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公开(公告)号：US20230366323A1
公开(公告)日：2023-11-16
申请号：US18224130
申请日：2023-07-20
CPC分类号： F01D11/003 , F01D25/16 , F05D2240/50 , F05D2240/55 , F05D2250/294 , F05D2250/38
摘要： A bearing compartment seal for a gas turbine engine includes a seal ring that defines an axis and has a radially inward facing sealing surface. A seal runner is configured to rotate relative to the seal ring. The seal runner has a runner surface facing the radially inward facing sealing surface. A plurality of grooves are spaced circumferentially along the runner surface. The plurality of grooves have a length in an axial direction that is at least 50% of an axial length of the runner surface.
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公开(公告)号：US11795821B1
公开(公告)日：2023-10-24
申请号：US17658461
申请日：2022-04-08
发明人： Dikran Mangardich
IPC分类号： F01D5/04
CPC分类号： F01D5/048 , F05D2220/323 , F05D2250/294 , F05D2260/941
摘要： A rotor for an aircraft engine, has: a hub extending circumferentially about a central axis, the hub having a bore, a gaspath-facing surface located radially outwardly of the bore relative to the central axis, a first face extending from the bore to the gaspath-facing surface, and a second face opposite the first face and extending from the bore to the gaspath-facing surface; blades circumferentially distributed about the central axis, the blades protruding away from the gaspath-facing surface of the hub; and a crack mitigator located on the first face, the crack mitigator extending circumferentially relative to the central axis, the crack mitigator extending axially from a baseline surface of the first face.
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公开(公告)号：US11702950B2
公开(公告)日：2023-07-18
申请号：US16388219
申请日：2019-04-18
CPC分类号： F01D11/12 , B05D3/007 , C23C4/01 , C23C4/11 , C23C4/18 , C23C28/042 , F01D11/122 , F01D25/005 , F05D2240/11 , F05D2250/294 , F05D2300/20 , Y02T50/60
摘要： A method of forming a coating includes disposing a substrate having a plurality of protrusions on a seal and layering a topcoat over the protrusions. The method of forming a coating also includes creating a wear pattern and converting the topcoat. A turbine section includes a casing, a plurality of blades within the casing, and a substrate deposited on the casing having a plurality of protrusions. The turbine also includes an unconverted topcoat disposed over the plurality of protrusions, the topcoat having segmented portions defining a plurality of faults extending from the protrusions through the topcoat. A method of forming a coating includes creating a channel in the coating during an initial rub event and converting the coating during a high-temperature event. Converting the coating includes preserving the channel created during the initial rub event.
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公开(公告)号：US20230184122A1
公开(公告)日：2023-06-15
申请号：US17546762
申请日：2021-12-09
CPC分类号： F01D11/003 , F01D25/16 , F05D2240/55 , F05D2240/50 , F05D2250/294 , F05D2250/38
摘要： A bearing compartment seal for a gas turbine engine includes a seal ring that defines an axis and has a radially inward facing sealing surface. A seal runner is configured to rotate relative to the seal ring. The seal runner has a runner surface facing the radially inward facing sealing surface. A plurality of grooves are spaced circumferentially along the runner surface. The plurality of grooves have a length in an axial direction that is at least 50% of an axial length of the runner surface.
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公开(公告)号：US20180087386A1
公开(公告)日：2018-03-29
申请号：US15714112
申请日：2017-09-25
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , F01D5/16 , F01D5/34 , F01D21/045 , F05D2240/304 , F05D2240/80 , F05D2250/141 , F05D2250/294 , F05D2250/75 , F05D2260/941 , F05D2300/437 , F05D2300/501 , Y02T50/671 , Y02T50/673
摘要： The invention relates to a fan blink (28) for an aircraft turbomachine, comprising a hub, an annular platform (42) and fan blades (44) arranged projecting from the annual platform. It also comprises a mechanical discharge slit (52) from a trailing edge (49) of the fan blade, associated with at least one of the fan blades (44), for the case of ingestion of a bird, the slit being made on the annular platform (42) going around the trailing edge (49).
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公开(公告)号：US09879548B2
公开(公告)日：2018-01-30
申请号：US14823604
申请日：2015-08-11
CPC分类号： F01D5/22 , F01D5/16 , F05D2240/30 , F05D2240/80 , F05D2250/182 , F05D2250/294 , F05D2260/96 , Y02T50/67
摘要： A damper system for a turbine having adjacent turbine bucket platforms including opposing slash faces having opposing grooves is provided. The system includes a pin having a substantially cylindrical-shaped body configured for positioning in the opposing grooves. A set of slots are provided in an outer surface of the pin and at spaced axial locations therealong. The set of slots face in a radially outward direction relative to the turbine bucket platforms.
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公开(公告)号：US20180016916A1
公开(公告)日：2018-01-18
申请号：US15207729
申请日：2016-07-12
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/189 , F01D25/12 , F01D25/14 , F05D2220/31 , F05D2220/32 , F05D2240/30 , F05D2250/231 , F05D2250/232 , F05D2250/294 , F05D2260/201 , F05D2260/204 , F05D2260/205 , F05D2260/221
摘要： Various embodiments include a heat transfer device, while other embodiments include a turbine component. In some cases, the device can include: a body portion having an inner surface and an outer surface, the inner surface defining an inner region; at least one aperture in the body portion, the at least one aperture positioned to direct fluid from the inner region through the body portion; and at least one fluid receiving feature formed in the outer surface of the body portion, the at least one fluid receiving feature positioned to receive post-impingement fluid from the at least one aperture, wherein the at least one aperture does not define any portion of the at least one fluid receiving feature, and the at least one fluid receiving feature segregates relatively higher velocity post-impingement fluid from relatively lower velocity fluid within an impingement cross-flow region.
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8.发明申请公开(公告)号：US20180010469A1
公开(公告)日：2018-01-11
申请号：US15547655
申请日：2015-12-08
CPC分类号： C04B41/81 , C04B41/91 , C23C4/134 , C23C16/045 , F01D5/14 , F01D5/147 , F01D5/18 , F01D5/186 , F01D5/28 , F01D5/282 , F01D5/288 , F01D9/023 , F01D11/08 , F01D11/12 , F01D11/122 , F04D29/324 , F04D29/542 , F04D29/5853 , F05D2220/32 , F05D2230/10 , F05D2230/312 , F05D2230/313 , F05D2230/90 , F05D2240/35 , F05D2250/132 , F05D2250/294 , F05D2250/60 , F05D2300/502 , F05D2300/5023 , F05D2300/6033 , Y02T50/672 , Y02T50/673 , Y02T50/676 , Y02T50/6765
摘要： Turbine engine (80) components, such as blades (92), vanes (104, 106), ring segment 110 abradable surfaces 120, or transitions (85), have furcated engineered groove features (EGFs) (403, 404, 418, 509, 511, 512) that cut into the outer surface of the component's thermal barrier coating (TBC). In some embodiments, the EGF planform pattern defines adjoining outer hexagons (560, 640, 670, 690, 710). In some embodiments, the EGF pattern further defines within each outer hexagon (560, 640, 670, 690, 710) a planform pattern of adjoining inner polygons (570, 580, 590, 600, 610, 680, 682, 700, 702, 704, 705, 720). At least three respective groove segments (509, 511, 512) within the EGF pattern (506, 507, 508) converge at each respective outer hexagonal vertex (510, 564) or inner polygonal vertex (574, 564, 604, 614) in a multifurcated pattern, so that crack-inducing stresses are attenuated in cascading fashion, as the stress (σA) is furcated (σB, σC) at each successive vertex juncture.
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公开(公告)号：US09835046B2
公开(公告)日：2017-12-05
申请号：US14608833
申请日：2015-01-29
申请人： ROLLS-ROYCE PLC
发明人： Julian Mark Reed
CPC分类号： F01D21/045 , F01D25/246 , F05D2220/36 , F05D2250/294 , F05D2260/36 , Y02T50/671
摘要： A fan containment system for fitment around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine, including: a fan case having an annular casing element for encircling an array of fan blades and an annular fan track liner lining a radially inner side of the casing element, including a first fan track liner panel positioned circumferentially adjacent a second fan track liner panel. An engagement arrangement engages the first fan track liner panel to the second, extending along at least a portion of adjacent sides of the liner panels, and is configured and the liner panels are shaped such that axial movement of the first fan track liner panel by a distance less than the length of the engagement arrangement, being measured in a direction parallel to the adjacent sides of the liner panels, disengages the first liner panel from the second.
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公开(公告)号：US09759069B2
公开(公告)日：2017-09-12
申请号：US14291104
申请日：2014-05-30
申请人： IHI Corporation
发明人： Kozo Nita , Yoji Okita , Chiyuki Nakamata , Kazuo Yonekura , Seiji Kubo , Osamu Watanabe
CPC分类号： F01D5/18 , F01D5/186 , F01D9/065 , F05D2250/294 , F05D2250/324 , F05D2260/202 , F23R2900/03041 , F23R2900/03043
摘要： The present invention is a turbine blade (1) having a hollow blade body (2). This turbine blade (1) is provided with: cooling air holes (5) that penetrate the blade body (2) from an internal wall surface (2e) to an external wall surface (2f) thereof, and are provided with a straight tube portion (5a) that is located on the internal wall surface (2e) side of the blade body (2), and an expanded diameter portion (5b) that is located on the external wall surface (2f) side of the blade body (2); and with a guide groove (6) that is located on an internal wall of the expanded diameter portion (5b) and that guides cooling air (Y) in the expanded diameter portion (5).
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