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公开(公告)号：US12071855B2
公开(公告)日：2024-08-27
申请号：US17976465
申请日：2022-10-28
发明人： Krzysztof Kowiel
CPC分类号： F01D25/04 , F01D9/065 , F01D25/30 , F16F1/3835 , F16F1/3842 , F05D2230/642 , F05D2250/40 , F05D2260/31 , F05D2260/96 , F16F2224/0225
摘要： An assembly is provided for a gas turbine engine. This engine assembly includes a gas turbine engine case, a conduit and a bushing. The gas turbine engine case includes a case wall and a boss at a port through the case wall. The conduit extends longitudinally along a centerline through the port and into an interior of the gas turbine engine case. The bushing circumscribes the conduit and is arranged within the port. The bushing is engaged with and laterally between the conduit and the boss. The bushing is configured from or otherwise includes a cellular material. The cellular material may be or otherwise include a cellular metal material and/or a cellular composite material.
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公开(公告)号：US12060891B2
公开(公告)日：2024-08-13
申请号：US17509958
申请日：2021-10-25
CPC分类号： F04D29/4206 , F01D25/04 , F04D17/10 , F04D29/4213
摘要： A centrifugal compressor of an aircraft engine includes an impeller and a shroud extending circumferentially around the impeller. A bellmouth disposed upstream of the impeller extends circumferentially and includes: a conduit section extending from a first end to an upstream-most location of the bellmouth, the first end of the conduit section secured to the shroud, and a peripheral section extending from the upstream-most location to a second end located radially outwardly of the first end, the peripheral section located radially outwardly of the conduit section and axially overlapping the conduit section. A stiffening member is located on the peripheral section of the bellmouth proximate the second end. The stiffening member extends circumferentially and provides the bellmouth with a dynamic vibration mode outside a range of dynamic vibration modes of the aircraft engine during operation.
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公开(公告)号：US20240263565A1
公开(公告)日：2024-08-08
申请号：US18618081
申请日：2024-03-27
CPC分类号： F01D25/04 , F01D5/141 , F01D5/145 , F01D5/18 , F01D9/041 , F02K1/827 , G10K11/16 , B64D2033/0226 , F05D2240/121 , F05D2250/184 , F05D2260/96 , F05D2260/961
摘要： An airfoil is provided defining a spanwise direction, a chordwise direction, a root end, a tip end, a leading edge end, and a trailing edge end. The airfoil includes: a leading edge extending from the leading edge end; a body extending along the spanwise direction between the root end and the tip end, the body including a plurality of cavity walls defining a plurality of cavities, each of the plurality of cavities having an inlet located at the leading edge; and a porous face sheet positioned on at least one inlet of the plurality of cavities.
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公开(公告)号：US12049845B2
公开(公告)日：2024-07-30
申请号：US17951619
申请日：2022-09-23
发明人： Nageswar Rao Ganji , Ravindra Shankar Ganiger , Hiranya Kumar Nath , Ambika Shivamurthy , Trevor H. Wood
CPC分类号： F02C6/08 , F01D17/105 , F01D25/04 , F05D2250/131 , F05D2260/606 , F05D2260/963
摘要： Variable bleed valves with struts for aerodynamic stability are described. An apparatus described herein includes a variable bleed valve port, and a strut disposed within the variable bleed valve port, the strut defining a plane and a plurality of holes disposed perpendicularly to the plane, the plurality of holes disposed in a pattern to dampen an acoustic response associated with the variable bleed valve port.
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公开(公告)号：US20240240571A1
公开(公告)日：2024-07-18
申请号：US18155118
申请日：2023-01-17
发明人： Trevor Howard Wood , Kishore Ramakrishnan , William Dwight Gerstler , Changjie Sun , Lana Maria Osusky
CPC分类号： F01D25/12 , F01D9/041 , F01D25/04 , F05D2220/32 , F05D2240/12 , F05D2260/202 , F05D2260/96
摘要： Airfoil include a body extending along a spanwise direction between a root end and a tip end, the body comprising a plurality of acoustic cavities each having an inlet on the airfoil; and at least one cooling channel having an inlet section an outlet section and a middle section within the airfoil extending between the inlet section and the outlet section; and at least one porous face sheet positioned on at least one inlet of the plurality of acoustic cavities.
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公开(公告)号：US11965425B2
公开(公告)日：2024-04-23
申请号：US17828112
申请日：2022-05-31
CPC分类号： F01D25/04 , F01D5/141 , F01D5/145 , F01D5/18 , F01D9/041 , F02K1/827 , G10K11/16 , B64D2033/0226 , F05D2240/121 , F05D2250/184 , F05D2260/96 , F05D2260/961
摘要： An airfoil is provided defining a spanwise direction, a chordwise direction, a root end, a tip end, a leading edge end, and a trailing edge end. The airfoil includes: a leading edge extending from the leading edge end; a body extending along the spanwise direction between the root end and the tip end, the body including a plurality of cavity walls defining a plurality of cavities, each of the plurality of cavities having an inlet located at the leading edge; and a porous face sheet positioned on at least one inlet of the plurality of cavities.
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公开(公告)号：US20240052780A1
公开(公告)日：2024-02-15
申请号：US17819426
申请日：2022-08-12
CPC分类号： F02C7/045 , F01D25/04 , F05D2220/32 , F05D2260/96
摘要： An inlet duct for a nacelle of a ducted fan engine includes an inlet portion at an upstream end of the inlet duct, an acoustic liner arranged downstream of the inlet portion, and a fan section arranged downstream of the acoustic liner. The inlet portion and the acoustic liner are coupled together at an inlet-acoustic liner interface extending circumferentially about the inner surface of the inlet duct, and the acoustic liner and the fan section are coupled together at a fan section hardwall-acoustic liner interface extending circumferentially about the inner surface of the inlet duct. At least one of the acoustic liner, the inlet-acoustic liner interface, and the fan section hardwall-acoustic liner interface having a structure that circumferentially alters a magnitude and a phase of an acoustic wave reflection of the inlet duct to attenuate flutter bite of a fan.
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公开(公告)号：US11815018B2
公开(公告)日：2023-11-14
申请号：US17551935
申请日：2021-12-15
CPC分类号： F02C7/045 , F01D25/04 , F05D2220/32 , F05D2260/962
摘要： A box-shaped air intake silencer with vertical baffles for a gas turbine system. The box-shaped silencer has a silencer housing having opposing ends with a first end closed and a second end opened to permit passage of air. Opposing sidewalls extend between the first end and the second end with each of the sidewalls operative to receive a perpendicular flow of intake air. A silencer having vertically, spaced baffles are disposed within the housing. A first end of the baffles face the first end of the housing and a second end of the baffles faces the second end of the housing. Each of the baffles extend horizontally between the first end and the second end of the housing. The baffles receive the perpendicular flow of intake air proximate the first end of the housing and direct the intake air towards the second end of the housing for passage therethrough.
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公开(公告)号：US11802492B2
公开(公告)日：2023-10-31
申请号：US17749805
申请日：2022-05-20
CPC分类号： F01D25/04 , F01D15/10 , F02C3/04 , F02C6/14 , F02C7/22 , F05D2220/32 , F05D2240/35 , F05D2260/96 , H02K7/003 , H02K7/1823
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：US11754094B2
公开(公告)日：2023-09-12
申请号：US17689260
申请日：2022-03-08
发明人： David A. Topol
CPC分类号： F04D29/661 , F01D5/02 , F01D5/12 , F01D5/26 , F01D9/041 , F01D25/04 , F04D29/324 , F04D29/544 , F04D29/66 , F04D29/663 , F04D29/666 , F05D2260/96 , Y02T50/60
摘要： A gas turbine engine according to an aspect of the present disclosure includes, among other things, a propulsor section, a compressor section including a first compressor and a second compressor, and a turbine section including a first turbine and a second turbine. The first compressor includes a plurality of arrays of airfoils defining a plurality of compressor stages. A number of airfoils in each downstream array of the plurality of arrays is a factor (F) of a number of airfoils in a respective immediately upstream array of the plurality of arrays. The factor (F) is between 1.19 and 1.55 for each of the downstream arrays of the first compressor.
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