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公开(公告)号:US20240110484A1
公开(公告)日:2024-04-04
申请号:US17937851
申请日:2022-10-04
CPC分类号: F01D5/16 , F01D9/041 , F01D25/06 , F05D2220/30 , F05D2230/60 , F05D2240/12 , F05D2240/30 , F05D2260/96
摘要: A vibration damping system includes a vibration damping element for a turbomachine nozzle or blade. A body opening extends through the turbomachine nozzle or blade between the tip end and the base end thereof. A vibration damping element includes a volute spring vibration damping element configured to be installed within the body opening in the turbomachine nozzle or blade. The volute spring vibration damping element includes a spiral coil of a metal sheet strip with a surface of the metal sheet strip contacting itself in a direction of an axis of the coil. The body opening has an inner dimension, and the volute spring vibration damping element has an outer dimension sized to frictionally engage the inner dimension of the body opening to dampen vibration. In certain embodiments, the body opening and the volute spring vibration damping element each have a conical perspective shape.
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公开(公告)号:US11913355B2
公开(公告)日:2024-02-27
申请号:US17947589
申请日:2022-09-19
发明人: Nicholas J. Kray , Nitesh Jain , Gary W. Bryant
摘要: Part-span shrouds for pitch controlled aircrafts are disclosed herein. An example apparatus includes a first portion extending from a first airfoil, the first portion including a first surface, the first surface being convex, a second portion extending from a second airfoil towards the first airfoil, the second portion including a second surface the first airfoil circumferentially adjacent to the second airfoil, the second surface being concave, and an interface formed by the first surface and the second surface, the interface reacting circumferential loads between the first airfoil and the second airfoil.
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公开(公告)号:US20240035385A1
公开(公告)日:2024-02-01
申请号:US18264343
申请日:2022-02-01
IPC分类号: F01D5/16
CPC分类号: F01D5/16 , F05D2260/96
摘要: Assembly comprising a body extending around a central axis, the body having an outer surface from which a plurality of blades extend, each of said blades having a blade root and a blade tip, defining an inner radial end and an outer radial end of the blade relative to the central axis, said blades having the same blade height measured radially relative to the central axis, characterized in that each of the blades is connected to the body by its blade root via a connection having a nonzero connection height, so that for the plurality of said blades, the connection height of two successive blades is different.
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公开(公告)号:US11879353B2
公开(公告)日:2024-01-23
申请号:US18049131
申请日:2022-10-24
发明人: Toshio Watanabe , Yuya Fukuda , Shigeki Senoo
CPC分类号: F01D5/143 , F01D5/16 , F01D5/225 , F05D2220/323 , F05D2250/38
摘要: A blade set of the present disclosure is exposed to a working fluid, which includes a blade main bodies which are disposed at intervals in a circumferential direction about an axis and each extending in a radial direction with respect to the axis wherein a tip end surface is formed on an outer circumferential side of each blade main body and the tip end surface of the blade main body includes a leading edge side region positioned on an upstream side in a flow direction of the working fluid along the axis and a trailing edge side region positioned on a downstream side in the flow direction, and a shroud which is provided on an outer circumferential side of the blade main bodies and covering either the leading edge side regions or the trailing edge side regions of the blade main bodies.
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公开(公告)号:US11828191B2
公开(公告)日:2023-11-28
申请号:US17614226
申请日:2020-05-27
发明人: Philippe Gérard Edmond Joly , Romain Nicolas Lagarde , Jean-Marc Claude Perrollaz , Laurent Jablonski , François Jean Comin , Edouard Antoine Dominique Marie De Jaeghere , Charles Jean-Pierre Douguet
CPC分类号: F01D5/16 , F01D5/10 , F01D5/22 , F01D5/26 , F01D25/06 , F05D2220/30 , F05D2240/30 , F05D2260/96
摘要: A turbomachine assembly includes a casing, first and second rotors, and a damper. The first rotor includes a disk and blades and is movable in rotation relative to the casing. The second rotor is movable relative to the casing around a longitudinal axis. The damper damps a movement of the first rotor relative to the second rotor. The damper includes first to third parts. The first part bears on the first rotor in a first area extending over a first angular sector around the longitudinal axis and applies a first centrifugal force on the first rotor. The second part bears on the first rotor in a second area that is smaller than the first angular sector and extends over a second angular sector around the longitudinal axis. The third part bears on the second rotor and applies a second centrifugal force on the second rotor.
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公开(公告)号:US11814982B2
公开(公告)日:2023-11-14
申请号:US17797287
申请日:2021-01-28
发明人: Jean-Philippe Mallat-Desmortiers , Peter Shamma Jeanty , Eric Jacques Delcoigne , Edouard Emmanuel Garreau , Thomas Tsassis , Samuel Laurent Noël Mathieu Juge , Lucas Geoffrey Desbois
CPC分类号: F01D5/142 , F01D5/16 , F05D2260/96
摘要: A rotor vane for an aircraft turbine engine includes a blade extending between an inner platform and an outer platform which carries at least one projecting lip. The blade has a lower surface and an upper surface, and the outer platform includes, on the side of the lower and upper surfaces, lateral edges configured to cooperate in a form-fitting manner with complementary lateral edges of adjacent vanes. Each of the lateral edges has an anti-wear coating, and one of the lateral edges forms a hollow tip (P) with a bowl configured to receive the coating and further including a first concave cylindrical surface portion, the geometric dimensions of which are optimized to limit the risk of cracks appearing when the coating is applied.
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公开(公告)号:US11808175B2
公开(公告)日:2023-11-07
申请号:US17109484
申请日:2020-12-02
CPC分类号: F01D9/041 , F01D5/141 , F01D5/16 , F05D2220/32 , F05D2240/121 , F05D2240/122 , F05D2240/123 , F05D2240/124 , F05D2240/125 , F05D2240/305 , F05D2240/306 , F05D2250/711 , F05D2260/941
摘要: Gas turbine engine (GTE) airfoils, such as rotor and turbofan blades, having multimodal thickness distributions include an airfoil tip, and an airfoil root opposite the airfoil tip in a spanwise direction. The GTE airfoil has a first, second and third locally-thickened region, with the first locally-thickened region defined at the airfoil root. A maximum thickness of each chord between the airfoil root and the airfoil tip transitions toward the leading edge between the first locally-thickened region and the second locally-thickened region, and the third locally-thickened region extends in the spanwise direction. A chord line that extends through the third locally-thickened region contains a first local thickness maxima and a second local thickness maxima interspersed with at least two local thickness minima, and the first local thickness maxima is defined by the third locally-thickened region and is greater than the second local thickness maxima.
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公开(公告)号:US11767765B2
公开(公告)日:2023-09-26
申请号:US17670591
申请日:2022-02-14
CPC分类号: F01D5/16 , F01D5/18 , F01D5/3007 , F05D2220/32 , F05D2230/00 , F05D2260/96
摘要: Rotor blades, vibrational dampening elements, and methods are provided. A rotor blade includes a platform, a shank extending radially inward from the platform, and an airfoil extending radially outward from the platform. One or more fluid chambers are defined within the rotor blade. Glass is disposed within each fluid chamber of the one or more fluid chambers. A mass is disposed within each fluid chamber of the one or more fluid chambers. The mass is movable within the glass relative to the airfoil.
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公开(公告)号:US11719161B2
公开(公告)日:2023-08-08
申请号:US17488690
申请日:2021-09-29
发明人: Bruce L. Morin , David A. Topol , Detlef Korte
IPC分类号: F01D5/02 , F02C7/24 , F02K3/06 , F01D5/12 , F01D9/04 , F01D15/12 , F01D17/10 , F01D5/16 , F01D25/04 , F02C3/107 , F02C7/36
CPC分类号: F02C7/24 , F01D5/02 , F01D5/12 , F01D5/16 , F01D9/041 , F01D15/12 , F01D17/105 , F01D25/04 , F02C3/107 , F02C7/36 , F02K3/06 , F05D2200/36 , F05D2210/31 , F05D2220/32 , F05D2220/327 , F05D2240/301 , F05D2240/307 , F05D2260/40311 , F05D2260/96 , Y02T50/60
摘要: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a propulsor section, a geared architecture, a high spool and a low spool. The high spool includes a high pressure compressor and a high pressure turbine. The low spool includes a low pressure compressor and a low pressure turbine. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to 1.55. A mechanical tip rotational Mach number of the blades is greater than or equal to 0.5 at an approach speed.
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公开(公告)号:US11713686B2
公开(公告)日:2023-08-01
申请号:US16613201
申请日:2018-05-16
CPC分类号: F01D5/28 , F01D5/147 , F01D5/16 , F05D2220/36 , F05D2240/121 , F05D2260/96 , F05D2300/514
摘要: An outlet guide vane for a turbofan engine, which results in reduced noise. The outlet guide vane may comprise an aerofoil, the aerofoil comprising at least porous section, wherein the at least one channel or porous section is positioned near the leading edge of the aerofoil.
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