Patents by Inventor David Patrick Calder
David Patrick Calder has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Publication number: 20180237130Abstract: An aircraft comprises an energy output component (EOC) outputting waste energy. An energy recovery unit (ERU) is operably coupled to the EOC to convert the waste energy into one of electrical energy or mechanical energy. An energy storage unit (ESU) is operably coupled to the ERU to store the one of electrical energy or mechanical energy recovered from the waste energy.Type: ApplicationFiled: December 31, 2014Publication date: August 23, 2018Inventors: David Patrick CALDER, Graham Patrick HOWARTH
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Publication number: 20180218723Abstract: An acoustic liner and a method of attenuating noise are provided. The acoustic liner includes a face sheet, a back sheet spaced from the face sheet, and a core layer extending between the face sheet and the back sheet. The core layer includes a plurality of resonant cells, each resonant cell including at least one cell wall coupled to the back sheet along a cell wall base edge. The at least one cell wall extends from the back sheet at an angle toward the face sheet. The at least one cell wall further coupled to the face sheet along a cell wall top edge. The resonant cell is formed in a predetermined shape and contains a volume in a space defined by the at least one cell wall, the back sheet, and the face sheet. The cell wall base edge length is greater than the cell wall top edge length.Type: ApplicationFiled: February 1, 2017Publication date: August 2, 2018Inventors: Wendy Wenling Lin, Michael Moses Martinez, Rudramuni Kariveerappa Majjigi, David Patrick Calder, Aaron Goldsholl
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Patent number: 9972896Abstract: An engine monitoring system for an aircraft engine having a nacelle extending annularly thereabout and a sensor positioned radially inward therefrom. The system includes an engine control device coupled communicatively to the sensor and configured to receive engine data from the sensor and/or receive instruction data from a transmitter device positioned radially outward from a nacelle radially outward surface. The system also includes a composite panel including at least a portion of the nacelle and a ground plane positioned radially inward from the nacelle radially outward surface, the composite panel including an antenna coupled communicatively to engine control device and a radome positioned radially outward from ground plane. The antenna is configured to at least one of receive engine data from the engine control device and transmit engine data to a receiver device, and receive instruction data from the transmitter device and transmit instruction data to the engine control device.Type: GrantFiled: June 23, 2016Date of Patent: May 15, 2018Assignee: GENERAL ELECTRIC COMPANYInventors: Selaka Bandara Bulumulla, David Patrick Calder, Michael Joseph Dell'Anno, Andrew Michael Roach
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Publication number: 20180017020Abstract: A turbine engine having an engine core, an inner cowl radially surrounding the engine core, an outer cowl radially surrounding the inner cowl and spaced from the inner cowl to form an annular passage between the inner and outer cowls that defines a nozzle, at least one control surface provided on the inner cowl and movable between a retracted position, where the nozzle has a first cross-sectional area, and an extended position where the nozzle has a second cross-sectional area that is less than the first cross-sectional area and an actuator operably coupled to the control surface and configured to move the control surface to control the cross-sectional area of the nozzle.Type: ApplicationFiled: February 11, 2015Publication date: January 18, 2018Inventors: Graham Frank HOWARTH, David Patrick CALDER
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Publication number: 20170369188Abstract: An engine monitoring system for an aircraft engine having a nacelle extending annularly thereabout and a sensor positioned radially inward therefrom. The system includes an engine control device coupled communicatively to the sensor and configured to receive engine data from the sensor and/or receive instruction data from a transmitter device positioned radially outward from a nacelle radially outward surface. The system also includes a composite panel including at least a portion of the nacelle and a ground plane positioned radially inward from the nacelle radially outward surface, the composite panel including an antenna coupled communicatively to engine control device and a radome positioned radially outward from ground plane. The antenna is configured to at least one of receive engine data from the engine control device and transmit engine data to a receiver device, and receive instruction data from the transmitter device and transmit instruction data to the engine control device.Type: ApplicationFiled: June 23, 2016Publication date: December 28, 2017Inventors: Selaka Bandara Bulumulla, David Patrick Calder, Michael Joseph Dell'Anno, Andrew Michael Roach
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Publication number: 20170356343Abstract: A thermal insulation blanket assembly having a thermal insulation blanket including an aerogel insulation material having a first surface and a second surface that is oppositely-disposed from the first surface, a backing covering the second surface of the aerogel insulation material, and a skin layer covering the first surface of the aerogel insulation material.Type: ApplicationFiled: June 8, 2016Publication date: December 14, 2017Inventors: Andrew Michael Roach, David Patrick Calder, Graham Frank Howarth
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Patent number: 9835112Abstract: A thrust reverser cascade having a frame and a body. The body comprises multiple layers formed by an additive manufacturing process where at least one of the layers is coupled to the frame.Type: GrantFiled: February 10, 2014Date of Patent: December 5, 2017Assignee: MRA Systems Inc.Inventors: David Patrick Calder, Graham Frank Howarth
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Publication number: 20170321631Abstract: A thrust reverser assembly for a gas turbine engine including a core engine, a nacelle surrounding at least a portion of the core engine defining a bypass duct between the nacelle and the core engine where an outer door movable between a stowed position and a deployed position extends outwards from the nacelle and a blocker door movable between a stowed position and an deployed position extends into an airflow conduit defined by the bypass duct to deflect air outwards.Type: ApplicationFiled: May 6, 2016Publication date: November 9, 2017Inventors: David Patrick Calder, Graham Frank Howarth, Andrew Michael Roach, Timothy Robert Beasman
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Patent number: 9309001Abstract: A system and method for ice protection of a component, wherein the system is adapted to be adhesively bonded to a surface of the component. The system includes a heating element layer, at least one thermally conductive adhesive layer that adhesively bonds a first side of the heating element layer to the component, an insulation layer, at least one thermally insulating adhesive layer that adhesively bonds a second side of the heating element to the insulation layer, an electrical bus bar adapted to provide a connection between a power supply and the heating element layer, and at least one temperature sensor.Type: GrantFiled: July 29, 2015Date of Patent: April 12, 2016Assignees: MRA SYSTEMS INC., KELLY AEROSPACE THERMAL SYSTEMS, LLCInventors: David Patrick Calder, Julian Alexander Opificius, Erik Thomas Pederson, David Cenit Flosdorf
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Patent number: 9193466Abstract: A system and method for ice protection of a component, wherein the system is adapted to be adhesively bonded to a surface of the component. The system includes a heating element layer, at least one thermally conductive adhesive layer that adhesively bonds a first side of the heating element layer to the component, an insulation layer, at least one thermally insulating adhesive layer that adhesively bonds a second side of the heating element to the insulation layer, an electrical bus bar adapted to provide a connection between a power supply and the heating element layer, and at least one temperature sensor.Type: GrantFiled: November 19, 2012Date of Patent: November 24, 2015Assignees: MRA Systems, Inc., Kelly Aerospace Thermal Systems, LLCInventors: David Patrick Calder, Julian Alexander Opificius, Erik Thomas Pederson, David Cenit Flosdorf
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Publication number: 20150329211Abstract: A system and method for ice protection of a component, wherein the system is adapted to be adhesively bonded to a surface of the component. The system includes a heating element layer, at least one thermally conductive adhesive layer that adhesively bonds a first side of the heating element layer to the component, an insulation layer, at least one thermally insulating adhesive layer that adhesively bonds a second side of the heating element to the insulation layer, an electrical bus bar adapted to provide a connection between a power supply and the heating element layer, and at least one temperature sensor.Type: ApplicationFiled: July 29, 2015Publication date: November 19, 2015Inventors: David Patrick Calder, Julian Alexander Opificius, Erik Thomas Pederson, David Cenit Flosdorf
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Publication number: 20150226157Abstract: A thrust reverser cascade having a frame and a body. The body comprises multiple layers formed by an additive manufacturing process where at least one of the layers is coupled to the frame.Type: ApplicationFiled: February 10, 2014Publication date: August 13, 2015Applicant: MRA Systems, Inc.Inventors: David Patrick Calder, Graham Frank Howarth
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Publication number: 20140014776Abstract: A system and method thereof is provided for electrically heating a component. The system includes at least one heating element adapted to be adhesively bonded to a surface on the component and means for controlling flow and duration of an electrical current to the heating element from a power supply. The controlling means comprises a first heating cycle for curing an adhesive to bond the heating element to the surface and has a second heating cycle for providing ice protection to the surface.Type: ApplicationFiled: November 27, 2012Publication date: January 16, 2014Applicants: KELLY AEROSPACE THERMAL SYSTEMS LLC, MRA SYSTEMS INC.Inventors: David Patrick Calder, Julian Alexander Opificius, Mark Fairbert, Erik Thomas Pederson, David Cenit Flosdorf
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Patent number: 8613398Abstract: A trans cowl for a jet engine includes a chevron coupled with a linear actuators. The chevron is movable by the linear actuator forward or aft to change a gas flow path formed by an core cowl and thrust reverser translating cowl. In a first position, the chevrons are disposed substantially parallel the gas flow path to attenuate drag and/or loss of engine thrust. In a second position, the chevrons are moved aft to project, or further project, into the gas flow path. In one embodiment, the linear actuator comprises a first component that is coupled with the outer cowl. A second component of the linear actuator is coupled with the chevron. When installed, the linear actuator can be coupled with a controller and an electrical power source. A position sensor coupled with the controller senses a position of the linear actuator and/or the chevron.Type: GrantFiled: June 17, 2011Date of Patent: December 24, 2013Assignee: General Electric CompanyInventors: David Patrick Calder, Pupinder Bhutiani
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Patent number: 8382039Abstract: An anti-icing system for a nacelle of an aircraft engine. The nacelle has an inlet lip that defines a leading edge of the nacelle, and further has an annular-shaped cavity adjacent and delimited in part by an interior surface of the inlet lip. An anti-icing system is located within the cavity and includes a manifold with a cross-sectional shape that conforms to the interior surface of the inlet lip. A wall of the manifold faces the interior surface of the inlet lip, and air is conducted to the manifold to cause heating of the inlet lip via the manifold wall.Type: GrantFiled: December 30, 2009Date of Patent: February 26, 2013Assignee: MRA Systems Inc.Inventor: David Patrick Calder
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Publication number: 20120321456Abstract: A trans cowl for a jet engine includes a chevron coupled with a linear actuators. The chevron is movable by the linear actuator forward or aft to change a gas flow path formed by an core cowl and thrust reverser translating cowl. In a first position, the chevrons are disposed substantially parallel the gas flow path to attenuate drag and/or loss of engine thrust. In a second position, the chevrons are moved aft to project, or further project, into the gas flow path. In one embodiment, the linear actuator comprises a first component that is coupled with the outer cowl. A second component of the linear actuator is coupled with the chevron. When installed, the linear actuator can be coupled with a controller and an electrical power source. A position sensor coupled with the controller senses a position of the linear actuator and/or the chevron.Type: ApplicationFiled: June 17, 2011Publication date: December 20, 2012Inventors: David Patrick Calder, Pupinder Bhutiani
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Publication number: 20110168843Abstract: An anti-icing system for a nacelle of an aircraft engine. The nacelle has an inlet lip that defines a leading edge of the nacelle, and further has an annular-shaped cavity adjacent and delimited in part by an interior surface of the inlet lip. An anti-icing system is located within the cavity and includes a manifold with a cross-sectional shape that conforms to the interior surface of the inlet lip. A wall of the manifold faces the interior surface of the inlet lip, and air is conducted to the manifold to cause heating of the inlet lip via the manifold wall.Type: ApplicationFiled: December 30, 2009Publication date: July 14, 2011Applicant: MRA SYSTEMS, INC.Inventor: David Patrick Calder
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Publication number: 20100163174Abstract: A process and apparatus for producing perforated composite structures, such as acoustic skins suitable for aircraft engine nacelle components. The process includes placing at least one mat member, a non-impregnated fabric member, and a pad member on a tool surface so that pins disposed on the mat member project through the fabric member to define holes therein, the fabric member is between the mat and pad members, and the mat, fabric and pad members yield a non-impregnated stack that conforms to the tool surface. The fabric member is then infused with a resin to yield a resin-impregnated fabric and the resin within the resin-impregnated fabric is partially cured, after which the partially-cured resin-impregnated fabric is removed from the tool surface and from between the mat and pad members. A post cure of the partially-cured resin-impregnated fabric can then be performed to yield the composite structure with the holes.Type: ApplicationFiled: December 30, 2008Publication date: July 1, 2010Applicant: MRA SYSTEMS, INC.Inventors: David Patrick Calder, Graham Frank Howarth
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Patent number: 6935154Abstract: An apparatus and a method for accurately and repeatably positioning metallic parts having variable length extrusions and shaped sheet metal in a modular die system that forms a joggle in the metallic parts. The apparatus of the present invention includes a standard joggle die system that is currently in use in the art. The apparatus further includes a movable back gage assembly that works in combination with the joggle die system to allow an operator to accurately position the workpiece between the joggle dies at a preselected position. The back gage assembly is movable in both the horizontal and vertical directions. The back gage assembly moves into a stored position away from the working area of the dies to permit the joggle to be formed in the workpiece. The back gage assembly can then move back into the working area to accurately position the next workpiece without the need for further adjustments.Type: GrantFiled: December 19, 2003Date of Patent: August 30, 2005Assignee: General Electric CompanyInventors: David Patrick Calder, Albert Randy Wolfe
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Publication number: 20040168501Abstract: An apparatus and a method for accurately and repeatably positioning metallic parts comprised of variable length extrusions and shaped sheet metal in a modular die system that forms a joggle in the metallic parts. The apparatus of the present invention is comprised of a standard joggle die system that is currently in use in the art. The apparatus farther includes a movable back gage assembly that works in combination with the joggle die system to allow an operator to accurately position the workpiece between the joggle dies at a preselected position. The back gage assembly is movable in both the horizontal and vertical directions. The back gage assembly moves into a stored position away from the working area of the dies to permit the joggle to be formed in the workpiece. The back gage assembly can then move back into the working area to accurately position the next workpiece without the need for further adjustments.Type: ApplicationFiled: December 19, 2003Publication date: September 2, 2004Applicant: General Electric CompanyInventors: David Patrick Calder, Albert Randy Wolfe