Patents by Inventor Douglas D. Dierksmeier
Douglas D. Dierksmeier 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).
-
Publication number: 20200224606Abstract: A gas turbine engine system includes a gas turbine engine, a gearbox, a first propulsor, and a second propulsor. The gas turbine engine is coupled with an input shaft of the gearbox and configured to power the gearbox during operation of the gas turbine engine. The gearbox is configured to drive selectively the first propulsor and the second propulsor.Type: ApplicationFiled: January 11, 2019Publication date: July 16, 2020Inventor: Douglas D. Dierksmeier
-
Patent number: 10704466Abstract: Vehicles, such as aircraft, may include turbine-based combined cycle power plants (TBCC) for power to achieve high-mach speeds. Cooling systems for such TBCC may include a turbine-generator arranged to be driven for rotation by ambient air to reduce the temperature of the ambient air while providing electric power for use under cocooning of a primary gas turbine engine in favor of a scramjet engine during high-mach travel.Type: GrantFiled: January 29, 2018Date of Patent: July 7, 2020Assignee: Rolls-Royce North American Technologies Inc.Inventor: Douglas D. Dierksmeier
-
Patent number: 10683866Abstract: An axial compressor comprises a plurality of compressor stages positioned axially adjacent within a casing. Each of the plurality of compressor stages comprise a rotor segment and a banded stator segment positioned axially adjacent the rotor segment. An annulus is formed between the casing and an outer flowpath ring of the stator segment. A pathway is provided that establishes an air flowpath between an entry pathway in a first stage and an exit pathway in a second stage.Type: GrantFiled: December 19, 2016Date of Patent: June 16, 2020Assignee: Rolls-Royce North American Technologies Inc.Inventors: Douglas D. Dierksmeier, Edward C. Rice, Ryan C. Humes
-
Patent number: 10683772Abstract: An axial compressor comprises a plurality of compressor stages positioned axially adjacent one another within a casing. Each of the plurality of compressor stages comprise a rotor segment and a banded stator segment positioned axially adjacent the rotor segment. An annulus is formed between the casing and an outer flowpath ring of the stator segment. A vane of each stator segment comprises a member extending into the annulus.Type: GrantFiled: December 19, 2016Date of Patent: June 16, 2020Assignee: Rolls-Royce North American Technologies Inc.Inventors: Douglas D. Dierksmeier, Edward C. Rice, Ryan C. Humes
-
Patent number: 10654576Abstract: A gas turbine engine includes a cooling air system, a coolant system, and a thermoelectric heat exchanger adapted for selective operation in response to operational states of the gas turbine engine.Type: GrantFiled: February 3, 2017Date of Patent: May 19, 2020Assignee: Rolls-Royce North American Technologies Inc.Inventors: Douglas D. Dierksmeier, Daniel K. Vetters, Michael A. Karam
-
Patent number: 10619503Abstract: A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.Type: GrantFiled: July 26, 2017Date of Patent: April 14, 2020Assignees: Rolls-Royce High Temperature Composites Inc., Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.Inventors: Daniel K. Vetters, David J. Thomas, Ted Freeman, Joseph Lamusga, Rick Uskert, Douglas D. Dierksmeier, Jun Shi, Todd Engel, Matt Brandt
-
Patent number: 10612468Abstract: A gas turbine engine includes a compressor, a cooling source, and a thermoelectric intercooler adapted for selective operation in response to operational states of the gas turbine engine.Type: GrantFiled: February 3, 2017Date of Patent: April 7, 2020Assignee: Rolls-Royce North American Technologies Inc.Inventors: Douglas D. Dierksmeier, Daniel K. Vetters, Michael A. Karam
-
Patent number: 10563620Abstract: An expandable exhaust cone assembly is described which is able to move from a collapsed position to an expanded position.Type: GrantFiled: August 12, 2016Date of Patent: February 18, 2020Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce CorporationInventors: Douglas D. Dierksmeier, Edward C. Rice, Ryan C. Humes
-
Patent number: 10563670Abstract: A compressor for use in a gas turbine engine is disclosed herein. The compressor includes a case, vanes, and a vane actuation system. The vanes are arranged circumferentially adjacent to one another about a central axis inside the case and each one of the vanes is configured for rotation about a vane axis generally perpendicular to the central axis. The vane actuation system is configured to cause rotation of at least one of the vanes about the vane axis.Type: GrantFiled: July 20, 2017Date of Patent: February 18, 2020Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.Inventors: Douglas D. Dierksmeier, Edward C. Rice, Ryan C. Humes
-
Publication number: 20200047896Abstract: A propulsor includes an electric motor, a fan unit, and a thrust system positioned downstream of and coupled to the fan unit.Type: ApplicationFiled: August 10, 2018Publication date: February 13, 2020Inventor: Douglas D. Dierksmeier
-
Publication number: 20190376396Abstract: A turbine blisk for use in a turbine rotor assembly in a gas turbine engine includes a turbine blade having a base end with a discrete bonding surface; an intermediate component having a first bonding surface and a second bonding surface; and a portion of a rotor disc having an outer surface that includes a bonding area. The discrete bonding surface of the base end of the turbine blade is attached to the first bonding surface of the intermediate component, thereby forming a first joint. The second bonding surface of the intermediate component is attached to the bonding area of the outer surface of the rotor disc, thereby forming a second joint. The first joint includes a diffusion bond, while the second joint includes a linear friction weld.Type: ApplicationFiled: June 12, 2018Publication date: December 12, 2019Inventor: Douglas D. Dierksmeier
-
Patent number: 10415403Abstract: A gas turbine engine, a blisk and methods of manufacturing are disclosed. The blisk includes a disk and a plurality of blades. Each blade includes a platform, an airfoil, and a shank portion radially extending between the platform and the disk. The airfoil includes cooling features. Cooling cavities are defined between shank portions of adjacent blades and are in communication to the internal of blades via cooling feed channels. A coverplate is coupled to a downstream side of the blisk to cover the cooling cavities. A plurality of inner tabs extends from an inner edge of the coverplate to securely couple the coverplate to the disk. The disk and the plurality of blades may be integrally formed or casted as a single unit. The platform, the airfoil, and the shank portion may be formed integrally as a single unit and bonded to the disk to form the blisk.Type: GrantFiled: January 13, 2017Date of Patent: September 17, 2019Assignee: Rolls-Royce North American Technologies Inc.Inventor: Douglas D. Dierksmeier
-
Publication number: 20190271231Abstract: A blisk for a turbine engine is provided, the blisk includes a hub, a rim positioned radially outward from the hub, and a blade. The rim an outer surface facing radially outward from the hub and an inner surface. The blade is integral to the rim and includes a leading end, a trailing end, an interior surface, and a radially inward end. A cooling passage extends from an inlet in the inner surface of the rim, from the inlet through a channel enclosed within the rim and extending along the outer surface of the rim, and from the channel through an opening at the trailing end of the blade into a chamber defined by the interior surface of the blade.Type: ApplicationFiled: March 5, 2018Publication date: September 5, 2019Applicant: Rolls-Royce North American Technologies Inc.Inventor: Douglas D. Dierksmeier
-
Publication number: 20190234308Abstract: Vehicles, such as aircraft, may include turbine-based combined cycle power plants (TBCC) for power to achieve high-mach speeds. Cooling systems for such TBCC may include a turbine-generator arranged to be driven for rotation by ambient air to reduce the temperature of the ambient air while providing electric power for use under cocooning of a primary gas turbine engine in favor of a scramjet engine during high-mach travel.Type: ApplicationFiled: January 29, 2018Publication date: August 1, 2019Inventor: Douglas D. Dierksmeier
-
Publication number: 20190195072Abstract: A disc for use in a turbine rotor is provided including a hub, a plurality of webs extending outwardly from the hub, and a plurality of rims. Each of the plurality of webs are separate from each other by a gap. Each rim is positioned at an outward end of one of the webs. Each rim is configured to receive a respective set of turbine blade.Type: ApplicationFiled: December 22, 2017Publication date: June 27, 2019Applicant: Rolls-Royce North American Technologies Inc.Inventors: Douglas D. Dierksmeier, Ryan C. Humes
-
Publication number: 20190136767Abstract: An improved system, apparatus and method may be configured for detecting coking in a gas turbine engine. The system may comprise one or more heatable collecting elements configured to be positioned in a fuel supply passage having an inlet and an outlet. The apparatus heatable collecting may be configured to generate heat at or over a fuel system temperature range to induce coking in at least one of the heatable collecting elements. The apparatus may also include a sensor configured to detect an indication of coking on the heatable collecting elements and, in response to the coking indication, communicate a coking condition signal to an engine control.Type: ApplicationFiled: December 26, 2018Publication date: May 9, 2019Inventors: David Farnum, Douglas D. Dierksmeier, Ben Moloney, Patrick C. Sweeney
-
Patent number: 10247015Abstract: A gas turbine engine and a blisk are disclosed, including methods of making the same. The blisk may include a disk, spars of airfoils, platforms, and shanks of airfoils integrally formed as a unit. Such blisk features may be integrally formed by a casting process or additive manufacturing. The blisk includes cooled airfoils, such that the spar is hollow, and a cover panel is bonded to an outer surface of standoffs to define passages between the cover panel and the spar. Cooling air is fed to the hollow spar through a cooling feed channel defined in the disk or shank portion.Type: GrantFiled: January 13, 2017Date of Patent: April 2, 2019Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.Inventors: Matthew T. Kush, Douglas D. Dierksmeier
-
Patent number: 10215035Abstract: A wheel assembly for a gas turbine engine is disclosed. The wheel assembly includes a disk arranged for rotation about a central axis and formed to include a plurality of slots. The wheel assembly also includes a plurality of blades sized to be received in the plurality of slots so that the blades are coupled to the disk for common rotation about the central axis. The wheel assembly further includes a plurality of blade biasers positioned in the slots between the disk and the blades so that the blade biasers are engaged with the disk and the blades to preload the blades away from the central axis.Type: GrantFiled: December 18, 2015Date of Patent: February 26, 2019Assignee: Rolls-Royce North American Technologies Inc.Inventors: Douglas D. Dierksmeier, Tab M. Heffernan
-
Patent number: 10196904Abstract: An airfoil may include a spar comprising a passageway inside of the spar for a cooling fluid, a pedestal on an outer surface of the spar, and an inlet configured to direct the cooling fluid from the passageway to the outer surface of the spar. The airfoil may further include a coversheet, wherein an inner surface of the coversheet is positioned on the pedestal of the spar and an edge of the coversheet is positioned along an end of the spar. The inner surface of the coversheet, the pedestal, and the outer surface of the spar may define a cooling path from the inlet to an outlet at the edge of the coversheet. The outlet at the edge of the coversheet may be configured to direct cooling fluid onto the end of the spar, onto a footing, and/or onto a fillet positioned along an intersection of the footing and the spar.Type: GrantFiled: January 24, 2016Date of Patent: February 5, 2019Assignees: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC., ROLLS-ROYCE CORPORATIONInventors: Tab M. Heffernan, Jeffrey F. Rhodes, Douglas D. Dierksmeier, Okey Kwon
-
Patent number: 10196988Abstract: An improved system, apparatus and method may be configured for detecting coking in a gas turbine engine. The system may comprise one or more heatable collecting elements configured to be positioned in a fuel supply passage having an inlet and an outlet. The apparatus heatable collecting may be configured to generate heat at or over a fuel system temperature range to induce coking in at least one of the heatable collecting elements. The apparatus may also include a sensor configured to detect an indication of coking on the heatable collecting elements and, in response to the coking indication, communicate a coking condition signal to an engine control.Type: GrantFiled: June 2, 2016Date of Patent: February 5, 2019Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.Inventors: David Farnum, Douglas D. Dierksmeier, Ben Moloney, Patrick C. Sweeney