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公开(公告)号：US11352903B2
公开(公告)日：2022-06-07
申请号：US16747065
申请日：2020-01-20
Applicant: United Technologies Corporation
Inventor： William S. Pratt , Matthew E. Bintz , Weston Behling , Kevin N. McCusker , Erica J. Harvie
IPC: F01D25/12
Abstract: A rotor stack for a gas turbine engine includes a first rotor disk with a first rotor spacer arm, the first rotor spacer arm having a first flange with an outboard flange surface and an inboard flange surface, a first hole along an axis through the first flange, the first hole having a counterbore in the outboard flange surface; a second rotor disk with a web having a second hole along the axis; a third rotor disk with a third rotor spacer arm, the third rotor spacer arm having a third flange with an outboard flange surface and an inboard flange surface, a third hole along the axis through the third flange, the third hole having a counterbore in the inboard flange surface; and a bushing with a tubular body and a flange that extends therefrom, the tubular body comprising at least one axial groove along an outer diameter thereof, the bushing extends through the first hole, the second hole and partially into the counterbore in the inboard flange surface of the third hole.
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公开(公告)号：US10781707B2
公开(公告)日：2020-09-22
申请号：US16131766
申请日：2018-09-14
Applicant: United Technologies Corporation
Inventor： David M. Dyer , Zachary J. Jeske , Michael Ronan , Matthew E. Bintz , John P. Tirone , Scott Gammons , Michael C. Firnhaber , Mark E. Simonds
Abstract: A vane stage includes a ringcase extending circumferentially about a center axis of the vane stage. The ringcase extends completely about the center axis to form a first ring. An inner shroud extends circumferentially about the center axis of the vane stage. The inner shroud extends completely about the center axis to form a second ring positioned radially within the ringcase relative the center axis. A plurality of stationary half vanes extend radially between the ringcase and the inner shroud, and are circumferentially spaced about the center axis. The plurality of stationary half vanes are integral with the ringcase and the inner shroud.
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公开(公告)号：US20180202362A1
公开(公告)日：2018-07-19
申请号：US15407586
申请日：2017-01-17
Applicant: United Technologies Corporation
Inventor： Matthew E. Bintz , Dilip Prasad
CPC classification number: F02C7/185 , F01D5/081 , F01D25/12 , F02C6/08 , F02C7/18 , F04D27/0207 , F05D2260/205 , F05D2260/207 , F05D2260/212 , F05D2260/232 , F05D2260/601 , Y02T50/675
Abstract: A gas turbine engine includes an engine core having a compressor section, a combustor fluidly connected to the compressor section, and a turbine section fluidly connected to the combustor section. At least one compressor bleed connects a compressor flowpath with a first cooled cooling air path. The first cooled cooling air path includes a supplementary coolant injector connected to a supplementary coolant supply. The cooled cooling air path including a portion exterior to the engine core.
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公开(公告)号：US09879560B2
公开(公告)日：2018-01-30
申请号：US14712999
申请日：2015-05-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Enzo Dibenedetto , Matthew E. Bintz
CPC classification number: F01D17/14 , F01D9/02 , F01D9/042 , F01D17/162 , F05D2220/323 , F05D2230/60
Abstract: A strut-flap vane system for a turbomachine includes a vane strut comprising an airfoil portion and a strut mount extending in a radially outward direction from the airfoil portion. The strut mount forms a hollow semi-cylinder and includes threading on an outer diameter thereof. The system includes an aft mount portion or portions defining a hollow semi-cylinder configured to form a strut cylinder with the strut mount such that the aft mount portion can be disposed in contact with the strut mount to form the strut cylinder. The strut cylinder defines a cylinder opening and the aft mount portion includes threading on an outer diameter thereof that aligns with the threading of the strut mount to allow a strut spanner nut to mesh with both the strut mount and the mount portion.
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公开(公告)号：US20160333726A1
公开(公告)日：2016-11-17
申请号：US14712999
申请日：2015-05-15
Applicant: United Technologies Corporation
Inventor： Enzo Dibenedetto , Matthew E. Bintz
CPC classification number: F01D17/14 , F01D9/02 , F01D9/042 , F01D17/162 , F05D2220/323 , F05D2230/60
Abstract: A strut-flap vane system for a turbomachine includes a vane strut comprising an airfoil portion and a strut mount extending in a radially outward direction from the airfoil portion. The strut mount forms a hollow semi-cylinder and includes threading on an outer diameter thereof. The system includes an aft mount portion or portions defining a hollow semi-cylinder configured to form a strut cylinder with the strut mount such that the aft mount portion can be disposed in contact with the strut mount to form the strut cylinder. The strut cylinder defines a cylinder opening and the aft mount portion includes threading on an outer diameter thereof that aligns with the threading of the strut mount to allow a strut spanner nut to mesh with both the strut mount and the mount portion.
Abstract translation: 用于涡轮机的支柱叶片系统包括：叶片支柱，其包括翼型部分和从翼型部分沿径向向外的方向延伸的支柱安装件。 支柱安装件形成中空的半圆筒，并且包括在其外径上的螺纹。 该系统包括后部安装部分或限定中空半圆柱体的部分，其构造成与支柱安装件形成支柱筒，使得后部安装部分可以布置成与支柱安装件接触以形成支柱筒。 支柱缸限定了气缸开口，并且后部安装部分包括在其外径上的螺纹，其与支柱安装件的螺纹对准，以允许支柱扳手与支柱安装件和安装部分啮合。
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Patent Agency Ranking
公开(公告)号：US20160146033A1
公开(公告)日：2016-05-26
申请号：US14937397
申请日：2015-11-10
Applicant: United Technologies Corporation
Inventor： Ryan Edward LeBlanc , Jordan T. Wall , Matthew E. Bintz
CPC classification number: F01D11/08 , F01D9/041 , F01D11/005 , F01D11/18 , F01D25/145 , F01D25/243 , F01D25/246 , F02C3/00 , F05D2220/32 , F05D2240/12 , F05D2240/15 , F05D2240/58 , F05D2240/80 , F05D2260/231
Abstract: A gas turbine engine includes first and second structures secured to one another at a bolted flange joint. A seal is supported by a third structure. A cover is arranged over the bolted flange joint and discrete from the first and second structures. The cover provides a seal land that engages the piston seal and protects the first structure from the adverse thermal environment.
Abstract translation: 燃气涡轮发动机包括在螺栓法兰接头处彼此固定的第一和第二结构。 密封件由第三结构支撑。 盖子布置在螺栓连接的法兰接头上并且离开第一和第二结构。 该盖提供了一个接合活塞密封件并保护第一个结构免受不良热环境的密封区域。
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公开(公告)号：US20160076378A1
公开(公告)日：2016-03-17
申请号：US14851588
申请日：2015-09-11
Applicant: United Technologies Corporation
Inventor： Matthew E. Bintz , Matthew P. Forcier , Paul J. Hiester
CPC classification number: F01D5/08 , F01D5/06 , F01D5/081 , F01D25/12 , F02C7/18 , F04D29/321 , F04D29/584 , F05D2220/30 , F05D2240/20 , F05D2260/20
Abstract: A rotor disk for a turbomachine includes a disk body, a rim configured to connect to or include a rotor blade disposed on a radially outward portion of the disk body, a bore defined in a radially inward portion of the disk body and configured to be radially adjacent to a shaft, and a thermal regulation aperture defined in the disk body, radially inward of the rim, for allowing flow to pass axially through the disk body when disposed in a stage of a turbomachine, and a thermal regulation aperture defined in the disk body for allowing flow to pass through the disk body when disposed in a stage of a turbomachine.
Abstract translation: 用于涡轮机的转子盘包括盘体，被配置为连接到或包括设置在盘体的径向向外部分上的转子叶片的边缘，限定在盘体的径向向内部分中的孔，并且被构造成径向地 邻近轴，并且限定在盘体中的热调节孔，位于轮辋的径向内侧，用于当设置在涡轮机的阶段中时允许流动轴向地通过盘体;以及限定在盘中的热调节孔 主体，用于当设置在涡轮机的阶段时允许流动通过盘体。
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公开(公告)号：US20210222580A1
公开(公告)日：2021-07-22
申请号：US16747065
申请日：2020-01-20
Applicant: United Technologies Corporation
Inventor： William S. Pratt , Matthew E. Bintz , Weston Behling , Kevin N. McCusker , Erica J. Harvie
Abstract: A rotor stack for a gas turbine engine includes a first rotor disk with a first rotor spacer arm, the first rotor spacer arm having a first flange with an outboard flange surface and an inboard flange surface, a first hole along an axis through the first flange, the first hole having a counterbore in the outboard flange surface; a second rotor disk with a web having a second hole along the axis; a third rotor disk with a third rotor spacer arm, the third rotor spacer arm having a third flange with an outboard flange surface and an inboard flange surface, a third hole along the axis through the third flange, the third hole having a counterbore in the inboard flange surface; and a bushing with a tubular body and a flange that extends therefrom, the tubular body comprising at least one axial groove along an outer diameter thereof, the bushing extends through the first hole, the second hole and partially into the counterbore in the inboard flange surface of the third hole.
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公开(公告)号：US20200232336A1
公开(公告)日：2020-07-23
申请号：US16251674
申请日：2019-01-18
Applicant: United Technologies Corporation
Inventor： William S. Pratt , Matthew E. Bintz , Steven D. Roberts , Adam Hart
Abstract: A vane arm assembly for a gas turbine engine is provided including: a vane arm having a first end, a second end opposite the first end, and an aperture proximate the second end, the aperture being defined by an aperture wall; a vane stem extending through the aperture of the vane arm; a mechanical fastener retaining a position of the vane arm in the longitudinal direction of the vane stem; and an impedance clip partially enclosing a portion of the second end of the vane arm to provide redundant position retention of the vane arm in the longitudinal direction of the vane stem.
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公开(公告)号：US20200088046A1
公开(公告)日：2020-03-19
申请号：US16131766
申请日：2018-09-14
Applicant: United Technologies Corporation
Inventor： David M. Dyer , Zachary J. Jeske , Michael Ronan , Matthew E. Bintz , John P. Tirone , Scott Gammons , Michael C. Firnhaber , Mark E. Simonds
Abstract: A vane stage includes a ringcase extending circumferentially about a center axis of the vane stage. The ringcase extends completely about the center axis to form a first ring. An inner shroud extends circumferentially about the center axis of the vane stage. The inner shroud extends completely about the center axis to form a second ring positioned radially within the ringcase relative the center axis. A plurality of stationary half vanes extend radially between the ringcase and the inner shroud, and are circumferentially spaced about the center axis. The plurality of stationary half vanes are integral with the ringcase and the inner shroud.
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