Patents by Inventor Julius John Montgomery
Julius John Montgomery 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: 11988096Abstract: A seal assembly for a rotary machine, such as a turbine engine, may include a seal rotor comprising a rotor face, a seal slider comprising a slider face, a seal stator, wherein the seal slider is slidably coupled to the seal stator, and wherein the slider face and the rotor face define a primary seal. The seal slider may be configured to slidably engage and retract the slider face with respect to the rotor face. The seal assembly may further include a secondary seal disposed between the seal slider and the seal stator. The secondary seal may be configured to compress and rebound and/or to expand and rebound, over at least a portion of a range of motion of the seal slider.Type: GrantFiled: June 16, 2022Date of Patent: May 21, 2024Assignees: General Electric Company, General Electric Deutschland Holding GmbHInventors: Ravindra Shankar Ganiger, Neelesh Nandkumar Sarawate, Rahul Anil Bidkar, Narendra Anand Hardikar, Kevin Randall McManus, Steven Douglas Johnson, Prateek Jalan, Antonio Guijarro Valencia, Julius John Montgomery, Rodrigo Rodriguez Erdmenger, Jose Maria Rey Villazon
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Patent number: 11976562Abstract: A system for controlling blade clearances within a gas turbine engine includes a rotor disk and a rotor blade coupled to the rotor disk. Additionally, the system includes an outer turbine component positioned outward of the rotor blade such that a clearance is defined between the rotor blade and the outer turbine component. Furthermore, the system includes a heat exchanger configured to receive a flow of cooling air bled from the gas turbine engine and transfer heat from the received flow of the cooling air to a flow of coolant to generate cooled cooling air. Moreover, the system includes a valve configured to control the flow of the coolant to the heat exchanger. In this respect, the cooled cooling air is supplied to at least one of the rotor disk or the rotor blade to adjust the clearance between the rotor blade and the outer turbine component.Type: GrantFiled: April 10, 2023Date of Patent: May 7, 2024Assignee: General Electric CompanyInventors: Steven Douglas Johnson, Julius John Montgomery, Brandon Wayne Miller, Robert Proctor, Bradley W. Fintel, Jeffrey Douglas Rambo
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Publication number: 20230279781Abstract: A seal assembly for a rotary machine, such as a turbine engine, may include a seal rotor comprising a rotor face, a seal slider comprising a slider face, a seal stator, wherein the seal slider is slidably coupled to the seal stator, and wherein the slider face and the rotor face define a primary seal. The seal slider may be configured to slidably engage and retract the slider face with respect to the rotor face. The seal assembly may further include a secondary seal disposed between the seal slider and the seal stator. The secondary seal may be configured to compress and rebound and/or to expand and rebound, over at least a portion of a range of motion of the seal slider.Type: ApplicationFiled: June 16, 2022Publication date: September 7, 2023Inventors: Ravindra Shankar Ganiger, Neelesh Nandkumar Sarawate, Rahul Anil Bidkar, Narendra Anand Hardikar, Kevin Randall McManus, Steven Douglas Johnson, Prateek Jalan, Antonio Guijarro Valencia, Julius John Montgomery, Rodrigo Rodriguez Erdmenger, Jose Maria Rey Villazon
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Publication number: 20230265764Abstract: A system for controlling blade clearances within a gas turbine engine includes a rotor disk and a rotor blade coupled to the rotor disk. Additionally, the system includes an outer turbine component positioned outward of the rotor blade such that a clearance is defined between the rotor blade and the outer turbine component. Furthermore, the system includes a heat exchanger configured to receive a flow of cooling air bled from the gas turbine engine and transfer heat from the received flow of the cooling air to a flow of coolant to generate cooled cooling air. Moreover, the system includes a valve configured to control the flow of the coolant to the heat exchanger. In this respect, the cooled cooling air is supplied to at least one of the rotor disk or the rotor blade to adjust the clearance between the rotor blade and the outer turbine component.Type: ApplicationFiled: April 10, 2023Publication date: August 24, 2023Inventors: Steven Douglas Johnson, Julius John Montgomery, Brandon Wayne Miller, Robert Proctor, Bradley W. Fintel, Jeffrey Douglas Rambo
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Publication number: 20220213802Abstract: A system for controlling blade clearances within a gas turbine engine includes a rotor disk and a rotor blade coupled to the rotor disk. Additionally, the system includes an outer turbine component positioned outward of the rotor blade such that a clearance is defined between the rotor blade and the outer turbine component. Furthermore, the system includes a heat exchanger configured to receive a flow of cooling air bled from the gas turbine engine and transfer heat from the received flow of the cooling air to a flow of coolant to generate cooled cooling air. Moreover, the system includes a valve configured to control the flow of the coolant to the heat exchanger. In this respect, the cooled cooling air is supplied to at least one of the rotor disk or the rotor blade to adjust the clearance between the rotor blade and the outer turbine component.Type: ApplicationFiled: January 6, 2021Publication date: July 7, 2022Inventors: Steven Douglas Johnson, Julius John Montgomery, Brandon Wayne Miller, Robert Proctor, Bradley W. Fintel, Jeffrey Douglas Rambo
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Patent number: 10443422Abstract: An apparatus relating to a rim seal for gas turbine engine comprising a wing extending into a buffer cavity with at least one set of protuberances including a first protuberance extending into the buffer cavity and a second protuberance extending from the wing into the buffer cavity, with the first and second protuberances being axially spaced from each other.Type: GrantFiled: February 10, 2016Date of Patent: October 15, 2019Assignee: General Electric CompanyInventors: Jonathan Russell Ratzlaff, Michael Thomas Hogan, Julius John Montgomery
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Patent number: 10240461Abstract: A stator rim structure for a gas turbine engine comprises a stator having an end wall and a discourager defining a channel therebetween. The end wall is adjacent to a hot gas flow and the discourager is adjacent to a purge flow. A rotor has an angel wing extending into the channel. At least one supply passage is disposed within the stator and extends through the discourager and at least one aperture fluidly couples the supply passage with the channel. A flow of cooling air is fed from the supply passage into the aperture and into the channel to form a fluidic dam discouraging ingestion of the hot gas flow.Type: GrantFiled: January 8, 2016Date of Patent: March 26, 2019Assignee: General Electric CompanyInventors: Jonathan Russell Ratzlaff, Julius John Montgomery, Michael Thomas Hogan
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Publication number: 20170226884Abstract: An apparatus relating to a rim seal for gas turbine engine comprising a wing extending into a buffer cavity with at least one set of protuberances including a first protuberance extending into the buffer cavity and a second protuberance extending from the wing into the buffer cavity, with the first and second protuberances being axially spaced from each other.Type: ApplicationFiled: February 10, 2016Publication date: August 10, 2017Inventors: Jonathan Russell Ratzlaff, Michael Thomas Hogan, Julius John Montgomery
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Publication number: 20170198585Abstract: A stator rim structure for a gas turbine engine comprises a stator having an end wall and a discourager defining a channel therebetween. The end wall is adjacent to a hot gas flow and the discourager is adjacent to a purge flow. A rotor has an angel wing extending into the channel. At least one supply passage is disposed within the stator and extends through the discourager and at least one aperture fluidly couples the supply passage with the channel. A flow of cooling air is fed from the supply passage into the aperture and into the channel to form a fluidic dam discouraging ingestion of the hot gas flow.Type: ApplicationFiled: January 8, 2016Publication date: July 13, 2017Inventors: Jonathan Russell Ratzlaff, Julius John Montgomery, Michael Thomas Hogan
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Patent number: 7363762Abstract: A method of assembling a gas turbine engine includes providing a gas turbine engine including a compressor, a combustor downstream from the compressor, and a turbine coupled to the compressor, and coupling a seal assembly aft of the compressor such that air discharged through the seal assembly facilitates reducing the cavity pressure, and therefore reducing the axial forces induced to an aft side of the compressor.Type: GrantFiled: November 16, 2005Date of Patent: April 29, 2008Assignee: General Electric CompanyInventors: Julius John Montgomery, Robert Proctor, Nathan Gerard Cormier, Christopher Charles Glynn, Glen William Royal
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Patent number: 7341429Abstract: A method of manufacturing a gas turbine engine includes providing a turbine mid-frame, coupling a plurality of rotor blades to a rotor disk, the rotor disk is coupled axially aft from the turbine mid-frame such that a cavity is defined between the rotor disk and the turbine mid-frame, and forming at least one opening extending through the turbine mid-frame to facilitate channeling cooling air into the gap, the opening configured to impart a high relative tangential velocity into the cooling air discharged from the opening.Type: GrantFiled: November 16, 2005Date of Patent: March 11, 2008Assignee: General Electric CompanyInventors: Julius John Montgomery, Robert Proctor, Nathan Gerard Cormier, Christopher Charles Glynn, Glen William Royal, Richard William Jendrix
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Patent number: 6722137Abstract: A butterfly valve for a gas turbine engine includes a valve shaft and a valve disk. The valve disk has a centerline axis that extends through the valve disk. The valve disk also includes a shaft opening, an outer periphery, an outer surface, a first side, and a second side. The first side is opposite the second side. The shaft opening extends through the valve disk adjacent the centerline axis, and is sized to receive the valve shaft therein. The disk outer surface extends over the first and second sides, and is tapered between the outer periphery and the centerline axis over at least one of the disk first and second sides.Type: GrantFiled: August 17, 2001Date of Patent: April 20, 2004Assignee: General Electric Co.Inventors: Robert Proctor, John William Hanify, Debra Lynn Prikkel, Michael Jay Epstein, Julius John Montgomery
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Patent number: 6550254Abstract: A gas turbine engine includes a compressor including a casing and a stator assembly. The casing extends around the stator assembly, the stator assembly including a plurality of stator vanes, and a plurality of bleed scoops. Adjacent stator vanes define a static high-pressure region, the bleed scoops formed at least partially within the high pressure region.Type: GrantFiled: August 17, 2001Date of Patent: April 22, 2003Assignee: General Electric CompanyInventors: Robert Proctor, Julius John Montgomery, Michael Jay Epstein, Roger Owen Barbe, Hai Buu Sam, James Bernar Ogzewalla, Andrew David Kemp, Bryan Keith Doloresco
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Publication number: 20030033815Abstract: A gas turbine engine includes a compressor including a casing and a stator assembly. The casing extends around the stator assembly, the stator assembly including a plurality of stator vanes, and a plurality of bleed scoops. Adjacent stator vanes define a static high-pressure region, the bleed scoops formed at least partially within the high pressure region.Type: ApplicationFiled: August 17, 2001Publication date: February 20, 2003Inventors: Robert Proctor, Julius John Montgomery, Michael Jay Epstein, Roger Owen Barbe, Hai Buu Sam, James Bernar Ogzewalla, Andrew David Kemp, Bryan Keith Doloresco
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Publication number: 20030034474Abstract: A butterfly valve for a gas turbine engine includes a valve shaft and a valve disk. The valve disk has a centerline axis that extends through the valve disk. The valve disk also includes a shaft opening, an outer periphery, an outer surface, a first side, and a second side. The first side is opposite the second side. The shaft opening extends through the valve disk adjacent the centerline axis, and is sized to receive the valve shaft therein. The disk outer surface extends over the first and second sides, and is tapered between the outer periphery and the centerline axis over at least one of the disk first and second sides.Type: ApplicationFiled: August 17, 2001Publication date: February 20, 2003Inventors: Robert Proctor, John William Hanify, Debra Lynn Prikkel, Michael Jay Epstein, Julius John Montgomery