air cooled oil cooler. The bypass valve including a valve body, a piston disposed in the valve body and moveable therein and an actuation component. The actuation component including a shape memory alloy. The actuation component responsive to a change in at least one of a thermal condition and a pressure exerted thereon so as to move the piston, thereby opening and closing the bypass valve.

Method and apparatus for assembling couplings for transferring fluids

A coupling used to transfer fluid between two conduits includes a seal arrangement that permits an inner sleeve to move axially and angularly without fluid leaking from the coupling. The coupling also includes a pair of coupling members coupled to the inner sleeve, around each end of the inner sleeve. The inner sleeve includes tapered ends sized to receive a seal including a spherical lip. Each coupling member includes a tapered end that compresses each seal during assembly of the coupling. The seal spherical lips maintain sealable contact between the inner sleeve and the coupling first and second members.

Gas turbine engine heat exchangers and methods of assembling the same

A heat exchanger assembly (130) comprises a heat exchanger body (202) including a first fluid circuit (100) and a second fluid circuit (102). The first circuit includes a first bypass valve (136) in flow communication with a first fluid circuit inlet channel (248). The first fluid circuit also includes a plurality of cooling channels (232) in flow communication with the first bypass valve. The first bypass valve is configured to deliver a first fluid to the plurality of cooling channels during a first mode of operation to facilitate reducing a temperature of the first fluid. The second fluid circuit includes a second bypass valve (137) configured to facilitate a flow of a second fluid through at least a portion of the heat exchanger body during the first mode of operation.

Thermal management system

Un procédé et un ensemble pour transporter de la chaleur depuis un échangeur de chaleur (52) ayant un boîtier (64) qui définit un chemin de fluide comportant au moins un passage de fluide (66) qui va d’un orifice d’entrée (68) de l’échangeur de chaleur à un orifice de sortie (70) de l’échangeur de chaleur, le boîtier (64) ayant un premier côté et un deuxième côté, opposé au premier côté, le boîtier comportant au moins une ouverture (79) qui s’étend à travers le boîtier (64), du premier côté au deuxième côté, et dans lequel l’ouverture (79) est séparée de manière fluide du chemin de fluide (66), et la chaleur du liquide circulant dans le chemin de fluide est transférée au boîtier via au moins un moyen parmi la conduction et la convection. A method and assembly for transporting heat from a heat exchanger (52) having a housing (64) that defines a fluid path including at least one fluid passage (66) that extends from an inlet port ( 68) of the heat exchanger to a heat exchanger outlet (70), the housing (64) having a first side and a second side, opposite the first side, the housing having at least one opening ( 79) which extends through the housing (64), from the first side to the second side, and in which the opening (79) is fluidly separated from the fluid path (66), and the heat of the liquid circulating in the fluid path is transferred to the housing via at least one of conduction and convection.

Thermal management system

A method and assembly for conveying heat from a heat exchanger having a housing defining a fluid pathway including at least one fluid passageway leading from an inlet port of the heat exchanger to an outlet port of the heat exchanger, the housing have a first side and a second side, opposite the first side where the housing includes at least one aperture extending through the housing from the first side to the second side and where the aperture is fluidly separate from the fluid pathway and heat from liquid flowing through the fluid pathway is transferred via at least one of conduction or convection to the housing.

Dual seated by-pass valve for surface coolers

A dual seated by -pass valve (136) is provided for a surface heat exchanger (50, 150). The valve provides a power element (716) and at least two seats and two poppets (724, 734) which are spring biased and responsive to movement of the power element to open and close pathways (704, 706) to core cooling channels (232) and de-congealing channels (248, 250).

AVIONIC HEAT EXCHANGER

Les moteurs à turbine d'avion sont commandés par des dispositifs électroniques complexes tels que le FADEC et les unités PSS. Ces dispositifs peuvent être affectés par l'environnement du moteur, y compris la condensation de l'eau évaporée. Les aspects de la présente divulgation comprennent des échangeurs de chaleur uniques destinés à contrôler la température de ces appareils électroniques afin d'assurer leur bon fonctionnement. La présente invention propose un ensemble de commande avionique qui comprend un dispositif de commande de moteur comportant un boîtier avionique définissant un extérieur et un intérieur, avec au moins un connecteur (60), s'étendant depuis l'extérieur du boîtier avionique, et au moins un capteur (62) situé à l'intérieur. L’ensemble de commande avionique comprend également un échangeur de chaleur (52) comportant un conduit (64) définissant une voie de circulation de fluide avec au moins un passage de fluide menant d'un orifice d'entrée (68) de l'échangeur de chaleur (52) à un orifice de sortie (70) de l'échangeur de chaleur (52). Le conduit (64) définit une longueur avec une face arrière, et lorsque le conduit (64) est relié sur le plan fonctionnel à l'extérieur du boîtier avionique, au moins une première partie de la face arrière est espacée de l'extérieur du boîtier avionique, et au moins une deuxième partie de la face arrière est en contact avec l'extérieur du boîtier avionique, et la chaleur du liquide s’écoulant dans la voie de circulation de fluide est transmise au boîtier avionique. Figure pour l’abrégé : Fig 2

Variable geometry heat exchanger apparatus

A heat exchanger apparatus including a surface cooler and a passive automatic retraction and extension system coupled to the surface cooler. The surface cooler having disposed therein one or more fluid flow channels configured for the passage therethrough of a heat transfer fluid to be cooled. The heat transfer fluid in a heat transfer relation on an interior side of said one or more fluid flow channels. The surface cooler including a plurality of fins projecting from an outer surface thereof. The passive automatic retraction and extension system including a thermal actuation component responsive to a change in temperature of at least one of the heat transfer fluid and a cooling fluid flow so as to actuate a change in a geometry of the surface cooler. Further disclosed is an engine including the heat exchanger apparatus.

ADDITIVE HEAT EXCHANGER AND FORMING METHOD

L’invention concerne un procédé (400) d’électroformage qui peut être utilisé pour préparer un échangeur de chaleur (100) par électroformage de l’échangeur de chaleur (100) sur un mandrin (58) ayant une surface (62) lisse et conductrice. Le mandrin (58) est façonné comme au moins une partie de l’échangeur de chaleur (100), et est retiré de l’échangeur de chaleur (100) électroformé. Figure pour l’abrégé : Fig. 2 An electroforming process (400) that can be used to prepare a heat exchanger (100) by electroforming the heat exchanger (100) on a mandrel (58) having a smooth and driver. The mandrel (58) is shaped as at least a part of the heat exchanger (100), and is removed from the electroformed heat exchanger (100). Figure for abstract: Fig. 2

Expansion joint

An expansion joint (18) includes a pair of tubular fittings (20,22) joined together by a bellows (28) for accommodating differential movement therebetween. The fittings (20, 22) include balls (20b, 22b) at respective distal ends thereof which engage complementary sockets (24, 26) fixedly joined to opposite ends of the bellows (28). The respective ball and sockets additionally accommodate pivotal and rotary movement. The bellows (28) allows pressure and spring forces to engage the sockets (24, 26) against their respective balls (20b, 22b) for continuously seating the balls (20b, 22b) in the sockets (24, 26) during operation and maintaining effective seals against leakage.

Heat exchanger for an intercooler and water extraction apparatus

A heat exchanger assembly is provided which may be modularly constructed for inline or off engine installation. A water extraction device is also provided which may be used independently or with the heat exchanger to remove water from a fluid flowpath.

Conformal surface heat exchanger for aircraft

A heat exchanger is described which conforms to external surface contours of an aircraft, such as an airplane or a helicopter, having a turbo-prop assembly. The heat exchanger is provided to cool engine fluids, which rise in temperature during engine operation.

Conformal surface heat exchanger for aircraft

A heat exchanger is described which conforms to external surface contours of an aircraft, such as an airplane or a helicopter, having a turbo-prop assembly. The heat exchanger is provided to cool engine fluids, which rise in temperature during engine operation.

Thermal management system

Un procédé et un ensemble pour transporter de la chaleur depuis un échangeur de chaleur (52) ayant un boîtier (64) qui définit un chemin de fluide comportant au moins un passage de fluide (66) qui va d’un orifice d’entrée (68) de l’échangeur de chaleur à un orifice de sortie (70) de l’échangeur de chaleur, le boîtier (64) ayant un premier côté et un deuxième côté, opposé au premier côté, le boîtier comportant au moins une ouverture (79) qui s’étend à travers le boîtier (64), du premier côté au deuxième côté, et dans lequel l’ouverture (79) est séparée de manière fluide du chemin de fluide (66), et la chaleur du liquide circulant dans le chemin de fluide est transférée au boîtier via au moins un moyen parmi la conduction et la convection. A method and assembly for transporting heat from a heat exchanger (52) having a housing (64) which defines a fluid path including at least one fluid passage (66) which extends from an inlet port ( 68) from the heat exchanger to an outlet (70) of the heat exchanger, the housing (64) having a first side and a second side, opposite the first side, the housing having at least one opening ( 79) which extends through the housing (64), from the first side to the second side, and in which the opening (79) is fluidly separated from the fluid path (66), and the heat of the liquid flowing in the fluid path is transferred to the housing via at least one of conduction and convection.

Gas turbine engine heat exchangers and methods of assembling the same

A heat exchanger assembly for use in a gas turbine engine includes a bypass valve and at least one body portion. The body portion includes at least one de-congealing inlet channel in flow communication with the bypass valve, a plurality of cooling channels in flow communication with the bypass valve and the at least one de-congealing inlet channel, and at least one de-congealing outlet channel in flow communication with the bypass valve and the at least one de-congealing inlet channel. The bypass valve is configured to deliver a fluid between the at least one de-congealing inlet channel and the plurality of cooling channels during a first mode of operation to facilitate reducing a temperature of the fluid. The bypass valve is further configured to deliver the fluid between the at least one de-congealing inlet channel and the at least one de-congealing outlet channel during a second mode of operation.

Methods of forming a heat exchanger

Rohrflanschverbindung mit definierter Montageposition

熱交換器内で金属をスカイビングしてフィンを形成する方法

【課題】シェービング（３０）を形成するためにスカイビングブレード（２０）を使用して金属物体（１０）をスカイビングする方法を提供すること。 【解決手段】スカイビングブレードを使用して金属をスカイビングする方法は、金属材料の表面にニックを形成するステップと、前記ニック内に前記スカイビングブレードを導入するステップと、シェービングを形成するために前記スカイビングブレードを前記ニックから前記金属材料内まで前進させるステップとを含む。シェービング（３０）を形成するのに使用される金属物体（１０）は、アルミニウムより高い硬度を有する金属材料から作られる。シェービング（３０）は、熱交換器を形成する金属物体上に形成することができる。 【選択図】図１

Gas turbine engine heat exchangers

Échangeur de chaleur additif et procédé de formation

L’invention concerne un procédé (400) d’électroformage qui peut être utilisé pour préparer un échangeur de chaleur (100) par électroformage de l’échangeur de chaleur (100) sur un mandrin (58) ayant une surface (62) lisse et conductrice. Le mandrin (58) est façonné comme au moins une partie de l’échangeur de chaleur (100), et est retiré de l’échangeur de chaleur (100) électroformé. Figure pour l’abrégé : Fig. 2