Patents by Inventor Sean Nolan
Sean Nolan 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: 20230375228Abstract: The disclosed technology includes a tankless liquid heater system for detecting buildup on a heating element, including: a chamber; at least one heating element to heat liquid in the chamber; at least one sensor to detect data associated with identifying buildup on the at least one heating element; and at least one device to: receive the data detected by the at least one sensor; determine, based on the data, an amount of the buildup on the at least one heating element; and adjust an operation of the at least one heating element based on the amount of the buildup on the at least one heating element.Type: ApplicationFiled: May 22, 2023Publication date: November 23, 2023Applicant: Rheem Manufacturing CompanyInventors: Christopher Mark Hayden, Harsha Satyanarayana, Sean Nolan, Divakar Mantha, Eric Jurczyszak, Sergiu Mihu
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Patent number: 11773866Abstract: A compressor section for a gas turbine engine includes a blade including a platform, a tip and an airfoil extending between the platform and tip. The airfoil includes a root portion adjacent to the platform, a midspan portion and a tip portion. Each of the root portion, midspan portion and tip portion define a meridional velocity at stage exit with the tip portion including a first meridional velocity greater than a second meridional velocity of the midspan portion. A blade for an axial compressor of a gas turbine engine and a method of operating a compressor section of a gas turbine engine are also disclosed.Type: GrantFiled: February 1, 2022Date of Patent: October 3, 2023Assignee: RTX CORPORATIONInventors: Simon W. Evans, Yuan Dong, Sean Nolan
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Patent number: 11767764Abstract: A turbomachine airfoil element includes an airfoil having 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 0.83-0.93 inch (21.1-23.6 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 0.80-0.90 inch (20.4-22.9 mm). The airfoil element includes at least two of a first mode with a frequency is 3135±10% Hz, a second mode with a frequency is 6634±10% Hz, a third mode with a frequency is 13260±10% Hz, a fourth mode with a frequency is 16838±10% Hz and a fifth mode with a frequency is 17980±10% Hz.Type: GrantFiled: September 24, 2020Date of Patent: September 26, 2023Assignee: RTX CORPORATIONInventors: Haiyun Li, Eliannah Hunderfund, Sean Nolan
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Publication number: 20220154728Abstract: A compressor section for a gas turbine engine includes a blade including a platform, a tip and an airfoil extending between the platform and tip. The airfoil includes a root portion adjacent to the platform, a midspan portion and a tip portion. Each of the root portion, midspan portion and tip portion define a meridional velocity at stage exit with the tip portion including a first meridional velocity greater than a second meridional velocity of the midspan portion. A blade for an axial compressor of a gas turbine engine and a method of operating a compressor section of a gas turbine engine are also disclosed.Type: ApplicationFiled: February 1, 2022Publication date: May 19, 2022Inventors: Simon W. Evans, Yuan Dong, Sean Nolan
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Patent number: 11248622Abstract: A compressor section for a gas turbine engine includes a blade including a platform, a tip and an airfoil extending between the platform and tip. The airfoil includes a root portion adjacent to the platform, a midspan portion and a tip portion. Each of the root portion, midspan portion and tip portion define a meridional velocity at stage exit with the tip portion including a first meridional velocity greater than a second meridional velocity of the midspan portion. A blade for an axial compressor of a gas turbine engine and a method of operating a compressor section of a gas turbine engine are also disclosed.Type: GrantFiled: September 2, 2016Date of Patent: February 15, 2022Assignee: Raytheon Technologies CorporationInventors: Simon W. Evans, Yuan Dong, Sean Nolan
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Patent number: 11231050Abstract: A turbomachine airfoil element includes an airfoil having 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 0.60-0.70 inch (15.3-17.8 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 0.90-1.00 inch (22.9-25.5 mm). The airfoil element includes at least two of a first mode with a frequency of 5327±10% Hz, a second mode with a frequency of 8393±10% Hz, a third mode with a frequency of 16289±10% Hz, a fourth mode with a frequency of 25049±10% Hz and a fifth mode with a frequency of 27423±10% Hz.Type: GrantFiled: January 12, 2018Date of Patent: January 25, 2022Assignee: Raytheon Technologies CorporationInventors: Haiyun Li, Eliannah Hunderfund, Sean Nolan, Joseph Steele, Marian A. Iskandar
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Patent number: 10865809Abstract: A turbomachine airfoil element includes an airfoil having 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 0.70-0.85 inch (17.8-20.3 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 0.85-0.95 inch (21.5-24.0 mm). The airfoil element includes at least two of a first mode with a frequency of 4508±10% Hz, a second mode with a frequency of 7466±10% Hz, a third mode with a frequency of 16104±10% Hz, a fourth mode with a frequency of 18397±10% Hz and a fifth mode with a frequency of 20855±10% Hz.Type: GrantFiled: January 12, 2018Date of Patent: December 15, 2020Assignee: Raytheon Technologies CorporationInventors: Haiyun Li, Eliannah Hunderfund, Sean Nolan
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Patent number: 10781695Abstract: 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 0.55-0.65 inch (14.0-16.5 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 0.76-0.86 inch (19.3-21.8 mm). The airfoil element includes at least two of a first mode with a frequency of 3335±10% Hz, a second mode with a frequency of 5715±10% Hz and a third mode with a frequency of 41797±10% Hz.Type: GrantFiled: January 12, 2018Date of Patent: September 22, 2020Assignee: Raytheon Technologies CorporationInventors: Charles H. Warner, William R. Edwards, Matthew R. Willett, Sean Nolan, Ernest D. Casparie
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Patent number: 10718223Abstract: 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 1.13-1.23 inch (28.7-31.2 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 0.64-0.74 inch (16.3-18.8 mm). The airfoil element includes at least two of a first mode with a frequency of 1634±10% Hz, a second mode with a frequency of 5611±10% Hz, a third mode with a frequency of 19027±10% Hz, a fourth mode with a frequency of 29268±10% Hz, a fifth mode with a frequency of 33103±10% Hz, a sixth mode with a frequency of 34908±10% Hz and a seventh mode with a frequency of 41277±10% Hz.Type: GrantFiled: January 11, 2018Date of Patent: July 21, 2020Assignee: Raytheon Technologies CorporationInventors: Charles H. Warner, William R. Edwards, Mark David Ring, Sean Nolan, Ernest D. Casparie
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Patent number: 10697304Abstract: 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 1.03-1.13 inch (26.2-28.7 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 0.93-1.03 inch (23.6-26.2 mm). The airfoil element includes at least two of a first mode with a frequency of 2182±10% Hz, a second mode with a frequency of 4966±10% Hz, a third mode with a frequency of 9675±10% Hz, a fourth mode with a frequency of 13154±10% Hz and a fifth mode with a frequency of 14056±10% Hz.Type: GrantFiled: January 12, 2018Date of Patent: June 30, 2020Assignee: Raytheon Technologies CorporationInventors: Haiyun Li, Eliannah Hunderfund, Sean Nolan
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Patent number: 10677266Abstract: 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 0.63-0.73 inch (16.0-18.5 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 0.61-0.71 inch (15.5-18.0 mm). The airfoil element includes at least two of a first mode with a frequency of 4852±10% Hz, a second mode with a frequency of 11917±10% Hz, a third mode with a frequency of 30842±10% Hz and a fourth mode with a frequency of 35225±10% Hz.Type: GrantFiled: January 12, 2018Date of Patent: June 9, 2020Assignee: Raytheon Technologies CorporationInventors: Charles H. Warner, William R. Edwards, Mark David Ring, Sean Nolan, Ernest D. Casparie
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Patent number: 10669856Abstract: 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 0.75-0.85 inch (19.1-21.6 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 0.56-0.66 inch (14.2-16.8 mm). The airfoil element includes at least two of a first mode with a frequency of 2740±10% Hz, a second mode with a frequency of 5956±10% Hz, a third mode with a frequency of 6554±10% Hz and a fourth mode with a frequency of 31959±10% Hz.Type: GrantFiled: January 12, 2018Date of Patent: June 2, 2020Assignee: Raytheon Technologies CorporationInventors: Charles H. Warner, William R. Edwards, Mark David Ring, Sean Nolan, Ernest D. Casparie
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Patent number: 10605260Abstract: Rotor of a gas turbine engines having a rotor hub and a plurality of blades extending from the rotor hub, wherein each blade has a full-span forward sweep along a leading edge of the blade that starts at an airfoil root of the blade at the hub and extends to a blade tip, wherein a sweep of a blade is a percentage of a root axial chord length of the respective blade.Type: GrantFiled: September 9, 2016Date of Patent: March 31, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Li Xing Pan, Yuan Dong, Simon W. Evans, Robert W. Fessenden, Sue-Li Kingsley Chuang, Sean Nolan
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Patent number: 10572670Abstract: Current security tools in the marketplace fall into different categories: Security Enforcement Tools which identify and block malicious activity, and Security Vulnerability Testing Tools which scan and identify security threats within an organisation. The disclosure describes Silently (invisible to the user) but as if it is the user, within the User's Context, Executing applications to test whether third party security products and security settings exhibit the correct behaviour. The application can continuously perform a test(s) and expects a security product to behave in a certain way, records the result of the test(s) and reports those results.Type: GrantFiled: September 12, 2017Date of Patent: February 25, 2020Assignee: INTROSPECTUS PTY LTDInventor: Eugene Sean Nolan
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Publication number: 20190390688Abstract: A compressor may include an airfoil configured to rotate about an axis. The airfoil may have a span measured radially from a root of the airfoil to a tip of the airfoil. A compressor case may be radially adjacent to the airfoil. The airfoil and the compressor case may define a clearance between the tip of the airfoil and a radially inner surface of the compressor case. A ratio of the clearance to the span may be 2.5 percent or less. A mass flow rate of the compressor may be 3.0 pounds-mass per second or less.Type: ApplicationFiled: August 5, 2019Publication date: December 26, 2019Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Robert W. FESSENDEN, Abhir A. ADHATE, Yuan DONG, Sean NOLAN, Li Xing PAN
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Patent number: 10415591Abstract: A compressor may include an airfoil configured to rotate about an axis. The airfoil may have a span measured radially from a root of the airfoil to a tip of the airfoil. A compressor case may be radially adjacent to the airfoil. The airfoil and the compressor case may define a clearance between the tip of the airfoil and a radially inner surface of the compressor case. A ratio of the clearance to the span may be between 1.5 to 2.5 percent.Type: GrantFiled: September 21, 2016Date of Patent: September 17, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Robert W Fessenden, Abhir A Adhate, Yuan Dong, Sean Nolan, Li Xing Pan
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Publication number: 20190080094Abstract: Current security tools in the marketplace fall into different categories: Security Enforcement Tools which identify and block malicious activity, and Security Vulnerability Testing Tools which scan and identify security threats within an organisation. The disclosure describes Silently (invisible to the user) but as if it is the user, within the User's Context, Executing applications to test whether third party security products and security settings exhibit the correct behaviour. The application can continuously perform a test(s) and expects a security product to behave in a certain way, records the result of the test(s) and reports those results.Type: ApplicationFiled: September 12, 2017Publication date: March 14, 2019Inventor: Eugene Sean Nolan
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Publication number: 20180080472Abstract: A compressor may include an airfoil configured to rotate about an axis. The airfoil may have a span measured radially from a root of the airfoil to a tip of the airfoil. A compressor case may be radially adjacent to the airfoil. The airfoil and the compressor case may define a clearance between the tip of the airfoil and a radially inner surface of the compressor case. A ratio of the clearance to the span may be between 1.5 to 2.5 percent.Type: ApplicationFiled: September 21, 2016Publication date: March 22, 2018Applicant: United Technologies CorporationInventors: Robert W. Fessenden, Abhir A. Adhate, Yuan Dong, Sean Nolan, Li Xing Pan
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Publication number: 20180073517Abstract: Rotor of a gas turbine engines having a rotor hub and a plurality of blades extending from the rotor hub, wherein each blade has a full-span forward sweep along a leading edge of the blade that starts at an airfoil root of the blade at the hub and extends to a blade tip, wherein a sweep of a blade is a percentage of a root axial chord length of the respective blade.Type: ApplicationFiled: September 9, 2016Publication date: March 15, 2018Inventors: Li Xing Pan, Yuan Dong, Simon W. Evans, Robert W. Fessenden, Sue-Li Kingsley Chuang, Sean Nolan
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Publication number: 20180066673Abstract: A compressor section for a gas turbine engine includes a blade including a platform, a tip and an airfoil extending between the platform and tip. The airfoil includes a root portion adjacent to the platform, a midspan portion and a tip portion. Each of the root portion, midspan portion and tip portion define a meridional velocity at stage exit with the tip portion including a first meridional velocity greater than a second meridional velocity of the midspan portion. A blade for an axial compressor of a gas turbine engine and a method of operating a compressor section of a gas turbine engine are also disclosed.Type: ApplicationFiled: September 2, 2016Publication date: March 8, 2018Inventors: Simon W. Evans, Yuan Dong, Sean Nolan