Patents by Inventor Christopher M. Quinn
Christopher M. Quinn 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: 20200382459Abstract: Aspects described herein relate to a computer system preventing embedded data from being surreptitiously transmitted in attached image files of e-mail messages, where the embedded data is inserted using steganography. The computer system may include a Simple Mail Transfer Protocol (SMTP) e-mail server that transforms an attached image file and replaces the original attached image file with the transformed image file. If the attached image file comprises a stego-image file (where data is embedded in the image), a recipient of the e-mail is unable to extract the embedded data because the recipient does not know a centrally managed key. In addition, the computer system may store images that a user sends as attached files in e-mail messages over a predetermined time duration. If the user sends an e-mail message having an attached image that matches previously sent stored images, an alarm may be generated indicating a potential steganography e-mail event.Type: ApplicationFiled: May 31, 2019Publication date: December 3, 2020Inventors: David Scott Strubbe, Christopher Stott, Christopher M. Quinn, James Brian Chilton, Michael Edward Trudelle
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Patent number: 10724397Abstract: A case for a gas turbine engine includes a plurality of distinct case sections in axial series. The case sections include, in axial order, a flange section, a forward shell section, a containment section, and an aft shell section. The forward shell section, the containment section, and the aft shell section are formed of a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers. The flange section is formed of a second plurality of non-crimp fabric layers. The plurality of unidirectional roving fiber layers do not have stitching or weaves. A ballistic liner is attached with the containment section, and a fiberglass layer encapsulates the plurality of unidirectional roving fiber layers, the plurality of non-crimp fabric layers, and the second plurality of non-crimp fabric layers.Type: GrantFiled: December 8, 2017Date of Patent: July 28, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Darin S. Lussier, Sreenivasa R. Voleti, Thomas J. Robertson, Jr., Christopher M. Quinn
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Patent number: 10578120Abstract: A platform for a fan of a gas turbine engine includes a body portion, a forward flange at a front of the body portion that includes an engagement feature that interacts with a forward flange of a lug of a hub of a fan of a gas turbine engine, and a pin integral with a rear portion of the body portion. The pin is receivable in an aperture in a rear flange of the lug.Type: GrantFiled: August 9, 2017Date of Patent: March 3, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Shelton O. Duelm, Christopher M. Quinn, Charles W. Brown
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Patent number: 10329925Abstract: A turbine engine component (100) comprises a fiber structure (125, 126) forming at least a portion of an airfoil (102). A matrix (128) embeds the fiber structure. A carbon nanotube filler (130) is in the matrix.Type: GrantFiled: June 26, 2014Date of Patent: June 25, 2019Assignee: United Technologies CorporationInventors: Sreenivasa R. Voleti, Christopher M. Quinn
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Patent number: 10119423Abstract: A fan hub assembly for a gas turbine engine includes a fan hub that is configured to rotate about an axis. The fan hub has an axially extending aperture and a platform. A fastener is received in the aperture in a slip fit relationship to secure the platform to the fan hub.Type: GrantFiled: September 17, 2013Date of Patent: November 6, 2018Assignee: United Technologies CorporationInventors: Colin J. Kling, Charles W. Brown, Christopher M. Quinn, Shelton O. Duelm, Peter V. Tomeo, Corey L. Hubbert
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Patent number: 10046539Abstract: A composite article includes a laminate structure of at least first and second fiber layers. Each of the layers includes a network of primary reinforcement fibers disposed in a matrix. The layers are bonded to each other along an interface of the matrices. The matrices include a concentration of secondary reinforcement particles locally at the interface to strengthen the interface.Type: GrantFiled: July 14, 2015Date of Patent: August 14, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Sreenivasa R. Voleti, Christopher M. Quinn
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Patent number: 10018048Abstract: Anti-rotation tabs for the platforms in the fan section of a gas turbine engine are provided. The anti-rotation tabs interface with the trailing edge of the spinner, thereby preventing the platform from rotating and twisting.Type: GrantFiled: December 16, 2013Date of Patent: July 10, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Andrew G. Alarcon, Christopher M. Quinn, James Glaspey, Matthew A. Turner
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Publication number: 20180100408Abstract: A case for a gas turbine engine includes a plurality of distinct case sections in axial series. The case sections include, in axial order, a flange section, a forward shell section, a containment section, and an aft shell section. The forward shell section, the containment section, and the aft shell section are formed of a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers. The flange section is formed of a second plurality of non-crimp fabric layers. The plurality of unidirectional roving fiber layers do not have stitching or weaves. A ballistic liner is attached with the containment section, and a fiberglass layer encapsulates the plurality of unidirectional roving fiber layers, the plurality of non-crimp fabric layers, and the second plurality of non-crimp fabric layers.Type: ApplicationFiled: December 8, 2017Publication date: April 12, 2018Inventors: Darin S. Lussier, Sreenivasa R. Voleti, Thomas J. Robertson, JR., Christopher M. Quinn
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Patent number: 9909503Abstract: A gas turbine engine includes a core engine, a fan coupled to be driven by the core engine, a first case structure around the core engine and a second case structure around the fan. The first case structure and the second case structure define a bypass passage there between. A vane structure includes an airfoil extending radially between the first case structure and the second case structure. A seal is configured to control leakage between the bypass passage and a core engine.Type: GrantFiled: February 22, 2013Date of Patent: March 6, 2018Assignee: United Technologies CorporationInventors: Keith T. Salamon, Matthew A. Turner, Christopher M. Quinn
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Patent number: 9840936Abstract: A case for a gas turbine engine includes a containment section with a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers. A method of manufacturing the case includes winding the plurality of unidirectional roving fiber layers around the plurality of non-crimp fabric layers.Type: GrantFiled: February 16, 2012Date of Patent: December 12, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Darin S. Lussier, Sreenivasa R. Voleti, Thomas J. Robertson, Jr., Christopher M. Quinn
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Publication number: 20170335859Abstract: A platform for a fan of a gas turbine engine includes a body portion, a forward flange at a front of the body portion that includes an engagement feature that interacts with a forward flange of a lug of a hub of a fan of a gas turbine engine, and a pin integral with a rear portion of the body portion. The pin is receivable in an aperture in a rear flange of the lug.Type: ApplicationFiled: August 9, 2017Publication date: November 23, 2017Inventors: Shelton O. Duelm, Christopher M. Quinn, Charles W. Brown
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Patent number: 9759226Abstract: A platform for a fan of a gas turbine engine includes a body portion, a forward flange at a front of the body portion that includes an engagement feature that interacts with a forward flange of a lug of a hub of a fan of a gas turbine engine, and a pin integral with a rear portion of the body portion. The pin is receivable in an aperture in a rear flange of the lug.Type: GrantFiled: February 3, 2014Date of Patent: September 12, 2017Assignee: United Technologies CorporationInventors: Shelton O. Duelm, Christopher M. Quinn, Charles W. Brown
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Publication number: 20160130952Abstract: A turbine engine component (100) comprises a fiber structure (125, 126) forming at least a portion of an airfoil (102). A matrix (128) embeds the fiber structure. A carbon nanotube filler (130) is in the matrix.Type: ApplicationFiled: June 26, 2014Publication date: May 12, 2016Applicant: United Technologies CorporationInventors: Sreenivasa R. Voleti, Christopher M. Quinn
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Patent number: 9267386Abstract: A fairing assembly includes an outer wall, a first side wall, a second side wall, and a saddle. The first side wall and the second side wall extend from opposing sides of the outer wall. Together the first side wall, the second side wall, and the outer wall form a cavity within the fairing assembly. The saddle is positioned within the cavity and extends between the first side wall and the second side wall. The saddle has a first rib adapted to connect to the first side wall and a second rib adapted to connect to the second side wall. The first rib and the second rib connect together at a central hub.Type: GrantFiled: June 29, 2012Date of Patent: February 23, 2016Assignee: United Technologies CorporationInventors: Matthew A. Turner, Charles W. Brown, Shari L. Bugaj, Christopher M. Quinn, David J. Hyland, Andrew G. Alarcon
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Publication number: 20160031182Abstract: According to various embodiments, a carbon fiber structure is presented. The carbon fiber structure may address loads presented to an engine component in various directions. For instance, non-planar surfaces of a composite comprising a structure disclosed herein may achieve enhanced stiffness and/or strength. Thus, delamination of elements comprising a structure disclosed herein may be reduced. A three dimensional weave of carbon fiber elements through-thickness may provide enhanced strength to the composite material.Type: ApplicationFiled: October 15, 2015Publication date: February 4, 2016Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: CHRISTOPHER M. QUINN, SREENIVASA R. VOLETI
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Publication number: 20160023429Abstract: A composite article includes a laminate structure of at least first and second fiber layers. Each of the layers includes a network of primary reinforcement fibers disposed in a matrix. The layers are bonded to each other along an interface of the matrices. The matrices include a concentration of secondary reinforcement particles locally at the interface to strengthen the interface.Type: ApplicationFiled: July 14, 2015Publication date: January 28, 2016Inventors: Sreenivasa R. Voleti, Christopher M. Quinn
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Publication number: 20150337661Abstract: Anti-rotation tabs for the platforms in the fan section of a gas turbine engine are provided. The anti-rotation tabs interface with the trailing edge of the spinner, thereby preventing the platform from rotating and twisting.Type: ApplicationFiled: December 16, 2013Publication date: November 26, 2015Inventors: Andrew G. Alarcon, Christopher M. Quinn, James Glaspey, Matthew A. Turner
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Publication number: 20150226130Abstract: A gas turbine engine includes a core engine, a fan coupled to be driven by the core engine, a first case structure around the core engine and a second case structure around the fan. The first case structure and the second case structure define a bypass passage there between. A vane structure includes an airfoil extending radially between the first case structure and the second case structure. A seal is configured to control leakage between the bypass passage and a core engine.Type: ApplicationFiled: February 22, 2013Publication date: August 13, 2015Inventors: Keith T. Salamon, Matthew A. Turner, Christopher M. Quinn
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Publication number: 20150218966Abstract: A fan hub assembly for a gas turbine engine includes a fan hub that is configured to rotate about an axis. The fan hub has an axially extending aperture and a platform. A fastener is received in the aperture in a slip fit relationship to secure the platform to the fan hub.Type: ApplicationFiled: September 17, 2013Publication date: August 6, 2015Inventors: Colin J. Kling, Charles W. Brown, Christopher M. Quinn, Shelton O. Duelm, Peter V. Tomeo, Corey L. Hubbert
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Publication number: 20150125305Abstract: A platform for a fan of a gas turbine engine includes a body portion, a forward flange at a front of the body portion that includes an engagement feature that interacts with a forward flange of a lug of a hub of a fan of a gas turbine engine, and a pin integral with a rear portion of the body portion. The pin is receivable in an aperture in a rear flange of the lug.Type: ApplicationFiled: February 3, 2014Publication date: May 7, 2015Applicant: United Technologies CorporationInventors: Shelton O. Duelm, Christopher M. Quinn, Charles W. Brown