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公开(公告)号：US06719296B2
公开(公告)日：2004-04-13
申请号：US10194391
申请日：2002-07-12
IPC分类号： F16J15447
CPC分类号： F16J15/38 , F01D11/003 , F01D11/025 , F05D2250/611 , F16J15/342 , F16J15/3452
摘要： A face seal assembly is provided having an annular seal body mounted in an axially moveable relationship to a seal support structure. A piston ring is disposed between the annular seal body and the seal support structure forming a secondary seal. A first locator spring, which is an annular wave spring, is disposed between said seal support structure and the piston ring to urge the piston ring in an axial direction. Optionally, a second locator spring, also a wave spring, may be disposed between the piston ring and the seal support structure for urging the piston ring in a radial direction.
摘要翻译： 提供一种面密封组件，其具有环形密封体，所述环形密封体以与所述密封件支撑结构轴向移动的关系安装。 活塞环设置在环形密封体和密封支撑结构之间，形成二次密封。 作为环形波形弹簧的第一定位弹簧设置在所述密封支撑结构和活塞环之间，以沿轴向推动活塞环。 可选地，第二定位弹簧（也可以是波形弹簧）可以设置在活塞环和密封支撑结构之间，用于沿径向推动活塞环。
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公开(公告)号：US5135185A
公开(公告)日：1992-08-04
申请号：US703720
申请日：1991-05-22
申请人： Arthur P. Adamson , Wu-Yang Tseng
发明人： Arthur P. Adamson , Wu-Yang Tseng
CPC分类号： B64D27/12
摘要： An aircraft engine is mounted on an aircraft wing such that the wing wake sheds along a zone at a predetermined position on the engine disk thereby minimizing dynamic loads or resonance. For a prechosen or design set of engine conditions the strength of the dynamic load is a function of the radial location of the zone on the disk having at least one relative minima between the centerline and the perimeter of the disk. The zone is positioned on the disk such that the value of the function is essentially a relative minima.
摘要翻译： 飞机发动机安装在飞行器机翼上，使得机翼沿着发动机盘上的预定位置的区域脱落，从而最小化动态载荷或共振。 对于发动机条件的预先设计或设计，动态载荷的强度是盘的区域的径向位置的函数，该区域在盘的中心线和周边之间具有至少一个相对最小值。 该区域位于盘上，使得该函数的值基本上是相对最小值。
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公开(公告)号：US5975537A
公开(公告)日：1999-11-02
申请号：US958245
申请日：1997-10-27
CPC分类号： F16J15/40 , F16J15/443
摘要： A rotor and stator assembly having a rotor and a stator with opposing surfaces defining an air bearing and an air dam of an aspirating face seal. In a first embodiment, the air bearing and the air dam are axially offset. In a second embodiment, the rotor has an axially extending protuberance located radially between the air bearing and the air dam. The axial offset and the protuberance each act to divert the air flow (e.g., compressed gas or combustion gases in a gas turbine or steam in a steam turbine) in a direction transverse to the air flow direction through the air bearing and the air dam, thus isolating the air flows from the air bearing and the air dam which improves seal performance.
摘要翻译： 具有转子和定子的转子和定子组件具有限定空气轴承的相对表面和吸气面密封件的空气坝。 在第一实施例中，空气轴承和空气坝被轴向偏移。 在第二实施例中，转子具有径向位于空气轴承和空气坝之间的轴向延伸突起。 轴向偏移和突起各自起作用以使空气流（例如，蒸汽轮机中的燃气轮机中的压缩气体或燃烧气体或蒸汽涡轮机中的蒸汽）沿与空气轴承和空气坝的空气流动方向横切， 从而隔离空气轴承和空气坝的空气流，从而提高密封性能。
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公开(公告)号：US5335920A
公开(公告)日：1994-08-09
申请号：US932514
申请日：1992-08-20
IPC分类号： F16J15/32 , F16J15/447
CPC分类号： F16J15/3288
摘要： A brush seal is provided having a plurality of bristle layers sandwiched between a pair of circumferential plates with the upstream layers of bristles having a higher first fundamental vibration frequency than downstream seal layers. Such a seal has bristles in the upstream layer or layers that have a greater cross sectional area, a lesser lay angle, are shorter, or some combination of the foregoing.
摘要翻译： 提供刷密封件，其具有夹在一对周向板之间的多个刷毛层，刷毛的上游层具有比下游密封层高的第一基本振动频率。 这种密封件具有上游层中具有刷毛，其具有更大的横截面积，较小的铺设角度，较短的或上述的某些组合。
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公开(公告)号：US5318309A
公开(公告)日：1994-06-07
申请号：US61330
申请日：1993-05-13
CPC分类号： F16J15/3288 , F01D11/02 , Y02T50/671
摘要： An improved brush seal for reducing swirl, recirculation and turbulence of an approaching gas stream to reduce irregular bristle wear and operating costs. The brush real may include a baffle of the honeycomb type or circumferentially stacked plates type, positive or negative steps in the flow path approaching a seal stage, and recirculation breakers.
摘要翻译： 改进的刷密封件，用于减少接近气流的涡流，再循环和湍流，以减少不规则的刷毛磨损和操作成本。 刷子实际上可以包括蜂窝类型的挡板或周向堆叠板类型，在接近密封台的流动路径中的正或负台阶和再循环断路器。
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公开(公告)号：US06240719B1
公开(公告)日：2001-06-05
申请号：US09207818
申请日：1998-12-09
IPC分类号： F02K304
CPC分类号： F01D21/045 , F01D21/04 , F01D25/16 , F01D25/162 , F05B2260/3011
摘要： A support structure for a gas turbine engine includes a support arm (214, 216) extending between a low pressure shaft (202) and a rotor. The support arm includes a fuse (220) having a low failure point. A high pressure stub shaft (270) axially and radially supports the low pressure shaft (202) after fuse failure. An axial gap (A) between a portion of the low pressure shaft and the stub shaft permits movement of the low pressure shaft after fuse failure. A radial gap (B) between the stub shaft (270) and the low pressure shaft (202) allows radial deflection of the low pressure rotor system after fuse failure.
摘要翻译： 用于燃气涡轮发动机的支撑结构包括在低压轴（202）和转子之间延伸的支撑臂（214,216）。 支撑臂包括具有低故障点的保险丝（220）。 保险丝故障后，高压短轴（270）轴向和径向地支撑低压轴（202）。 在低压轴的一部分和短轴之间的轴向间隙（A）允许熔丝故障后低压轴的移动。 短轴（270）和低压轴（202）之间的径向间隙（B）允许在保险丝故障之后低压转子系统的径向偏转。
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7.发明授权Blade tip clearance control apparatus with shroud segment position adjustment by unison ring movement 失效叶片间隙控制装置，通过协调环运动调整护罩段位置
公开(公告)号：US5035573A
公开(公告)日：1991-07-30
申请号：US507428
申请日：1990-03-21
申请人： Wu-Yang Tseng , Ambrose A. Hauser
发明人： Wu-Yang Tseng , Ambrose A. Hauser
CPC分类号： F01D11/22
摘要： A clearnace control apparatus has a plurality of positioning mechanisms and an annular unison ring for controlling the clearance between the rotor blade tips and shroud segments of a gas turbine engine casing. The positioning mechanisms are supported by circumferentially-spaced casing bosses, connected to the shroud, and actuatable by the unison ring for moving radially toward and away from the rotor blade tips. As the positioning mechanisms are moved radially, the shroud segments move therewith toward and away from the rotor axis to positioned between inner and outer positions which define minimum and maximum clearances between the shroud segments and rotor blade tips. The unison ring has circumferentially spaced slots defined therethrough each extending in a transverse inclined relation to the respective directions of movement of the unison ring and positioning mechanisms and having spaced opposite ends defining first and second angularly displaced limit positions of the unison ring. The positioning mechanisms are coupled to the unison ring by pins which extend through the respective inclined slots.
摘要翻译： 叶片控制装置具有多个定位机构和用于控制燃气涡轮发动机壳体的转子叶片尖端和护罩段之间的间隙的环形共振环。 定位机构由连接到护罩的周向隔开的套管凸台支撑，并且可由协调环致动，用于朝向和离开转子叶片尖端径向移动。 当定位机构径向移动时，护罩段与转子轴线一起移动并且远离转子轴线定位在内部和外部位置之间，其限定护罩段和转子叶片尖端之间的最小和最大间隙。 协调环具有限定在其中的周向间隔开的槽，每个槽以协调的环和定位机构的相应运动方向横向倾斜地延伸，并且具有间隔开的相对端限定协调环的第一和第二角度位移极限位置。 定位机构通过延伸通过相应的倾斜槽的销耦合到协调环。
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公开(公告)号：US4971641A
公开(公告)日：1990-11-20
申请号：US490506
申请日：1990-03-01
IPC分类号： B64C11/26
CPC分类号： B64C11/26 , B64D2027/026
摘要： An aircraft propeller blade is constructed by forming two shells of composite material laminates and bonding the two shells to a metallic spar with foam filler pieces interposed between the shells at desired locations. The blade is then balanced radially and chordwise.
摘要翻译： 飞机螺旋桨叶片通过形成复合材料层压体的两个壳体并且将两个壳体结合到金属翼梁构造，其中泡沫填充片插入在所需位置的壳体之间。 然后将叶片径向和弦并入。
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公开(公告)号：US4784575A
公开(公告)日：1988-11-15
申请号：US157179
申请日：1988-02-12
CPC分类号： B64C11/18 , B64C11/20 , B64D2027/026 , Y10S416/02
摘要： A propulsor blade for an aircraft engine includes an airfoil section formed in the shape of a scimitar. A metallic blade spar is interposed between opposed surfaces of the blade and is bonded to the surfaces to establish structural integrity of the blade. The metallic blade spar includes a root end allowing attachment of the blade to the engine.
摘要翻译： 用于飞行器发动机的推进器叶片包括形成为弯曲形状的翼型部分。 金属叶片翼片插入在叶片的相对表面之间并且结合到表面以建立叶片的结构完整性。 金属叶片翼梁包括允许叶片附接到发动机的根部端部。
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公开(公告)号：US4732538A
公开(公告)日：1988-03-22
申请号：US773514
申请日：1985-09-05
CPC分类号： F01D7/00 , F01D5/084 , F05D2260/74 , F05D2260/76 , Y02T50/673 , Y02T50/676
摘要： Air control means in a gas turbine engine having a variable pitch rotatable airfoil and means for varying the pitch of the airfoil are disclosed. The air control means comprises a platform fixedly attached to a radially inner end of the airfoil. The platform is generally positioned on a rotatable annular surface, which surface defines outer and inner spaces. In a first position, an edge portion of the platform substantially conforms to the annular surface. In a second position, the edge portion is displaced radially outwardly from the surface thereby allowing fluid communication between the outer and inner spaces.
摘要翻译： 公开了一种具有变桨距可旋转翼型的燃气涡轮发动机中的空气控制装置和用于改变翼型节距的装置。 空气控制装置包括固定地连接到翼型件的径向内端的平台。 平台通常位于可旋转的环形表面上，该表面限定外部和内部空间。 在第一位置，平台的边缘部分基本上符合环形表面。 在第二位置，边缘部分从表面径向向外移位，从而允许外部和内部空间之间的流体连通。
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