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公开(公告)号：US20150377041A1
公开(公告)日：2015-12-31
申请号：US14765491
申请日：2013-12-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Julian Partyka , Jonathan Perry Sandoval
CPC classification number: F01D5/32 , F01D5/02 , F01D5/082 , F01D5/12 , F01D5/3015 , F01D5/3046 , F01D11/006 , F02C3/04 , F05D2220/32 , F05D2230/60 , Y02T50/676
Abstract: 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.
Abstract translation: 根据本公开的一个方面，公开了一种转子。 转子可以包括具有中心轴的盘，从盘径向延伸的翼型，从盘径向延伸的卡口接头和锁。 锁可以进一步包括一个短突片和一个长突片，两者都从盘片径向延伸并且沿轴向相对于中心轴线方向延伸。 长突片可以具有比短突片更大的轴向长度。
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公开(公告)号：US11371375B2
公开(公告)日：2022-06-28
申请号：US16544013
申请日：2019-08-19
Applicant: United Technologies Corporation
Inventor： Joshua G. LaPera , Julian Partyka , Timothy J. Harding
Abstract: 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.
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公开(公告)号：US10655480B2
公开(公告)日：2020-05-19
申请号：US14997864
申请日：2016-01-18
Applicant: United Technologies Corporation
Inventor： Steven D. Porter , Julian Partyka
Abstract: 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.
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公开(公告)号：US20180128119A1
公开(公告)日：2018-05-10
申请号：US15343965
申请日：2016-11-04
Applicant: United Technologies Corporation
Inventor： Raymond S Hummel , Steven D. Porter , Julian Partyka
IPC: F01D9/02
CPC classification number: F01D9/02 , F01D5/027 , F01D5/3015 , F01D25/04 , F04D29/662 , F05B2260/966 , F05D2220/32 , F05D2260/941 , F05D2260/96 , G01M1/32 , G01M1/36
Abstract: 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.
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公开(公告)号：US09945237B2
公开(公告)日：2018-04-17
申请号：US14765491
申请日：2013-12-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Julian Partyka , Jonathan Perry Sandoval
CPC classification number: F01D5/32 , F01D5/02 , F01D5/082 , F01D5/12 , F01D5/3015 , F01D5/3046 , F01D11/006 , F02C3/04 , F05D2220/32 , F05D2230/60 , Y02T50/676
Abstract: 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.
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Patent Agency Ranking
公开(公告)号：US20200025210A1
公开(公告)日：2020-01-23
申请号：US14997864
申请日：2016-01-18
Applicant: United Technologies Corporation
Inventor： Steven D. Porter , Julian Partyka
Abstract: 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.
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公开(公告)号：US10364688B2
公开(公告)日：2019-07-30
申请号：US15343965
申请日：2016-11-04
Applicant: United Technologies Corporation
Inventor： Raymond S Hummel , Steven D Porter , Julian Partyka
Abstract: 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.
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公开(公告)号：US20170370226A1
公开(公告)日：2017-12-28
申请号：US15190398
申请日：2016-06-23
Applicant: United Technologies Corporation
Inventor： Raymond S. Hummel , Julian Partyka
CPC classification number: F01D5/066 , F01D5/027 , F01D5/08 , F01D5/082 , F01D5/3015 , F01D11/00 , F01D25/08 , F04D29/321 , F05D2220/32 , F05D2260/941 , Y02T50/676
Abstract: 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.
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公开(公告)号：US20150354389A1
公开(公告)日：2015-12-10
申请号：US14730400
申请日：2015-06-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： David R Pack , Julian Partyka , James D Hill , Gabriel L Suciu , Gregory M Dolansky , Brian D Merry
CPC classification number: F01D11/008 , F01D5/06 , F01D11/001 , F01D11/005 , F05D2220/32 , F05D2240/55 , Y02T50/671
Abstract: 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.
Abstract translation: 用于燃气涡轮发动机的密封段包括在第一径向跨度和第二径向跨度之间延伸的第一轴向跨度。 第二轴向跨度在第一径向跨度和第二径向跨度之间延伸，第一径向跨度，第二径向跨度，第一轴向跨度和第二轴向跨度形成扭矩箱。
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公开(公告)号：US10400603B2
公开(公告)日：2019-09-03
申请号：US15190398
申请日：2016-06-23
Applicant: United Technologies Corporation
Inventor： Raymond S. Hummel , Julian Partyka
Abstract: 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.
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