Patents by Inventor Robert E. Malecki
Robert E. Malecki 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: 11970974Abstract: A gas turbine engine and engine mount structure includes a core engine including a compressor section, a combustor section and a turbine section mounted within a core engine housing. The fan, the compressor section and the turbine section rotate about an axis of rotation. An outer nacelle surrounds the fan, and is spaced from the core engine housing to define a bypass duct. The fan delivers air into the bypass duct and into the core engine housing. The nacelle is formed with camber so as to be curved in a first plane away from the axis of rotation in a first lateral direction. An engine mount structure extends from the nacelle at an angle that is non-parallel and non-perpendicular to the first plane, and has a component in a lateral direction that is opposed to the first lateral direction. An aircraft is also disclosed.Type: GrantFiled: January 7, 2022Date of Patent: April 30, 2024Assignee: RTX CorporationInventors: Robert E. Malecki, Andrew Hahn, Marc J. Muldoon, Jesse M. Chandler, Joseph B. Staubach
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Patent number: 11781505Abstract: A gas turbine engine assembly includes, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan, a nacelle including an inlet portion forward of the fan, a length of the inlet portion having a dimension L, and a dimensional relationship of L/D between 0.30 and 0.40.Type: GrantFiled: March 11, 2021Date of Patent: October 10, 2023Assignee: RTX CORPORATIONInventors: Wesley K. Lord, Robert E. Malecki, Yuan J. Qiu, Becky E. Rose, Jonathan Gilson
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Patent number: 11781447Abstract: A gas turbine engine assembly may include, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a geared architecture, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan through the geared architecture, a nacelle surrounding the fan, the nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L between the first reference plane and the second reference plane. A dimensional relationship of L/D may be between 0.30 and 0.40.Type: GrantFiled: September 23, 2021Date of Patent: October 10, 2023Assignee: RTX CORPORATIONInventors: Wesley K. Lord, Robert E. Malecki, Yuan J. Qiu, Becky E. Rose, Jonathan Gilson
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Patent number: 11391216Abstract: A propulsion system includes a fan, a gear, a turbine configured to drive the gear to, in turn, drive the fan. The turbine has an exit point, and a diameter (Dt) is defined at the exit point. A nacelle surrounds a core engine housing. The fan is configured to deliver air into a bypass duct defined between the nacelle and the core engine housing. A core engine exhaust nozzle is provided downstream of the exit point. A downstream most point of the core engine exhaust nozzle is defined at a distance from the exit point. A ratio of the distance to the diameter is greater than or equal to about 0.90.Type: GrantFiled: May 9, 2019Date of Patent: July 19, 2022Assignee: Raytheon Technologies CorporationInventors: Frederick M. Schwarz, Robert E. Malecki
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Publication number: 20220136440Abstract: A gas turbine engine and engine mount structure includes a core engine including a compressor section, a combustor section and a turbine section mounted within a core engine housing. The fan, the compressor section and the turbine section rotate about an axis of rotation. An outer nacelle surrounds the fan, and is spaced from the core engine housing to define a bypass duct. The fan delivers air into the bypass duct and into the core engine housing. The nacelle is formed with camber so as to be curved in a first plane away from the axis of rotation in a first lateral direction. An engine mount structure extends from the nacelle at an angle that is non-parallel and non-perpendicular to the first plane, and has a component in a lateral direction that is opposed to the first lateral direction. An aircraft is also disclosed.Type: ApplicationFiled: October 30, 2020Publication date: May 5, 2022Inventors: Robert E. Malecki, Andrew Hahn, Marc J. Muldoon, Jesse M. Chandler, Joseph B. Staubach
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Publication number: 20220136441Abstract: A gas turbine engine and engine mount structure includes a core engine including a compressor section, a combustor section and a turbine section mounted within a core engine housing. The fan, the compressor section and the turbine section rotate about an axis of rotation. An outer nacelle surrounds the fan, and is spaced from the core engine housing to define a bypass duct. The fan delivers air into the bypass duct and into the core engine housing. The nacelle is formed with camber so as to be curved in a first plane away from the axis of rotation in a first lateral direction. An engine mount structure extends from the nacelle at an angle that is non-parallel and non-perpendicular to the first plane, and has a component in a lateral direction that is opposed to the first lateral direction. An aircraft is also disclosed.Type: ApplicationFiled: January 7, 2022Publication date: May 5, 2022Inventors: Robert E. Malecki, Andrew Hahn, Marc J. Muldoon, Jesse M. Chandler, Joseph B. Staubach
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Patent number: 11286811Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a geared architecture, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan through the geared architecture, a nacelle surrounding the fan, the nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L measured along an engine axis between the first reference plane and the second reference plane. A dimensional relationship of L/D is between 0.20 and 0.40.Type: GrantFiled: April 23, 2019Date of Patent: March 29, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Wesley K. Lord, Robert E. Malecki, Yuan J. Qiu, Becky E. Rose, Jonathan Gilson
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Patent number: 11236701Abstract: A nacelle for a gas turbine engine includes a ring shaped body defining a center axis and having a radially outward surface and a radially inward surface. An aft portion of the radially inward surface includes an axially extending convergent-divergent exit nozzle. An axially extending secondary duct passes through the nacelle in the convergent-divergent exit nozzle. The axially extending secondary duct includes an inlet at a convergent portion of the convergent-divergent exit nozzle and an outlet at a divergent portion of the convergent-divergent exit nozzle.Type: GrantFiled: July 10, 2018Date of Patent: February 1, 2022Assignee: Raytheon Technologies CorporationInventors: Dmitriy B. Sidelkovskiy, Oleg Petrenko, Robert E. Malecki, Steven H. Zysman
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Publication number: 20220010689Abstract: A gas turbine engine assembly may include, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a geared architecture, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan through the geared architecture, a nacelle surrounding the fan, the nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L between the first reference plane and the second reference plane. A dimensional relationship of L/D may be between 0.30 and 0.40.Type: ApplicationFiled: September 23, 2021Publication date: January 13, 2022Inventors: Wesley K. Lord, Robert E. Malecki, Yuan J. Qiu, Becky E. Rose, Jonathan Gilson
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Publication number: 20210285403Abstract: A gas turbine engine assembly includes, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan, a nacelle including an inlet portion forward of the fan, a length of the inlet portion having a dimension L, and a dimensional relationship of L/D between 0.30 and 0.40.Type: ApplicationFiled: March 11, 2021Publication date: September 16, 2021Inventors: Wesley K. Lord, Robert E. Malecki, Yuan J. Qiu, Becky E. Rose, Jonathan Gilson
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Patent number: 11015550Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan, a nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L measured along an engine axis between the first reference plane and the second reference plane. A dimensional relationship of L/D is no more than 0.45.Type: GrantFiled: February 2, 2018Date of Patent: May 25, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Wesley K. Lord, Robert E. Malecki, Yuan J. Qiu, Becky E. Rose, Jonathan Gilson
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Patent number: 10724541Abstract: A fan assembly for a gas turbine engine includes a fan including a plurality of fan blades. Each fan blade extends radially outwardly from a fan hub to a blade tip. The plurality of blade tips define a fan diameter. A nacelle surrounds the fan and defines a fan inlet upstream of the fan, relative to an airflow direction into the fan. The nacelle has a forwardmost edge defining an inlet length from the forwardmost edge to a leading edge of a fan blade of the plurality of fan blades. A ratio of inlet length to fan diameter is between 0.20 and 0.45. A nacelle inner surface defines a nacelle flowpath. The nacelle flowpath has a convex throat portion and a concave diffusion portion between the throat portion and the leading edge of the fan blade at a bottommost portion of the nacelle.Type: GrantFiled: December 14, 2016Date of Patent: July 28, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Yuan J. Qiu, Robert E. Malecki, Wesley K. Lord
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Publication number: 20200063603Abstract: A gas turbine engine assembly includes a fan. A diameter of the fan has a dimension D. The fan has a pressure ratio of greater than 1.20 and less than 1.45. A leading edge on an inlet portion of a nacelle is within a first reference plane oriented at an oblique angle. A forward most portion on the fan blade leading edges is in a second reference plane. A length of the inlet portion has a dimension L different at a plurality of locations on the inlet portion. A geared architecture has a gear reduction ratio of greater than 2.3, a bypass ratio is greater than 10, and a low pressure turbine includes a pressure ratio greater than 5:1. A dimensional relationship of UD is between 0.25 and 0.45. The leading edge on the inlet portion is further from the second reference plane near the top of the assembly.Type: ApplicationFiled: October 21, 2019Publication date: February 27, 2020Inventors: Wesley K. Lord, Robert E. Malecki, Yuan J. Qiu, Becky E. Rose, Jonathan Gilson
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Publication number: 20200025036Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a geared architecture, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan through the geared architecture, a nacelle surrounding the fan, the nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L measured along an engine axis between the first reference plane and the second reference plane. A dimensional relationship of L/D is between 0.20 and 0.40.Type: ApplicationFiled: April 23, 2019Publication date: January 23, 2020Inventors: Wesley K. Lord, Robert E. Malecki, Yuan J. Qiu, Becky E. Rose, Jonathan Gilson
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Patent number: 10479519Abstract: A fan assembly for a gas turbine engine includes a fan including a plurality of fan blades extending radially outwardly from a fan hub to a blade tip defining a fan diameter. A nacelle surrounds the fan and defines a fan inlet upstream of the fan, relative to an airflow direction into the fan. The nacelle has a forwardmost edge defining an inlet length from the forwardmost edge to a leading edge of a fan blade. A ratio of inlet length to fan diameter is between 0.20 and 0.45. A nacelle inner surface defines a nacelle flowpath having a convex throat portion and a diffusion portion between the throat portion and the leading edge of the fan blade at a topmost portion of the nacelle. The throat portion has a minimum throat radius measured from a fan central axis greater than a blade tip radius.Type: GrantFiled: December 14, 2016Date of Patent: November 19, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Yuan J. Qiu, Steven H. Zysman, Robert E. Malecki, Wesley K. Lord
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Patent number: 10450898Abstract: The present disclosure relates generally to an aerodynamic track fairing assembly used on an engine nacelle, the track fairing assembly positionable on the aft section of the engine nacelle, the aerodynamic track fairing assembly including: an upper section extending toward an aft end of the aft section of the engine nacelle; a bottom section extending toward the aft end of the aft section of the engine nacelle, the bottom section affixed to the upper section to form a track cavity therebetween; and a fairing fitting disposed within the track cavity and affixed to the bottom section.Type: GrantFiled: February 13, 2015Date of Patent: October 22, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Dmitriy B. Sidelkovskiy, Steven H. Zysman, Robert E. Malecki
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Patent number: 10436121Abstract: A propulsion system includes a fan, a gear, a turbine configured to drive the gear to, in turn, drive the fan. The turbine has an exit point, and a diameter (Dt) is defined at the exit point. A nacelle surrounds a core engine housing. The fan is configured to deliver air into a bypass duct defined between the nacelle and the core engine housing. A core engine exhaust nozzle is provided downstream of the exit point. A downstream most point of the core engine exhaust nozzle is defined at a distance from the exit point. A ratio of the distance to the diameter is greater than or equal to about 0.90.Type: GrantFiled: September 27, 2013Date of Patent: October 8, 2019Assignee: United Technologies CorporationInventors: Frederick M. Schwarz, Robert E. Malecki
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Patent number: 10436120Abstract: A propulsion system includes a fan, a gear, a turbine configured to drive the gear to, in turn, drive the fan. The turbine has an exit point, and a diameter (Dt) is defined at the exit point. A nacelle surrounds a core engine housing. The fan is configured to deliver air into a bypass duct defined between the nacelle and the core engine housing. A core engine exhaust nozzle is provided downstream of the exit point. A downstream most point of the core engine exhaust nozzle is defined at a distance from the exit point. A ratio of the distance to the diameter is greater than or equal to about 0.90.Type: GrantFiled: March 11, 2013Date of Patent: October 8, 2019Assignee: United Technologies CorporationInventors: Frederick M. Schwarz, Robert E. Malecki
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Publication number: 20190271269Abstract: A propulsion system includes a fan, a gear, a turbine configured to drive the gear to, in turn, drive the fan. The turbine has an exit point, and a diameter (Dt) is defined at the exit point. A nacelle surrounds a core engine housing. The fan is configured to deliver air into a bypass duct defined between the nacelle and the core engine housing. A core engine exhaust nozzle is provided downstream of the exit point. A downstream most point of the core engine exhaust nozzle is defined at a distance from the exit point. A ratio of the distance to the diameter is greater than or equal to about 0.90.Type: ApplicationFiled: May 9, 2019Publication date: September 5, 2019Inventors: Frederick M. Schwarz, Robert E. Malecki
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Patent number: 10371092Abstract: A nacelle for a gas turbine engine includes a ring shaped body defining a center axis and having a radially outward surface and a radially inward surface. An aft portion of the radially inward surface includes an axially extending convergent-divergent exit nozzle. An axially extending secondary duct passes through the nacelle in the convergent-divergent exit nozzle. The axially extending secondary duct includes an inlet at a convergent portion of the convergent-divergent exit nozzle and an outlet at a divergent portion of the convergent-divergent exit nozzle.Type: GrantFiled: August 4, 2015Date of Patent: August 6, 2019Assignee: United Technologies CorporationInventors: Dmitriy B. Sidelkovskiy, Oleg Petrenko, Robert E. Malecki, Steven H. Zysman