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1. 发明授权

US06233823B1 Method of making plastically formed hybrid airfoil 失效
标题翻译：制造塑性混合翼型的方法
公开(公告)号：US06233823B1
公开(公告)日：2001-05-22
申请号：US09588077
申请日：2000-06-06
申请人： Jan C. Schilling
发明人： Jan C. Schilling
IPC分类号： B23P1500
CPC分类号： F01D5/147 , F04D29/023 , F04D29/388 , F05D2300/43 , Y02T50/672 , Y02T50/673 , Y10T29/49336 , Y10T29/49337
摘要： A plain blank is sized to produce an airfoil. The blank is plastically formed to include a pocket blending smoothly in one side thereof. Leading and trailing edges of the airfoil are benched. And, filler is placed into the pocket to effect an aerodynamic profile for the airfoil.
摘要翻译：一个普通的坯料的大小可以产生一个翼型。坯料被塑性地形成为包括在其一侧平滑地混合的口袋。机翼的前缘和后缘均匀。并且，将填料放入口袋中以实现翼型的空气动力学特性。

2. 发明授权

US6099257A Plastically formed hybrid airfoil 失效
标题翻译：塑性混合翼型
公开(公告)号：US6099257A
公开(公告)日：2000-08-08
申请号：US386424
申请日：1999-08-31
申请人： Jan C. Schilling
发明人： Jan C. Schilling
IPC分类号： F01D5/14 , F04D29/02 , F04D29/38 , B63H1/26
CPC分类号： F01D5/147 , F04D29/023 , F04D29/388 , F05D2300/43 , Y02T50/672 , Y02T50/673 , Y10T29/49336 , Y10T29/49337
摘要： A plain blank is sized to produce an airfoil. The blank is plastically formed to include a pocket blending smoothly in one side thereof. Leading and trailing edges of the airfoil are benched. And, filler is placed into the pocket to effect an aerodynamic profile for the airfoil.
摘要翻译：一个普通的坯料的大小可以产生一个翼型。坯料被塑性地形成为包括在其一侧平滑地混合的口袋。机翼的前缘和后缘均匀。并且，将填料放入口袋中以实现翼型的空气动力学特性。

3. 发明授权

US6039542A Panel damped hybrid blade 失效
标题翻译：面板阻尼混合叶片
公开(公告)号：US6039542A
公开(公告)日：2000-03-21
申请号：US997832
申请日：1997-12-24
申请人： Jan C. Schilling , Jay L. Cornell , Joseph T. Stevenson
发明人： Jan C. Schilling , Jay L. Cornell , Joseph T. Stevenson
IPC分类号： F04D29/38 , F01D5/16 , F02K3/04 , B64C11/16
CPC分类号： F01D5/16 , F05D2220/36 , Y02T50/672 , Y02T50/673 , Y10S416/50
摘要： A fan blade includes a metal airfoil having first and second opposite sides extending radially between a root and a tip, and axially between a leading edge and a trailing edge. The airfoil further includes a pocket disposed in the first side having an elastomeric filler bonded therein. A panel is bonded to the filler along the pocket for allowing differential movement therebetween for damping vibratory response of the airfoil.
摘要翻译：风扇叶片包括具有在根部和尖端之间径向延伸的第一和第二相对侧以及在前缘和后缘之间的轴向的金属翼型件。机翼还包括设置在第一侧中的口袋，其中粘合有弹性体填料。面板沿着口袋粘合到填料上，以允许它们之间的差动运动来阻止翼型的振动响应。

4. 发明授权

US5630319A Dome assembly for a multiple annular combustor 失效
标题翻译：多环形燃烧器的圆顶组件
公开(公告)号：US5630319A
公开(公告)日：1997-05-20
申请号：US440437
申请日：1995-05-12
申请人： Jan C. Schilling , Edward C. Vickers
发明人： Jan C. Schilling , Edward C. Vickers
IPC分类号： F23R3/10 , F23R3/28 , F23R3/34 , F02C1/00
CPC分类号： F23R3/10 , F23R3/283 , F23R3/346 , F05B2230/60 , F05B2230/70 , F05B2230/80
摘要： A dome assembly for a multiple annular combustor is disclosed as including an annular dome plate having at least two radial domes, wherein each of the radial domes include a plurality of circumferentially spaced openings therein. A heat shield is positioned within each of the openings, with a threaded forward end located upstream of the dome plate and an aft end located downstream of the dome plate. A retainer nut with threads formed on an annular surface thereof is matingly engagable with the forward end of each heat shield. When the retainer nut is tightened onto the heat shield forward end, the heat shield is mechanically attached to the dome plate. Preferably, at least one centerbody extends axially downstream from either the radially outer or inner side of the aft end. The dome assembly includes a ferrule within each of the dome plate openings for receiving an air/fuel mixer therein, the ferrule having an annular sealing flange extending radially therefrom. A retaining ring is positioned upstream of the heat shield forward end to produce a gap therebetween. The ferrule sealing flange is positioned within the gap to prevent air from flowing between the heat shield and the air/fuel mixer.
摘要翻译：公开了一种用于多环形燃烧器的圆顶组件，包括具有至少两个径向圆顶的环形圆顶板，其中每个径向圆顶包括多个周向间隔开的开口。隔热罩设置在每个开口内，螺纹前端位于圆顶板的上游，后端位于圆顶板的下游。具有形成在其环形表面上的螺纹的保持螺母与每个隔热罩的前端配合地接合。当保持螺母拧紧到隔热罩前端时，隔热罩机械地连接到圆顶板。优选地，至少一个中心体从后端的径向外侧或内侧的轴向延伸。圆顶组件包括在每个圆顶板开口内的用于在其中容纳空气/燃料混合器的套圈，套圈具有从其径向延伸的环形密封凸缘。保持环位于隔热罩前端的上游，以在它们之间产生间隙。套圈密封法兰位于间隙内，以防止空气在隔热罩和空气/燃料混合器之间流动。

5. 发明授权

US5282358A Gas turbine engine dual inner central drive shaft 失效
标题翻译：燃气涡轮发动机双内中心驱动轴
公开(公告)号：US5282358A
公开(公告)日：1994-02-01
申请号：US705844
申请日：1991-05-28
申请人： Jan C. Schilling
发明人： Jan C. Schilling
IPC分类号： F01D5/02 , F16C3/02 , F16D1/02 , F02K3/02
CPC分类号： F16C3/02 , F01D5/026 , F16D1/02
摘要： A dual inner central drive shaft in a gas turbine engine includes rearward and forward shaft portions which overlap and interengage with one another. The rearward shaft portion includes an elongated cylindrical inner middle portion and a rear conical end portion, whereas the forward shaft portion includes an elongated cylindrical outer middle portion and a front conical end portion. The respective opposite ends of the inner and outer middle portions of the rearward and forward shaft portions have intermeshing rear and front sets of radially projecting and circumferentially spaced splines which extend parallel to the shaft axis so as to rigidly secure the outer and inner middle portions of the rearward and forward shaft portions together for concurrent rotary motion of the rearward and forward shaft portions in both clockwise and counterclockwise directions.
摘要翻译：燃气涡轮发动机中的双内中心驱动轴包括彼此重叠和相互接合的向后和向前的轴部分。后轴部包括细长的圆筒形的中间部分和后锥形端部，而前轴部分包括细长的圆筒形外部中间部分和前部锥形端部。后轴和前轴部分的内外中间部分的相应两端具有相互啮合的后组和前组，其径向突出且周向间隔开的花键平行于轴的轴线延伸，以便刚性地将向后和向前的轴部分一起用于顺时针和逆时针方向上的向后和向前轴部分的同时旋转运动。

6. 发明授权

US4190397A Windage shield 失效
标题翻译：防风盾
公开(公告)号：US4190397A
公开(公告)日：1980-02-26
申请号：US854186
申请日：1977-11-23
申请人： Jan C. Schilling , James E. Gutknecht
发明人： Jan C. Schilling , James E. Gutknecht
IPC分类号： F01D25/24 , F02C7/18 , F02C7/24
CPC分类号： F01D25/243 , F02C7/18 , F02C7/24 , F05B2260/301 , F05D2260/97
摘要： An improved windage shield is provided for use with turbomachinery members partially defining an internal flow path wherein the members are connected by a fastener which protrudes beyond one of the members. The windage shield comprises a portion which is captured between the fastener and one of the members and a cylindrical section which extends downstream of the members to form a smooth cover for isolating the members from the internal fluid flow. The protruding fastener end is recessed into, and generally flush with, the captured portion of the windage shield.
摘要翻译：提供了一种改进的防风罩，用于部分地限定内部流动路径的涡轮机构构件，其中构件通过突出超过其中一个构件的紧固件连接。防风罩包括被捕获在紧固件和其中一个构件之间的部分，以及在构件的下游延伸以形成用于将构件与内部流体流隔离的平滑盖的圆柱形部分。突出的紧固件端部与所述防风罩的所捕获的部分凹入并且通常与其齐平。

7. 发明授权

US06206631B1 Turbomachine fan casing with dual-wall blade containment structure 失效
标题翻译：涡轮机风扇外壳采用双壁叶片安全壳结构
公开(公告)号：US06206631B1
公开(公告)日：2001-03-27
申请号：US09390877
申请日：1999-09-07
申请人： Jan C. Schilling
发明人： Jan C. Schilling
IPC分类号： F01D2524
CPC分类号： F01D21/045 , F01D25/24 , Y02T50/671
摘要： A blade containment structure for turbomachinery, such as a high bypass turbofan engine. The blade containment structure includes a first casing member having a wall that defines an inner containment shell that immediately surrounds the blades of the turbomachine, and a second casing member assembled to the first casing member. The second casing member has a wall that defines an outer containment shell that surrounds the inner containment shell, such that a cavity is defined by and between the inner and outer containment shells. The first casing member is formed from a high-toughness material such as steel or a nickel-base alloy, while the second casing member is formed from a lower-weight and potentially lower-toughness material as compared to the material of the first casing member.
摘要翻译：用于涡轮机械的叶片容纳结构，例如高旁通涡轮风扇发动机。叶片容纳结构包括具有壁的第一壳体构件，该壁限定了立即围绕涡轮机的叶片的内部容纳壳体，以及组装到第一壳体构件的第二壳体构件。第二壳体构件具有限定围绕内部容纳壳体的外部容纳壳体的壁，使得空腔由内部和外部容纳壳体限定并在其之间。第一壳体构件由诸如钢或镍基合金的高韧性材料形成，而第二壳体构件由与第一壳体构件的材料相比较低重量且潜在地较低韧性的材料形成。

8. 发明授权

US5490764A Unshrouded blading for high bypass turbofan engines 失效
标题翻译：无旁路叶片用于高旁路涡扇发动机
公开(公告)号：US5490764A
公开(公告)日：1996-02-13
申请号：US257602
申请日：1994-05-23
申请人： Jan C. Schilling
发明人： Jan C. Schilling
IPC分类号： F01D5/16 , F01D5/28
CPC分类号： F01D5/288 , F01D5/16 , Y02T50/672
摘要： Metal alloy fan blades reinforced with a metal matrix composite for enhancing stiffness of the fan blades without a significant weight penalty, and which are suitable for use in high bypass turbofan engines. The metal matrix composite is bonded to each fan blade near its root so as to increase stiffness and thereby provide frequency and stability control to the fan blades. As a result, a lower engine weight can be realized by using more fan blades without the need for a part span shroud.
摘要翻译：金属合金风扇叶片用金属基质复合材料增强，用于增强风扇叶片的刚度，而不会显着减轻重量，适用于高旁路涡扇风机。金属基复合材料在其根部附近结合到每个风扇叶片，以增加刚度，从而为风扇叶片提供频率和稳定性控制。因此，通过使用更多的风扇叶片而不需要部分跨度护罩，可以实现较低的发动机重量。

9. 发明授权

US5299914A Staggered fan blade assembly for a turbofan engine 失效
标题翻译：用于涡轮风扇发动机的交错风扇叶片组件
公开(公告)号：US5299914A
公开(公告)日：1994-04-05
申请号：US757854
申请日：1991-09-11
申请人： Jan C. Schilling
发明人： Jan C. Schilling
IPC分类号： F01D5/14 , F02C7/05 , F04D29/32
CPC分类号： F02C7/05 , F01D5/141 , F04D29/324 , F05D2240/301 , Y02T50/672 , Y02T50/673
摘要： A turbofan gas turbine engine fan stage having alternating relatively rugged, preferably hollow titanium, blades and staggered relatively less rugged, preferably composite, blades. The blades are staggered such that the leading edges of the rugged titanium blades are positioned forward of the leading edges of the less rugged composite blades. One embodiment provides that all fan blades have trailing edges at the same axial position while another embodiment provides that all fan blades are of the same size and shape.
摘要翻译：涡轮风扇燃气涡轮发动机风扇台具有交替相对粗糙的，优选中空的钛，叶片和交错相对较不坚固，优选复合的叶片。刀片交错，使得坚固的钛刀片的前缘位于较不坚固的复合刀片的前缘的前方。一个实施例提供了所有风扇叶片具有相同轴向位置的后缘，而另一实施例规定所有风扇叶片具有相同的尺寸和形状。

10. 发明授权

US5205513A Method and system for the removal of large turbine engines 失效
标题翻译：拆除大型涡轮发动机的方法和系统
公开(公告)号：US5205513A
公开(公告)日：1993-04-27
申请号：US765797
申请日：1991-09-26
申请人： Jan C. Schilling
发明人： Jan C. Schilling
IPC分类号： B64D27/18
CPC分类号： B64D27/18
摘要： A detachable support structure for a large turbine aircraft engine having a nacelle which is attached to an auxiliary support frame. The auxiliary support frame has an upper portion which is attached to an upper portion of the nacelle. The auxiliary support frame has a lower portion which is detachable from the upper portion of the auxiliary frame. The lower portion of the auxiliary frame is connected to a lower portion of the nacelle, the lower portion of the nacelle being detachable from the upper portion of the nacelle. By removing the lower portion of the nacelle and the lower portion of the auxiliary support frame, the thrust producing section of the turbine engine can be removed intact.
摘要翻译：用于具有附接到辅助支撑框架的机舱的大型涡轮机飞机发动机的可拆卸支撑结构。辅助支撑框架具有附接到机舱的上部的上部。辅助支撑框架具有可从辅助框架的上部分离的下部。辅助框架的下部连接到机舱的下部，机舱的下部可从机舱的上部分离。通过移除机舱的下部和辅助支撑架的下部，涡轮发动机的推力产生部分可以被完整地移除。

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