Patents by Inventor Carl S. Richardson
Carl S. Richardson 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: 11767763Abstract: 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 1.01-1.15 inch (25.7-29.3 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 0.54-0.66 inch (13.6-16.8 mm). The airfoil element includes at least two of a first mode with a frequency of 2033 ± 15% Hz, a second mode with a frequency of 7023 ± 15% Hz, a third mode with a frequency of 12082 ± 15% Hz and a fourth mode with a frequency of 19769 ± 15% Hz.Type: GrantFiled: January 12, 2018Date of Patent: September 26, 2023Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Charles H. Warner, Carl S. Richardson, Ling Liu, Robert W. Fessenden
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Patent number: 11230939Abstract: A vane seal system includes a first non-rotatable vane segment that has a first airfoil with a first pocket at one end thereof. A second non-rotatable vane segment includes a second airfoil with a second pocket at one end thereof spaced by a gap from the first pocket. A seal member spans across the gap and extends in the first pocket and the second pocket. The seal member includes a seal element and at least one spring portion configured to positively locate the seal member in a sealing direction. Also disclosed is a seal for a vane seal system and a method related thereto for damping relative movement between a first pocket and a second pocket.Type: GrantFiled: August 10, 2020Date of Patent: January 25, 2022Assignee: Raytheon Technologies CorporationInventors: Mark J. Rogers, Carl S. Richardson, Richard K. Hayford, Kenneth E. Carman, Jonathan J. Earl
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Publication number: 20210108530Abstract: A vane seal system includes a first non-rotatable vane segment that has a first airfoil with a first pocket at one end thereof. A second non-rotatable vane segment includes a second airfoil with a second pocket at one end thereof spaced by a gap from the first pocket. A seal member spans across the gap and extends in the first pocket and the second pocket. The seal member includes a seal element and at least one spring portion configured to positively locate the seal member in a sealing direction. Also disclosed is a seal for a vane seal system and a method related thereto for damping relative movement between a first pocket and a second pocket.Type: ApplicationFiled: August 10, 2020Publication date: April 15, 2021Inventors: Mark J. Rogers, Carl S. Richardson, Richard K. Hayford, Kenneth E. Carman, Jonathan J. Earl
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Patent number: 10808563Abstract: A vane seal system includes a first non-rotatable vane segment that has a first airfoil with a first pocket at one end thereof. A second non-rotatable vane segment includes a second airfoil with a second pocket at one end thereof spaced by a gap from the first pocket. A seal member spans across the gap and extends in the first pocket and the second pocket. The seal member includes a seal element and at least one spring portion configured to positively locate the seal member in a sealing direction. Also disclosed is a seal for a vane seal system and a method related thereto for damping relative movement between a first pocket and a second pocket.Type: GrantFiled: September 9, 2014Date of Patent: October 20, 2020Assignee: Raytheon Technologies CorporationInventors: Mark J. Rogers, Carl S. Richardson, Richard K. Hayford, Kenneth E. Carman, Jonathan J. Earl
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Patent number: 10801330Abstract: A turbomachine airfoil element includes an airfoil that 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 0.46-0.58 inch (11.6-14.7 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 0.66-0.79 inch (16.7-20.0 mm. A first mode has a frequency of 35681±15% Hz and a second mode has a frequency of 39218±15% Hz.Type: GrantFiled: January 12, 2018Date of Patent: October 13, 2020Assignee: Raytheon Technologies CorporationInventors: Charles H. Warner, Carl S. Richardson, Brian J. Schuler, Sue-Li Chuang
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Patent number: 10794191Abstract: 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 0.78-0.91 inch (19.7-23.1 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 0.49-0.62 inch (12.5-15.6 mm). The airfoil element includes at least two of a first mode with a frequency of 3533±15% Hz, a second mode with a frequency of 8291±15% Hz, a third mode with a frequency of 17362±15% Hz and a fourth mode with a frequency of 23365±15% Hz.Type: GrantFiled: January 12, 2018Date of Patent: October 6, 2020Assignee: Raytheon Technologies CorporationInventors: Charles H. Warner, Carl S. Richardson, Jeff M. Carrico, Robert W. Fessenden
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Patent number: 10119410Abstract: A vane seal system includes a non-rotatable vane segment that has an airfoil with a pocket at one end thereof. The pocket spans in an axial direction between forward and trailing sides, with respect to the airfoil, and in a lateral direction between open lateral sides. A seal member extends in the pocket. The seal member includes a seal element and at least one spring portion that is configured to positively locate the seal member in the axial direction in the pocket. A method for positioning the seal member in a vane seal system includes positively locating the seal member in the axial direction in the pocket using the spring portion.Type: GrantFiled: September 23, 2014Date of Patent: November 6, 2018Assignee: United Technologies CorporationInventors: Mark J. Rogers, Carl S. Richardson, Richard K. Hayford, Kenneth E. Carman, Jonathan J. Earl
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Patent number: 10018061Abstract: A vane tip machining fixture assembly includes a first clamp ring mountable to a fixture, the first clamp ring includes a rigid back ring mounted to a resilient ring.Type: GrantFiled: March 11, 2014Date of Patent: July 10, 2018Assignee: United Technologies CorporationInventors: Carl S. Richardson, John A. Szymbor
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Patent number: 9988915Abstract: One exemplary embodiment of this disclosure relates to a stator segment. The stator segment includes a first circumferential end face, and a second circumferential end face. Further, the first and second circumferential end faces are misaligned relative to one another.Type: GrantFiled: March 11, 2014Date of Patent: June 5, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Jonathan J. Earl, Carl S. Richardson
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Patent number: 9896971Abstract: An assembly for a turbine engine includes a stator vane arrangement and an anti-rotation lug that is rotatably connected to a turbine engine case. The stator vane arrangement includes a platform, an airfoil and an anti-rotation slot. The platform extends circumferentially around an axial centerline and is engaged with the case. The airfoil extends radially from the platform and is arranged circumferentially around the centerline. The slot extends radially into the platform, and is mated with the lug. The lug is configured with a substantially equilateral polygonal geometry.Type: GrantFiled: September 28, 2012Date of Patent: February 20, 2018Assignee: United Technologies CorporationInventor: Carl S. Richardson
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Patent number: 9797262Abstract: A vane cluster includes a split damped outer shroud and an inner shroud spaced from the split damped outer shroud with a multiple of stator vane airfoils that extend between the split damped outer shroud and the inner shroud.Type: GrantFiled: May 23, 2014Date of Patent: October 24, 2017Assignee: United Technologies CorporationInventors: Carl S. Richardson, Mark J. Rogers, Jonathan J. Earl, Kenneth E. Carman, Richard K. Hayford
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Publication number: 20160333890Abstract: A gas turbine engine includes a circumferential array of vanes slidably supported in an inner case shroud segment. Multiple segments are secured to one another to provide an annular engine static structure section. The inner case shroud segment and the vanes have different material properties than one another.Type: ApplicationFiled: December 26, 2014Publication date: November 17, 2016Inventors: Richard K. Hayford, Mark J. Rogers, Carl S. Richardson, Jonathan J. Earl
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Publication number: 20160237839Abstract: A vane seal system includes a first non-rotatable vane segment that has a first airfoil with a first pocket at one end thereof. A second non-rotatable vane segment includes a second airfoil with a second pocket at one end thereof spaced by a gap from the first pocket. A seal member spans across the gap and extends in the first pocket and the second pocket. The seal member includes a seal element and at least one spring portion configured to positively locate the seal member in a sealing direction. Also disclosed is a seal for a vane seal system and a method related thereto for damping relative movement between a first pocket and a second pocket.Type: ApplicationFiled: September 9, 2014Publication date: August 18, 2016Inventors: Mark J. Rogers, Carl S. Richardson, Richard K. Hayford, Kenneth E. Carman, Jonathan J. Earl
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Publication number: 20160215637Abstract: A vane seal system includes a non-rotatable vane segment that has an airfoil with a pocket at one end thereof. The pocket spans in an axial direction between forward and trailing sides, with respect to the airfoil, and in a lateral direction between open lateral sides. A seal member extends in the pocket. The seal member includes a seal element and at least one spring portion that is configured to positively locate the seal member in the axial direction in the pocket. A method for positioning the seal member in a vane seal system includes positively locating the seal member in the axial direction in the pocket using the spring portion.Type: ApplicationFiled: September 23, 2014Publication date: July 28, 2016Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Mark J. Rogers, Carl S. Richardson, Richard K. Hayford, Kenneth E. Carman, Jonathan J. Earl
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Publication number: 20160032742Abstract: One exemplary embodiment of this disclosure relates to a stator segment. The stator segment includes a first circumferential end face, and a second circumferential end face. Further, the first and second circumferential end faces are misaligned relative to one another.Type: ApplicationFiled: March 11, 2014Publication date: February 4, 2016Inventors: Jonathan J. EARL, Carl S. RICHARDSON
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Publication number: 20160017735Abstract: A vane tip machining fixture assembly includes a first clamp ring mountable to a fixture, the first clamp ring includes a rigid back ring mounted to a resilient ring.Type: ApplicationFiled: March 11, 2014Publication date: January 21, 2016Inventors: Carl S. Richardson, John A. Szymbor
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Patent number: 9181814Abstract: A gas turbine engine stator segment has a shroud band and a plurality of blade sections. Each of the blade sections has a first section with a first thickness, second section with a second thickness and a fairing section transitioning between the first and second section. The second section thickness is less than the first section thickness.Type: GrantFiled: November 24, 2010Date of Patent: November 10, 2015Assignee: United Technology CorporationInventors: Hope C. Rowley, Paul W. Baumann, Edwin M. Worth, Carl S. Richardson
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Publication number: 20150030443Abstract: A vane cluster includes a split damped outer shroud and an inner shroud spaced from the split damped outer shroud with a multiple of stator vane airfoils that extend between the split damped outer shroud and the inner shroud.Type: ApplicationFiled: May 23, 2014Publication date: January 29, 2015Applicant: United Technologies CorporationInventors: Carl S. Richardson, Mark J. Rogers, Jonathan J. Earl, Kenneth E. Carman, Richard K. Hayford
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Publication number: 20140219791Abstract: An assembly for a turbine engine includes a stator vane arrangement and an anti-rotation lug that is rotatably connected to a turbine engine case. The stator vane arrangement includes a platform, an airfoil and an anti-rotation slot. The platform extends circumferentially around an axial centerline and is engaged with the case. The airfoil extends radially from the platform and is arranged circumferentially around the centerline. The slot extends radially into the platform, and is mated with the lug. The lug is configured with a substantially equilateral polygonal geometry.Type: ApplicationFiled: September 28, 2012Publication date: August 7, 2014Applicant: United Technologies CorporationInventor: Carl S. Richardson
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Publication number: 20120128497Abstract: A gas turbine engine stator segment has a shroud band and a plurality of blade sections. Each of the blade sections has a first section with a first thickness, second section with a second thickness and a fairing section transitioning between the first and second section. The second section thickness is less than the first section thickness.Type: ApplicationFiled: November 24, 2010Publication date: May 24, 2012Inventors: Hope C. Rowley, Paul W. Baumann, Edwin M. Worth, Carl S. Richardson