Patents by Inventor Jason D. Himes
Jason D. Himes 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: 12331646Abstract: An air seal is provided which extends axially between a first side and a second side. The air seal includes an axial flange, a radial flange, a seal element, a retainer neck and a retainer head. The axial flange extends axially to the second side. The radial flange is connected to the axial flange at the second side. The radial flange projects radially outward from the axial flange to a distal end. The seal element projects radially outward from the distal end of the radial flange. The retainer neck is connected to the radial flange at the distal end of the radial flange. The retainer neck projects axially out from the radial flange towards the first side and then projects radially outward to the retainer head. The retainer head projects axially towards the first side and away from the retainer neck to an axial end of the retainer head.Type: GrantFiled: May 13, 2024Date of Patent: June 17, 2025Assignee: RTX CorporationInventors: Sebastian Ruiz Espinel, Ryan P. Humelsine, Richard N. Allen, Kar D. Chin, Jason D. Himes, Victor A. Lammoglia Hoyos, Argenis Roberto Cruz Mercado, Carlos Rendon Roman, Rachel Irujo, Wilfred J. De Jesus Vargas, Bryan D. Roseberry, James J. Gander, Amy M. Sunnarborg
-
Patent number: 10989054Abstract: A balance ring for a gas turbine engine has a ring shaped body with a first radial thickness, an anti-rotation tab extending outward from the body and at least one millable balancing feature connected to the body.Type: GrantFiled: September 25, 2014Date of Patent: April 27, 2021Assignee: Raytheon Technologies CorporationInventors: Jason D. Himes, Peter Josef Karner
-
Patent number: 10822952Abstract: An assembly according to an exemplary aspect of the present disclosure includes, among other things, a disk, a cover plate providing a cavity at a first axial side of the disk, a passageway including an inlet provided by a notch in at least one of the disk and the cover plate in fluid communication with the cavity, and the passageway extending from the inlet to an exit provided at a second axial side of the disk opposite the first axial side, the exit in fluid communication with the inlet, and the passageway configured to provide fluid flow from the cavity to the exit.Type: GrantFiled: September 17, 2014Date of Patent: November 3, 2020Assignee: Raytheon Technologies CorporationInventors: Jeffrey S. Beattie, Jason D. Himes, Matthew Andrew Hough, Christopher Corcoran
-
Patent number: 10570763Abstract: A seal assembly for a gas turbine engine includes a primary seal that includes an inner face that has a protrusion configured to seal relative to a seal land. The protrusion provided on segmented shoes is circumferentially spaced from one another by gaps. The shoes are positioned in a relaxed state. A removable material encases the protrusion with the shoes in the relaxed state.Type: GrantFiled: June 22, 2015Date of Patent: February 25, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: Jason D. Himes
-
Patent number: 10247003Abstract: A rotating component for a turbine engine includes a rotor portion protruding radially outward, at least one overweight region is located in the rotor portion, and at least one additively manufactured counterweight region is positioned relative to the at least one overweight region such that the rotating component is circumferentially balanced.Type: GrantFiled: September 25, 2014Date of Patent: April 2, 2019Assignee: United Technologies CorporationInventor: Jason D. Himes
-
Patent number: 10184345Abstract: A cover plate assembly according to an exemplary aspect of the present disclosure includes, among other things, a first cover plate and a second cover plate in contact with a portion of the first cover plate to at least axially retain the first cover plate.Type: GrantFiled: August 4, 2014Date of Patent: January 22, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: Jason D. Himes
-
Patent number: 9835032Abstract: A rotor disk is provided. The rotor disk may comprise a disk lug and a trench. The disk lug may be fixed to a distal surface of the rotor disk. The trench may be disposed on a surface of the disk lug. The trench may extend radially inwards from a distal surface of the disk lug. The trench may be configured to at least partially define a flow path by which cooling air may reach a distal surface of the disk lug in order to provide disk lug cooling.Type: GrantFiled: June 1, 2015Date of Patent: December 5, 2017Assignee: United Technologies CorporationInventors: David Richard Griffin, Zachary Mott, Christopher Corcoran, Ross Wilson, Jason D Himes
-
Publication number: 20160369642Abstract: A seal assembly for a gas turbine engine includes a primary seal that includes an inner face that has a protrusion configured to seal relative to a seal land. The protrusion provided on segmented shoes is circumferentially spaced from one another by gaps. The shoes are positioned in a relaxed state. A removable material encases the protrusion with the shoes in the relaxed state.Type: ApplicationFiled: June 22, 2015Publication date: December 22, 2016Inventor: Jason D. Himes
-
Publication number: 20160348510Abstract: A rotor disk is provided. The rotor disk may comprise a disk lug and a trench. The disk lug may be fixed to a distal surface of the rotor disk. The trench may be disposed on a surface of the disk lug. The trench may extend radially inwards from a distal surface of the disk lug. The trench may be configured to at least partially define a flow path by which cooling air may reach a distal surface of the disk lug in order to provide disk lug cooling.Type: ApplicationFiled: June 1, 2015Publication date: December 1, 2016Applicant: United Technologies CorporationInventors: David Richard Griffin, Zachary Mott, Christopher Corcoran, Ross Wilson, Jason D. Himes
-
Publication number: 20160237825Abstract: A rotating component for a turbine engine includes a rotor portion protruding radially outward, at least one overweight region is located in the rotor portion, and at least one additively manufactured counterweight region is positioned relative to the at least one overweight region such that the rotating component is circumferentially balanced.Type: ApplicationFiled: June 18, 2015Publication date: August 18, 2016Inventor: Jason D. Himes
-
Publication number: 20160222787Abstract: An assembly according to an exemplary aspect of the present disclosure includes, among other things, a disk, a cover plate providing a cavity at a first axial side of the disk, a passageway including an inlet provided by a notch in at least one of the disk and the cover plate in fluid communication with the cavity, and the passageway extending from the inlet to an exit provided at a second axial side of the disk opposite the first axial side, the exit in fluid communication with the inlet, and the passageway configured to provide fluid flow from the cavity to the exit.Type: ApplicationFiled: September 17, 2014Publication date: August 4, 2016Inventors: Jeffrey S. Beattie, Jason D. Himes, Matthew Andrew Hough, Christopher Corcoran
-
Publication number: 20160090841Abstract: A gas turbine engine rotor assembly includes a rotor disk with a slot. A rotor blade has a root supported within the slot. A heat shield is arranged in a cavity in the slot between the root and the rotor disk. An axial retention feature is configured to axially maintain the heat shield within the slot.Type: ApplicationFiled: February 16, 2015Publication date: March 31, 2016Inventors: Jason D. Himes, Scott D. Virkler, Jordan Tresser, Dwayne K. Mecklenburg, Ross Wilson, David Richard Griffin
-
Patent number: 9212556Abstract: A gas turbine engine section comprises a rotatable shaft, first and second axially adjacent components, a nut, and a multifunction positioning lock washer. The first and second axially adjacent components are located on the rotatable shaft and are separated by an axial separation distance. The nut is configured to thread onto the rotatable shaft to hold one of the first and second axially adjacent components in compression. The multifunction positioning lock washer has antirotation geometry configured to prevent the nut from tightening or loosening. The axial length of the multifunction positioning lock washer is adjusted by removing material based on measurement of the axial separation distance to take in tolerances and reduce the axial separation distance.Type: GrantFiled: August 21, 2012Date of Patent: December 15, 2015Assignee: United Technologies CorporationInventors: James L. Lucas, Jason D. Himes
-
Publication number: 20140248136Abstract: A gas turbine engine section comprises a rotatable shaft, first and second axially adjacent components, a nut, and a multifunction positioning lock washer. The first and second axially adjacent components are located on the rotatable shaft and are separated by an axial separation distance. The nut is configured to thread onto the rotatable shaft to hold one of the first and second axially adjacent components in compression. The multifunction positioning lock washer has antirotation geometry configured to prevent the nut from tightening or loosening.Type: ApplicationFiled: August 21, 2012Publication date: September 4, 2014Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: James L. Lucas, Jason D. Himes