Patents by Inventor J. Place
J. Place 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: 12006836Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes an airfoil section extending in a radial direction from a root section to a tip portion. The airfoil section has an external wall and an internal wall. The airfoil section establishes an internal cooling arrangement including a first cooling passage having a first section and a tip flag section. The tip flag section extends in the chordwise direction along the tip portion from the first section. The first section includes a plurality of branched paths established by at least one turning vane.Type: GrantFiled: July 1, 2022Date of Patent: June 11, 2024Assignee: RTX CORPORATIONInventors: Dominic J. Mongillo, Emma J. Place, Christopher J. Peters, Jeffrey J. DeGray, Timothy J. Jennings, Raymond Surace, Jeremy B. Fredette
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Patent number: 12002561Abstract: A peristaltic pump, and related system method are provided. The peristaltic pump includes a cam shaft, first and second pinch-valve cams, first and second pinch-valve cam followers, a plunger cam, a plunger-cam follower, a tube receiver, and a spring-biased plunger. The first and second pinch-valve cams are coupled to the cam shaft. The first and second pinch-valve cam followers each engage the first and second pinch-valve cams, respectively. The plunger cam is coupled to the cam shaft. The plunger-cam follower engages the plunger cam. The tube receiver is configured to receive a tube. The spring-biased plunger is coupled to the plunger-cam follower such that the expansion of the plunger cam along a radial angle intersecting the plunger-cam follower as the cam shaft rotates pushes the plunger cam follower towards the plunger and thereby disengages the spring-biased plunger from the tube. A spring coupled to the spring-biased plunger biases the spring-biased plunger to apply the crushing force to the tube.Type: GrantFiled: March 30, 2022Date of Patent: June 4, 2024Assignee: DEKA Research & Development CorpInventors: Dean Kamen, John M. Kerwin, Colin H. Murphy, Larry B. Gray, Christopher C. Langenfeld, Michael J. Slate, Michael S. Place
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Publication number: 20240115804Abstract: A pump for pumping fluid includes a tube platen, a plunger, a bias member, inlet and outlet valves, an actuator mechanism, a position sensor, and a processor. The plunger is configured for actuation toward and away from the infusion-tube when the tube platen is disposed opposite to the plunger. The tube platen can hold an intravenous infusion tube. The bias member is configured to urge the plunger toward the tube platen.Type: ApplicationFiled: October 10, 2023Publication date: April 11, 2024Inventors: Dean KAMEN, John M. Kerwin, Colin H. Murphy, Jonathan Parker, Daniel F. Pawlowski, Dirk A. Van Der Merwe, Larry B. Gray, Christopher C. Langenfeld, Michael S Place, Michael J. Slate
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Patent number: 11913353Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes a platform section and an airfoil section extending in a spanwise direction from the platform section to a tip portion establishing a tip. The airfoil section has an external wall defining pressure and suction sides extending in a chordwise direction between a leading edge and a trailing edge, and the pressure and suction sides are spaced apart in a thickness direction between the leading edge and the trailing edge. The tip portion includes a tip pocket and a tip shelf extending inwardly from the tip. The tip pocket and tip shelf are on opposite sides of a shelf wall.Type: GrantFiled: August 5, 2022Date of Patent: February 27, 2024Assignee: RTX CORPORATIONInventors: Emma J. Place, Dominic J. Mongillo, Jeremy B. Fredette
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Patent number: 11898459Abstract: Disclosed is a turbine blade for a gas turbine engine having a plurality of cooling holes defined therein, the plurality of cooling holes being located in an airfoil of the turbine blade according to coordinates of Table 1, wherein the coordinates of Table 1 are distances from a point of origin O on the turbine blade, the point of origin being located at a center point of an inner diameter edge of a forward root face of a root of the turbine blade.Type: GrantFiled: July 1, 2022Date of Patent: February 13, 2024Assignee: RTX CORPORATIONInventors: Emma J. Place, Dominic J. Mongillo, Jr., Jeremy B Fredette
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Patent number: 11773726Abstract: A core is provided for fabricating a blade to include an airfoil. The airfoil includes pressure and suction surfaces, leading and trailing edges extending along the pressure and suction surfaces and a tip shelf with a first sweep configuration and a wall. The core includes channel sections configured to form internal channels within the airfoil by casting processes and tip rods extending from respective portions of the channel sections proximate to a tip shelf location. The respective portions of the channel sections have a second sweep configuration corresponding to the first sweep configuration. The tip rods are configured to extend through the wall at an angle of about 5-12 degrees inclusive relative to a normal angle of the wall during the casting processes to form through-holes angled at about 5-12 degrees inclusive in the wall.Type: GrantFiled: October 11, 2021Date of Patent: October 3, 2023Assignee: RTX CORPORATIONInventors: Emma J. Place, Carlos Calixtro
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Patent number: 11773731Abstract: A damper seal for a gas turbine engine includes a damper body extending in a first direction between a leading edge portion and a trailing edge portion, extending in a second direction between first and second sidewalls, and extending in a third direction between a convex outer damper face and a concave inner damper face. The inner damper face establishes a damper pocket. The leading and trailing edge portions slope inwardly from opposite ends of the damper body to bound the damper pocket in the first direction. The first and second sidewalls extend from the leading edge portion to the trailing edge portion and slope inwardly from opposite sides of the damper body to bound the damper pocket in the second direction. The outer damper face is pre-formed according to a first predetermined geometry that substantially corresponds to a second predetermined geometry of a platform undersurface bounding a neck pocket of an airfoil. A method of damping for a gas turbine engine is also disclosed.Type: GrantFiled: January 4, 2022Date of Patent: October 3, 2023Assignee: RTX CORPORATIONInventors: Emma J. Place, Jeffrey Michael Jacques, Anthony C. Evans, Joshua W. Richards
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Publication number: 20230250725Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes an airfoil section extending in a radial direction from a root section to a tip portion. The airfoil section has an external wall and an internal wall. The airfoil section establishes an internal cooling arrangement including a first cooling passage having a first section and a tip flag section. The tip flag section extends in the chordwise direction along the tip portion from the first section. The first section includes a plurality of branched paths established by at least one turning vane.Type: ApplicationFiled: July 1, 2022Publication date: August 10, 2023Inventors: Dominic J. Mongillo, Emma J. Place, Christopher J. Peters, Jeffrey J. DeGray, Timothy J. Jennings, Raymond Surace, Jeremy B. Fredette
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Publication number: 20230212950Abstract: A damper seal for a gas turbine engine includes a damper body extending in a first direction between a leading edge portion and a trailing edge portion, extending in a second direction between first and second sidewalls, and extending in a third direction between a convex outer damper face and a concave inner damper face. The inner damper face establishes a damper pocket. The leading and trailing edge portions slope inwardly from opposite ends of the damper body to bound the damper pocket in the first direction. The first and second sidewalls extend from the leading edge portion to the trailing edge portion and slope inwardly from opposite sides of the damper body to bound the damper pocket in the second direction. The outer damper face is pre-formed according to a first predetermined geometry that substantially corresponds to a second predetermined geometry of a platform undersurface bounding a neck pocket of an airfoil. A method of damping for a gas turbine engine is also disclosed.Type: ApplicationFiled: January 4, 2022Publication date: July 6, 2023Inventors: Emma J. Place, Jeffrey Michael Jacques, Anthony C. Evans, Joshua W. Richards
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Patent number: 11603304Abstract: A beverage pod for a beverage machine is provided. The beverage pod can include a container having an internal space and a container flange defining an opening to the internal space, a plug sealing the opening of the container, and a cap secured to the container flange. A beverage medium can be located within the internal space of the container. The cap can be operable to selectively engage a portion of the plug to release the beverage medium through the plug and the cap.Type: GrantFiled: March 22, 2019Date of Patent: March 14, 2023Assignee: Bedford Systems LLCInventors: Ian Scott Rice, Catherine Fox, Daniel J. Place, Enrico Raffaele Cafaro
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Publication number: 20230045259Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes a platform section and an airfoil section extending in a spanwise direction from the platform section to a tip portion establishing a tip. The airfoil section has an external wall defining pressure and suction sides extending in a chordwise direction between a leading edge and a trailing edge, and the pressure and suction sides are spaced apart in a thickness direction between the leading edge and the trailing edge. The tip portion includes a tip pocket and a tip shelf extending inwardly from the tip. The tip pocket and tip shelf are on opposite sides of a shelf wall.Type: ApplicationFiled: August 5, 2022Publication date: February 9, 2023Inventors: Emma J. Place, Dominic J. Mongillo, Jeremy B. Fredette
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Patent number: 11434768Abstract: An airfoil core includes a first core portion that has a hybrid skin core, a tip flag core, and a trailing edge core. A second core portion has a serpentine core and a leading edge core.Type: GrantFiled: May 17, 2021Date of Patent: September 6, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Christopher J. Peters, Emma J. Place, Jeffrey J. DeGray, Dominic J. Mongillo, Timothy J. Jennings, Raymond Surace, Jeremy B. Fredette
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Publication number: 20220025769Abstract: A core is provided for fabricating a blade to include an airfoil. The airfoil includes pressure and suction surfaces, leading and trailing edges extending along the pressure and suction surfaces and a tip shelf with a first sweep configuration and a wall. The core includes channel sections configured to form internal channels within the airfoil by casting processes and tip rods extending from respective portions of the channel sections proximate to a tip shelf location. The respective portions of the channel sections have a second sweep configuration corresponding to the first sweep configuration. The tip rods are configured to extend through the wall at an angle of about 5-12 degrees inclusive relative to a normal angle of the wall during the casting processes to form through-holes angled at about 5-12 degrees inclusive in the wall.Type: ApplicationFiled: October 11, 2021Publication date: January 27, 2022Inventors: Emma J. Place, Carlos Calixtro
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Patent number: 11143035Abstract: A core is provided for fabricating a blade to include an airfoil. The airfoil includes pressure and suction surfaces, leading and trailing edges extending along the pressure and suction surfaces and a tip shelf with a first sweep configuration and a wall. The core includes channel sections configured to form internal channels within the airfoil by casting processes and tip rods extending from respective portions of the channel sections proximate to a tip shelf location. The respective portions of the channel sections have a second sweep configuration corresponding to the first sweep configuration. The tip rods are configured to extend through the wall at an angle of about 5-12 degrees inclusive relative to a normal angle of the wall during the casting processes to form through-holes angled at about 5-12 degrees inclusive in the wall.Type: GrantFiled: October 16, 2019Date of Patent: October 12, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Emma J. Place, Carlos Calixtro
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Publication number: 20210277785Abstract: An airfoil core includes a first core portion that has a hybrid skin core, a tip flag core, and a trailing edge core. A second core portion has a serpentine core and a leading edge core.Type: ApplicationFiled: May 17, 2021Publication date: September 9, 2021Inventors: Christopher J. Peters, Emma J. Place, Jeffrey J. DeGray, Dominic J. Mongillo, Timothy J. Jennings, Raymond Surace, Jeremy B. Fredette
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Patent number: 11053803Abstract: Methods for forming airfoil, cores for forming airfoil, and airfoils for gas turbine engines are described. The methods include forming an airfoil body about a core assembly, the core assembly comprising at least one core structure having a radially extending purge slot protrusion extending from a portion of the at least one core structure, removing the core assembly from the airfoil body to form one or more internal cavities, wherein at least one internal cavity has a cavity extension define by the purge slot protrusion, and forming a squealer pocket in a tip of the formed airfoil body, wherein a cavity purge slot is formed at the cavity extension to fluidly connect the respect internal cavity with the squealer pocket. The radially extending protrusion has a radial height that is equal to or less than five times a width thereof.Type: GrantFiled: October 4, 2019Date of Patent: July 6, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Emma J. Place, Jeremy B. Fredette, Timothy J. Jennings
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Patent number: 11041395Abstract: Methods for forming airfoils, core assemblies, and airfoils for gas turbine engines are described. The methods include forming an airfoil body about a core assembly configured to define one or more internal cavities of the airfoil body, the core assembly comprising at least core structure having a purge slot protrusion extending from a portion of the core structure, removing the core assembly from the airfoil body to form one or more internal cavities, wherein at least one internal cavity has a cavity extension define by the purge slot protrusion, and forming a squealer pocket in a tip of the formed airfoil body, wherein a cavity purge slot is formed at the cavity extension to fluidly connect the respect internal cavity with the squealer pocket.Type: GrantFiled: June 26, 2019Date of Patent: June 22, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Tracy A. Propheter-Hinckley, Emma J. Place, Timothy J. Jennings, Jeremy B. Fredette
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Patent number: 11028703Abstract: An airfoil including a pressure sidewall and a suction sidewall extending from a root section of the airfoil to a tip region of the airfoil and a leading edge and a trailing edge defines a chord length of the airfoil therebetween. A tip shelf is formed along the tip region of the airfoil between the pressure sidewall and a tip shelf wall with a tip shelf discourager that extends from the tip shelf.Type: GrantFiled: June 7, 2018Date of Patent: June 8, 2021Assignee: Raytheon Technologies CorporationInventor: Emma J. Place
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Patent number: 11015457Abstract: A method of forming an airfoil, includes forming a hybrid skin core, a tip flag core, and a trailing edge core. The hybrid skin core, tip flag core, and trailing edge core are connected to form a first core portion. A leading edge core and a serpentine core are formed. The first core portion, the leading edge core, and the serpentine core are assembled together to form an airfoil core. An airfoil is formed around the airfoil core.Type: GrantFiled: November 28, 2018Date of Patent: May 25, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Christopher J. Peters, Emma J. Place, Jeffrey J. DeGray, Dominic J. Mongillo, Timothy J. Jennings, Raymond Surace, Jeremy B. Fredette
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Publication number: 20210115799Abstract: A core is provided for fabricating a blade to include an airfoil. The airfoil includes pressure and suction surfaces, leading and trailing edges extending along the pressure and suction surfaces and a tip shelf with a first sweep configuration and a wall. The core includes channel sections configured to form internal channels within the airfoil by casting processes and tip rods extending from respective portions of the channel sections proximate to a tip shelf location. The respective portions of the channel sections have a second sweep configuration corresponding to the first sweep configuration. The tip rods are configured to extend through the wall at an angle of about 5-12 degrees inclusive relative to a normal angle of the wall during the casting processes to form through-holes angled at about 5-12 degrees inclusive in the wall.Type: ApplicationFiled: October 16, 2019Publication date: April 22, 2021Inventors: Emma J. Place, Carlos Calixtro