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公开(公告)号：US11603903B2
公开(公告)日：2023-03-14
申请号：US17156135
申请日：2021-01-22
摘要： A rotating machine system can include a rotating machine. The rotating machine system can include a housing. The housing can include an inner surface. The housing can surround at least a portion of the rotating machine. The inner surface of the housing can be spaced from the rotating machine such that a space is defined therebetween. The rotating machine system can include one or more super elastic wires. The one or more super elastic wires can be positioned in the space and can be operatively connected to the rotating machine and the inner surface of the housing. The one or more super elastic wires can reduce vibration within the rotating machine system.
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公开(公告)号：US11560849B2
公开(公告)日：2023-01-24
申请号：US17503814
申请日：2021-10-18
发明人： Bruce L. Morin , David A. Topol , Detlef Korte
IPC分类号： F02C7/24 , F02K3/06 , F01D5/02 , F01D5/12 , F01D9/04 , F01D15/12 , F01D17/10 , F01D5/16 , F01D25/04 , F02C3/107 , F02C7/36
摘要： A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a propulsor section including a propulsor, a turbine section including a first turbine and a second turbine, a compressor section driven by the turbine section, the compressor section including a first compressor and a second compressor, and a geared architecture driven by the first turbine. The propulsor is driven by the first turbine via the geared architecture. 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 configured to be greater than or equal to 0.5 at an approach speed.
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公开(公告)号：US11525464B2
公开(公告)日：2022-12-13
申请号：US17209303
申请日：2021-03-23
发明人： Maksim Pankratov
IPC分类号： F04D29/66 , F02C7/00 , F01D5/10 , F01D25/04 , F16F15/129
摘要： A gas turbine engine rotor having an axis, comprising: a body about the axis having an inner surface, a seat having an outer seat edge at a first radial location surrounded by the inner surface at a second radial location, a lip along the inner surface having an inner lip edge spaced axially away from the seat to define a gap, the lip at a rated axial location between the inner lip edge and the seat facing toward the seat at a normal angle; a damper in the gap having first and second damper surfaces, the first damper surface adjacent the seat; and a split ring in the gap adjacent the second damper surface, having an outer ring edge spaced from the inner surface, engaging the lip at the rated axial location and resiliently expandable against the lip deflects the split ring to load the damper against the seat.
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公开(公告)号：US11350223B2
公开(公告)日：2022-05-31
申请号：US16886836
申请日：2020-05-29
发明人： Shinichi Sasaki , Takaaki Asada
IPC分类号： H04R23/00 , H04R1/10 , B32B38/08 , F01D25/04 , H04R31/00 , B32B37/10 , H04R29/00 , H04R19/00
摘要： A thermal excitation acoustic-wave-generating device includes a first acoustic wave source that includes a first heating element and a substrate that includes a main surface along which the first heating element is disposed, a second acoustic wave source that includes a second heating element and a facing body that includes a main surface along which the second heating element is disposed, and a pair of electrodes connected to the first and second heating elements. The first and second acoustic wave sources are arranged such that the first and second heating elements are separated from each other and face each other. The pair of electrodes are disposed between the first and second acoustic wave sources.
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公开(公告)号：US11346243B2
公开(公告)日：2022-05-31
申请号：US15491638
申请日：2017-04-19
摘要： The present disclosure is directed to a gas turbine engine assembly having a compressor configured to increase pressure of incoming air, a combustion chamber, at least one turbine coupled to a generator, a torsional damper, and a controller. The combustion chamber is configured to receive a pressurized air stream from the compressor. Further, fuel is injected into the pressurized air in the combustion chamber and ignited so as to raise a temperature and energy level of the pressurized air. The turbine is operatively coupled to the combustion chamber so as to receive combustion products that flow from the combustion chamber. The generator is coupled to the turbine via a shaft. Thus, the torsional damper is configured to dampen torsional oscillations of the generator. Moreover, the controller is configured to provide additional damping control to the generator.
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公开(公告)号：US11248675B2
公开(公告)日：2022-02-15
申请号：US16262222
申请日：2019-01-30
发明人： Leszek Marek Rzeszutek , Christopher Charles Glynn , Darek Tomasz Zatorski , Jakub Jan Broniszewski
摘要： The present application relates to a frictional damper, a frictional damper assembly and method for installing the frictional damper. The frictional damper comprises a split ring; and a disk spring positioned against the split ring and tensioned by the split ring in an installed state.
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公开(公告)号：US11111816B2
公开(公告)日：2021-09-07
申请号：US16409115
申请日：2019-05-10
申请人： ROLLS-ROYCE plc
发明人： Bharat M. Lad
摘要： The blades for a rotor of a gas turbine engine are all manufactured to the same design. However, manufacturing tolerances mean that in practice each individual blade is different to the others. It is proposed to arrange the blades around the circumference of the rotor in a manner that limits excessive stress being induced in the blades due to differences in the vibration response between a given blade and its two neighbouring blades.
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公开(公告)号：US20210215064A1
公开(公告)日：2021-07-15
申请号：US17023907
申请日：2020-09-17
摘要： A bracket assembly includes a first bracket arranged along a damping axis and having a clevis body, a second bracket, and a vibration isolator including an elastomeric body. The second bracket is arranged along the damping axis and has a clevis portion and a mount portion. The clevis portion slidably receives the clevis body of the first bracket. The elastomeric body is arranged axially between the first bracket and the second bracket and is fixedly arranged between the clevis portion of the second bracket and the clevis body of the first bracket through an on-axis load path and through an off-axis load path extending through the bracket assembly. Actuator arrangements and methods of damping vibrational forces are also described.
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公开(公告)号：US11035254B2
公开(公告)日：2021-06-15
申请号：US16723815
申请日：2019-12-20
发明人： Katsumi Azuma , Kouichirou Ishihara
IPC分类号： F01D25/24 , F01D9/02 , F02B37/18 , F01D17/10 , F01D25/04 , F01D9/04 , F01D25/00 , F02B37/00 , F01D5/04 , F02B33/40
摘要： Turbine housing assemblies and related turbocharger systems are provided. One exemplary turbine housing assembly includes a core structure having a voided inner region defining an axial outlet and an outer surface defining an inner contour of a volute and an inner sheet metal shell having an inner base portion defining an inlet in fluid communication with the volute and a volute portion defining an outer contour of the volute, wherein at least a portion of the core structure defining the axial outlet extends in an axial direction through an opening in the inner sheet metal shell defined by the volute portion. The turbine housing assembly also includes an outer sheet metal shell surrounding the volute portion and including an outer base portion circumscribing the inner base portion.
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公开(公告)号：US11021998B2
公开(公告)日：2021-06-01
申请号：US16535231
申请日：2019-08-08
摘要： A support assembly for a bearing of a gas turbine engine includes a shaft extending along an axial direction. The support assembly includes an outer race positioned radially exterior to the bearing such that the outer race supports the bearing. Additionally, the support assembly includes a shape memory alloy damper positioned radially exterior to the outer race and at least partially supporting the outer race. Moreover, the shape memory alloy damper includes a plurality of sleeves. One or more sleeves of the plurality of sleeves include a shape memory alloy material.
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