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公开(公告)号：US10598015B2
公开(公告)日：2020-03-24
申请号：US15794676
申请日：2017-10-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Nicholas Waters Oren , Ross Wilson
IPC: F16B7/04 , F01D5/02 , F01D25/16 , F02C3/073 , F16B39/282
Abstract: An anti-rotation assembly may include a first shaft, a second shaft, and a locking sprocket. The first shaft may have a first crenelated end rim, the second shaft may have a second crenelated end rim, and the locking sprocket may be configured to engage the first crenelated end rim and the second crenelated end rim to anti-rotatably couple the first shaft to the second shaft. That is, the locking sprocket may be configured to prevent relative rotation between the two shafts. The anti-rotation assembly may further include an axial retaining ring configured to axially retain the locking sprocket.
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公开(公告)号：US20200056482A1
公开(公告)日：2020-02-20
申请号：US16103138
申请日：2018-08-14
Applicant: United Technologies Corporation
Inventor： Nicholas Waters Oren , Ross Wilson
Abstract: A balancing assembly for a rotating component of a gas turbine engine includes a balance weight configured for insertion into a complimentary balance weight slot in the rotating component. The balance weight has a dovetail shaped cross-section and the balance weight slot has a complimentary dovetail shaped cross-section. A retaining ring configured for installation to the rotating component axially retains the balance weight in the balance weight slot. A method of correcting an imbalance of a rotating assembly includes inserting a balance weight into a balance weight slot in a rotating component of the rotating assembly, and installing a retaining ring at the rotating component to retain the balance weight in the balance weight slot in an axial direction. The balance weight has a dovetail shaped cross section, and the balance weight slot has a complimentary dovetail shaped cross section to retain the balance weight at the balance weight slot.
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公开(公告)号：US10539029B2
公开(公告)日：2020-01-21
申请号：US15070789
申请日：2016-03-15
Applicant: United Technologies Corporation
Inventor： Nicholas Waters Oren , Steven D. Porter
Abstract: According to one or more embodiments, a cover plate for a gas turbine engine is provided. The cover plate includes a cover plate body that extends from a disc blade attachment radially along an outside surface of a disc web to a disc bore of a disc creating a cavity between the cover plate body and the disc web of the disc, and an attachment protrusion extending from the inner most end of the cover plate body toward the disc bore, and wherein the attachment protrusion is configured to engage with a retention ring.
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公开(公告)号：US20170268354A1
公开(公告)日：2017-09-21
申请号：US15070789
申请日：2016-03-15
Applicant: United Technologies Corporation
Inventor： Nicholas Waters Oren , Steven D. Porter
CPC classification number: F01D9/02 , F01D5/066 , F01D5/3015 , F01D25/246 , F02C3/04 , F05D2220/32 , F05D2260/30
Abstract: According to one or more embodiments, a cover plate for a gas turbine engine is provided. The cover plate includes a cover plate body that extends from a disc blade attachment radially along an outside surface of a disc web to a disc bore of a disc creating a cavity between the cover plate body and the disc web of the disc, and an attachment protrusion extending from the inner most end of the cover plate body toward the disc bore, and wherein the attachment protrusion is configured to engage with a retention ring.
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公开(公告)号：US10982545B2
公开(公告)日：2021-04-20
申请号：US16392912
申请日：2019-04-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Nicholas Waters Oren , Conway Chuong
Abstract: A rotor assembly is disclosed. In various embodiments, the rotor assembly includes a first rotor having a first plurality of tabs; a second rotor having a second plurality of tabs; and a rotor coupling ring having an anti-rotation tab configured for disposition between an adjacent pair of tabs from one of the first plurality of tabs or the second plurality of tabs.
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Patent Agency Ranking
公开(公告)号：US20170268353A1
公开(公告)日：2017-09-21
申请号：US15070772
申请日：2016-03-15
Applicant: United Technologies Corporation
Inventor： Steven D. Porter , Nicholas Waters Oren
CPC classification number: F01D9/02 , F01D5/02 , F01D5/026 , F01D5/066 , F01D5/3015 , F02C3/04 , F05D2220/32 , F05D2260/30
Abstract: A disc of a gas turbine engine system is provided. The disc includes a disc bore including, an interstage coupling disposed on an axially extending surface at a peripheral edge of the disc bore that includes a protrusion that extends axially beyond an outer surface of the disc bore, and a groove formed on the axially extending surface of the disc bore wherein an aft surface of the groove is also a forward surface of the interstage coupling, wherein the groove includes a forward surface that extends radially into the disc bore to a groove floor that is cut into the disc bore and extends axially to the aft surface that extends radially outward to at least the axially extending surface of the disc bore, and a disc web that extends radially outward from the disc bore, relative to an axis of rotation of the gas turbine engine.
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公开(公告)号：US20170268352A1
公开(公告)日：2017-09-21
申请号：US15070703
申请日：2016-03-15
Applicant: United Technologies Corporation
Inventor： Nicholas Waters Oren , Steven D. Porter
CPC classification number: F01D9/02 , F01D5/02 , F01D5/026 , F01D5/066 , F01D5/082 , F01D5/3015 , F02C3/04 , F05D2220/32 , F05D2260/30 , Y02T50/676
Abstract: A disc of a gas turbine engine system with particular retaining ring placement and engagement implementation are provided. For example, the disc includes a disc bore including, a groove formed on an axially extending surface of the disc bore, wherein the groove includes a forward surface that extends radially into the disc bore to a groove floor that is cut into the disc bore and extends axially to an aft surface that extends radially outward to at least the axially extending surface of the disc bore, and a scallop formed along at least one surface of the groove, wherein the scallop is configured to provide a flow path, and a disc web that extends radially outward from the disc bore, relative to an axis of rotation of the gas turbine engine.
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公开(公告)号：US10883370B2
公开(公告)日：2021-01-05
申请号：US16103138
申请日：2018-08-14
Applicant: United Technologies Corporation
Inventor： Nicholas Waters Oren , Ross Wilson
Abstract: A balancing assembly for a rotating component of a gas turbine engine includes a balance weight configured for insertion into a complimentary balance weight slot in the rotating component. The balance weight has a dovetail shaped cross-section and the balance weight slot has a complimentary dovetail shaped cross-section. A retaining ring configured for installation to the rotating component axially retains the balance weight in the balance weight slot. A method of correcting an imbalance of a rotating assembly includes inserting a balance weight into a balance weight slot in a rotating component of the rotating assembly, and installing a retaining ring at the rotating component to retain the balance weight in the balance weight slot in an axial direction. The balance weight has a dovetail shaped cross section, and the balance weight slot has a complimentary dovetail shaped cross section to retain the balance weight at the balance weight slot.
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公开(公告)号：US20190383144A1
公开(公告)日：2019-12-19
申请号：US16011056
申请日：2018-06-18
Applicant: United Technologies Corporation
Inventor： Nicholas Waters Oren
Abstract: A balancing assembly for a rotating component of a gas turbine engine includes a balance pin configured for insertion into an opening in the rotating component, a balance clip configured for installation to the rotating component over the balance pin to retain the balance pin in the opening via exertion of a retention force on the balance pin. A method of correcting an imbalance of a rotating assembly includes inserting a balance pin into a balancing opening in a rotating component of the rotating assembly, and installing a balance clip at the balancing opening over the balance pin to retain the balance pin in the balancing opening via exertion of a retention force by the balance clip on the balance pin.
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公开(公告)号：US10400615B2
公开(公告)日：2019-09-03
申请号：US15070696
申请日：2016-03-15
Applicant: United Technologies Corporation
Inventor： Nicholas Waters Oren , Steven D. Porter
Abstract: A disc of a gas turbine engine system with particular retaining ring placement and engagement implementation are provided. For example, the disc includes a disc bore including, a groove formed on an axially extending surface of the disc bore, wherein the groove includes a forward surface that extends radially into the disc bore to a groove floor that is cut into the disc bore, and wherein the groove extends axially to an aft surface that extends radially outward to at least the axially extending surface of the disc bore, and a disc web that extends radially outward from the disc bore, relative to an axis of rotation of the gas turbine engine.
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