Patents by Inventor Julian Partyka
Julian Partyka 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: 11371375Abstract: A gas turbine engine includes a shaft and a heatshield that circumscribes the shaft. The heatshield defines a cylindrical body that has radially inner and outer sides and extends between first and second axial ends. The heatshield is exclusively supported on the shaft at the first and second axial ends. The heatshield includes at least one seal member on the radially outer side. A damper member is disposed at the radially inner side of the heatshield for attenuating vibration of the heatshield.Type: GrantFiled: August 19, 2019Date of Patent: June 28, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Joshua G. LaPera, Julian Partyka, Timothy J. Harding
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Publication number: 20210054756Abstract: A gas turbine engine includes a shaft and a heatshield that circumscribes the shaft. The heatshield defines a cylindrical body that has radially inner and outer sides and extends between first and second axial ends. The heatshield is exclusively supported on the shaft at the first and second axial ends. The heatshield includes at least one seal member on the radially outer side. A damper member is disposed at the radially inner side of the heatshield for attenuating vibration of the heatshield.Type: ApplicationFiled: August 19, 2019Publication date: February 25, 2021Inventors: Joshua G. LaPera, Julian Partyka, Timothy J. Harding
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Publication number: 20210017870Abstract: A curvic seal for a gas turbine engine includes a cylindrical seal with a retention feature.Type: ApplicationFiled: May 29, 2020Publication date: January 21, 2021Applicant: Raytheon Technologies CorporationInventors: Julian Partyka, Scott D. Virkler, Jonathan P. Sandoval
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Patent number: 10822979Abstract: A curvic seal for a gas turbine engine includes a cylindrical seal with a retention feature.Type: GrantFiled: March 14, 2014Date of Patent: November 3, 2020Assignee: Raytheon Technologies CorporationInventors: Julian Partyka, Scott D Virkler, Jonathan P Sandoval
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Patent number: 10655480Abstract: According to one embodiment, a mini-disk of a gas turbine engine having an axis is provided. The mini-disk includes a bore, a web extending radially with respect to the axis of the gas turbine engine from the bore, a base extending axially with respect to the axis of the gas turbine engine from the bore, a connector located on an end of the base, the connector configured to connect with a hub arm of the gas turbine engine, and an expansion feature configured in the base and located between the bore and the connector, the expansion feature configured to reduce an axial stiffness of the base.Type: GrantFiled: January 18, 2016Date of Patent: May 19, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Steven D. Porter, Julian Partyka
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Publication number: 20200025210Abstract: According to one embodiment, a mini-disk of a gas turbine engine having an axis is provided. The mini-disk includes a bore, a web extending radially with respect to the axis of the gas turbine engine from the bore, a base extending axially with respect to the axis of the gas turbine engine from the bore, a connector located on an end of the base, the connector configured to connect with a hub arm of the gas turbine engine, and an expansion feature configured in the base and located between the bore and the connector, the expansion feature configured to reduce an axial stiffness of the base.Type: ApplicationFiled: January 18, 2016Publication date: January 23, 2020Inventors: Steven D. Porter, Julian Partyka
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Patent number: 10400603Abstract: Mini-disks of gas turbine engines are provided having an axially extending portion extending axially with respect to an axis of the engine, the axially extending portion configured to engage with a hub arm of a compressor of the engine, a radially extending portion extends radially with respect to the axis, the radially extending portion configured to engage with an attachment of a turbine disk of the gas turbine engine, an intermediate portion extending between the axially extending portion and the radially extending portion, and at least one mini-disk connector configured to engage with a portion of the turbine disk of the gas turbine engine to prevent radial movement of the mini-disk during operation.Type: GrantFiled: June 23, 2016Date of Patent: September 3, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Raymond S. Hummel, Julian Partyka
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Patent number: 10378453Abstract: A turbine section for a gas turbine engine includes a first rotor assembly with a first rotor assembly bleed air source and an aft cavity that is in fluid communication with the first rotor assembly bleed air source. A second rotor assembly includes a forward cavity. A vane bleed air source is in fluid communication with the forward cavity. A seal extends between the first rotor assembly and the second rotor assembly.Type: GrantFiled: September 3, 2015Date of Patent: August 13, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Gabriel L. Suciu, Julian Partyka, David R. Pack, James D. Hill
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Patent number: 10364688Abstract: A minidisk for a rotor system may comprise a balance flange defining a hole array, which may include a first hole having a first width. The first hole may be configured to receive a balance weight. A second hole and a third hole may have a second width. The second hole and the third hole may be disposed adjacent to the first hole. The second width may be greater than the first width.Type: GrantFiled: November 4, 2016Date of Patent: July 30, 2019Assignee: United Technologies CorporationInventors: Raymond S Hummel, Steven D Porter, Julian Partyka
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Patent number: 10323519Abstract: A rotor disc assembly includes a rotor disc and a minidisc. The rotor disc has a first extension member, a first finger, and a second finger. The first extension member axially extends from a disc body disposed about an axis. The first finger extends axially from the first extension member. The second finger is circumferentially spaced apart from the first finger. The second finger extends axially from the first extension member. Each of the first finger and the second finger has a first portion and a second portion that extends radially from a distal end of the first portion. The minidisc is operatively connected to the rotor disc. The minidisc has an interlocking finger that radially extends from a minidisc body and is disposed between the first finger and the second finger. The interlocking finger, the first portion, and second portion define a ring groove.Type: GrantFiled: June 23, 2016Date of Patent: June 18, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Steven D. Porter, Julian Partyka, Raymond S. Hummel
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Patent number: 10309251Abstract: A rotor assembly includes a first rotor, a second rotor mounted on the first rotor and co-rotatable there with, and a thermal shield interlocked with the second rotor for co-rotation there with.Type: GrantFiled: March 10, 2014Date of Patent: June 4, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Jonathan Perry Sandoval, Julian Partyka
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Patent number: 10024183Abstract: A disk-seal arrangement for a gas turbine engine rotor includes a blade retention disk having a longitudinally opening slot therein and a seal disk juxtaposed to said blade retention disk and a single anti-rotation tab received within the blade retention disk slot. The seal disk also includes a pair of balance slots disposed immediately adjacent the antirotation tab to offset the weight thereof for preserving rotor balance. A split ring is disposed longitudinally between the blade retention and seal disks for reacting longitudinal loading therebetween. The ends of the split ring seat against side surfaces of the antirotation between the split ring and the blade retention and seal disks.Type: GrantFiled: March 14, 2014Date of Patent: July 17, 2018Assignee: United Technologies CorporationInventors: Julian Partyka, Jonathan P. Sandoval
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Patent number: 10024238Abstract: A cooling system for providing a buffer cooled cooling air to a turbine section of a gas turbine engine is disclosed. The cooling system may comprise a first conduit configured to transmit a cooling air toward the turbine section, a heat exchanger configured to cool a bleed airflow diverted from the first conduit to provide a buffer air, and a bypass conduit configured to direct at least a portion of the buffer air through at least one passageway that bypasses a bearing compartment of the gas turbine engine. The cooling system may further comprise a manifold configured to allow the cooling air exiting the first conduit and the buffer air exiting the bypass conduit to mix and provide the buffer cooled cooling air, and a nozzle assembly configured to deliver the buffer cooled cooling air to the turbine section.Type: GrantFiled: January 12, 2015Date of Patent: July 17, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Justin J. Phillips, James D. Hill, William K. Ackermann, Chris J. Niggemeier, Gabriel L. Suciu, Anthony R. Bifulco, Julian Partyka
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Publication number: 20180128119Abstract: A minidisk for a rotor system may comprise a balance flange defining a hole array, which may include a first hole having a first width. The first hole may be configured to receive a balance weight. A second hole and a third hole may have a second width. The second hole and the third hole may be disposed adjacent to the first hole. The second width may be greater than the first width.Type: ApplicationFiled: November 4, 2016Publication date: May 10, 2018Applicant: United Technologies CorporationInventors: Raymond S Hummel, Steven D. Porter, Julian Partyka
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Patent number: 9945237Abstract: In accordance with one aspect of the disclosure, a rotor is disclosed. The rotor may include a disk having a central axis, an airfoil radially extending from the disk, a bayonet tab extending radially from the disk, and a lock. The lock may further include a short tab and a long tab, both extending radially from the disk and in an axial direction with respect to the central axis. The long tab may have a greater axial length than the short tab.Type: GrantFiled: December 18, 2013Date of Patent: April 17, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Julian Partyka, Jonathan Perry Sandoval
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Publication number: 20170370224Abstract: A rotor disc assembly includes a rotor disc and a minidisc. The rotor disc has a first extension member, a first finger, and a second finger. The first extension member axially extends from a disc body disposed about an axis. The first finger extends axially from the first extension member. The second finger is circumferentially spaced apart from the first finger. The second finger extends axially from the first extension member. Each of the first finger and the second finger has a first portion and a second portion that extends radially from a distal end of the first portion. The minidisc is operatively connected to the rotor disc. The minidisc has an interlocking finger that radially extends from a minidisc body and is disposed between the first finger and the second finger. The interlocking finger, the first portion, and second portion define a ring groove.Type: ApplicationFiled: June 23, 2016Publication date: December 28, 2017Inventors: Steven D. Porter, Julian Partyka, Raymond S. Hummel
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Publication number: 20170370226Abstract: Mini-disks of gas turbine engines are provided having an axially extending portion extending axially with respect to an axis of the engine, the axially extending portion configured to engage with a hub arm of a compressor of the engine, a radially extending portion extends radially with respect to the axis, the radially extending portion configured to engage with an attachment of a turbine disk of the gas turbine engine, an intermediate portion extending between the axially extending portion and the radially extending portion, and at least one mini-disk connector configured to engage with a portion of the turbine disk of the gas turbine engine to prevent radial movement of the mini-disk during operation.Type: ApplicationFiled: June 23, 2016Publication date: December 28, 2017Inventors: Raymond S. Hummel, Julian Partyka
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Patent number: 9719363Abstract: A seal segment for a gas turbine engine includes a first axial span that extends between the first radial span and the second radial span. A second axial span extends between the first radial span and the second radial span, the first radial span, the second radial span, the first axial span and the second axial span forming a torque box.Type: GrantFiled: June 4, 2015Date of Patent: August 1, 2017Assignee: United Technologies CorporationInventors: David R Pack, Julian Partyka, James D. Hill, Gabriel L Suciu, Gregory M Dolansky, Brian D Merry
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Publication number: 20170191369Abstract: A curvic seal for a gas turbine engine includes a cylindrical seal with a retention feature.Type: ApplicationFiled: March 14, 2014Publication date: July 6, 2017Inventors: Julian Partyka, Scott D Virkler, Jonathan P Sandoval
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Publication number: 20160186666Abstract: A turbine section for a gas turbine engine includes a first rotor assembly with a first rotor assembly bleed air source and an aft cavity that is in fluid communication with the first rotor assembly bleed air source. A second rotor assembly includes a forward cavity. A vane bleed air source is in fluid communication with the forward cavity. A seal extends between the first rotor assembly and the second rotor assembly.Type: ApplicationFiled: September 3, 2015Publication date: June 30, 2016Inventors: Gabriel L. Suciu, Julian Partyka, David R. Pack, James D. Hill