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1. 发明授权

US4513975A Thermally responsive labyrinth seal 失效
标题翻译：热响应迷宫密封
公开(公告)号：US4513975A
公开(公告)日：1985-04-30
申请号：US604561
申请日：1984-04-27
申请人： Ambrose A. Hauser , Rolf R. Hetico , Thomas G. Wakeman
发明人： Ambrose A. Hauser , Rolf R. Hetico , Thomas G. Wakeman
IPC分类号： F01D11/02 , F01D11/04 , F16J15/16 , F16J15/44 , F16J15/447
CPC分类号： F01D11/04 , F01D11/02 , F16J15/162 , F16J15/443 , Y10S277/93
摘要： An improved rotary labyrinth seal such as may be used in a gas turbine engine. The seal includes a rotor with at least one seal tooth and a stator with an abradable shroud and casing. The first and second members cooperate to inhibit the flow of fluid therebetween. The improvement comprises a conduit for conducting a portion of the fluid through the casing for heat transfer between the fluid and second member. In this manner, the thermal response of the stator is improved.
摘要翻译：一种改进的旋转迷宫式密封件，例如可用于燃气涡轮发动机。密封件包括具有至少一个密封齿的转子和具有可磨损护罩和外壳的定子。第一和第二构件协作以抑制它们之间的流体流动。该改进包括用于将一部分流体引导通过壳体以用于流体和第二构件之间的热传递的导管。以这种方式，改善了定子的热响应。

2. 发明授权

US5224831A Fan blade protection system 失效
标题翻译：风扇叶片保护系统
公开(公告)号：US5224831A
公开(公告)日：1993-07-06
申请号：US877351
申请日：1992-04-30
申请人： Thomas C. Hermans , Thomas G. Wakeman , Ambrose A. Hauser
发明人： Thomas C. Hermans , Thomas G. Wakeman , Ambrose A. Hauser
IPC分类号： B64C11/02 , F01D5/30 , F01D21/04
CPC分类号： F01D21/045 , B64C11/06 , B64C11/306 , F01D5/30 , B64D2027/005 , F05D2220/324 , Y02T50/66
摘要： In one type of aircraft propulsion system, propeller blades are mounted on a ring which surrounds a turbine. An annular space exists between the turbine and the ring. If a propeller blade should break free, the unbalanced centrifugal load tends to deform the ring. The invention reduces the deformation, as by locating spacers between the turbine and the ring.
摘要翻译：在一种类型的飞行器推进系统中，螺旋桨叶片安装在环绕涡轮机的环上。在涡轮和环之间存在环形空间。如果螺旋桨叶片脱落，离心力不平衡会使环变形。本发明通过在涡轮机和环之间定位隔板来减少变形。

3. 发明授权

US4863352A Blade carrying means 失效
标题翻译：刀片携带方式
公开(公告)号：US4863352A
公开(公告)日：1989-09-05
申请号：US667663
申请日：1984-11-02
申请人： Ambrose A. Hauser , Thomas G. Wakeman , William J. Strock , David B. Morris
发明人： Ambrose A. Hauser , Thomas G. Wakeman , William J. Strock , David B. Morris
IPC分类号： F04D29/36 , B64C11/02 , B64C11/06 , F01D5/02 , F01D7/00 , F16C19/56
CPC分类号： F16C19/56 , B64C11/06 , F01D5/02 , B64D2027/026 , Y02T50/671
摘要： Blade carrying means for variable pitch propulsor blades of a gas turbine engine are disclosed. The blade carrying means comprise dual, axially positioned rings and a plurality of generally cylindrical bearing journals supported between the rings. Each of the journals has a radially outer and inner edge and is adapted to support a single propulsor blade. The blade carrying means also comprise stiffening means, such as a bulkhead attached to the inner edge, for preventing distortion of the journal inner edge.
摘要翻译：公开了一种用于燃气涡轮发动机的变桨距推进叶片的叶片承载装置。刀片承载装置包括双轴向定位的环和支撑在环之间的多个大致圆柱形的轴承轴颈。每个轴颈具有径向外部和内部边缘，并且适于支撑单个推进器叶片。叶片承载装置还包括加强装置，例如附接到内边缘的隔板，用于防止轴颈内边缘的变形。

4. 发明授权

US5108259A Flexible connector for use in aircraft 失效
标题翻译：用于飞机的柔性连接器
公开(公告)号：US5108259A
公开(公告)日：1992-04-28
申请号：US286101
申请日：1988-12-19
申请人： Thomas G. Wakeman , Ambrose A. Hauser
发明人： Thomas G. Wakeman , Ambrose A. Hauser
IPC分类号： B64C11/06 , B64C11/02 , F01D5/02 , F01D25/16 , F02C7/20
CPC分类号： B64C11/02 , F01D25/162 , F01D5/021 , B64D2027/026 , Y02T50/673
摘要： The invention concerns a connector, in an aircraft engine, for mounting a ring to a turbine rotor which the ring surrounds. The ring carries propeller blades, and the connector transmits both thrust and torque loads between the ring and the rotor, without significant deformation. However, the connector does deform in order to accommodate differential thermal growth between the ring and the rotor.
摘要翻译：本发明涉及在飞行器发动机中用于将环安装到环包围的涡轮转子上的连接器。该环承载螺旋桨叶片，并且连接器在环和转子之间传递推力和扭矩载荷，而没有显着的变形。然而，连接器确实变形以适应环和转子之间的差热生长。

5. 发明授权

US5112191A Rotating cowling 失效
标题翻译：旋转缠绕
公开(公告)号：US5112191A
公开(公告)日：1992-05-12
申请号：US336375
申请日：1989-04-11
申请人： William J. Strock , Thomas G. Wakeman , Ambrose A. Hauser
发明人： William J. Strock , Thomas G. Wakeman , Ambrose A. Hauser
IPC分类号： B64C11/06 , B64D29/00
CPC分类号： B64C11/06 , B64D29/00 , B64D2027/026 , Y02T50/66
摘要： The invention concerns a cowling for aircraft propulsion systems of the counterrotating propeller type. The cowling includes a pair of mounting rings located fore and aft of a propeller array. Removable panels extend between the mounting rings and contain openings through which the propeller blades extend.
摘要翻译：本发明涉及用于逆转螺旋桨型飞机推进系统的整流罩。整流罩包括位于螺旋桨阵列前后的一对安装环。可移动面板在安装环之间延伸并包含螺旋桨叶片延伸通过的开口。

6. 发明授权

US5272868A Gas turbine engine lubrication system 失效
标题翻译：燃气轮机发动机润滑系统
公开(公告)号：US5272868A
公开(公告)日：1993-12-28
申请号：US43073
申请日：1993-04-05
申请人： John J. Ciokajlo , Ambrose A. Hauser , Samuel H. Davison
发明人： John J. Ciokajlo , Ambrose A. Hauser , Samuel H. Davison
IPC分类号： F02C7/00 , F01D25/18 , F02C7/06 , F02K3/06 , F02K3/072 , F16C33/66 , F16N7/36
CPC分类号： F16C33/6659 , F01D25/18 , F02K3/072 , F16N7/363 , F16N2210/02
摘要： A lubrication system for a gas turbine engine includes first and second coaxially rotor shafts having at least one differential bearing disposed in outer and inner seats thereof. An annular first scoop extends axially from a first portion of the first shaft, and an annular second scoop extends axially from the inner seat of the second shaft. A plurality of first holes extend axially through the first shaft and radially below the first scoop, and a plurality of second holes extend axially through the inner seat of the second shaft and below the second scoop. An annular first shell extends axially between the second scoop and the first shaft from above the first holes. And, oil is injected under the first scoop for flow by centrifugal force from rotation of the first shaft through the first holes and along the first shell into the second scoop for flow through the second holes to lubricate the bearing.
摘要翻译：用于燃气涡轮发动机的润滑系统包括第一和第二同轴转子轴，其具有设置在其内部和内部座中的至少一个差速轴承。环形第一勺从第一轴的第一部分轴向延伸，并且环形第二勺从第二轴的内座轴向延伸。多个第一孔轴向地延伸穿过第一轴并在第一勺的径向下方延伸，并且多个第二孔轴向延伸穿过第二轴的内座且在第二勺下方。环形第一壳体从第一孔的上方在第二勺和第一轴之间轴向延伸。并且，通过离心力将油注入第一勺以通过第一轴从第一孔旋转并沿着第一壳进入第二勺以流过第二孔以润滑轴承。

7. 发明授权

US5049033A Blade tip clearance control apparatus using cam-actuated shroud segment positioning mechanism 失效
标题翻译：叶片间隙控制装置采用凸轮驱动的护罩段定位机构
公开(公告)号：US5049033A
公开(公告)日：1991-09-17
申请号：US482139
申请日：1990-02-20
申请人： Robert J. Corsmeier , Ambrose A. Hauser
发明人： Robert J. Corsmeier , Ambrose A. Hauser
IPC分类号： F01D11/08 , F01D11/22 , F02C3/073
CPC分类号： F01D11/22 , Y10T74/1896
摘要： A clearance control apparatus has a positioning mechanism for controlling clearance between rotor blade tips and a shroud segment of a gas turbine engine casing, and a rotatable lever for actuating the mechanism. The positioning mechanism is supported by a casing boss, coupled to the shroud segment, and actuatable for moving the shroud segment toward and away from the rotor blade tips to reach a position at which a desired clearance is established. The mechanism includes a shaft and a pair of cam elements. The shaft is mounted by the boss for radial movement toward and away from the rotor axis and coupled at its inner end to the shroud segment. An outer cam element is attached to the outer end of the shaft and spaced outwardly from the boss. An inner cam element is attached to an end of the lever mounted to the boss for rotational movement about a longitudinal axis of the shaft. The inner cam element is located between an outer end of the boss and the outer cam element and engaged with the outer cam element such that rotation of the inner cam element with rotation of the lever produces radial movement of the outer cam element and of the shaft and shroud segment therewith toward and away from the rotor blade tips.
摘要翻译：间隙控制装置具有用于控制转子叶片尖端与燃气涡轮发动机壳体的护罩部分之间的间隙的定位机构和用于致动机构的可旋转杆。该定位机构由与外壳段联接的套管凸台支撑，并且可致动以使护罩段朝向和远离转子叶片尖端移动以到达建立期望间隙的位置。该机构包括轴和一对凸轮元件。轴由凸台安装以径向移动并远离转子轴线并且在其内端处连接到护罩段。外凸轮元件附接到轴的外端并与凸起向外间隔开。内凸轮元件附接到安装到凸台的杠杆的端部，用于围绕轴的纵向轴线旋转运动。内凸轮元件位于凸台的外端和外凸轮元件之间并与外凸轮元件接合，使得内凸轮元件在杠杆的旋转下的旋转产生外凸轮元件和轴的径向运动和护罩部分，朝向和离开转子叶片尖端。

8. 发明授权

US5035573A Blade tip clearance control apparatus with shroud segment position adjustment by unison ring movement 失效
标题翻译：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
IPC分类号： F01D11/08 , F01D11/22 , F02C3/073
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。

9. 发明授权

US5018942A Mechanical blade tip clearance control apparatus for a gas turbine engine 失效
标题翻译：用于燃气涡轮发动机的机械叶片间隙控制装置
公开(公告)号：US5018942A
公开(公告)日：1991-05-28
申请号：US404923
申请日：1989-09-08
申请人： John J. Ciokajlo , Ambrose A. Hauser
发明人： John J. Ciokajlo , Ambrose A. Hauser
IPC分类号： F01D11/08 , F01D11/22 , F02C3/073
CPC分类号： F01D11/22 , Y02T50/671
摘要： A gear-actuated mechanical clearance control apparatus is operable for controlling the clearance between rotor blade tips and the casing shroud of a gas turbine engine. The apparatus includes a pair of annular rings which extend about the casing shroud, a shroud hanger disposed between the casing and an opening in the casing and between the annular rings, and a shroud segment defining a circumferential portion of the casing shroud and disposed in the casing opening. The apparatus also has an actuating mechanism which includes driven gear sectors on the annular rings which face toward one another and a gear disposed between the annular rings and having a peripheral driving gear sector which intermeshes with the driven gear sectors of the annular rings. Upon rotation of the gear, the annular rings undergo opposite circumferential movement causing radial movement of the shroud hanger and the shroud segment therewith to establish the clearance between the shroud segment and rotor blade outer tips.
摘要翻译：齿轮致动的机械间隙控制装置可操作用于控制转子叶片尖端与燃气涡轮发动机的壳体护罩之间的间隙。该装置包括围绕套管罩延伸的一对环形环，设置在壳体和壳体中的开口之间以及环形环之间的护罩悬挂器，以及限定套管护罩的圆周部分并设置在壳体护罩中的护罩段套管开口。该装置还具有致动机构，该致动机构包括环形环上的从动齿轮部分，其彼此面对，并且齿轮设置在环形环之间并且具有与环形环的从动齿轮部分相互啮合的外围驱动齿轮部分。在齿轮旋转时，环形圈经受相反的周向移动，导致护罩悬挂器和护罩段的径向运动，从而建立护罩段和转子叶片外部尖端之间的间隙。

10. 发明授权

US4758129A Power frame 失效
标题翻译：电源框架
公开(公告)号：US4758129A
公开(公告)日：1988-07-19
申请号：US739804
申请日：1985-05-31
申请人： William J. Strock , Ambrose A. Hauser
发明人： William J. Strock , Ambrose A. Hauser
IPC分类号： F01D1/24 , F01D5/02 , F01D5/06 , F01D5/18 , F01D7/00 , F01D9/06 , F02K3/072 , F02C3/04
CPC分类号： F01D5/18 , F01D5/02 , F01D7/00 , F01D9/065 , F02K3/072 , F05D2260/74 , F05D2260/76 , Y02T50/676
摘要： A rotor stage disposed within an annular fluid flowpath in a turbomachine is disclosed. The rotor stage includes outer and inner rings and a plurality of first and second airfoils. The outer and inner rings define flowpath surfaces for said flowpath. The first and second airfoils extend between the rings for transferring energy between the fluid and the rotor stage. At least one of the first airfoils surrounds means for transmitting energy across the flowpath.
摘要翻译：公开了一种设置在涡轮机中的环形流体流路内的转子级。转子级包括外圈和内圈以及多个第一和第二翼型件。外圈和内圈限定所述流路的流路面。第一和第二翼型件在环之间延伸以在流体和转子级之间传递能量。第一翼型中的至少一个围绕用于在流动路径上传递能量的装置。

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