Patents by Inventor Mark E. Simonds
Mark E. Simonds 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: 11408296Abstract: A vane stage includes an arcuate platform defining an axial centerline axis having a pair of flanges that extend radially inward from the platform. The flanges are axially spaced from one another and from respective forward and aft ends of the platform. The vane stage includes a vane extending radially outward from the platform and a seal carrier mounted to the flanges of the platform. A method for constructing a vane stage includes sliding a seal carrier between flanges of an arcuate platform. Each flange includes at least a pair of through holes and interfaces with a respective axial side of the seal carrier. The method includes drilling through holes in each axial side of the seal carrier by using the through holes of each flange as guides.Type: GrantFiled: February 11, 2019Date of Patent: August 9, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Mark E. Simonds, Steven J. Feigleson
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Patent number: 10794200Abstract: A vane stage includes a ringcase extending circumferentially about a center axis of the vane stage. The ringcase extends completely about the center axis to form a first ring. An inner shroud extends circumferentially about the center axis of the vane stage. The inner shroud extends completely about the center axis to form a second ring positioned radially within the ringcase relative the center axis. A plurality of stationary half vanes extend radially between the ringcase and the inner shroud, and are circumferentially spaced about the center axis. The plurality of stationary half vanes are integral with the ringcase and the inner shroud.Type: GrantFiled: November 8, 2018Date of Patent: October 6, 2020Assignee: United Technologies CorporationInventor: Mark E. Simonds
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Patent number: 10781707Abstract: A vane stage includes a ringcase extending circumferentially about a center axis of the vane stage. The ringcase extends completely about the center axis to form a first ring. An inner shroud extends circumferentially about the center axis of the vane stage. The inner shroud extends completely about the center axis to form a second ring positioned radially within the ringcase relative the center axis. A plurality of stationary half vanes extend radially between the ringcase and the inner shroud, and are circumferentially spaced about the center axis. The plurality of stationary half vanes are integral with the ringcase and the inner shroud.Type: GrantFiled: September 14, 2018Date of Patent: September 22, 2020Assignee: United Technologies CorporationInventors: David M. Dyer, Zachary J. Jeske, Michael Ronan, Matthew E. Bintz, John P. Tirone, Scott Gammons, Michael C. Firnhaber, Mark E. Simonds
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Patent number: 10711613Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 2.58-2.88 inch (65.4-73.1 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.59-1.89 inch (40.3-48.0 mm). The airfoil element includes at least two of a first mode with a frequency of 2088±10% Hz, a second mode with a frequency of 3099±10% Hz, a third mode with a frequency of 6890±10% Hz, a fourth mode with a frequency of 7207±10% Hz, a fifth mode with a frequency of 11241±10% Hz, a sixth mode with a frequency of 11916±10% Hz and a seventh mode with a frequency of 12600±10% Hz.Type: GrantFiled: January 12, 2018Date of Patent: July 14, 2020Assignee: Raytheon Technologies CorporationInventors: William R. Edwards, Mark E. Simonds, Steven J. Feigleson, Lisa I. Brilliant
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Patent number: 10619498Abstract: A fan exit stator assembly of a gas turbine engine may include a radially inward shroud defining a first slot, a radially outward shroud, and a vane. The vane may include a base portion extending through the first slot and a tip portion coupled to the radially outward shroud. The vane may also include a retainer plate disposed radially inward of the radially inward shroud that projects in a circumferential direction from the base portion of the vane. A circumferential plate dimension of the retainer plate in the circumferential direction is greater than a first slot radius in the circumferential direction of the first slot, thus preventing radially outward movement of the vane relative to the radially inward shroud.Type: GrantFiled: September 6, 2017Date of Patent: April 14, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Mark E. Simonds, Rahul Kuwar, Aniket Katti, Sridhar Bagathi, Raghavan Kotur
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Publication number: 20200088045Abstract: A vane stage includes a ringcase extending circumferentially about a center axis of the vane stage. The ringcase extends completely about the center axis to form a first ring. An inner shroud extends circumferentially about the center axis of the vane stage. The inner shroud extends completely about the center axis to form a second ring positioned radially within the ringcase relative the center axis. A plurality of stationary half vanes extend radially between the ringcase and the inner shroud, and are circumferentially spaced about the center axis. The plurality of stationary half vanes are integral with the ringcase and the inner shroud.Type: ApplicationFiled: November 8, 2018Publication date: March 19, 2020Inventor: Mark E. Simonds
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Publication number: 20200088046Abstract: A vane stage includes a ringcase extending circumferentially about a center axis of the vane stage. The ringcase extends completely about the center axis to form a first ring. An inner shroud extends circumferentially about the center axis of the vane stage. The inner shroud extends completely about the center axis to form a second ring positioned radially within the ringcase relative the center axis. A plurality of stationary half vanes extend radially between the ringcase and the inner shroud, and are circumferentially spaced about the center axis. The plurality of stationary half vanes are integral with the ringcase and the inner shroud.Type: ApplicationFiled: September 14, 2018Publication date: March 19, 2020Inventors: David M. Dyer, Zachary J. Jeske, Michael Ronan, Matthew E. Bintz, John P. Tirone, Scott Gammons, Michael C. Firnhaber, Mark E. Simonds
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Patent number: 10557412Abstract: An outer diameter shroud for retaining a stator of a gas turbine engine having an axis includes an annular body positioned around the axis, extending in an axial direction, and defining a plurality of slots each configured to receive a portion of one of a plurality of stators. The outer diameter shroud further includes a shroud flange coupled to the annular body, extending in a direction perpendicular to the annular body, and configured to be fastened to a case of the gas turbine engine.Type: GrantFiled: May 30, 2017Date of Patent: February 11, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Paul W. Baumann, Brian Barainca, Rolf Thorsen, Mark E. Simonds, Gary F. Fowler, Hector M. Pinero
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Publication number: 20200024992Abstract: A vane stage includes an arcuate platform defining an axial centerline axis having a pair of flanges that extend radially inward from the platform. The flanges are axially spaced from one another and from respective forward and aft ends of the platform. The vane stage includes a vane extending radially outward from the platform and a seal carrier mounted to the flanges of the platform. A method for constructing a vane stage includes sliding a seal carrier between flanges of an arcuate platform. Each flange includes at least a pair of through holes and interfaces with a respective axial side of the seal carrier. The method includes drilling through holes in each axial side of the seal carrier by using the through holes of each flange as guides.Type: ApplicationFiled: February 11, 2019Publication date: January 23, 2020Inventors: Mark E. Simonds, Steven J. Feigleson
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Patent number: 10294808Abstract: A fastener retention mechanism for retaining fasteners of a stator assembly in a gas turbine engine is provided. The fastener retention mechanism including: a base having a first rail, a second rail, and a base surface extending therebetween, the first rail and second rail being in a facing spaced relationship with respect to each other and define a channel extending therebetween; a cover releasably connected to the base, the cover having a first foot, second foot, and cover surface extending between the first foot and second foot, wherein the first foot and second foot are configured to interlock with the first rail and second rail, respectively, such that the channel is covered by the cover surface when the cover is secured to the base; and wherein the cover is secured to the base by the interlocking of the first foot and second foot with the first rail and second rail.Type: GrantFiled: April 21, 2016Date of Patent: May 21, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: Mark E. Simonds
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Patent number: 10280779Abstract: An example seal includes, among other things, a plug body to limit flow through an axially extending interface between a first component and a second component, the plug body to flow when positioned within both a cavity of the first component and a cavity of the second component.Type: GrantFiled: September 8, 2014Date of Patent: May 7, 2019Assignee: United Technologies CorporationInventor: Mark E. Simonds
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Publication number: 20190078469Abstract: A retention system for a stator vane assembly including a stator vane having a radially inner end and a radially outer end. Also included is an outer diameter shroud coupled to the radially outer end of the stator vane. Further included is an inner diameter shroud coupled to the radially inner end of the stator vane. Yet further included is a flange of the outer diameter shroud coupled to a frame member with a mechanical fastener. Also included is an inner shroud flange extending radially inwardly and defining a radial recess, the radial recess allowing radial movement of the radially inner end of the stator vane.Type: ApplicationFiled: September 11, 2017Publication date: March 14, 2019Inventor: Mark E. Simonds
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Publication number: 20190071988Abstract: A fan exit stator assembly of a gas turbine engine may include a radially inward shroud defining a first slot, a radially outward shroud, and a vane. The vane may include a base portion extending through the first slot and a tip portion coupled to the radially outward shroud. The vane may also include a retainer plate disposed radially inward of the radially inward shroud that projects in a circumferential direction from the base portion of the vane. A circumferential plate dimension of the retainer plate in the circumferential direction is greater than a first slot radius in the circumferential direction of the first slot, thus preventing radially outward movement of the vane relative to the radially inward shroud.Type: ApplicationFiled: September 6, 2017Publication date: March 7, 2019Applicant: United Technologies CorporationInventors: MARK E. SIMONDS, RAHUL KUWAR, ANIKET KATTI, SRIDHAR BAGATHI, RAGHAVAN KOTUR
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Patent number: 10202857Abstract: A vane stage includes an arcuate platform defining a axial centerline axis having a pair of flanges that extend radially inward from the platform. The flanges are axially spaced from one another and from respective forward and aft ends of the platform. The vane stage includes a vane extending radially outward from the platform and a seal carrier mounted to the flanges of the platform. A method for constructing a vane stage includes sliding a seal carrier between flanges of an arcuate platform. Each flange includes at least a pair of through holes and interfaces with a respective axial side of the seal carrier. The method includes drilling through holes in each axial side of the seal carrier by using the through holes of each flange as guides.Type: GrantFiled: February 6, 2015Date of Patent: February 12, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Mark E. Simonds, Steven J. Feigleson
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Publication number: 20180347465Abstract: An outer diameter shroud for retaining a stator of a gas turbine engine having an axis includes an annular body positioned around the axis, extending in an axial direction, and defining a plurality of slots each configured to receive a portion- of one of a plurality of stators. The outer diameter shroud further includes a shroud flange coupled to the annular body, extending in a direction perpendicular to the annular body, and configured to be fastened to a case of the gas turbine engine.Type: ApplicationFiled: May 30, 2017Publication date: December 6, 2018Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Paul W. Baumann, Brian Barainca, Rolf Thorsen, Mark E. Simonds, Gary F. Fowler, Hector M. Pinero
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Publication number: 20170306776Abstract: A fastener retention mechanism for retaining fasteners of a stator assembly in a gas turbine engine is provided. The fastener retention mechanism including: a base having a first rail, a second rail, and a base surface extending therebetween, the first rail and second rail being in a facing spaced relationship with respect to each other and define a channel extending therebetween; a cover releasably connected to the base, the cover having a first foot, second foot, and cover surface extending between the first foot and second foot, wherein the first foot and second foot are configured to interlock with the first rail and second rail, respectively, such that the channel is covered by the cover surface when the cover is secured to the base; and wherein the cover is secured to the base by the interlocking of the first foot and second foot with the first rail and second rail.Type: ApplicationFiled: April 21, 2016Publication date: October 26, 2017Inventor: Mark E. Simonds
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Patent number: 9546571Abstract: A turbine engine includes a vane and a case with a flange ring. The flange ring defines a channel that extends axially into a side of the flange ring to a channel end surface. The vane has a mounting lug that projects into the channel. The mounting lug includes a lug end surface that extends radially between substantially parallel lug side surfaces, where the lug end surface is engaged with the channel end surface.Type: GrantFiled: August 22, 2012Date of Patent: January 17, 2017Assignee: United Technologies CorporationInventor: Mark E. Simonds
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Publication number: 20160230574Abstract: A vane stage includes an arcuate platform defining a axial centerline axis having a pair of flanges that extend radially inward from the platform. The flanges are axially spaced from one another and from respective forward and aft ends of the platform. The vane stage includes a vane extending radially outward from the platform and a seal carrier mounted to the flanges of the platform. A method for constructing a vane stage includes sliding a seal carrier between flanges of an arcuate platform. Each flange includes at least a pair of through holes and interfaces with a respective axial side of the seal carrier. The method includes drilling through holes in each axial side of the seal carrier by using the through holes of each flange as guides.Type: ApplicationFiled: February 6, 2015Publication date: August 11, 2016Inventors: Mark E. Simonds, Steven J. Feigleson
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Publication number: 20160215642Abstract: An example seal includes, among other things, a plug body to limit flow through an axially extending interface between a first component and a second component, the plug body to flow when positioned within both a cavity of the first component and a cavity of the second component.Type: ApplicationFiled: September 8, 2014Publication date: July 28, 2016Applicant: United Technologies CorporationInventor: Mark E. Simonds
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Publication number: 20140056702Abstract: A turbine engine includes a vane and a case with a flange ring. The flange ring defines a channel that extends axially into a side of the flange ring to a channel end surface. The vane has a mounting lug that projects into the channel. The mounting lug includes a lug end surface that extends radially between substantially parallel lug side surfaces, where the lug end surface is engaged with the channel end surface.Type: ApplicationFiled: August 22, 2012Publication date: February 27, 2014Applicant: United Technologies CorporationInventor: Mark E. Simonds