Patents by Inventor Daniel C. Crites
Daniel C. Crites 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: 11713693Abstract: A turbine vane includes an airfoil that extends from an inner diameter to an outer diameter, and from a leading edge to a trailing edge. The turbine vane includes an inner platform coupled to the airfoil at the inner diameter. The turbine vane includes a cooling system defined in the airfoil including a first conduit in proximity to the leading edge to cool the leading edge and a second conduit to cool the trailing edge. The first conduit has an inlet at the outer diameter to receive a cooling fluid and an outlet portion that is defined at least partially through the inner platform. The first conduit includes a plurality of cooling features that extend from a first surface of the first conduit, and the first surface of the first conduit is opposite the leading edge.Type: GrantFiled: February 22, 2021Date of Patent: August 1, 2023Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Steven Whitaker, Daniel C. Crites, Mark C. Morris, Ardeshir Riahi
-
Patent number: 11448093Abstract: A turbine vane includes an airfoil that extends from an inner diameter to an outer diameter, and from a leading edge to a trailing edge. The turbine vane includes an inner platform coupled to the airfoil at the inner diameter. The turbine vane includes a cooling system defined in the airfoil including a first conduit in proximity to the leading edge to cool the leading edge and a second conduit to cool the trailing edge. The first conduit has an inlet at the outer diameter to receive a cooling fluid and an outlet portion that is defined at least partially through the inner platform. The first conduit includes a plurality of cooling features that extend between a first surface and a second surface of the first conduit, and the first surface of the first conduit is opposite the leading edge.Type: GrantFiled: February 19, 2021Date of Patent: September 20, 2022Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Steven Whitaker, Daniel C. Crites, Mark C. Morris, Ardeshir Riahi
-
Patent number: 11333042Abstract: A turbine blade includes an airfoil that has a tip region that extends from the leading edge toward the trailing edge, and the tip region is bounded by a wall that extends at an angle. The leading edge has a leading edge cooling circuit that is defined from the platform to a tip flag channel, and the leading edge cooling circuit is in fluid communication with the tip flag channel. The pressure side includes at least one tip dust hole defined through the wall proximate the pressure side, and the at least one tip dust hole has an inlet and an outlet. The airfoil has at least one rib defined on the wall that extends at a second angle to direct the particles and a portion of the cooling fluid into the inlet.Type: GrantFiled: August 20, 2020Date of Patent: May 17, 2022Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Daniel C. Crites, Mark C. Morris, Steven Whitaker, David Waldman
-
Patent number: 11286791Abstract: An engine component includes a body having an internal surface and an external surface, the internal surface at least partially defining an internal cooling circuit. The component further includes a plurality of cooling holes formed in the body and extending between the internal cooling circuit and the external surface of the body. The plurality of cooling holes includes a first cooling hole with a metering portion and a diffuser portion extending from the metering portion to the external surface of the body.Type: GrantFiled: September 23, 2020Date of Patent: March 29, 2022Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Daniel C. Crites, Mark C. Morris, David R. Waldman, Ardeshir Riahi
-
Patent number: 11199099Abstract: An airfoil for a rotor blade in a gas turbine engine includes a first side wall and a second side wall joined to the first side wall at a leading edge and a trailing edge. The airfoil further includes a tip cap extending between the first and second side walls such that the tip cap and at least portions of the first and second side walls form a blade tip and an internal cooling system. The internal cooling system includes a leading edge cooling circuit, a central cooling circuit, and a trailing edge cooling circuit. Each of the internal passages within the leading edge cooling circuit, the central cooling circuit, and the trailing edge cooling circuit is bounded in the radial outward direction with a surface that has at least one escape hole or that is positively angled in the radial outward direction relative to a chordwise axis.Type: GrantFiled: March 23, 2020Date of Patent: December 14, 2021Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Daniel C. Crites, Michael Kahrs, Brandan Wakefield, Ardeshir Riahi
-
Publication number: 20210372289Abstract: A turbine nozzle for a gas turbine engine includes a plurality of nozzle segments that are configured to be assembled into a full ring such that each one of the plurality of nozzle segments is adjacent to another one of the plurality of nozzle segments. Each one of the plurality of nozzle segments includes an endwall segment and a nozzle vane. The turbine nozzle includes a feather seal interface defined by endwall segments of adjacent ones of the plurality of nozzle segments. The feather seal interface is defined along an area of reduced pressure drop through a pressure field defined between adjacent nozzle vanes of the plurality of nozzle segments to reduce leakage through the plurality of nozzle segments. The turbine nozzle includes a feather seal received within the feather seal interface that cooperates with the feather seal interface to reduce leakage through the plurality of nozzle segments.Type: ApplicationFiled: August 10, 2021Publication date: December 2, 2021Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Benjamin Dosland Kamrath, Jason Smoke, Daniel C. Crites, Mark C. Morris
-
Patent number: 11156116Abstract: A turbine nozzle for a gas turbine engine includes a plurality of nozzle segments that are configured to be assembled into a full ring such that each one of the plurality of nozzle segments is adjacent to another one of the plurality of nozzle segments. Each one of the plurality of nozzle segments includes an endwall segment and a nozzle vane. The turbine nozzle includes a feather seal interface defined by endwall segments of adjacent ones of the plurality of nozzle segments. The feather seal interface is defined along an area of reduced pressure drop through a pressure field defined between adjacent nozzle vanes of the plurality of nozzle segments to reduce leakage through the plurality of nozzle segments. The turbine nozzle includes a feather seal received within the feather seal interface that cooperates with the feather seal interface to reduce leakage through the plurality of nozzle segments.Type: GrantFiled: April 8, 2019Date of Patent: October 26, 2021Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Benjamin Dosland Kamrath, Jason Smoke, Daniel C. Crites, Mark C. Morris
-
Publication number: 20210231017Abstract: An engine component includes a body having an internal surface and an external surface, the internal surface at least partially defining an internal cooling circuit. The component further includes a plurality of cooling holes formed in the body and extending between the internal cooling circuit and the external surface of the body. The plurality of cooling holes includes a first cooling hole with a metering portion and a diffuser portion extending from the metering portion to the external surface of the body.Type: ApplicationFiled: September 23, 2020Publication date: July 29, 2021Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Daniel C. Crites, Mark C. Morris, David R. Waldman, Ardeshir Riahi
-
Publication number: 20210172336Abstract: A turbine vane includes an airfoil that extends from an inner diameter to an outer diameter, and from a leading edge to a trailing edge. The turbine vane includes an inner platform coupled to the airfoil at the inner diameter. The turbine vane includes a cooling system defined in the airfoil including a first conduit in proximity to the leading edge to cool the leading edge and a second conduit to cool the trailing edge. The first conduit has an inlet at the outer diameter to receive a cooling fluid and an outlet portion that is defined at least partially through the inner platform. The first conduit includes a plurality of cooling features that extend between a first surface and a second surface of the first conduit, and the first surface of the first conduit is opposite the leading edge.Type: ApplicationFiled: February 19, 2021Publication date: June 10, 2021Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Steven Whitaker, Daniel C. Crites, Mark C. Morris, Ardeshir Riahi
-
Publication number: 20210172337Abstract: A turbine vane includes an airfoil that extends from an inner diameter to an outer diameter, and from a leading edge to a trailing edge. The turbine vane includes an inner platform coupled to the airfoil at the inner diameter. The turbine vane includes a cooling system defined in the airfoil including a first conduit in proximity to the leading edge to cool the leading edge and a second conduit to cool the trailing edge. The first conduit has an inlet at the outer diameter to receive a cooling fluid and an outlet portion that is defined at least partially through the inner platform. The first conduit includes a plurality of cooling features that extend from a first surface of the first conduit, and the first surface of the first conduit is opposite the leading edge.Type: ApplicationFiled: February 22, 2021Publication date: June 10, 2021Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Steven Whitaker, Daniel C. Crites, Mark C. Morris, Ardeshir Riahi
-
Patent number: 11021965Abstract: An engine component includes a body having an internal surface and an external surface, the internal surface at least partially defining an internal cooling circuit. The component further includes a plurality of cooling holes formed in the body and extending between the internal cooling circuit and the external surface of the body. The plurality of cooling holes includes a first cooling hole with a metering portion with a constant cross-sectional area and a cross-sectional shape having a maximum height that is offset relative to a longitudinal centerline of the metering portion; and a diffuser portion extending from the metering portion to the external surface of the body.Type: GrantFiled: May 19, 2016Date of Patent: June 1, 2021Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Daniel C. Crites, Mark C. Morris, David R. Waldman, Ardeshir Riahi
-
Patent number: 11015472Abstract: A turbine engine includes a turbine wheel including a rotor disk and turbine blades connected to the rotor disk through blade mounts. The blade mounts and the rotor disk have fore and aft surfaces. The blade mount includes a blade attachment surface connecting the fore and aft surfaces with the turbine blade extending from the blade attachment surface. A gap is defined between and separating adjacent blade mounts and extends into the rotor disk. The gap includes a pocket having a fore opening and a rotor relief hole. The turbine wheel further includes a plug disposed in a rotor relief opening and a pocket seal disposed in the pocket. The turbine engine further includes a fore seal plate having an edge abutting the blade mounts about a circumference of the turbine wheel and a finger extending toward and contacting the plug to maintain the plug in the rotor relief opening.Type: GrantFiled: September 8, 2020Date of Patent: May 25, 2021Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Steve Halfmann, Daniel C. Crites, Michael Kahrs, Ardeshir Riahi, Jude Miller
-
Patent number: 10989067Abstract: A turbine vane includes an airfoil that extends from an inner diameter to an outer diameter, and from a leading edge to a trailing edge. The turbine vane includes an inner platform coupled to the airfoil at the inner diameter. The turbine vane includes a cooling system defined in the airfoil including a first conduit in proximity to the leading edge to cool the leading edge and a second conduit to cool the trailing edge. The first conduit has an inlet at the outer diameter to receive a cooling fluid and an outlet portion that is defined at least partially through the inner platform. The first conduit includes a plurality of cooling features that extend between a first surface and a second surface of the first conduit, and the first surface of the first conduit is opposite the leading edge.Type: GrantFiled: July 13, 2018Date of Patent: April 27, 2021Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Steven Whitaker, Daniel C. Crites, Mark C. Morris, Ardeshir Riahi
-
Patent number: 10954801Abstract: A cooling circuit to receive a cooling fluid includes at least one shaped cooling pin disposed in the cooling circuit. The at least one shaped cooling pin has a first end and a second end extending along an axis. The first end has a first curved surface defined by a minor diameter and the second end has a second curved surface defined by a major diameter. The first curved surface is to be upstream in the cooling fluid and the minor diameter is less than the major diameter.Type: GrantFiled: August 20, 2019Date of Patent: March 23, 2021Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Benjamin Dosland Kamrath, Jason Smoke, Daniel C. Crites
-
Publication number: 20210003023Abstract: A turbine engine includes a turbine wheel including a rotor disk and turbine blades connected to the rotor disk through blade mounts. The blade mounts and the rotor disk have fore and aft surfaces. The blade mount includes a blade attachment surface connecting the fore and aft surfaces with the turbine blade extending from the blade attachment surface. A gap is defined between and separating adjacent blade mounts and extends into the rotor disk. The gap includes a pocket having a fore opening and a rotor relief hole. The turbine wheel further includes a plug disposed in a rotor relief opening and a pocket seal disposed in the pocket. The turbine engine further includes a fore seal plate having an edge abutting the blade mounts about a circumference of the turbine wheel and a finger extending toward and contacting the plug to maintain the plug in the rotor relief opening.Type: ApplicationFiled: September 8, 2020Publication date: January 7, 2021Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Steve Halfmann, Daniel C. Crites, Michael Kahrs, Ardeshir Riahi, Jude Miller
-
Publication number: 20200378277Abstract: A turbine blade includes an airfoil that has a tip region that extends from the leading edge toward the trailing edge, and the tip region is bounded by a wall that extends at an angle. The leading edge has a leading edge cooling circuit that is defined from the platform to a tip flag channel, and the leading edge cooling circuit is in fluid communication with the tip flag channel. The pressure side includes at least one tip dust hole defined through the wall proximate the pressure side, and the at least one tip dust hole has an inlet and an outlet. The airfoil has at least one rib defined on the wall that extends at a second angle to direct the particles and a portion of the cooling fluid into the inlet.Type: ApplicationFiled: August 20, 2020Publication date: December 3, 2020Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Daniel C. Crites, Mark C. Morris, Steven Whitaker, David Waldman
-
Publication number: 20200378262Abstract: An airfoil for a rotor blade in a gas turbine engine includes a first side wall and a second side wall joined to the first side wall at a leading edge and a trailing edge. The airfoil further includes a tip cap extending between the first and second side walls such that the tip cap and at least portions of the first and second side walls form a blade tip and an internal cooling system. The internal cooling system includes a leading edge cooling circuit, a central cooling circuit, and a trailing edge cooling circuit. Each of the internal passages within the leading edge cooling circuit, the central cooling circuit, and the trailing edge cooling circuit is bounded in the radial outward direction with a surface that has at least one escape hole or that is positively angled in the radial outward direction relative to a chordwise axis.Type: ApplicationFiled: March 23, 2020Publication date: December 3, 2020Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Daniel C. Crites, Michael Kahrs, Brandan Wakefield, Ardeshir Riahi
-
Patent number: 10851660Abstract: Turbine wheels, turbine engines, and methods of forming the turbine wheels are provided herein. In an embodiment, a turbine wheel includes a rotor disk and a plurality of turbine blades. Each turbine blade is operatively connected to the rotor disk through a blade mount, which is bonded to the rotor disk. The blade mount and the rotor disk have a fore surface on a higher pressure side thereof and an aft surface on a lower pressure side thereof. The blade mount includes a blade attachment surface that extends between and connects the fore surface and the aft surface. The turbine blade extends from the blade attachment surface. A gap is defined between adjacent blade mounts. The gap separates the blade mounts and extends into the rotor disk. The gap includes a pocket that has a fore opening in the fore surface. A pocket seal is disposed in the pocket.Type: GrantFiled: September 24, 2019Date of Patent: December 1, 2020Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Steve Halfmann, Daniel C. Crites, Michael Kahrs, Ardeshir Riahi, Jude Miller
-
Publication number: 20200353577Abstract: Turbine wheels, turbine engines, and methods of fabricating the turbine wheels are provided. An exemplary method includes fabricating a turbine wheel that includes a rotor disk and a plurality of turbine blades operatively connected to the rotor disk through a blade mount. The method includes locating a cooling passage within a blade mount preliminary configuration and a cooling inlet on a surface of the blade mount preliminary configuration. A rotor disk bonding surface geometry and a blade mount bonding surface geometry are designed based upon a stress analysis of the turbine wheel and locations of the cooling passage and cooling inlet. A rotor disk production configuration and a blade mount production configuration are generated based upon the preliminary configurations. A blade mount and a rotor disk are formed based upon the production configurations. A blade ring including a plurality of blade mounts is formed and bonded to the rotor disk.Type: ApplicationFiled: July 28, 2020Publication date: November 12, 2020Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Michael Kahrs, Daniel C. Crites, Jude Miller, Steve Halfmann, Jason Smoke, Ardeshir Riahi, David K. Jan
-
Publication number: 20200318488Abstract: A turbine nozzle for a gas turbine engine includes a plurality of nozzle segments that are configured to be assembled into a full ring such that each one of the plurality of nozzle segments is adjacent to another one of the plurality of nozzle segments. Each one of the plurality of nozzle segments includes an endwall segment and a nozzle vane. The turbine nozzle includes a feather seal interface defined by endwall segments of adjacent ones of the plurality of nozzle segments. The feather seal interface is defined along an area of reduced pressure drop through a pressure field defined between adjacent nozzle vanes of the plurality of nozzle segments to reduce leakage through the plurality of nozzle segments. The turbine nozzle includes a feather seal received within the feather seal interface that cooperates with the feather seal interface to reduce leakage through the plurality of nozzle segments.Type: ApplicationFiled: April 8, 2019Publication date: October 8, 2020Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Benjamin Dosland Kamrath, Jason Smoke, Daniel C. Crites, Mark C. Morris