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1. 发明授权

US5215442A Turbine blade platform damper 失效
标题翻译：涡轮叶片平台阻尼器
公开(公告)号：US5215442A
公开(公告)日：1993-06-01
申请号：US770839
申请日：1991-10-04
申请人： Charles E. Steckle , Philip W. Dietz , Kenneth Willgoose
发明人： Charles E. Steckle , Philip W. Dietz , Kenneth Willgoose
IPC分类号： F01D5/16 , F01D5/22
CPC分类号： F01D5/22 , Y02T50/673 , Y10S416/50 , Y10T29/49337
摘要： A vibration damper for rotor blades of a gas turbine engine has a shaft and a contact head connected thereto. The shaft is slidably inserted in a cylindrical recess incorporated in the rotor blade platform. During rotation of the rotor disk, the shaft of the damping member slides along the shaft axis, whereby the damping member is moved at least in the radial and circumferential directions by centrifugal forces. The contact head of the damping member of one rotor blade finally bears against the platform portion of an adjacent rotor blade, serving to damp vibratory motion of both blades.

2. 发明授权

US5369882A Turbine blade damper 失效
标题翻译：涡轮叶片阻尼器
公开(公告)号：US5369882A
公开(公告)日：1994-12-06
申请号：US144368
申请日：1993-11-02
申请人： Philip W. Dietz , Charles E. Steckle , Robert J. Corsmeier
发明人： Philip W. Dietz , Charles E. Steckle , Robert J. Corsmeier
IPC分类号： F01D5/22 , B23P15/00
CPC分类号： F01D5/22 , Y02T50/671 , Y02T50/673 , Y10S416/50 , Y10T29/49318 , Y10T29/49321 , Y10T29/49325
摘要： A generally wedge-shaped vibration damper for rotor blades of a gas turbine engine has a pair of scrubbing surfaces and is loosely retained in a pocket incorporated in the rotor blade platform. The pocket is partly defined by a plurality of surfaces which orient the damper so that it is slidably displaceable and rotatable only in a predetermined plane. During rotation of the rotor disk, the damper of one rotor blade is displaced in a plane transverse to the rotor axis of rotation by centrifugal forces to a position at which one scrubbing surface of the damper abuts a side surface of the platform of the adjacent rotor blade and the other scrubbing surface abuts an inner surface of the platform of the rotor blade in which the damper is inserted. The scrubbing action of the damper serves to damp vibratory motion in the platforms of both blades.
摘要翻译：用于燃气涡轮发动机的转子叶片的大致楔形振动阻尼器具有一对擦洗表面，并且松散地保持在并入转子叶片平台中的凹穴中。口袋部分地由多个表面限定，这些表面使阻尼器定向，使得其仅在预定平面内可滑动地移位和旋转。在转子盘的旋转期间，一个转子叶片的阻尼器在垂直于转子旋转轴线的平面中通过离心力移动到阻尼器的一个擦洗表面抵靠相邻转子的平台的侧表面的位置叶片和另一个擦洗表面邻接在其中插入阻尼器的转子叶片的平台的内表面。阻尼器的擦洗动作用于减弱两个叶片的平台中的振动运动。

3. 发明授权

US5302085A Turbine blade damper 失效
公开(公告)号：US5302085A
公开(公告)日：1994-04-12
申请号：US830143
申请日：1992-02-03
申请人： Philip W. Dietz , Charles E. Steckle , Robert J. Corsmeier
发明人： Philip W. Dietz , Charles E. Steckle , Robert J. Corsmeier
IPC分类号： F01D5/22 , F01D5/26
CPC分类号： F01D5/22 , Y02T50/671 , Y02T50/673 , Y10S416/50 , Y10T29/49318 , Y10T29/49321 , Y10T29/49325
摘要： A generally wedge-shaped vibration damper for rotor blades of a gas turbine engine has a pair of scrubbing surfaces and is loosely retained in a pocket incorporated in the rotor blade platform. The pocket is partly defined by a plurality of surfaces which orient the damper so that it is slidably displaceable and rotatable only in a predetermined plane. During rotation of the rotor disk, the damper of one rotor blade is displaced in a plane transverse to the rotor axis of rotation by centrifugal forces to a position at which one scrubbing surface of the damper abuts a side surface of the platform of the adjacent rotor blade and the other scrubbing surface abuts an inner surface of the platform of the rotor blade in which the damper is inserted. The scrubbing action of the damper serves to damp vibratory motion in the platforms of both blades.

4. 发明授权

US5165856A Fan blade mount 失效
标题翻译：风扇叶片安装
公开(公告)号：US5165856A
公开(公告)日：1992-11-24
申请号：US658273
申请日：1991-02-20
申请人： Jan C. Schilling , Charles E. Steckle
发明人： Jan C. Schilling , Charles E. Steckle
IPC分类号： B64C11/04 , F01D5/16 , F01D5/30
CPC分类号： F01D5/3053 , B64C11/04 , F01D5/16 , B64D2027/026 , Y02T50/672 , Y02T50/673 , Y10S416/50
摘要： An aircraft propeller system of the unducted fan type includes a plurality of propeller blades which are respectively fastened to a rotor, rotate about an axis of rotation and also rotate about a pitch axis. Each blade is fastened to the rotor by a hinge which has a pivot axis to reduce the effective stiffness of each blade, the pivot axis being non-parallel to the axis of rotation.
摘要翻译：未被引导的风扇类型的飞机螺旋桨系统包括多个螺旋桨叶片，它们分别固定在转子上，围绕旋转轴线旋转，并且还围绕桨距轴线旋转。每个叶片通过具有枢转轴线的铰链紧固到转子，以减小每个叶片的有效刚度，枢转轴线不平行于旋转轴线。

5. 发明授权

US6053697A Trilobe mounting with anti-rotation apparatus for an air duct in a gas turbine rotor 失效
标题翻译：三叶安装在燃气轮机转子中用于空气管道的防旋转装置
公开(公告)号：US6053697A
公开(公告)日：2000-04-25
申请号：US105478
申请日：1998-06-26
申请人： Arthur J. Piekarski , James M. Forrester , Charles E. Steckle , Richard F. Gutta
发明人： Arthur J. Piekarski , James M. Forrester , Charles E. Steckle , Richard F. Gutta
IPC分类号： F01D5/00 , F01D5/02 , F01D5/08 , F01D11/00 , F02C7/18 , F01D5/14
CPC分类号： F01D5/026 , F01D11/005 , F01D5/00 , F01D5/08 , F02C7/18 , F05D2220/74 , F05D2230/64 , F05D2240/20
摘要： An air duct assembly for a gas turbine compressor rotor in a gas turbine engine is described. The rotor includes a compressor spool shaft and at least one stage disk, and the air duct assembly includes an elongate hollow cylindrical air duct configured to couple to a stage disk at a first end of the air duct. The second end of the air duct is configured to couple to the spool shaft. The second end of the air duct includes a plurality of lobes depending radially inward, a spool shaft insert configured to fit into an opening in the spool shaft, and a plurality of pins coupled to the spool shaft insert and configured to extend from the insert and to engage the lobes of the second end of the air duct.
摘要翻译：描述了一种用于燃气涡轮发动机中的燃气轮机压缩机转子的空气管道组件。转子包括压缩机线轴和至少一个级盘，并且空气管道组件包括细长的中空圆柱形空气管道，其被配置为在空气管道的第一端处耦合到平台盘。风道的第二端构造成联接到卷轴。空气管道的第二端包括多个沿径向向内的突起，构造成装配到卷筒轴中的开口中的卷轴轴插入件，以及耦合到卷轴轴插入件并被构造成从插入件延伸的多个销以接合空气管道的第二端的叶片。

6. 发明授权

US5354176A Fan blade mount 失效
标题翻译：风扇叶片安装
公开(公告)号：US5354176A
公开(公告)日：1994-10-11
申请号：US129005
申请日：1993-09-29
申请人： Jan C. Schilling , Charles E. Steckle
发明人： Jan C. Schilling , Charles E. Steckle
IPC分类号： B64C11/06 , B64C11/04 , F01D5/16 , F01D5/30 , F04D29/34
CPC分类号： F01D5/3053 , B64C11/04 , F01D5/16 , B64D2027/026 , Y02T50/66 , Y02T50/672 , Y02T50/673
摘要： A variable pitch propeller blade system includes a conductive clevis attached to a rotor, a mating non-conductive clevis fastened to a non-conductive propeller blade, a pin journaling through bores in each clevis, joining the clevises to form a hinge joint, and a conductive path along a substantial part of the propeller blade.
摘要翻译：可变螺距螺旋桨叶片系统包括连接到转子的导电U形夹，固定在非导电螺旋桨叶片上的配合的不导电的U形夹，通过每个U形夹中的孔的轴销，将U形夹连接以形成铰链接头，以及沿着螺旋桨叶片的主要部分的导电路径。

7. 发明授权

US5749701A Interstage seal assembly for a turbine 失效
标题翻译：涡轮机级间密封组件
公开(公告)号：US5749701A
公开(公告)日：1998-05-12
申请号：US740450
申请日：1996-10-28
申请人： Jonathon P. Clarke , Charles E. Steckle , Kevin W. McMahan , George A. Durgin , Randall C. Bauer
发明人： Jonathon P. Clarke , Charles E. Steckle , Kevin W. McMahan , George A. Durgin , Randall C. Bauer
IPC分类号： F01D11/00 , F01D11/02
CPC分类号： F01D11/001 , F05D2260/20
摘要： A seal assembly positioned between forward and aft rotor stages of a turbine separates a forward cavity and an aft cavity on each side thereof. The seal assembly includes a seal body connected to a platform portion of a stator nozzle located between the forward and aft rotor stages, wherein an inner seal cavity in flow communication with an insert in the stator nozzle is formed therebetween. A static seal member is arranged in sealing relationship with a rotary toothed member between the forward and aft cavities, with the static seal member being connected to the seal body. An intermediate member is positioned between the seal body and the static seal member to define a plenum therebetween in flow communication with the inner seal cavity, the intermediate member having a plurality of angled passages formed therein in which a first end thereof is in flow communication with the plenum and a second end thereof is in flow communication with the aft cavity. Accordingly, air entering the stator nozzle insert flows into the inner seal cavity and then into the plenum so that it exits through the angled passages into the aft cavity at an angle with respect to an axis of rotation of the aft rotor stage. In this way, such air will acquire a tangential velocity component in the direction of rotation of the aft rotor stage.
摘要翻译：定位在涡轮机的前后转子级之间的密封组件在其每侧分离前腔和后空腔。密封组件包括密封体，其连接到位于前部和后部转子级之间的定子喷嘴的平台部分，其中在其间形成有与定子喷嘴中的插入件流动连通的内部密封腔。静密封构件与前后空腔之间的旋转齿形构件密封关系，静密封构件与密封体连接。中间构件位于密封体和静态密封构件之间，以在其间限定与内密封腔流动连通的中间构件，中间构件具有形成在其中的多个成角度的通道，其中第一端与第一端部气室和其第二端与后腔流体连通。因此，进入定子喷嘴插入件的空气流入内密封空腔，然后进入通风室，使得其相对于后转子级的旋转轴线成角度地离开成角度的通道进入后空腔。以这种方式，这样的空气将在后转子级的旋转方向上获得切向速度分量。

8. 发明授权

US5102302A Fan blade mount 失效
标题翻译：风扇叶片
公开(公告)号：US5102302A
公开(公告)日：1992-04-07
申请号：US201232
申请日：1988-06-02
申请人： Jan C. Schilling , Charles E. Steckle
发明人： Jan C. Schilling , Charles E. Steckle
IPC分类号： B64C11/06 , B64C11/04 , F01D5/16 , F01D5/30
CPC分类号： F01D5/3053 , B64C11/04 , F01D5/16 , B64D2027/026 , Y02T50/66 , Y02T50/672 , Y02T50/673
摘要： 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.
摘要翻译：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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