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1. 发明授权

US09677426B2 Exhaust-gas turbocharger 有权
公开(公告)号：US09677426B2
公开(公告)日：2017-06-13
申请号：US14375484
申请日：2013-02-11
申请人： BorgWarner Inc.
发明人： Martin Becker
IPC分类号： F01D25/24 , F01D5/06
CPC分类号： F01D25/243 , F01D5/066 , F05D2220/40 , F05D2240/00 , F05D2250/192 , F05D2260/31
摘要： An exhaust-gas turbocharger (1) having a compressor (2), which has a compressor housing (3); a turbine (4), which has a turbine housing (5): and a bearing housing (6), which is arranged between the compressor housing (3) and the turbine housing (5) and is connected to the compressor housing (3) by way of a compressor-side connecting device and to the turbine housing (5) by way of a turbine-side connecting device (7). The turbine housing-side and/or compressor-side connecting device (7) is in the form of a taper key bolted joint having bolts (8, 9, 10) which are arranged at least substantially perpendicularly to an exhaust-gas turbocharger longitudinal axis (L).

2. 发明授权

US09611048B2 ATR axial V-groove 有权
公开(公告)号：US09611048B2
公开(公告)日：2017-04-04
申请号：US14187038
申请日：2014-02-21
申请人： United Technologies Corporation
发明人： Gabriel L. Suciu , Jesse M. Chandler
IPC分类号： F01D25/24 , B64D29/06 , F01D25/28 , F01D9/02
CPC分类号： B64D29/06 , F01D9/02 , F01D25/24 , F01D25/28 , F05D2220/32 , F05D2230/70 , F05D2230/72 , F05D2230/80 , F05D2240/121 , F05D2240/122 , F05D2240/128 , F05D2240/1281 , F05D2240/14 , F05D2240/55 , F05D2240/91 , F05D2250/192 , F05D2250/292 , F05D2250/294 , F05D2250/34 , F05D2250/75 , F05D2260/96 , Y10T29/49721
摘要： A gas turbine engine nacelle includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion. A rail is coupled to the fore pylon connecting portion and extends in the aft direction from the first annular portion. A second annular portion is positioned aft of the first portion and coupled to the rail. The second portion is movable along an engine core centerline between a closed position and at least one open position. The second annular portion is configured to engage with the first annular portion in the closed position, thereby providing access to the engine core. A mating axial groove and rib connection is located between the first annular portion and the second annular portion.

3. 发明授权

US09181814B2 Turbine engine compressor stator 有权
标题翻译：涡轮发动机压缩机定子
公开(公告)号：US09181814B2
公开(公告)日：2015-11-10
申请号：US12953688
申请日：2010-11-24
申请人： Hope C. Rowley , Paul W. Baumann , Edwin M. Worth , Carl S. Richardson
发明人： Hope C. Rowley , Paul W. Baumann , Edwin M. Worth , Carl S. Richardson
IPC分类号： F01D9/04 , F04D29/54 , F01D5/20 , F01D11/00 , F04D29/02
CPC分类号： F01D9/041 , F01D5/20 , F01D11/001 , F04D29/023 , F04D29/542 , F04D29/544 , F05D2230/21 , F05D2250/192 , F05D2250/292 , F05D2250/70
摘要： A gas turbine engine stator segment has a shroud band and a plurality of blade sections. Each of the blade sections has a first section with a first thickness, second section with a second thickness and a fairing section transitioning between the first and second section. The second section thickness is less than the first section thickness.
摘要翻译：燃气涡轮发动机定子段具有护罩带和多个叶片部分。每个叶片部分具有第一厚度的第一部分，具有第二厚度的第二部分和在第一和第二部分之间过渡的整流部分。第二部分厚度小于第一部分厚度。

4. 发明授权

US08727695B2 Chamfer-fillet gap for thermal management 有权
标题翻译：倒角焊接间隙用于热管理
公开(公告)号：US08727695B2
公开(公告)日：2014-05-20
申请号：US12634089
申请日：2009-12-09
申请人： Mark Owen Caswell
发明人： Mark Owen Caswell
IPC分类号： F01D25/14 , F01D11/24
CPC分类号： F01D5/082 , F01D5/085 , F01D11/001 , F01D25/12 , F05D2250/192 , F05D2260/20 , Y02T50/676
摘要： An apparatus and method is disclosed herein in which a heat-transfer fluid can be directed through a gap defined between a fillet and a chamfer. The apparatus includes a first member having a body portion and a flange portion projecting from the body portion. The flange portion extends along an endless path encircling an axis to define a receiving aperture. A fillet is defined at a junction of the body portion and an inner surface of the flange portion. The apparatus also includes a second member having a plug portion receivable in the receiving aperture. The plug portion includes a first surface operable to abut the body portion and limit movement of the plug portion into the receiving aperture. The plug portion also includes a second surface slidably engageable with the inner surface of the flange portion to guide movement of the plug portion into the receiving aperture along the axis. A chamfer is defined at a junction of the first and second surfaces such that a gap is defined between the fillet and the chamfer when the plug portion is received in the receiving aperture. The apparatus also includes at least one passageway extending at least partially through at least one of the first member and the second member. The at least one passageway extends between the gap and an opening spaced from the gap. The at least one passageway is operable to receive a heat-transfer fluid to transfer heat relative to the fillet.
摘要翻译：本文公开了一种装置和方法，其中传热流体可以被引导通过在圆角和倒角之间限定的间隙。该装置包括具有主体部分和从主体部分突出的凸缘部分的第一部件。凸缘部分沿着环绕轴线的环形路径延伸以限定接收孔。在本体部分与凸缘部分的内表面的接合部处限定圆角。该装置还包括具有可接收在接收孔中的插头部分的第二构件。插头部分包括可操作以抵靠主体部分并限制插头部分进入接收孔的运动的第一表面。插头部分还包括可与凸缘部分的内表面可滑动地接合的第二表面，以引导插头部分沿轴线移动到接收孔中。在第一和第二表面的接合处限定了倒角，使得当插头部分被接收在接收孔中时，在圆角和倒角之间限定间隙。该装置还包括至少一个至少部分地穿过第一构件和第二构件中的至少一个的通道。所述至少一个通道在所述间隙和与所述间隙间隔开的开口之间延伸。所述至少一个通道可操作以接收传热流体以相对于所述圆角传递热量。

5. 发明申请

US20100272559A1 Chamfer rail pockets for turbine vane shrouds 有权
标题翻译：用于涡轮叶片护罩的倒角轨道槽
公开(公告)号：US20100272559A1
公开(公告)日：2010-10-28
申请号：US11655546
申请日：2007-01-19
申请人： Tracy A. Propheter-Hinckley
发明人： Tracy A. Propheter-Hinckley
IPC分类号： F01D11/08 , B21D53/84
CPC分类号： F01D11/005 , F05D2230/21 , F05D2240/11 , F05D2240/55 , F05D2250/192 , F05D2250/292 , Y02T50/671 , Y10T29/49297
摘要： A shroud rail for retaining a feather seal in a vane shroud of a gas turbine engine comprises a slot for, receiving the feather seal, and a chamfer rail pocket for lightening the shroud rail. The slot traverses the vane shroud and includes a slot base extending from a leading edge to a trailing edge of the shroud rail, and a slot wall extending generally perpendicularly from the slot base. The chamfer rail pocket comprises a pocket wall extending along the slot wall, and a chamfer wall extending from the pocket wall at an angle oblique to the slot base.
摘要翻译：用于将羽毛密封件保持在燃气涡轮发动机的叶片护罩中的护罩导轨包括用于接收羽毛密封件的槽和用于减轻护罩导轨的倒角轨道槽。狭槽横过叶片护罩并且包括从护罩导轨的前缘延伸到后缘的槽基座以及从槽基座大致垂直延伸的槽壁。倒角轨道槽包括沿着槽壁延伸的袋壁和从凹槽壁以与槽基部倾斜的角度延伸的倒角壁。

6. 发明申请

US20090044541A1 APPARATUS AND METHOD FOR REDUCTION OF JET NOISE FROM SINGLE JETS 有权
标题翻译：从单流喷射器减少喷射噪声的装置和方法
公开(公告)号：US20090044541A1
公开(公告)日：2009-02-19
申请号：US12013045
申请日：2008-01-11
申请人： Krishnamurthy Viswanathan
发明人： Krishnamurthy Viswanathan
IPC分类号： F02K1/44 , B23P17/00
CPC分类号： F02K1/48 , F02K1/386 , F02K1/44 , F05D2250/192 , Y10T29/49398
摘要： An exhaust flow nozzle for use with a jet engine. The exhaust flow nozzle includes a beveled downstream edge portion that helps to direct noise generated by the jet engine upwardly away from a ground surface during takeoff and landing operations. One specific embodiment makes use of a linearly moveable flow altering component that is positioned outside the final flow nozzle. When the flow altering component is in its retracted position it has no effect on the exhaust flow leaving the flow nozzle. Alternative embodiments involve the use of varying edge shapes for the final flow nozzle.
摘要翻译：一种用于喷气发动机的排气喷嘴。排气流喷嘴包括斜面的下游边缘部分，其有助于在起飞和着陆操作期间将由喷气发动机产生的噪声引导离开地面。一个具体实施例使用位于最终流动喷嘴外侧的可线性移动的流动改变部件。当流动改变部件处于其缩回位置时，其对离开流动喷嘴的排气流没有影响。替代实施例涉及对最终流动喷嘴使用变化的边缘形状。

7. 发明授权

US07377108B2 Apparatus and method for reduction jet noise from single jets 有权
标题翻译：从单喷嘴减少喷气噪声的装置和方法
公开(公告)号：US07377108B2
公开(公告)日：2008-05-27
申请号：US10822348
申请日：2004-04-09
申请人： Krishnamurthy Viswanathan
发明人： Krishnamurthy Viswanathan
IPC分类号： F02K1/00
CPC分类号： F02K1/48 , F02K1/386 , F02K1/44 , F05D2250/192 , Y10T29/49398
摘要： An exhaust flow nozzle for use with a jet engine. The exhaust flow nozzle includes a beveled downstream edge portion that helps to direct noise generated by the jet engine upwardly away from a ground surface during takeoff and landing operations. One preferred embodiment makes use of a linearly moveable flow altering component that is positioned outside the final flow nozzle. When the flow altering component is in its retracted position it has no effect on the exhaust flow leaving the flow nozzle. Alternative embodiments involve the use of varying edge shapes for the final flow nozzle.
摘要翻译：一种用于喷气发动机的排气喷嘴。排气流喷嘴包括斜面的下游边缘部分，其有助于在起飞和着陆操作期间将由喷气发动机产生的噪声引导离开地面。一个优选实施例使用位于最终流动喷嘴外部的线性可移动流动改变部件。当流动改变部件处于其缩回位置时，其对离开流动喷嘴的排气流没有影响。替代实施例涉及对最终流动喷嘴使用变化的边缘形状。

8. 发明授权

US06824359B2 Turbine blade 有权
标题翻译：涡轮叶片
公开(公告)号：US06824359B2
公开(公告)日：2004-11-30
申请号：US10355664
申请日：2003-01-31
申请人： Wieslaw A. Chlus , Stanley J. Funk
发明人： Wieslaw A. Chlus , Stanley J. Funk
IPC分类号： F01D518
CPC分类号： F01D5/187 , F01D5/189 , F01D5/20 , F05D2230/10 , F05D2230/13 , F05D2240/122 , F05D2240/304 , F05D2250/191 , F05D2250/192 , F05D2250/712 , F05D2260/22141 , F05D2260/607
摘要： A turbine blade has a platform and an airfoil extending from a root at the platform to a tip. The airfoil has an internal cooling passageway network including at least one trailing edge cavity. A group of trailing edge holes extends from the trailing edge to the trailing edge cavity and a group of tip holes extends from the tip to the trailing edge cavity.
摘要翻译：涡轮叶片具有平台和从平台上的根延伸到尖端的翼型件。翼型件具有包括至少一个后缘腔的内部冷却通道网络。一组后缘孔从后缘延伸到后缘腔，并且一组尖端孔从尖端延伸到后缘腔。

9. 发明授权

US06742989B2 Structures of turbine scroll and blades 有权
标题翻译：涡轮机叶片和叶片的结构
公开(公告)号：US06742989B2
公开(公告)日：2004-06-01
申请号：US10270541
申请日：2002-10-16
申请人： Katsuyuki Osako , Shozo Maekawa , Motoki Ebisu , Ryoji Utsumi , Takashi Mikogami
发明人： Katsuyuki Osako , Shozo Maekawa , Motoki Ebisu , Ryoji Utsumi , Takashi Mikogami
IPC分类号： F01D514
CPC分类号： F01D5/048 , F01D9/026 , F05D2220/40 , F05D2250/192 , F05D2250/61
摘要： The improvements are made in the turbine scroll and the turbine blades. The scroll structure for the radial turbines is characterized by the foregoing scroll having a scroll width ratio between the width in the radial direction (&Dgr;R) and the width in the direction of the rotation (B) ranging from &Dgr;R/B=0.3 to 0.7. It is further characterized by the configuration in which the turbine blades have cut-away areas at the blade corners by a prescribed amount, which are provided on the inlet edge at the shroud side and hub side where the operating gas flows.
摘要翻译：在涡轮机涡旋和涡轮机叶片中进行了改进。用于径向涡轮机的涡旋结构的特征在于上述涡旋件具有在径向宽度（DeltaR）和旋转方向（B）之间的宽度范围为ΔR/ B = 0.3至0.7的涡卷宽度比。其特征还在于，涡轮叶片具有在叶片角落处的规定量的切割区域，其设置在工作气体流动的护罩侧和轮毂侧的入口边缘。

10. 发明授权

US4109867A Two-position nozzle 失效
标题翻译：双位喷嘴
公开(公告)号：US4109867A
公开(公告)日：1978-08-29
申请号：US759593
申请日：1977-01-14
申请人： Charles E. Ebeling, Jr.
发明人： Charles E. Ebeling, Jr.
IPC分类号： F02K9/86 , B64D33/04
CPC分类号： F02K9/86 , F05D2250/192
摘要： A dual-position nozzle having a stationary outer support structure or thr holder and an inner sustain throat assembly which translates during boost-sustain transition is provided. The throat holder includes inner and outer metal support rings joined by three tubular struts. During boost operation, the sustain nozzle assembly is mechanically joined to the throat holder by a split beveled retaining ring which is engaged in a groove in the inner metal ring of the throat holder. Upon command, expanding gases act to withdraw a pin from a gap in the retaining ring permitting the sustain nozzle to translate under viscous and pressure forces to the sustain phase position.
摘要翻译：提供了具有固定外部支撑结构或喉部保持器的双位置喷嘴和在升压 - 维持转换期间平移的内部维持喉部组件。喉部保持器包括通过三个管状支柱连接的内部和外部金属支撑环。在升压操作期间，维持喷嘴组件通过分开的斜面保持环机械连接到喉部保持环，所述分离的斜面保持环接合在喉部保持器的内部金属环中的凹槽中。根据命令，膨胀气体用于从保持环中的间隙中取出销，使得维持喷嘴在粘性和压力下平移到维持相位。

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