Patents by Inventor Ludovic Prunet
Ludovic Prunet 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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Patent number: 11667374Abstract: A blade pitch actuation mechanism comprising a rotating race member in which is formed a race configured to receive a trunnion pin attached to a blade, whereby the race defines a cam profile such that rotation of the race member causes the trunnion pin received in the race to rotate as it slides over the cam profile.Type: GrantFiled: March 15, 2021Date of Patent: June 6, 2023Assignee: RATIER-FIGEAC SASInventors: Ludovic Prunet, Patrick Moles, Kevin Le Meur
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Patent number: 11413828Abstract: A method of making an aircraft blade is provided. The method comprises the steps of: assembling two or more fibre-reinforced thermoplastic composite parts into a blade assembly; and welding the fibre-reinforced thermoplastic composite parts together utilising an additional thermoplastic located at least at locations where the parts will abut when assembled. The additional thermoplastic has a melting or softening temperature lower than a melting temperature of each of the fibre-reinforced thermoplastic composite parts being assembled. The step of welding comprises heating the blade assembly to a temperature above the melting/softening temperature of the additional thermoplastic and below the melting temperature of each of the fibre-reinforced thermoplastic composite parts so as to melt/soften the additional thermoplastic and thereby weld the fibre-reinforced thermoplastic composite parts together to form the aircraft blade.Type: GrantFiled: May 21, 2018Date of Patent: August 16, 2022Assignee: RATIER-FIGEAC SASInventors: Kévin Le Meur, Patrice Brion, Ludovic Prunet, Fabien Ramirez
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Patent number: 11371364Abstract: A method of manufacturing a fabric structure for use in manufacturing a composite aircraft blade. The method comprises: combining yarns including both reinforcing material filaments and a matrix material with yarns of reinforcing material filaments and/or yarns including at least one filament of matrix material; or by combining yarns of reinforcing material filaments with yarns including at least one filament of matrix material; or by combining yarns each comprising both reinforcing material filaments and matrix material. Combining may comprise weaving, knitting or braiding. The matrix material may be a thermoplastic.Type: GrantFiled: May 21, 2018Date of Patent: June 28, 2022Assignee: RATIER-FIGEAC SASInventors: Kévin Le Meur, Patrice Brion, Ludovic Prunet
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Publication number: 20210284324Abstract: A blade pitch actuation mechanism comprising a rotating race member in which is formed a race configured to receive a trunnion pin attached to a blade, whereby the race defines a cam profile such that rotation of the race member causes the trunnion pin received in the race to rotate as it slides over the cam profile.Type: ApplicationFiled: March 15, 2021Publication date: September 16, 2021Inventors: Ludovic PRUNET, Patrick MOLES, Kevin LE MEUR
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Publication number: 20210284345Abstract: A blade de-icing system for a blade to be de-iced that has a body extending between a leading edge and a trailing edge, said leading edge ending at an apex. The system includes a de-icer component having a recess formed therein and being positioned on said leading edge of said blade so that said de-icer component covers and extends away from said apex and so that said recess is positioned at said apex of said leading edge; and an anti-erosion strip provided in said recess of said de-icer component; wherein said anti-erosion strip and said recess are sized and shaped such that said anti-erosion strip fits within said recess so that outer surface of said anti-erosion strip is flush with the outer surface of said de-icer component. A method of manufacturing the same is also described herein.Type: ApplicationFiled: March 15, 2021Publication date: September 16, 2021Inventors: Ludovic PRUNET, Arnaud ANDRZEJEWSKI
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Patent number: 11019687Abstract: This disclosure provides a heating device. The heating device comprises an electrically conductive fabric and first and second electrical connections. The first and second electrical connections are each connected to the conductive fabric at a first end of the device. When the electrical connections are connected to a power source current flows from the first electrical connection, though the conductive fabric and to the second electrical connection thereby generating heat.Type: GrantFiled: August 17, 2017Date of Patent: May 25, 2021Assignee: RATIER-FIGEAC SASInventors: Pierre-Alex Picard, Ludovic Prunet
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Patent number: 10746030Abstract: A method is disclosed for manufacture of a composite blade with an airfoil and a root, wherein the blade comprises a core of chopped fibre composite material and a textile composite material encasing the chopped fibre core. The method comprises: forming a blade insert using chopped fibre composite; surrounding the blade insert with a plurality of layers of a textile in a textile composite material; and thermoforming the blade insert and the surrounding textile composite material in a thermoforming mould in order to consolidate the part.Type: GrantFiled: April 27, 2018Date of Patent: August 18, 2020Assignee: RATIER-FIGEAC SASInventors: Kévin Le Meur, Patrice Brion, Ludovic Prunet
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Publication number: 20180333922Abstract: A method of making an aircraft blade is provided. The method comprises the steps of: assembling two or more fibre-reinforced thermoplastic composite parts into a blade assembly; and welding the fibre-reinforced thermoplastic composite parts together utilising an additional thermoplastic located at least at locations where the parts will abut when assembled. The additional thermoplastic has a melting or softening temperature lower than a melting temperature of each of the fibre-reinforced thermoplastic composite parts being assembled. The step of welding comprises heating the blade assembly to a temperature above the melting/softening temperature of the additional thermoplastic and below the melting temperature of each of the fibre-reinforced thermoplastic composite parts so as to melt/soften the additional thermoplastic and thereby weld the fibre-reinforced thermoplastic composite parts together to form the aircraft blade.Type: ApplicationFiled: May 21, 2018Publication date: November 22, 2018Inventors: Kévin LE MEUR, Patrice BRION, Ludovic PRUNET, Fabien RAMIREZ
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Publication number: 20180334912Abstract: A method is disclosed for manufacture of a composite blade with an airfoil and a root, wherein the blade comprises a core of chopped fibre composite material and a textile composite material encasing the chopped fibre core. The method comprises: forming a blade insert using chopped fibre composite; surrounding the blade insert with a plurality of layers of a textile in a textile composite material; and thermoforming the blade insert and the surrounding textile composite material in a thermoforming mould in order to consolidate the part.Type: ApplicationFiled: April 27, 2018Publication date: November 22, 2018Inventors: Kévin LE MEUR, Patrice BRION, Ludovic PRUNET
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Publication number: 20180334913Abstract: A method of manufacturing a fabric structure for use in manufacturing a composite aircraft blade. The method comprises: combining yarns including both reinforcing material filaments and a matrix material with yarns of reinforcing material filaments and/or yarns including at least one filament of matrix material; or by combining yarns of reinforcing material filaments with yarns including at least one filament of matrix material; or by combining yarns each comprising both reinforcing material filaments and matrix material. Combining may comprise weaving, knitting or braiding. The matrix material may be a thermoplastic.Type: ApplicationFiled: May 21, 2018Publication date: November 22, 2018Inventors: Kévin LE MEUR, Patrice BRION, Ludovic PRUNET
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Publication number: 20180054859Abstract: This disclosure provides a heating device. The heating device comprises an electrically conductive fabric and first and second electrical connections. The first and second electrical connections are each connected to the conductive fabric at a first end of the device. When the electrical connections are connected to a power source current flows from the first electrical connection, though the conductive fabric and to the second electrical connection thereby generating heat.Type: ApplicationFiled: August 17, 2017Publication date: February 22, 2018Inventors: Pierre-Alex PICARD, Ludovic PRUNET
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Publication number: 20170334577Abstract: A propeller blade assembly includes an airfoil having a base, a tip and a leading edge and a root extending from the base of the airfoil for attaching the airfoil to a hub. The assembly further comprises an electrically conductive sheath for electrically grounding the airfoil. The electrically conductive sheath is attached to the leading edge of the airfoil and extends from the base to the tip of the airfoil. The assembly further comprises an electrically conductive element for electrically connecting the electrically conductive sheath to the root or hub. Also disclosed is an electrically conductive sheath for grounding an airfoil and a method for assembling a propeller blade assembly.Type: ApplicationFiled: May 23, 2017Publication date: November 23, 2017Inventors: Arnaud ANDRZEJEWSKI, Pierre-Alex PICARD, Ludovic PRUNET, Frederic VIGIER, Patrick MOLES
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Patent number: 9505486Abstract: A propeller blade includes a foam core, an adhesive layer formed on the core and a structural layer that covers at least a portion of the adhesive layer and that surrounds at least a portion of the foam core.Type: GrantFiled: November 30, 2012Date of Patent: November 29, 2016Assignee: HAMILTON SUNDSTRAND CORPORATIONInventors: David P. Nagle, Ludovic Prunet, Patrice Brion
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Patent number: 9488056Abstract: According to one embodiment, a propeller blade includes a foam core and a structural layer formed of multiple layers that surrounds at least a portion of the foam core. The structural layer includes a mid-thickness location defined between the foam core and an outer edge of the structural layer and the multiple layers include at least one unidirectional layer and at least one biased layer disposed asymmetrically about the mid-thickness location.Type: GrantFiled: April 30, 2013Date of Patent: November 8, 2016Assignees: RATIER-FIGEAC SAS, HAMILTON SUNDSTRAND CORPORATIONInventors: David P. Nagle, Patrice Brion, Ludovic Prunet
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Publication number: 20130287584Abstract: According to one embodiment, a propeller blade includes a foam core and a structural layer formed of multiple layers that surrounds at least a portion of the foam core. The structural layer includes a mid-thickness location defined between the foam core and an outer edge of the structural layer and the multiple layers include at least one unidirectional layer and at least one biased layer disposed asymmetrically about the mid-thickness location.Type: ApplicationFiled: April 30, 2013Publication date: October 31, 2013Applicants: RATIER-FIGEAC SAS, HAMILTON SUNDTRAND CORPORATIONInventors: David P. Nagle, Patrice Brion, Ludovic Prunet
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Publication number: 20130136616Abstract: A propeller blade includes a honeycomb core and a structural layer that surrounds at least a portion of the honeycomb core.Type: ApplicationFiled: November 30, 2012Publication date: May 30, 2013Inventor: Ludovic Prunet
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Publication number: 20130136614Abstract: A propeller blade includes a foam core, an adhesive layer formed on the core and a structural layer that covers at least a portion of the adhesive layer and that surrounds at least a portion of the foam core.Type: ApplicationFiled: November 30, 2012Publication date: May 30, 2013Inventors: David P. Nagle, Ludovic Prunet, Patrice Brion