Patents by Inventor Steven J. Feigleson
Steven J. Feigleson 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: 11698002Abstract: 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 3.46-3.76 inch (87.8-95.5 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 1.98-2.28 inch (50.2-57.8 mm). The airfoil element includes at least one of a first mode with a frequency of 1056 ± 10% Hz and a second mode with a frequency of 1582 ± 10% Hz.Type: GrantFiled: January 11, 2018Date of Patent: July 11, 2023Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: William R. Edwards, Steven J. Feigleson, Kate Hudon
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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: 11248538Abstract: A split case assembly for a gas turbine engine includes an outer diameter case defining a partial case structure for a gas turbine engine and multiple fixed-variable vanes attached to an inner diameter surface of the outer diameter case. Each of the fixed-variable vanes protrudes radially inward from the outer diameter case. Each of the fixed-variable vanes in the plurality of fixed-variable vanes is interfaced with one of a plurality of inner diameter boxes at a radially inward end of the fixed-variable vane, such that the inner diameter boxes define an inner diameter of a flow path and the outer diameter case defines an outer diameter flow path. Each of the fixed-variable vanes are interfaced with the one of the plurality of inner diameter boxes through at least one inner diameter shoe in a plurality of inner diameter shoes.Type: GrantFiled: September 18, 2015Date of Patent: February 15, 2022Assignee: Raytheon Technologies CorporationInventors: Thomas J. Robertson, Jr., Nathan F. Champion, Steven J. Feigleson
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Patent number: 10815826Abstract: An airfoil extends in a radial direction a span in a range 3.97-4.27 inch (100.9-108.6 mm). A chord length extends in a chordwise direction from a leading edge to a trailing edge at 50% span in a range 1.28-1.58 inch (32.4-40.0 mm). The airfoil includes at least two of a first mode with a frequency of 243±10% Hz, a second mode with a frequency of 374±10% Hz, a third mode with a frequency of 741±10% Hz, a fourth mode with a frequency of 1198±10% Hz, a fifth mode with a frequency of 1663±10% Hz, a sixth mode with a frequency of 2411±10% Hz, a seventh mode with a frequency of 3734±10% Hz, an eighth mode with a frequency of 6738±10% Hz and a ninth mode with a frequency of 8977±10% Hz.Type: GrantFiled: January 11, 2018Date of Patent: October 27, 2020Assignee: Raytheon Technologies CorporationInventors: William R. Edwards, Steven J. Feigleson, Kate Hudon
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Patent number: 10801364Abstract: An airfoil 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 3.26-3.56 inch (82.9-90.5 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 1.25-1.55 inch (31.8-39.4 mm). The airfoil element includes at least two of a first mode with a frequency of 323±10% Hz, a second mode with a frequency of 476±10% Hz, a third mode with a frequency of 1005±10% Hz, a fourth mode with a frequency of 2670±10% Hz, a fifth mode with a frequency of 3255±10% Hz and a sixth mode with a frequency of 7628±10% Hz.Type: GrantFiled: January 11, 2018Date of Patent: October 13, 2020Assignee: Raytheon Technologies CorporationInventors: William R. Edwards, Steven J. Feigleson, Kate Hudon
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Patent number: 10794223Abstract: A case assembly is provided. The case assembly comprises a first flange and a spot face in the first flange. The spot face has a D-shaped perimeter. A jacking insert is disposed in the spot face and has a D-shaped geometry. A threaded cylinder extends from the jacking insert into the first flange. A jacking insert is also provided. The jacking insert comprises a flat portion having a D-shaped geometry and a cylindrical portion having an internal thread configured to interface with a bolt.Type: GrantFiled: December 13, 2017Date of Patent: October 6, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Daniel S. Rogers, Stephen W. Milks, Steven J. Feigleson
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Patent number: 10788049Abstract: 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 2.59-2.89 inch (65.7-73.3 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 1.46-1.76 inch (37.1-44.7 mm). The airfoil element includes at least two of a first mode with a frequency of 703±10% Hz, a second mode with a frequency of 3574±10% Hz, a third mode with a frequency of 8100±10% Hz, a fourth mode with a frequency of 9450±10% Hz, a fifth mode with a frequency of 11116±10% Hz and a sixth mode with a frequency of 11620±10% Hz.Type: GrantFiled: January 15, 2018Date of Patent: September 29, 2020Assignee: Raytheon Technologies CorporationInventors: William R. Edwards, Stephen W. Milks, Steven J. Feigleson, Mark A. Stephens, Joseph C. Straccia
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Patent number: 10787910Abstract: 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 2.59-2.89 inch (65.7-73.3 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 1.35-1.65 inch (34.4-42.0 mm). The airfoil element includes at least two of a first mode with a frequency of 2241±10% Hz, a second mode with a frequency of 3598±10% Hz and a third mode with a frequency of 6212±10% Hz.Type: GrantFiled: January 11, 2018Date of Patent: September 29, 2020Assignee: Raytheon Technologies CorporationInventors: William R. Edwards, Steven J. Feigleson, Kate Hudon
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Patent number: 10767488Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and is joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 3.18-3.48 inch (80.7-88.4 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 1.17-1.47 inch (29.6-37.3 mm). The airfoil element includes at least two of a first mode with a frequency of 333±10% Hz, a second mode with a frequency of 1554±10% Hz, a third mode with a frequency of 2356±10% Hz, a fourth mode with a frequency of 2830±10% Hz, a fifth mode with a frequency of 4075±10% Hz and a sixth mode with a frequency of 5239±10% Hz.Type: GrantFiled: January 15, 2018Date of Patent: September 8, 2020Assignee: Raytheon Technologies CorporationInventors: William R. Edwards, Stephen W. Milks, Steven J. Feigleson, Mark A. Stephens, Joseph C. Straccia
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Patent number: 10760447Abstract: 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 3.84-4.14 inch (97.5-105.1 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 1.16-1.46 inch (29.5-37.1 mm). The airfoil element includes at least two of a first mode with a frequency of 326±10% Hz, a second mode with a frequency of 1252±10% Hz, a third mode with a frequency of 2475±10% Hz, a fourth mode with a frequency of 2951±10% Hz, a fifth mode with a frequency of 4356±10% Hz and a sixth mode with a frequency of 6086±10% Hz.Type: GrantFiled: January 12, 2018Date of Patent: September 1, 2020Assignee: Raytheon Technologies CorporationInventors: William R. Edwards, Stephen W. Milks, Steven J. Feigleson, Mark A. Stephens, Joseph C. Straccia
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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: 10683761Abstract: 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 2.13-2.43 inch (54.2-61.8 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 3.56-3.86 inch (90.3-97.9 mm). The airfoil element includes at least one of a first mode with a frequency of 1049±10% Hz and a second mode with a frequency of 1271±10% Hz.Type: GrantFiled: January 15, 2018Date of Patent: June 16, 2020Assignee: Raytheon Technologies CorporationInventors: William R. Edwards, Stephen W. Milks, Steven J. Feigleson, Mark A. Stephens, Joseph C. Straccia
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Patent number: 10590783Abstract: A stator assembly of a gas turbine engine according to an example of the present disclosure includes, among other things, a first shroud extending about an assembly axis to bound a flow path. The first shroud defines a first shroud opening. An airfoil has an airfoil body extending from a first end portion. The first end portion is received in the first shroud opening and defines a pair of airfoil openings. A retention clip has an intermediate portion connecting a first leg portion and a second leg portion. The intermediate portion is compressible to position the first and second leg portions in the pair of airfoil openings such that the retention clip limits movement of the airfoil relative to the first shroud.Type: GrantFiled: May 26, 2017Date of Patent: March 17, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Brian Barainca, Dennis R. Tremblay, Steven J. Feigleson
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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: 10494936Abstract: A stator assembly having: an inner air seal carrier having a mounting body; a plurality of guide vanes secured to the mounting body via a plurality of fasteners; and a fastener retention mechanism secured to the mounting body via the plurality of fasteners. The fastener retention mechanism having: a housing defining an inner chamber; and a filler located within the inner chamber. The portions of the plurality of fasteners are encapsulated within the filler.Type: GrantFiled: May 23, 2016Date of Patent: December 3, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: David Biolsi, Kevin C. Eckland, Steven J. Feigleson, Thomas Freeman
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Patent number: 10465541Abstract: A method of assembling gas turbine engine front architecture includes positioning a first shroud and a first shroud portion radially relative to one another. Multiple vanes are arranged circumferentially between the first shroud and the first shroud portion. A second shroud portion is secured to the first shroud portion about the vanes. The first and second shroud portions provide a second shroud. The vanes are mechanically isolated from the first and second shrouds.Type: GrantFiled: March 12, 2014Date of Patent: November 5, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: Steven J. Feigleson
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Patent number: 10316749Abstract: Conduits for guiding the motion of an inner diameter shroud of a low pressure compressor of a gas turbine engine are disclosed. The inner diameter shroud has at least three slots formed in one or more radially inwardly extending flanges. Each of the conduits are configured to assemble with a respective one of the at least three slots. Each conduit comprises a bushing having a first panel, and the first panel is capable of being inserted in a respective one of the slots of the inner diameter shroud. The conduit further comprises a bracket capable of being attached to a bearing support of a fan intermediate case of the gas turbine engine. The bushing is capable of being attached to the bracket.Type: GrantFiled: September 16, 2015Date of Patent: June 11, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Daniel S. Rogers, Stephen W. Milks, Steven J. Feigleson
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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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Patent number: 10167737Abstract: A turbofan engine structural guide vane is mounted to a forward bulkhead of a core engine case structure at an inner end and to a fan case at an outer end. A plurality of shear pins extend from the aft portion of the structural guide vane into a corresponding plurality of openings defined in the bulkhead for bearing circumferential loads.Type: GrantFiled: March 12, 2013Date of Patent: January 1, 2019Assignee: United Technologies CorporationInventors: Gregory E. Reinhardt, Paul Thomas Rembish, Steven L. Conner, Thomas B. Hyatt, Steven J. Feigleson, Carl Brian Klinetob
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Publication number: 20180340432Abstract: A stator assembly of a gas turbine engine according to an example of the present disclosure includes, among other things, a first shroud extending about an assembly axis to bound a flow path. The first shroud defines a first shroud opening. An airfoil has an airfoil body extending from a first end portion. The first end portion is received in the first shroud opening and defines a pair of airfoil openings. A retention clip has an intermediate portion connecting a first leg portion and a second leg portion. The intermediate portion is compressible to position the first and second leg portions in the pair of airfoil openings such that the retention clip limits movement of the airfoil relative to the first shroud.Type: ApplicationFiled: May 26, 2017Publication date: November 29, 2018Inventors: Brian Barainca, Dennis R. Tremblay, Steven J. Feigleson