Patents by Inventor Kate Hudon
Kate Hudon 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: 11867195Abstract: A gas turbine engine includes a combustor section arranged between a compressor section and a turbine section. The compressor section includes at least a low pressure compressor and a high pressure compressor. The high pressure compressor is arranged upstream of the combustor section. A fan section is included. The low pressure compressor is downstream from the fan section. An airfoil is arranged in the low pressure compressor and includes pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoil has an axial stacking offset at a 10% span position that is positive and greater than or equal to an axial stacking offset at the 100% span position. The axial stacking offsets measured relative to an aftward direction.Type: GrantFiled: April 18, 2022Date of Patent: January 9, 2024Assignee: RTX CorporationInventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
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Patent number: 11767856Abstract: An airfoil for a gas turbine engine includes a pressure side and a suction side that extends in a radially outward direction from a 0% span position to a 100% span position. The airfoil has a stagger angle defined as an angle between an airfoil chord and a tangential plane normal to an engine longitudinal axis. The airfoil has a relationship between stagger angle and span position that defines a curve with the stagger angle greater than 35° from 0% span to at least 50% span. The stagger angle at 100% span is greater than the stagger angle at 50% span.Type: GrantFiled: December 15, 2021Date of Patent: September 26, 2023Assignee: RTX CorporationInventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
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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: 11408436Abstract: A gas turbine engine includes a combustor section arranged between a compressor section and a turbine section. The compressor section includes at least a low pressure compressor and a high pressure compressor. The high pressure compressor is arranged upstream of the combustor section. A fan section has an array of twenty-six or fewer fan blades. The low pressure compressor is downstream from the fan section. An airfoil is arranged in the low pressure compressor and includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between an axial stacking offset and span position that includes a curve with a negative slope from 90% span to 100% span. The negative slope leans forward relative to an engine axis.Type: GrantFiled: January 16, 2020Date of Patent: August 9, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
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Publication number: 20220235792Abstract: A gas turbine engine includes a combustor section arranged between a compressor section and a turbine section. The compressor section includes at least a low pressure compressor and a high pressure compressor. The high pressure compressor is arranged upstream of the combustor section. A fan section is included. The low pressure compressor is downstream from the fan section. An airfoil is arranged in the low pressure compressor and includes pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoil has an axial stacking offset at a 10% span position that is positive and greater than or equal to an axial stacking offset at the 100% span position. The axial stacking offsets measured relative to an aftward direction.Type: ApplicationFiled: April 18, 2022Publication date: July 28, 2022Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
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Patent number: 11391294Abstract: A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a tangential stacking offset and span position that defines a curve that is non-linear.Type: GrantFiled: December 20, 2019Date of Patent: July 19, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
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Publication number: 20220106965Abstract: An airfoil for a gas turbine engine includes a pressure side and a suction side that extends in a radially outward direction from a 0% span position to a 100% span position. The airfoil has a stagger angle defined as an angle between an airfoil chord and a tangential plane normal to an engine longitudinal axis. The airfoil has a relationship between stagger angle and span position that defines a curve with the stagger angle greater than 35° from 0% span to at least 50% span. The stagger angle at 100% span is greater than the stagger angle at 50% span.Type: ApplicationFiled: December 15, 2021Publication date: April 7, 2022Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
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Patent number: 11236616Abstract: 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 4.47-4.77 inch (113.5-121.2 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 2.57-2.87 inch (65.3-72.9 mm). The airfoil element includes at least two of a first mode with a frequency of 297±10% Hz, a second mode with a frequency of 1035±10% Hz, a third mode with a frequency of 1488±10% Hz, a fourth mode with a frequency of 1524±10% Hz, a fifth mode with a frequency of 2855±10% Hz and a sixth mode with a frequency of 4462±10% Hz.Type: GrantFiled: January 11, 2018Date of Patent: February 1, 2022Assignee: Raytheon Technologies CorporationInventors: Kurt R. Heinemann, Sumin Tao, Christopher B. Jelks, Xuedong Zhou, Mark David Ring, Konstantinos Panagiotis Giannakopoulos, Kate Hudon, John Joseph Papalia
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Patent number: 11209013Abstract: A gas turbine engine includes a combustor section arranged between a compressor section and a turbine section. The compressor section includes at least a low pressure compressor and a high pressure compressor. The high pressure compressor is arranged upstream of the combustor section. A fan section has an array of twenty-six or fewer fan blades. The low pressure compressor is downstream from the fan section. An airfoil is provided in the compressor section outside the high pressure compressor section and includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a stagger angle and span position that defines a curve with the stagger angle greater than 35° from 0% span to at least 50% span. The stagger angle has a positive slope from 20% span to 100% span.Type: GrantFiled: January 14, 2020Date of Patent: December 28, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
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Patent number: 11193496Abstract: A gas turbine engine includes a combustor section arranged between a compressor section and a turbine section. The compressor section includes at least a low pressure compressor and a high pressure compressor. The high pressure compressor is arranged upstream of the combustor section. A fan section has an array of twenty-six or fewer fan blades. The low pressure compressor is downstream from the fan section. An airfoil is arranged in the low pressure compressor and includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber angle and span position that defines a curve with a decreasing camber angle within the range of 80% span to 100% span. The camber angle is less than 20° within the entire range of 40% span to 100% span.Type: GrantFiled: January 13, 2020Date of Patent: December 7, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
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Patent number: 11193497Abstract: A gas turbine engine includes a combustor section arranged between a compressor section and a turbine section. A fan section has an array of twenty-six or fewer fan blades. An airfoil includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge angle and span position that defines a curve with the leading edge angle of less than 40° at 100% span.Type: GrantFiled: February 11, 2020Date of Patent: December 7, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
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Patent number: 11041507Abstract: A compressor airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between leading edge sweep angle and span position defined by a curve in which the leading edge sweep angle is positive at 0% span and crosses to a negative leading edge sweep angle at a span position less than 80% span. A negative sweep angle is in the forward direction. A positive sweep angle is in the rearward direction. The airfoil has a relationship between trailing edge sweep angle and span position defined by a curve in which the trailing edge sweep angle is negative at 0% span and changes less than 10° from 0% span to 90% span.Type: GrantFiled: October 2, 2019Date of Patent: June 22, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
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Patent number: 10914315Abstract: A gas turbine engine includes a combustor section, a compressor section, and a turbine section. A high pressure compressor is arranged upstream of the combustor section. A fan section has an array of twenty-six or fewer fan blades. A low pressure compressor is counter-rotating relative to the fan blades and downstream from the fan section. The airfoil outside of the compressor section is rotatable relative to an engine static structure. The airfoil includes pressure and suction sides extending from a 0% span position to a 100% span position. A relationship between a leading edge angle and span position that defines a curve with at least one of a decreasingly negative slope or a positive slope from 80% span to 100% span. The leading edge angle is defined by a tangential plane normal to an engine axis and a line tangent to a camber mean line at the leading edge.Type: GrantFiled: November 12, 2019Date of Patent: February 9, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Edward J. Gallagher, Lisa I Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
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Patent number: 10890195Abstract: A compressor airfoil of a turbine engine that has a geared architecture includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a trailing edge angle and span position that defines a curve with a non-negative slope from 0% span to 20% span corresponding to a non-decreasing trailing edge angle.Type: GrantFiled: October 29, 2019Date of Patent: January 12, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
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Patent number: 10844727Abstract: 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 3.68-3.98 inch (93.5-101.1 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 1.75-2.05 inch (44.5-52.1 mm). The airfoil element includes at least two of a first mode with a frequency of 436±10% Hz, a second mode with a frequency of 1557±10% Hz, a third mode with a frequency of 1424±10% Hz, a fourth mode with a frequency of 1870±10% Hz, a fifth mode with a frequency of 3321±10% Hz and a sixth mode with a frequency of 3957±10% Hz.Type: GrantFiled: January 11, 2018Date of Patent: November 24, 2020Assignee: Raytheon Technologies CorporationInventors: Kurt R. Heinemann, Sumin Tao, Christopher B. Jelks, Xuedong Zhou, Mark David Ring, Konstantinos Panagiotis Giannakopoulos, Kate Hudon, John Joseph Papalia
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Patent number: 10815785Abstract: 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 2.99-3.29 inch (75.9-83.6 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 1.44-1.74 inch (36.6-44.2 mm). The airfoil element includes at least two of a first mode with a frequency of 430±10% Hz, a second mode with a frequency of 1459±10% Hz, a third mode with a frequency of 2036±10% Hz, a fourth mode with a frequency of 3615±10% Hz, a fifth mode with a frequency of 4722±10% Hz and a sixth mode with a frequency of 5591±10% Hz.Type: GrantFiled: January 12, 2018Date of Patent: October 27, 2020Assignee: Raytheon Technologies CorporationInventors: Kurt R. Heinemann, Sumin Tao, Christopher B. Jelks, Xuedong Zhou, Mark David Ring, Konstantinos Panagiotis Giannakopoulos, Kate Hudon, John Joseph Papalia
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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: 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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Publication number: 20200291955Abstract: A gas turbine engine includes a combustor section arranged between a compressor section and a turbine section. The compressor section includes at least a low pressure compressor and a high pressure compressor. The high pressure compressor is arranged upstream of the combustor section. A fan section has an array of twenty-six or fewer fan blades. The low pressure compressor is downstream from the fan section. An airfoil is arranged in the low pressure compressor and includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between an axial stacking offset and span position that includes a curve with a negative slope from 90% span to 100% span. The negative slope leans forward relative to an engine axis.Type: ApplicationFiled: January 16, 2020Publication date: September 17, 2020Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon