Patents by Inventor Bruce L. Morin
Bruce L. Morin 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: 20230296114Abstract: An aircraft system includes, among other things, an aircraft and a gas turbine engine coupled to the aircraft. The gas turbine engine includes a propulsor section including a propulsor, a compressor section, a turbine section including a first turbine and a second turbine, and a gear reduction between the propulsor and the second turbine. The second turbine includes a number of turbine blades in each of a plurality of rows of the second turbine. The second turbine blades operating at least some of the time at a rotational speed. The number of blades and the rotational speed being such that the following formula holds true for a majority of the blade rows of the second turbine: 5500 Hz?(number of blades×speed)/60 sec?10000 Hz. The gas turbine engine is rated to produce 15,000 pounds of thrust or more.Type: ApplicationFiled: May 25, 2023Publication date: September 21, 2023Inventors: Bruce L. Morin, Detlef Korte
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Patent number: 11719161Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a propulsor section, a geared architecture, a high spool and a low spool. The high spool includes a high pressure compressor and a high pressure turbine. The low spool includes a low pressure compressor and a low pressure turbine. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to 1.55. A mechanical tip rotational Mach number of the blades is greater than or equal to 0.5 at an approach speed.Type: GrantFiled: September 29, 2021Date of Patent: August 8, 2023Assignees: RAYTHEON TECHNOLOGIES CORPORATION, MTU AERO ENGINES AGInventors: Bruce L. Morin, David A. Topol, Detlef Korte
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Patent number: 11560849Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a propulsor section including a propulsor, a turbine section including a first turbine and a second turbine, a compressor section driven by the turbine section, the compressor section including a first compressor and a second compressor, and a geared architecture driven by the first turbine. The propulsor is driven by the first turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to 1.55. A mechanical tip rotational Mach number of the blades is configured to be greater than or equal to 0.5 at an approach speed.Type: GrantFiled: October 18, 2021Date of Patent: January 24, 2023Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Bruce L. Morin, David A. Topol, Detlef Korte
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Patent number: 11512631Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean.Type: GrantFiled: August 11, 2021Date of Patent: November 29, 2022Assignee: Raytheon Technologies CorporationInventors: Jonathan Gilson, Bruce L. Morin, Ramons A. Reba, David A. Topol, Wesley K. Lord
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Patent number: 11480106Abstract: An acoustic liner for a gas turbine engine includes an acoustic panel that is curved about a central axis. The acoustic panel includes a support backing, a face sheet, and a cellular structure disposed between the support backing and the face sheet. The face sheet has elongated slots that extend along respective slot centerlines in the plane of the face sheet. The slot centerlines are sloped at oblique angles to the central axis.Type: GrantFiled: May 14, 2019Date of Patent: October 25, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Bruce L. Morin, Anthony R. Bifulco
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Publication number: 20220220899Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a propulsor section including a propulsor, a turbine section including a first turbine and a second turbine, a compressor section driven by the turbine section, the compressor section including a first compressor and a second compressor, and a geared architecture driven by the first turbine. The propulsor is driven by the first turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to 1.55. A mechanical tip rotational Mach number of the blades is configured to be greater than or equal to 0.5 at an approach speed.Type: ApplicationFiled: October 18, 2021Publication date: July 14, 2022Inventors: Bruce L. Morin, David A. Topol, Detlef Korte
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Patent number: 11346282Abstract: A section for a gas turbine engine includes a rotating structure, a stationary structure, and a flow guide assembly arranged generally between the rotating structure and the stationary structure. A flow path is defined between the flow guide assembly and one of the rotating structure and the stationary structure. The flow guide assembly includes a plurality of apertures configured to disrupt acoustic waves of air in the flow path. A seal is configured to establish a sealing relationship between the rotating structure and the stationary structure, and wherein an inlet to the flow path is adjacent the seal. A gas turbine engine and a method of disrupting acoustic waves in a flow path of a gas turbine engine are also disclosed.Type: GrantFiled: January 18, 2019Date of Patent: May 31, 2022Assignee: Raytheon Technologies CorporationInventors: Ramons A. Reba, Bruce L. Morin, Daniel L. Gysling, Carson A. Roy Thill, Jose R. Paulino, JinQuan Xu, Stephen A. Morford
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Publication number: 20220010732Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a propulsor section, a geared architecture, a high spool and a low spool. The high spool includes a high pressure compressor and a high pressure turbine. The low spool includes a low pressure compressor and a low pressure turbine. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to 1.55. A mechanical tip rotational Mach number of the blades is greater than or equal to 0.5 at an approach speed.Type: ApplicationFiled: September 29, 2021Publication date: January 13, 2022Inventors: Bruce L. Morin, David A. Topol, Detlef Korte
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Publication number: 20210372323Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean.Type: ApplicationFiled: August 11, 2021Publication date: December 2, 2021Inventors: Jonathan Gilson, Bruce L. Morin, Ramons A. Reba, David A. Topol, Wesley K. Lord
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Patent number: 11168614Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a turbine section including a fan drive turbine, a compressor section driven by the turbine section, a geared architecture driven by the fan drive turbine, and a fan driven by the fan drive turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to about 1.55. A mechanical tip rotational Mach number of the blades is configured to be greater than or equal to about 0.5 at an approach speed.Type: GrantFiled: March 30, 2020Date of Patent: November 9, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Bruce L. Morin, David A. Topol, Detlef Korte
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Patent number: 11143109Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a turbine section including a fan drive turbine, a geared architecture driven by the fan drive turbine, and a fan driven by the fan drive turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to about 1.55. A mechanical tip rotational Mach number of the blades is configured to be greater than or equal to about 0.5 at an approach speed.Type: GrantFiled: January 13, 2020Date of Patent: October 12, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Bruce L. Morin, David A. Topol, Detlef Korte
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Patent number: 11118507Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean.Type: GrantFiled: May 6, 2020Date of Patent: September 14, 2021Assignee: Raytheon Technologies CorporationInventors: Jonathan Gilson, Bruce L. Morin, Ramons A. Reba, David A. Topol, Wesley K. Lord
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Publication number: 20210158792Abstract: A face skin for an acoustic panel may comprise a sheet defining a first surface and a second surface. A plurality of slots may be formed through the face skin using abrasive blasting. Each slot of the plurality of slots may comprise a first semi-circular wall and a second semi-circular wall opposite the first semi-circular wall.Type: ApplicationFiled: November 21, 2019Publication date: May 27, 2021Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Brian Kenneth Holland, Bruce L. Morin, Michael Joseph Murphy, Steven H. Zysman
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Publication number: 20200400075Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a turbine section including a fan drive turbine, a compressor section driven by the turbine section, a geared architecture driven by the fan drive turbine, and a fan driven by the fan drive turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to about 1.55. A mechanical tip rotational Mach number of the blades is configured to be greater than or equal to about 0.5 at an approach speed.Type: ApplicationFiled: March 30, 2020Publication date: December 24, 2020Inventors: Bruce L. Morin, David A. Topol, Detlef Korte
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Publication number: 20200386154Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean.Type: ApplicationFiled: May 6, 2020Publication date: December 10, 2020Inventors: Jonathan Gilson, Bruce L. Morin, Ramons A. Reba, David A. Topol, Wesley K. Lord
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Publication number: 20200347785Abstract: An acoustic liner for a gas turbine engine includes an acoustic panel that is curved about a central axis. The acoustic panel includes a support backing, a face sheet, and a cellular structure disposed between the support backing and the face sheet. The face sheet has elongated slots that extend along respective slot centerlines in the plane of the face sheet. The slot centerlines are sloped at oblique angles to the central axis.Type: ApplicationFiled: May 14, 2019Publication date: November 5, 2020Inventors: Bruce L. Morin, Anthony R. Bifulco
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Publication number: 20200291859Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a turbine section including a fan drive turbine, a geared architecture driven by the fan drive turbine, and a fan driven by the fan drive turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to about 1.55. A mechanical tip rotational Mach number of the blades is configured to be greater than or equal to about 0.5 at an approach speed.Type: ApplicationFiled: January 13, 2020Publication date: September 17, 2020Applicant: MTU Aero Engines GmbHInventors: Bruce L. Morin, David A. Topol, Detlef Korte
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Publication number: 20200284270Abstract: A method of designing a gas turbine engine comprises the steps of including a fan section with a fan. A turbine section is included having a first turbine and a high pressure turbine. A gear reduction is included between the fan and the first turbine, the gear reduction being configured to receive an input from the first turbine and to turn the fan at a lower speed than the first turbine in operation. The first turbine is designed to include a number of turbine blades in each of a plurality of rows of the first turbine, the first turbine blades operating at least some of the time at a rotational speed, and the number of blades and the rotational speed being such that the following formula holds true for at least one of the blade rows of the first turbine: (number of blades×speed)/60?5500.Type: ApplicationFiled: April 15, 2020Publication date: September 10, 2020Inventors: Bruce L. Morin, Detlef Korte
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Publication number: 20200232390Abstract: A section for a gas turbine engine includes a rotating structure, a stationary structure, and a flow guide assembly arranged generally between the rotating structure and the stationary structure. A flow path is defined between the flow guide assembly and one of the rotating structure and the stationary structure. The flow guide assembly includes a plurality of apertures configured to disrupt acoustic waves of air in the flow path. A seal is configured to establish a sealing relationship between the rotating structure and the stationary structure, and wherein an inlet to the flow path is adjacent the seal. A gas turbine engine and a method of disrupting acoustic waves in a flow path of a gas turbine engine are also disclosed.Type: ApplicationFiled: January 18, 2019Publication date: July 23, 2020Inventors: Ramons A. Reba, Bruce L. Morin, Daniel L. Gysling, Carson A. Roy Thill, Jose R. Paulino, JinQuan Xu, Stephen A. Morford
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Patent number: 10704415Abstract: In accordance with one aspect of the disclosure, a gas turbine engine, method of using and designing such is disclosed. The gas turbine engine may comprise a fan including a plurality of blades, and a variable area fan nozzle. The fan may be configured to have a design point fan tip leading edge relative flow angle ?ADP, and may be further configured to have an off-design point fan tip leading edge relative flow angle ? at an off-design fan operating point. The variable area fan nozzle may be configured to manipulate the amount of air flowing through the fan so that the absolute value of a difference between the design point fan tip leading edge relative flow angle ?ADP and the off-design point fan tip leading edge relative flow angle ? is in a specified range.Type: GrantFiled: March 11, 2014Date of Patent: July 7, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Bruce L. Morin, Wesley K. Lord