Patents by Inventor Derek A. Rice
Derek A. Rice 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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Publication number: 20240109564Abstract: A method is provided that can include activating at least two wireless communication channels in parallel, between a first wireless transceiver and a second wireless transceiver. Each of the at least two wireless communication channels can operate at a different radio carrier frequency, and the first wireless transceiver may be part of a first vehicle. The method can also include transmitting, by the first wireless transceiver, common information in parallel on the at least two wireless communication channels to the second wireless transceiver and deactivating the at least two wireless communication channels.Type: ApplicationFiled: December 12, 2023Publication date: April 4, 2024Inventors: Padam Dhoj Swar, Carl L. Haas, Danial Rice, Rebecca W. Dreasher, Adam Hausmann, Matthew Steven Vrba, Edward J. Kuchar, James Lucas, Andrew Ryan Staats, Jerrid D. Chapman, Jeffrey D. Kernwein, Janmejay Tripathy, Stephen Craven, Tania Lindsley, Derek K. Woo, Ann K. Grimm, Scott Sollars, Phillip A. Burgart, James Allen Oswald, Shannon K. Struttmann, Stuart J. Barr, Keith Smith, Francois P. Pretorius, Craig K. Green, Kendrick Gawne, Irwin Morris, Joseph W. Gorman, Srivallidevi Muthusami, Mahesh Babu Natarajan, Jeremiah Dirnberger, Adam Franco
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Publication number: 20240075815Abstract: A refuse vehicle includes a chassis, an energy storage device supported by the chassis and configured to provide electrical power to a prime mover, wherein activation of the prime mover selectively drives the refuse vehicle, a body for storing refuse therein supported by the chassis, a first hydraulic pump configured to convert electrical power into hydraulic power, a second first hydraulic pump configured to convert electrical power into hydraulic power, and a motor coupled to at least one of the body or the chassis and configured to drive the first hydraulic pump and drive the second hydraulic pump.Type: ApplicationFiled: August 30, 2023Publication date: March 7, 2024Inventors: Jeffrey Koga, Emily Davis, Jerrod Kappers, Vince Schad, Robert S. Messina, Christopher K. Yakes, Vincent Hoover, Clinton T. Weckwerth, Zachary L. Klein, John Beck, Brendan Chan, Skylar A. Wachter, Nader Nasr, Chad K. Smith, Logan Gary, Derek A. Wente, Shawn Naglik, Mike J. Bolton, Jacob Wallin, Quincy Wittman, Christopher J. Rukas, Dylan Hess, Jason Rice, Zhenyi Wei, Bashar Amin, Catherine Linsmeier, Joshua D. Rocholl, Dale Matsumoto
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Patent number: 11220922Abstract: A diffuser and deswirl flow structure includes a plurality of tube structures with an outer wall that is hollow and elongate and that extends between a first portion and a second portion. The plurality of tube structures is disposed in an annular arrangement about the longitudinal axis. The flow structure also includes a plurality of flow passages extending through the tube structures. The plurality of flow passages extend from the first portion to the second portion, respectively. The plurality of flow passages respectfully include a diffuser portion, which is proximate the first portion and configured to diffuse a fluid flow from a compressor wheel. The plurality of flow passages respectfully include a deswirl portion, which is proximate the second portion and configured to deswirl the fluid flow from the diffuser portion. The outer wall defines the diffuser portion and the deswirl portion. The outer wall is self-supporting.Type: GrantFiled: June 17, 2020Date of Patent: January 11, 2022Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Michael Barton, Raymond Mccage, Derek Rice
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Publication number: 20210396144Abstract: A diffuser and deswirl flow structure includes a plurality of tube structures with an outer wall that is hollow and elongate and that extends between a first portion and a second portion. The plurality of tube structures is disposed in an annular arrangement about the longitudinal axis. The flow structure also includes a plurality of flow passages extending through the tube structures. The plurality of flow passages extend from the first portion to the second portion, respectively. The plurality of flow passages respectfully include a diffuser portion, which is proximate the first portion and configured to diffuse a fluid flow from a compressor wheel. The plurality of flow passages respectfully include a deswirl portion, which is proximate the second portion and configured to deswirl the fluid flow from the diffuser portion. The outer wall defines the diffuser portion and the deswirl portion. The outer wall is self-supporting.Type: ApplicationFiled: June 17, 2020Publication date: December 23, 2021Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Michael Barton, Raymond Mccage, Derek Rice
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Publication number: 20150308273Abstract: A turbine engine component for a gas turbine engine includes an inner disk, an outer shroud, and a plurality of blades. Each blade comprises a blade root and an airfoil body. The blade root is plated at least in part with a noble metal, and is coupled to the inner disk. The airfoil body extends at least partially between the blade root and the outer shroud.Type: ApplicationFiled: November 14, 2014Publication date: October 29, 2015Applicant: HONEYWELL INTERNATIONAL INC.Inventors: James S. Perron, William C. Baker, Derek A. Rice
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Patent number: 9114488Abstract: A rotor component assembly including at least one void space formed therein that provides for reduction in weight of the component and/or cooling of the component during operation. The rotor component is formed by positioning a coated mild steel insert within a mold having an internal cross-section substantially the same in dimensions as the final rotor component. The mold is filled with a superalloy metal powder and undergoes hot-isostatic pressing to consolidate the powder about the coated core insert and form a superalloy structure. The mold is removed from about the superalloy structure and the core insert is removed from within the superalloy structure, thereby defining the at least one internal void within the rotor component.Type: GrantFiled: November 21, 2006Date of Patent: August 25, 2015Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Derek A. Rice, Brian A. Hann, Andrew F. Hieber
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Patent number: 7832986Abstract: A dual alloy turbine rotor is provided and includes an integrally formed blade ring and a disk. The blade ring is made of a first alloy and includes a ring portion and a plurality of airfoils extending therefrom, where the ring portion includes an inner surface, and each airfoil includes an internal cavity formed therein. The disk is made of a second alloy and may have a beveled outer peripheral surface. The disk is disposed within the ring portion such that the disk outer peripheral surface contacts at least a portion of the ring portion inner surface. Methods of manufacturing the turbine rotor are also provided.Type: GrantFiled: March 7, 2007Date of Patent: November 16, 2010Assignee: Honeywell International Inc.Inventors: William C. Baker, Thomas E. Strangman, Derek A. Rice, James S. Perron, Christopher Zollars
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Patent number: 7744986Abstract: A coating system is used on an engine component having an outer surface configured to be exposed to a first plurality of particles impinging against the outer surface at an angle within a first angle range and a second plurality of particles impinging at an angle in a second angle range. The system includes a bond layer overlying the engine component outer surface, a first erosion-resistant layer comprising a first material that is more resistant to erosion by particles impinging the component outer surface at an angle within the first angle range than by particles impinging within the second angle range, an interlayer overlying the first erosion-resistant layer, and a second erosion-resistant layer comprising a second material that is more resistant to erosion by particles impinging the component outer surface at an angle within the second angle range than by particles impinging within the first angle range.Type: GrantFiled: November 21, 2008Date of Patent: June 29, 2010Assignee: Honeywell International Inc.Inventors: Derek A. Rice, Adrienne Lamm
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Patent number: 7516526Abstract: A spun metal form used to manufacture a dual alloy turbine wheel. The spun metal form prevents braze alloy contamination of the hub/casting interface by relocating the braze joint away from the interface. The spun metal form allows for the re-working of components after failed vacuum brazing and increases the time to failure of dual alloy turbine wheels.Type: GrantFiled: November 3, 2004Date of Patent: April 14, 2009Assignee: Honeywell International Inc.Inventors: Derek A. Rice, Venkatesh S. Krishnan, David R. Waldman, Gary G. Capek, Devinder N. Katariya
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Publication number: 20090075043Abstract: A coating system is used on an engine component having an outer surface configured to be exposed to a first plurality of particles impinging against the outer surface at an angle within a first angle range and a second plurality of particles impinging at an angle in a second angle range. The system includes a bond layer overlying the engine component outer surface, a first erosion-resistant layer comprising a first material that is more resistant to erosion by particles impinging the component outer surface at an angle within the first angle range than by particles impinging within the second angle range, an interlayer overlying the first erosion-resistant layer, and a second erosion-resistant layer comprising a second material that is more resistant to erosion by particles impinging the component outer surface at an angle within the second angle range than by particles impinging within the first angle range.Type: ApplicationFiled: November 21, 2008Publication date: March 19, 2009Applicant: Honeywell International Inc.Inventors: Derek A. Rice, Adrienne Lamm
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Publication number: 20090068016Abstract: A turbine engine component for a gas turbine engine includes an inner disk, an outer shroud, and a plurality of blades. Each blade comprises a blade root and an airfoil body. The blade root is plated at least in part with a noble metal, and is coupled to the inner disk. The airfoil body extends at least partially between the blade root and the outer shroud.Type: ApplicationFiled: April 20, 2007Publication date: March 12, 2009Applicant: HONEYWELL INTERNATIONAL, INC.Inventors: James S. Perron, William C. Baker, Derek A. Rice
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Publication number: 20080219853Abstract: A dual alloy turbine rotor is provided and includes an integrally formed blade ring and a disk. The blade ring is made of a first alloy and includes a ring portion and a plurality of airfoils extending therefrom, where the ring portion includes an inner surface, and each airfoil includes an internal cavity formed therein. The disk is made of a second alloy and may have a beveled outer peripheral surface. The disk is disposed within the ring portion such that the disk outer peripheral surface contacts at least a portion of the ring portion inner surface. Methods of manufacturing the turbine rotor are also provided.Type: ApplicationFiled: March 7, 2007Publication date: September 11, 2008Inventors: William C. Baker, Thomas E. Strangman, Derek A. Rice, James S. Perron, Christopher Zollars
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Publication number: 20080166561Abstract: A coating system is used on an engine component having an outer surface configured to be exposed to a first plurality of particles impinging against the outer surface at an angle within a first angle range and a second plurality of particles impinging at an angle in a second angle range. The system includes a bond layer overlying the engine component outer surface, a first erosion-resistant layer comprising a first material that is more resistant to erosion by particles impinging the component outer surface at an angle within the first angle range than by particles impinging within the second angle range, an interlayer overlying the first erosion-resistant layer, and a second erosion-resistant layer comprising a second material that is more resistant to erosion by particles impinging the component outer surface at an angle within the second angle range than by particles impinging within the first angle range.Type: ApplicationFiled: August 16, 2005Publication date: July 10, 2008Inventors: Derek A. Rice, Adrienne Lamm
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Publication number: 20080115358Abstract: A rotor component assembly including at least one void space formed therein that provides for reduction in weight of the component and/or cooling of the component during operation. The rotor component is formed by positioning a coated mild steel insert within a mold having an internal cross-section substantially the same in dimensions as the final rotor component. The mold is filled with a superalloy metal powder and undergoes hot-isostatic pressing to consolidate the powder about the coated core insert and form a superalloy structure. The mold is removed from about the superalloy structure and the core insert is removed from within the superalloy structure, thereby defining the at least one internal void within the rotor component.Type: ApplicationFiled: November 21, 2006Publication date: May 22, 2008Inventors: Derek A. Rice, Brian A. Hann, Andrew F. Hieber
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Publication number: 20070128363Abstract: Apparatus and compositions for a turbine disk capable of sustained operation at turbine disk rim temperatures in excess of 1300° F., wherein the turbine disk comprises a superalloy substrate, and a ductile oxidation barrier coating disposed on at least an outer portion of the turbine disk. The oxidation barrier coating may comprise a ductile metal, such as platinum, palladium, or platinum alloyed with Al, Cr, Ni, Pd, Ti, or Zr. Methods for providing an oxidation barrier-coated turbine disk are also disclosed.Type: ApplicationFiled: December 7, 2005Publication date: June 7, 2007Inventors: Derek Rice, Andrew Hieber, Daniel Greving
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Publication number: 20070081912Abstract: Methods are provided for manufacturing turbine disks each having a hub surrounded by a rim, the hub having a first microstructure and the rim having a second microstructure that is coarser than the first microstructure, the methods employing a first powder alloy having a first gamma prime solvus temperature and a second powder alloy having a second gamma prime solvus temperature that is less than the first gamma prime solvus temperature. One method includes the steps of forming an ingot from the first and second powder alloys, the ingot having an inner section having the first microstructure and an outer section having a microstructure that is less coarse than the second microstructure, and exposing the ingot to a temperature between the first and second gamma prime solvus temperatures while forming the ingot into a plurality of turbine disks to transform the microstructure of the outer section into the second microstructure.Type: ApplicationFiled: October 11, 2005Publication date: April 12, 2007Inventors: Brian Hann, Derek Rice, Andrew Hieber, Daniel Greving
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Publication number: 20060239825Abstract: A method for bi-casting a turbine rotor may include applying an oxidation resistant coating to individually cast rotor blades, and bi-casting the coated blades into a dual alloy blade ring, wherein the oxidation resistant coating prevents formation of an oxide scale on the surface of the rotor blades during bi-casting and allows diffusion bonding of the rotor blades to the blade ring. The oxidation resistant coating may comprise a platinum group metal or alloy thereof.Type: ApplicationFiled: April 21, 2005Publication date: October 26, 2006Applicant: Honeywell International Inc.Inventors: Derek Rice, William Baker, James Perron
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Patent number: 7097422Abstract: A hoop stress relief mechanism is disclosed for use on a rotary body to relieve stress caused by both thermal and centrifugal forces. The mechanism may consist of a J-shaped slot cut from the outer rim of the rotary body a distance inwardly toward the axis of rotation, the slot having a curve in its inward end that curves back towards the outer rim. The J-shaped slot may extend through the rotary body to join its two faces. The J-shaped slot may be fabricated by an electric discharge wire machine. The electric discharge wire machine may make multiple passes in order to smooth the bottom surface of the curved slot portion.Type: GrantFiled: February 3, 2004Date of Patent: August 29, 2006Assignee: Honeywell International, Inc.Inventors: Derek A. Rice, David R. Waldman, Redge How, Maher A. Serag, Paul D. Rippey, Charles P. Silcox, Henry L. Chester, Ramasami (Rajan) Thiyagarajan, Hsin-Yi Liu, Paul E. Hruska, Richard E. Jackson, David A. Innes, Gordon B. Bailey
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Publication number: 20060099078Abstract: A hoop stress relief mechanism is disclosed for use on a rotary body to relieve stress caused by both thermal and centrifugal forces. The mechanism may consist of a J-shaped slot cut from the outer rim of the rotary body a distance inwardly toward the axis of rotation, the slot having a curve in its inward end that curves back towards the outer rim. The J-shaped slot may extend through the rotary body to join its two faces. The J-shaped slot may be fabricated by an electric discharge wire machine. The electric discharge wire machine may make multiple passes in order to smooth the bottom surface of the curved slot portion.Type: ApplicationFiled: February 3, 2004Publication date: May 11, 2006Applicant: Honeywell International Inc.,Inventors: Derek Rice, David Waldman, Redge How, Maher Serag, Paul Rippey, Charles Silcox, Chester Henry, Ramasami (Rajan) Thiyagarajan, Hsin-Yi Liu, Paul Hruska, Richard Jackson, David Innes, Gordon Bailey
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Patent number: 7000306Abstract: A spun metal form used to manufacture a dual alloy turbine wheel. The spun metal form prevents braze alloy contamination of the hub/casting interface by relocating the braze joint away from the interface. The spun metal form allows for the re-working of components after failed vacuum brazing and increases the time to failure of dual alloy turbine wheels.Type: GrantFiled: August 16, 2004Date of Patent: February 21, 2006Assignee: Honeywell International, Inc.Inventors: Derek A. Rice, Venkatesh S. Krishnan, David R. Waldman, Gary G. Capek, Devinder N. Katariya