Patents by Inventor Gregory Carl Gemeinhardt
Gregory Carl Gemeinhardt 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: 20230228198Abstract: A component for a gas turbine engine. The component includes a continuous fiber blade including an airfoil extending radially between a root and a tip and a blade attachment feature positioned at or adjacent to the root. The component further includes a platform coupled to the root of the continuous fiber blade. The platform includes a plurality of chopped fibers. Additionally, the component includes a thermoplastic polymer contained in both the continuous fiber blade and the platform. Moreover, the continuous fiber blade and platform are coupled together such that the continuous fiber blade and platform form a monolithic composite body.Type: ApplicationFiled: November 29, 2022Publication date: July 20, 2023Inventors: Gregory Carl Gemeinhardt, Nicholas Joseph Kray, Andreas Mastorakis
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Patent number: 11286782Abstract: An airfoil that includes an airfoil body having a root and a tip, and convex and concave sides that extend between a leading edge and a trailing edge. The airfoil also includes at least a first cladding element that is attached to the airfoil body. The first cladding element includes a first portion and a second portion. The second portion is configured to separate from the first portion when the first cladding element encounters a force of at least a predetermined amount.Type: GrantFiled: December 7, 2018Date of Patent: March 29, 2022Assignee: General Electric CompanyInventors: Gregory Carl Gemeinhardt, Douglas Duane Ward, David William Crall, Nicholas Joseph Kray
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Patent number: 10815798Abstract: A blade for the fan section of a turbine engine comprising a composite core defining a pressure side and a suction side extending axially between a core leading edge and a core trailing edge defining a chord-wise direction and extending radially between a core root and a core tip defining a span-wise direction and a leading edge strip made of materials with different elasticity and mounted to the core leading edge.Type: GrantFiled: February 8, 2018Date of Patent: October 27, 2020Assignee: General Electric CompanyInventors: Nicholas Joseph Kray, Gregory Carl Gemeinhardt, Douglas Duane Ward, David William Crall
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Publication number: 20200318486Abstract: A component for a gas turbine engine. The component includes a continuous fiber blade including an airfoil extending radially between a root and a tip and a blade attachment feature positioned at or adjacent to the root. The component further includes a platform coupled to the root of the continuous fiber blade. The platform includes a plurality of chopped fibers. Additionally, the component includes a thermoplastic polymer contained in both the continuous fiber blade and the platform. Moreover, the continuous fiber blade and platform are coupled together such that the continuous fiber blade and platform form a monolithic composite body.Type: ApplicationFiled: April 4, 2019Publication date: October 8, 2020Inventors: Gregory Carl Gemeinhardt, Nicholas Joseph Kray, Andreas Mastorakis
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Publication number: 20200182062Abstract: An airfoil that includes an airfoil body having a root and a tip, and convex and concave sides that extend between a leading edge and a trailing edge. The airfoil also includes at least a first cladding element that is attached to the airfoil body. The first cladding element includes a first portion and a second portion. The second portion is configured to separate from the first portion when the first cladding element encounters a force of at least a predetermined amount.Type: ApplicationFiled: December 7, 2018Publication date: June 11, 2020Inventors: Gregory Carl Gemeinhardt, Douglas Duane Ward, David William Crall, Nicholas Joseph Kray
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Publication number: 20190368361Abstract: Fan blade includes airfoil with leading and trailing edges, pressure and suction sides extending outwardly from airfoil base to airfoil tip, and tip cladding with non-symmetric pressure and suction side cladding flanks bonded to airfoil tip along pressure and suction sides respectively. Pressure and suction side cladding flanks may include non-symmetric or different pressure and suction side cladding radial heights and/or different pressure and suction side cladding radial locations of pressure and suction side cladding flank portions of pressure and suction side cladding flanks in tip cladding portion of tip cladding. One cladding radial heights may be variable in tip cladding portion. Chordwise extending seam may be in pressure side cladding flank portion and/or chordwise extending slot may be in suction side cladding flank portion. Cladding flanks may be stronger, more ductile, or less brittle than composite material of composite core of airfoil.Type: ApplicationFiled: June 5, 2018Publication date: December 5, 2019Inventors: Nicholas Joseph Kray, Douglas Duane Ward, Gregory Carl Gemeinhardt, David William Crall, Wendy Wen-Ling Lin
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Patent number: 10450870Abstract: An airfoil for an aircraft engine is provided. The airfoil may include a plurality of composite plies extending in a chordwise direction from a leading edge to a trailing edge and in a spanwise direction between an airfoil tip and an airfoil base. The airfoil may include at least one discontinuous ply having a first ply segment, a second ply segment, and a butt joint disposed between the first ply segment and the second ply segment. The butt joint may be disposed along a first fragment profile to frangibly attach the first and second ply segments.Type: GrantFiled: February 9, 2016Date of Patent: October 22, 2019Assignee: General Electric CompanyInventors: Phani Nandula, Suresh Subramanian, Nicholas Joseph Kray, Gregory Carl Gemeinhardt
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Publication number: 20190242260Abstract: A blade for the fan section of a turbine engine comprising a composite core defining a pressure side and a suction side extending axially between a core leading edge and a core trailing edge defining a chord-wise direction and extending radially between a core root and a core tip defining a span-wise direction and a leading edge strip mounted to the core leading edge.Type: ApplicationFiled: February 8, 2018Publication date: August 8, 2019Inventors: Nicholas Joseph Kray, Gregory Carl Gemeinhardt, Douglas Duane Ward, David William Crall
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Publication number: 20190242399Abstract: A blade for a turbine engine comprising a composite core defining a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction. The composite core is formed from two materials with different compositions.Type: ApplicationFiled: February 8, 2018Publication date: August 8, 2019Inventors: Nicholas Joseph Kray, Gregory Carl Gemeinhardt, Douglas Duane Ward, David William Crall, Wendy Wen-Ling Lin
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Publication number: 20190153876Abstract: A high temperature polymer composite includes nanocomposite material, such as carbon nanotubes, dispersed in polymer matrix composite resin interlayer region, which may include bismaleimide or polyamide resin, between fiber containing plies. The nanocomposite material may be in an operating temperature in a range between 400-800 degrees Fahrenheit. Gas turbine engine parts or components such as airfoils, stator vanes, casings, and ducts may be made of the high temperature polymer composite.Type: ApplicationFiled: November 21, 2017Publication date: May 23, 2019Inventors: Gregory Carl Gemeinhardt, Thomas Michael Sutter
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Patent number: 10247014Abstract: Compressor blades constructed of composite materials are disclosed. Some example compressor blades may include a composite blade panel including an airfoil having a span extending radially outward with respect to an axis of rotation and/or a blade attachment feature radially inward from the airfoil with respect to the axis of rotation. The blade attachment feature may be circumferentially oriented with respect to the axis of rotation. The blade attachment feature may be arranged to releasably engage a generally circumferentially oriented spool attachment feature. The spool attachment feature may be generally shaped as a circumferential dovetail slot configured to slidably receive the blade attachment feature therein.Type: GrantFiled: May 21, 2014Date of Patent: April 2, 2019Assignee: General Electric CompanyInventors: Joseph Nicholas Kray, Gregory Carl Gemeinhardt, Prakash Kashiram Jadhav, Douglas Edward Klei, Phani Nandula, Suresh Subramanian
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Patent number: 10099434Abstract: An airfoil structure is presented. The airfoil structure includes an outer casing substantially surrounding a composite core. The composite core includes a plurality of fiber bands, each of the plurality of fiber bands is placed at a predetermined position and orientation at a time, wherein the plurality of fiber bands are interwoven in an in-plane and out-of-plane orientation by interleaving each of the plurality of fiber bands placed in a plane with one or more of the plurality of fiber bands of an adjacent plane to define an interleaved structure. A method for manufacturing an airfoil structure including the composite core is also presented.Type: GrantFiled: September 16, 2014Date of Patent: October 16, 2018Assignee: GENERAL ELECTRIC COMPANYInventors: Todd Alan Anderson, Nicholas Joseph Kray, Gregory Carl Gemeinhardt, Michael Harvey Schneider
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Patent number: 10041354Abstract: A method of manufacturing a rotor blade is provided. The method includes forming a preform from a plurality of composite plies, the preform including an airfoil portion and a dovetail portion, removing a cutout portion from the dovetail portion of the preform to define a cutout in the preform, wherein the removing the cutout portion facilitates reducing residual stresses in the preform, and inserting an insert into the cutout formed by the removal of the cutout portion.Type: GrantFiled: September 14, 2011Date of Patent: August 7, 2018Assignee: General Electric CompanyInventors: Nicholas Joseph Kray, Douglas Duane Ward, Phillip Wayne Rambo, Gregory Carl Gemeinhardt
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Patent number: 9835239Abstract: A housing that includes a polymer, a reinforcing material, and a thermally conductive filler. A first housing component is defined by the polymer such that the reinforcing material and a thermally conductive filler are embedded within the polymer. The thermally conductive filler is configured such that heat can be passively conducted through the first housing component. The housing can be configured to be an aircraft gearbox housing.Type: GrantFiled: January 21, 2016Date of Patent: December 5, 2017Assignee: General Electric CompanyInventors: Warren Rosal Ronk, Gregory Carl Gemeinhardt
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Patent number: 9777579Abstract: A composite article including composite component extending heightwise from a component base to a component tip and lengthwise between spaced apart component first and second edges. Component plies having widthwise spaced apart ply first and second sides and ply edges therebetween. Component mounted on a spar which includes a shank extending heightwise into the composite component, tab at upper end of shank and substantially or fully embedded in the composite component, and tab tip. Ply edges of at least a first portion of the plies directly or indirectly contacting or pressing against the tab. Ply edges of at least a second portion of the plies may directly or indirectly contact or press against the tab tip. Ply edges of first portion may press against one or more indented or recessed surfaces in the tab. The composite article may be a composite blade or vane including a composite airfoil.Type: GrantFiled: December 10, 2012Date of Patent: October 3, 2017Assignee: General Electric CompanyInventors: Nicholas Joseph Kray, Scott Roger Finn, Peggy Lynn Baehmann, Dong-Jin Shim, Gregory Carl Gemeinhardt
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Publication number: 20170234160Abstract: A facing sheet for a fan casing comprising a support layer that includes a set of partitioned cavities with open faces and a facing sheet comprising a polymer matrix composite having a nanostructure.Type: ApplicationFiled: February 11, 2016Publication date: August 17, 2017Inventors: Gregory Carl Gemeinhardt, Michael Dominic Schulte
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Publication number: 20170226867Abstract: An airfoil for an aircraft engine is provided. The airfoil may include a plurality of composite plies extending in a chordwise direction from a leading edge to a trailing edge and in a spanwise direction between an airfoil tip and an airfoil base. The airfoil may include at least one discontinuous ply having a first ply segment, a second ply segment, and a butt joint disposed between the first ply segment and the second ply segment. The butt joint may be disposed along a first fragment profile to frangibly attach the first and second ply segments.Type: ApplicationFiled: February 9, 2016Publication date: August 10, 2017Inventors: Phani Nandula, Suresh Subramanian, Nicholas Joseph Kray, Gregory Carl Gemeinhardt
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Publication number: 20170211682Abstract: A housing that includes a polymer, a reinforcing material, and a thermally conductive filler. A first housing component is defined by the polymer such that the reinforcing material and a thermally conductive filler are embedded within the polymer. The thermally conductive filler is configured such that heat can be passively conducted through the first housing component. The housing can be configured to be an aircraft gearbox housing.Type: ApplicationFiled: January 21, 2016Publication date: July 27, 2017Inventors: Warren Rosal Ronk, Gregory Carl Gemeinhardt
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Publication number: 20160186774Abstract: A process for fabricating a thermoplastic-fiber composite includes heating a thermoplastic resin to a liquid state, unidirectionally orienting fibers, impregnating the fibers with the thermoplastic resin in the liquid state to produce composite laminae, and performing an automated machine lay-up process to produce a composite laminate comprising a plurality of the composite laminae.Type: ApplicationFiled: July 28, 2014Publication date: June 30, 2016Inventors: Paul Stephen MANICKE, Douglas Duane WARD, Gregory Carl GEMEINHARDT
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Publication number: 20160130955Abstract: Compressor blades constructed of composite materials are disclosed. Some example compressor blades may include a composite blade panel including an airfoil having a span extending radially outward with respect to an axis of rotation and/or a blade attachment feature radially inward from the airfoil with respect to the axis of rotation. The blade attachment feature may be circumferentially oriented with respect to the axis of rotation. The blade attachment feature may be arranged to releasably engage a generally circumferentially oriented spool attachment feature. The spool attachment feature may be generally shaped as a circumferential dovetail slot configured to slidably receive the blade attachment feature therein.Type: ApplicationFiled: May 21, 2014Publication date: May 12, 2016Inventors: Joseph Nicholas KRAY, Gregory Carl GEMEINHARDT, Prakash Kashiram JADHAV, Douglas Edward KLEI, Phani NANDULA, Suresh SUBRAMANIAN