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公开(公告)号：US06206631B1
公开(公告)日：2001-03-27
申请号：US09390877
申请日：1999-09-07
Applicant: Jan C. Schilling
Inventor： Jan C. Schilling
IPC: F01D2524
CPC classification number: F01D21/045 , F01D25/24 , Y02T50/671
Abstract: 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.
Abstract translation: 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 。
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公开(公告)号：US5490764A
公开(公告)日：1996-02-13
申请号：US257602
申请日：1994-05-23
Applicant: Jan C. Schilling
Inventor： Jan C. Schilling
CPC classification number: F01D5/288 , F01D5/16 , Y02T50/672
Abstract: 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.
Abstract translation: 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。
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公开(公告)号：US5299914A
公开(公告)日：1994-04-05
申请号：US757854
申请日：1991-09-11
Applicant: Jan C. Schilling
Inventor： Jan C. Schilling
CPC classification number: F02C7/05 , F01D5/141 , F04D29/324 , F05D2240/301 , Y02T50/672 , Y02T50/673
Abstract: 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.
Abstract translation: 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。
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公开(公告)号：US5205513A
公开(公告)日：1993-04-27
申请号：US765797
申请日：1991-09-26
Applicant: Jan C. Schilling
Inventor： Jan C. Schilling
IPC: B64D27/18
CPC classification number: B64D27/18
Abstract: 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.
Abstract translation: 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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公开(公告)号：US5188505A
公开(公告)日：1993-02-23
申请号：US772302
申请日：1991-10-07
Applicant: Jan C. Schilling , James W. Tucker , Carl C. Koch
Inventor： Jan C. Schilling , James W. Tucker , Carl C. Koch
IPC: F01D21/04
CPC classification number: F01D21/045 , Y02T50/672
Abstract: A containment system for wide chord turbofan fan blades, the system having a containment housing which forms a nesting area to accommodate broken blades and blade parts. Connected to the containment housing and constituting a part of the nesting area are structural rings which are positioned so that centrifugal forces will direct the larger blade fragments to impact upon the structural rings causing the large blade fragments to break into smaller fragments which are then easily housed in the nesting area, thus reducing the required area of the nesting area and minimizing the weight of the containment system.
Abstract translation: 用于宽弦涡扇风扇叶片的容纳系统，该系统具有容纳壳体，其形成嵌套区域以容纳破碎的叶片和叶片部件。 连接到容纳壳体并构成嵌套区域的一部分是结构环，其被定位成使得离心力将引导较大的叶片碎片撞击结构环，导致大的叶片碎片破碎成更小的碎片，然后容易地容纳 在嵌套区域中，因此减少了嵌套区域的所需面积并使密封系统的重量最小化。
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Patent Agency Ranking16.发明授权
公开(公告)号：US5174525A
公开(公告)日：1992-12-29
申请号：US765804
申请日：1991-09-26
Applicant: Jan C. Schilling
Inventor： Jan C. Schilling
IPC: F02C7/20
CPC classification number: F02C7/20
Abstract: A structure for removing bending caused by an inlet lift load in the engine core of an aircraft having a support frame which is attached to a frame mount which connects to the pylon floor. The frame mount is located between a forward mount and a rear mount and to the front of the engine core. As a result of the frame mount, the moment created by the inlet lift load is not reacted through the engine core so engine performance is not affected.
Abstract translation: 一种用于消除由具有支撑框架的飞行器的发动机芯中的入口升程负载引起的弯曲的结构，该支撑框架附接到连接到塔架地板的框架安装件。 框架安装座位于前部安装座和后部安装座之间，并位于发动机机芯的前部。 作为框架安装的结果，由入口提升负载产生的力矩不会通过发动机缸体反作用，因此发动机性能不受影响。
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公开(公告)号：US5102302A
公开(公告)日：1992-04-07
申请号：US201232
申请日：1988-06-02
Applicant: Jan C. Schilling , Charles E. Steckle
Inventor： Jan C. Schilling , Charles E. Steckle
CPC classification number: F01D5/3053 , B64C11/04 , F01D5/16 , B64D2027/026 , Y02T50/66 , Y02T50/672 , Y02T50/673
Abstract: In an aircraft propeller which can change in pitch, each propeller blade is mounted upon a hinge, which reduces the effective stiffness of each blade. The angle of the hinge pin can be constructed such that the angle between torsional and flexural nodes is favorable.
Abstract translation: 在可以改变桨距的飞机螺旋桨中，每个螺旋桨叶片安装在铰链上，这降低了每个叶片的有效刚度。 铰链销的角度可以构造成扭转和弯曲节点之间的角度是有利的。
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公开(公告)号：US20100196147A1
公开(公告)日：2010-08-05
申请号：US12362689
申请日：2009-01-30
Applicant: Jan C. Schilling
Inventor： Jan C. Schilling
CPC classification number: F01D9/041 , F01D5/141 , F01D5/28 , F04D29/023 , F04D29/522 , F04D29/542 , F04D29/646 , F05D2300/50 , F05D2300/522 , Y02T50/672 , Y02T50/673
Abstract: A vane frame for a turbomachine and a method for minimizing the weight of a vane frame. The vane frame includes an inner shroud made up of a plurality of inner shroud segments, an outer shroud circumscribing the inner shroud and made up of a plurality of outer shroud segments, and guide vanes structurally interconnecting the inner and outer shrouds. The guide vanes include a plurality of first guide vanes between and connecting first pairs of the inner and outer shroud segments, and a plurality of second guide vanes between and connecting second pairs of the inner and outer shroud segments. The first and second guide vanes are formed of different first and second materials, respectively, with the first material having lower strength, modulus, and/or density than the second material. The structural interconnection between the inner and outer shrouds is dominated by the second guide vanes.
Abstract translation: 用于涡轮机的叶片框架和用于使叶片框架的重量最小化的方法。 叶片框架包括由多个内护罩段构成的内护罩，外护罩，其围绕内护罩并由多个外护罩区段构成，导向叶片在结构上互连内护罩和外护罩。 导向叶片包括在第一对内护罩段和外护罩段之间并连接第一对内护罩段和外护罩段之间的多个第一导叶，以及在内护罩段和外护罩段之间并连接第二对内护罩段和外护罩区段之间的多个第二导叶。 第一和第二导叶分别由不同的第一和第二材料形成，其中第一材料具有比第二材料低的强度，模量和/或密度。 内外护罩之间的结构互连由第二导叶支配。
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公开(公告)号：US5993152A
公开(公告)日：1999-11-30
申请号：US950084
申请日：1997-10-14
Applicant: Jan C. Schilling
Inventor： Jan C. Schilling
CPC classification number: F01D17/162 , F05D2250/71 , F05D2260/74 , F05D2260/76
Abstract: An actuation system for variable stator vanes pivotally mounted in a casing includes a plurality of levers joined to the respective vanes. An actuation ring coaxially surrounds the casing adjacent to the levers. A plurality of circumferentially spaced apart ring guides are joined to the casing for guiding circumferential rotation of the ring. Respective slip joints are provided between each of the levers and the actuation ring for varying pivot length of the levers as the ring is rotated for effecting nonlinear vane actuation.
Abstract translation: 枢转地安装在壳体中的可变定子叶片的致动系统包括连接到相应叶片的多个杆。 致动环同轴地围绕与杠杆相邻的壳体。 多个周向间隔开的环形引导件接合到壳体以引导环的周向旋转。 在每个杠杆和致动环之间设置有各自的滑动接头，以在环旋转时改变杆的枢转长度，以实现非线性叶片致动。
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公开(公告)号：US5947688A
公开(公告)日：1999-09-07
申请号：US995975
申请日：1997-12-22
Applicant: Jan C. Schilling , Jay L. Cornell , Joseph T. Stevenson
Inventor： Jan C. Schilling , Jay L. Cornell , Joseph T. Stevenson
CPC classification number: F01D5/147 , F01D5/16 , F05D2240/80 , Y02T50/672 , Y02T50/673
Abstract: A fan blade includes a metal airfoil having first and second opposite sides extending radially between a root and tip, and axially between a leading edge and a trailing edge. The airfoil further includes a plurality of pockets disposed in the first side and separated by corresponding ribs. A filler is bonded in the pocket, and is coextensive with the airfoil first side. Radial and diagonal ribs respectively intersect solely each other for selectively increasing torsional and bending stiffness to increase frequency margin between adjacent torsional and bending resonant modes of vibration.
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