Patents by Inventor Michael M. Joly
Michael M. Joly 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).
-
Patent number: 12385399Abstract: A gas turbine engine is provided and includes a first fan blade including a suction surface, a second fan blade comprising a pressure surface and neighboring the first fan blade and a throat region interposed between the suction surface of the first fan blade and the pressure surface of the second fan blade. The throat region includes a passage throat located at a minimum distance between the pressure and suction surfaces. The first and second fan blades are configured such that a pre-compression region is defined in the throat region ahead of the passage throat. Each of the first and second fan blades includes a mean camber line defining a flattened suction surface.Type: GrantFiled: August 8, 2023Date of Patent: August 12, 2025Assignee: RTX CORPORATIONInventors: Byron R. Monzon, Bronwyn Power, Michael M. Joly, Jason H. Elliott, Xuetao Li, Christopher Beaudry Miller
-
Patent number: 12366167Abstract: A gas turbine engine is provided and includes a first fan blade including a suction surface, a second fan blade comprising a pressure surface and neighboring the first fan blade and a throat region interposed between the suction surface of the first fan blade and the pressure surface of the second fan blade. The throat region includes a passage throat located at a minimum distance between the pressure and suction surfaces. The first and second fan blades are configured such that a pre-compression region is defined in the throat region ahead of the passage throat. Each of the first and second fan blades includes a mean camber line defining a flattened suction surface.Type: GrantFiled: August 18, 2023Date of Patent: July 22, 2025Assignee: RTX CORPORATIONInventors: Byron R. Monzon, Bronwyn Power, Michael M. Joly, Jason H. Elliott, Xuetao Li, Christopher Beaudry Miller
-
Patent number: 12247529Abstract: An airfoil for a gas turbine engine including an airfoil body extending between a leading edge and a trailing edge and between a pressure side and a suction side. The airfoil body includes a strut portion extending from the leading edge and a flap portion extending from the trailing edge. The flap portion is pivotable relative to the strut portion. A flexible skin surrounds both the strut portion and the flap portion on both the pressure side and the suction side.Type: GrantFiled: February 23, 2023Date of Patent: March 11, 2025Assignee: RTX CorporationInventors: Michael M. Joly, Zaffir A. Chaudhry, Andrzej Ernest Kuczek, Om P. Sharma, Georgi Kalitzin, Simon W. Evans
-
Patent number: 12044240Abstract: A compressor includes a housing, a first compression stage defined within the housing, a second compression stage defined within the housing, and a motor disposed between the first compression stage and the second compression stage relative to a flow of fluid through the compressor. The first compression component of the first compression stage has a mixed-flow configuration and the second compression component of the second compression stage has a radial-flow configuration.Type: GrantFiled: May 15, 2020Date of Patent: July 23, 2024Assignee: CARRIER CORPORATIONInventors: Vishnu Sishtla, William T. Cousins, Michael M. Joly
-
Patent number: 11965514Abstract: A refrigerant compressor assembly (20A, 20B, 20C) includes an axial compressor (22B, 22C, 22) that includes at least one axial stage. A downstream compressor (24) is located fluidly downstream of the axial compressor (22B, 22C, 22) and includes one of a mixed-flow impeller (46) or a centrifugal impeller (96). At least one motor (26, 27) is in driving engagement with at least one of the axial compressor (22B, 22C, 22) and the downstream compressor (24).Type: GrantFiled: July 20, 2020Date of Patent: April 23, 2024Assignee: Carrier CorporationInventors: Michael M. Joly, Chaitanya Vishwajit Halbe, Vishnu M. Sishtla, William T. Cousins
-
Publication number: 20240052747Abstract: A gas turbine engine is provided and includes a first fan blade including a suction surface, a second fan blade comprising a pressure surface and neighboring the first fan blade and a throat region interposed between the suction surface of the first fan blade and the pressure surface of the second fan blade. The throat region includes a passage throat located at a minimum distance between the pressure and suction surfaces. The first and second fan blades are configured such that a pre-compression region is defined in the throat region ahead of the passage throat. Each of the first and second fan blades includes a mean camber line defining a flattened suction surface.Type: ApplicationFiled: August 18, 2023Publication date: February 15, 2024Inventors: Byron R. Monzon, Bronwyn Power, Michael M. Joly, Jason H. Elliott, Xuetao Li, Christopher Beaudry Miller
-
Publication number: 20240052746Abstract: A gas turbine engine is provided and includes a first fan blade including a suction surface, a second fan blade comprising a pressure surface and neighboring the first fan blade and a throat region interposed between the suction surface of the first fan blade and the pressure surface of the second fan blade. The throat region includes a passage throat located at a minimum distance between the pressure and suction surfaces. The first and second fan blades are configured such that a pre-compression region is defined in the throat region ahead of the passage throat. Each of the first and second fan blades includes a mean camber line defining a flattened suction surface.Type: ApplicationFiled: August 8, 2023Publication date: February 15, 2024Inventors: Byron R. Monzon, Bronwyn Power, Michael M. Joly, Jason H. Elliott, Xuetao Li, Christopher Beaudry Miller
-
Patent number: 11873730Abstract: An apparatus is provided for a gas turbine engine. This engine apparatus includes an airfoil extending spanwise along a span line from a base to a tip. The airfoil extends laterally between a pressure side and a suction side. The airfoil extends longitudinally along a camber line from a leading edge to a trailing edge. The airfoil includes a first section and a second section arranged longitudinally between the first section and the trailing edge along the camber line. An angle between the camber line and a reference plane changes according to a slope as the airfoil extends longitudinally along the camber line. The slope in the second section is greater than the slope in the first section.Type: GrantFiled: November 28, 2022Date of Patent: January 16, 2024Assignee: RTX CORPORATIONInventors: Michael M. Joly, Gorazd Medic
-
Publication number: 20230193855Abstract: An airfoil for a gas turbine engine including an airfoil body extending between a leading edge and a trailing edge and between a pressure side and a suction side. The airfoil body includes a strut portion extending from the leading edge and a flap portion extending from the trailing edge. The flap portion is pivotable relative to the strut portion. A flexible skin surrounds both the strut portion and the flap portion on both the pressure side and the suction side.Type: ApplicationFiled: February 23, 2023Publication date: June 22, 2023Inventors: Michael M. Joly, Zaffir A. Chaudhry, Andrzej Ernest Kuczek, Om P. Sharma, Georgi Kalitzin, Simon W. Evans
-
Patent number: 11655778Abstract: A gas turbine engine includes a fan section, a compressor section, and a turbine section. The fan section has a plurality of vane assemblies spaced circumferentially about an engine axis. The vane assemblies each include an airfoil extending between a leading edge and a trailing edge, a control rod extending through the airfoil, and a mechanism driven by the control rod to change the shape of the airfoil. A vane system for a gas turbine engine is also disclosed.Type: GrantFiled: August 6, 2021Date of Patent: May 23, 2023Assignee: Raytheon Technologies CorporationInventors: Michael M. Joly, Zaffir A. Chaudhry, Andrzej Ernest Kuczek, Om P. Sharma, Georgi Kalitzin, Simon W. Evans
-
Patent number: 11592034Abstract: A mixed-flow compressor includes an impeller attached to a shaft and rotatable about a shaft axis. A vaneless diffuser is located axially downstream of the impeller and has a converging portion and a diverging portion. A vaned diffuser is located axially downstream of the vaneless diffuser.Type: GrantFiled: June 16, 2020Date of Patent: February 28, 2023Assignee: CARRIER CORPORATIONInventors: Chaitanya Vishwajit Halbe, Michael M. Joly, William T. Cousins, Vishnu M. Sishtla
-
Patent number: 11585347Abstract: A centrifugal compressor includes a casing. An impeller is arranged within the casing. The impeller is rotatable about an axis. A diffuser section is arranged within the casing. The diffuser section is positioned axially downstream from an outlet of the impeller and includes a forward portion fixed relative to the impeller and an aft portion distinct from the forward portion.Type: GrantFiled: May 15, 2020Date of Patent: February 21, 2023Assignee: Carrier CorporationInventors: Michael M. Joly, Vishnu M. Sishtla
-
Publication number: 20230044195Abstract: A gas turbine engine includes a fan section, a compressor section, and a turbine section. The fan section has a plurality of vane assemblies spaced circumferentially about an engine axis. The vane assemblies each include an airfoil extending between a leading edge and a trailing edge, a control rod extending through the airfoil, and a mechanism driven by the control rod to change the shape of the airfoil. A vane system for a gas turbine engine is also disclosed.Type: ApplicationFiled: August 6, 2021Publication date: February 9, 2023Inventors: Michael M. Joly, Zaffir A. Chaudhry, Andrzej Ernest Kuczek, Om P. Sharma, Georgi Kalitzin, Simon W. Evans
-
Publication number: 20220374570Abstract: An iterative optimization component of a computer aided design system includes an optimization module having at least one of at least one solver configured to determine at least one value corresponding to a set of parameters defining a sample point and an algorithmic analysis configured to determine the at least one value corresponding to the set of parameters defining the sample point. The optimization module further includes at least one of a surrogate assisted optimization process and an algorithmic optimization process. The at least one of the surrogate assisted optimization process and the algorithmic optimization process determine at least one optimum point in a design space using an initial set of sample points and output the optimum point as at least one additional sample point.Type: ApplicationFiled: May 21, 2021Publication date: November 24, 2022Inventor: Michael M. Joly
-
Patent number: 11499569Abstract: A compressor includes a housing. An impeller is located within the housing and rotatable about an impeller axis in a first rotational direction. A rotor section is rotatable about the impeller axis in a second rotational direction opposite the first rotational direction.Type: GrantFiled: June 16, 2020Date of Patent: November 15, 2022Inventors: Michael M. Joly, Chaitanya Vishwajit Halbe, William T. Cousins, Vishnu M. Sishtla
-
Patent number: 11421708Abstract: An impeller mountable within a centrifugal compressor includes a hub having a front side and a back side, the hub being rotatable about an axis of rotation and a plurality of vanes extending outwardly from the front side of the hub such that a plurality of passages is defined between adjacent vanes. The plurality of vanes is oriented such that a flow output from the plurality of passages adjacent the back side of the impeller is arranged at an angle to the axis of rotation of less than 20 degrees.Type: GrantFiled: January 9, 2019Date of Patent: August 23, 2022Assignee: CARRIER CORPORATIONInventors: William T. Cousins, Vishnu M. Sishtla, Michael M. Joly
-
Publication number: 20220228593Abstract: A refrigerant compressor assembly (20A, 20B, 20C) includes an axial compressor (22B, 22C, 22) that includes at least one axial stage. A downstream compressor (24) is located fluidly downstream of the axial compressor (22B, 22C, 22) and includes one of a mixed-flow impeller (46) or a centrifugal impeller (96). At least one motor (26, 27) is in driving engagement with at least one of the axial compressor (22B, 22C, 22) and the downstream compressor (24).Type: ApplicationFiled: July 20, 2020Publication date: July 21, 2022Inventors: Michael M. Joly, Chaitanya Vishwajit Halbe, Vishnu M. Sishtla, William T. Cousins
-
Publication number: 20220186746Abstract: A compressor including a casing and an impeller arranged within the casing. The impeller is rotatable about an axis. A diffuser section is arranged within the casing. The diffuser section is positioned downstream from an outlet of the impeller and includes a first set of vanes disposed circumferentially about the diffuser section and a second set of vanes disposed circumferentially about the diffuser section. At least one vane in the second set of vanes includes an aspiration slot.Type: ApplicationFiled: July 20, 2020Publication date: June 16, 2022Inventors: Michael M. Joly, Chaitanya Vishwajit Halbe, Vishnu M. Sishtla
-
Patent number: 11346366Abstract: A centrifugal compressor includes a shaft defining an axis, an impeller mounted to the shaft for rotation about the axis, and a diffuser section including a first wall, a second wall, and an opening defined between the first wall and the second wall. The opening of the diffuser section is arranged in fluid communication with the impeller. The first wall is rotatable about the axis and rotation of the first wall about the axis is mechanically driven.Type: GrantFiled: January 31, 2020Date of Patent: May 31, 2022Assignee: CARRIER CORPORATIONInventors: Michael M. Joly, Xiaodan Cai, Chaitanya V. Halbe, William T. Cousins, Vishnu M. Sishtla
-
Publication number: 20220065256Abstract: A compressor includes a housing, a first compression stage defined within the housing, a second compression stage defined within the housing, and a motor disposed between the first compression stage and the second compression stage relative to a flow of fluid through the compressor. The first compression component of the first compression stage has a mixed-flow configuration and the second compression component of the second compression stage has a radial-flow configuration.Type: ApplicationFiled: May 15, 2020Publication date: March 3, 2022Inventors: Vishnu Sishtla, William T. Cousins, Michael M. Joly