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1. 发明授权

US5361580A Gas turbine engine rotor support system 失效
标题翻译：燃气轮机发动机转子支撑系统
公开(公告)号：US5361580A
公开(公告)日：1994-11-08
申请号：US80666
申请日：1993-06-18
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： F01D5/06 , F01D25/16 , F02C3/067 , F02C7/06 , F02C7/20 , F02K3/06 , F02K3/02
CPC分类号： F02C7/06 , F01D25/162 , F02C3/067
摘要： A gas turbine engine rotor support system includes outer and inner rotors having respective outer and inner blades interdigitated in respective blade row stages. A stationary rear frame includes a rear support shaft. A rotatable aft frame is disposed forwardly of the rear frame includes an aft support shaft. And, a rotatable forward frame is disposed forwardly of the aft frame and includes a forward support shaft. The forward and aft frames support the outer and inner rotors, and a first bearing is disposed between the aft shaft and the rear shaft for supporting the aft shaft; a second bearing is disposed between the forward shaft and the aft shaft for supporting the forward shaft; and a third bearing is disposed between a core shaft of a core turbine and the forward shaft for supporting the core shaft thereon.
摘要翻译：燃气涡轮发动机转子支撑系统包括外转子和内转子，其具有在相应的叶片排级中交错指定的相应外部和内部叶片。固定的后框架包括后支撑轴。在后框架的前方设置有可旋转的后框架，其包括后支撑轴。并且，可旋转的前框架设置在后框架的前方并且包括前支撑轴。前后框架支撑外转子和内转子，并且第一轴承设置在后轴和后轴之间，用于支撑后轴; 第二轴承设置在前轴和后轴之间，用于支撑前轴; 并且第三轴承设置在芯涡轮机的芯轴与用于将芯轴支撑在其上的前轴之间。

2. 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。

3. 发明授权

US5443590A Rotatable turbine frame 失效
标题翻译：可旋转涡轮机架
公开(公告)号：US5443590A
公开(公告)日：1995-08-22
申请号：US80669
申请日：1993-06-18
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： F01D5/02 , F01D25/16 , F02C3/067 , F02K3/06 , F01D1/24
CPC分类号： F01D25/162 , F01D5/02 , F02C3/067
摘要： A rotatable turbine frame includes annular outer and inner bands having a plurality of circumferentially spaced apart struts extending therebetween. An annular drive shaft is fixedly joined to the inner band for transmitting output torque therefrom, and the struts are backwardly radially inclined relative to the direction of rotation of the frame so that gas flow between the struts tends to straighten the inclined struts to effect a compressive load component therein.
摘要翻译：可旋转的涡轮机框架包括环形的外部和内部带，其具有在其间延伸的多个周向间隔开的支柱。环形驱动轴固定地连接到内带以传递输出扭矩，并且支柱相对于框架的旋转方向向后径向倾斜，使得支柱之间的气流倾向于使倾斜支柱拉直以实现压缩负载组件。

4. 发明授权

US4222708A Method and apparatus for reducing eccentricity in a turbomachine 失效
标题翻译：减少涡轮机偏心率的方法和装置
公开(公告)号：US4222708A
公开(公告)日：1980-09-16
申请号：US919534
申请日：1978-06-26
申请人： Samuel H. Davison
发明人： Samuel H. Davison
IPC分类号： B23P21/00 , F01D11/08 , F01D25/00 , F01D25/24 , F01D25/26 , F01D25/28
CPC分类号： F01D25/265 , F01D25/243 , F01D25/28 , F05D2230/644 , Y10S403/07 , Y10T403/125
摘要： An inherent eccentricity between the rotor bearings and the stator shroud is reduced by intentionally fabricating into each of a pair of frame annuluses, outer and inner surfaces which are relatively eccentric, and then rotating the annuluses with respect to each other until the inherent eccentricity is substantially offset. A method is provided to determine the optimum relative rotational positions as a function of the measured inherent eccentricity, and restrictions in the number of possible rotational positions are considered.
摘要翻译：转子轴承和定子护罩之间的固有的偏心度被有意地制造成一对框架环形物，相对偏心的外表面和内表面，然后相对于彼此旋转，直到固有偏心基本上抵消。提供了一种确定作为测量的固有偏心度的函数的最佳相对旋转位置的方法，并且考虑可能的旋转位置的数量的限制。

5. 发明授权

US5136837A Aircraft engine starter integrated boundary bleed system 失效
标题翻译：飞机发动机起动器集成边界卸载系统
公开(公告)号：US5136837A
公开(公告)日：1992-08-11
申请号：US489150
申请日：1990-03-06
申请人： Samuel H. Davison
发明人： Samuel H. Davison
IPC分类号： F02C7/057 , F02C6/08 , F02C7/277 , F02C7/32 , F02C7/36 , F02C9/16 , F02K3/06 , F04D25/02
CPC分类号： F02C6/08 , F02C7/32 , F02C7/36 , F04D25/02 , F05D2220/50 , Y02T50/671
摘要： An aircraft gas turbine engine is provided with a compressed air supply system generally used for meeting customer or aircraft bleed air requirements. The compressed air supply system comprises an auxiliary compressor, a means for mechanically driving the system from a rotor of the gas turbine rotor, and a cycle varying means, such as a variable speed drive, for operating the auxiliary compressor cycle independently of the aircraft gas turbine engine compressor cycle. The preferred embodiment provides a means for bleeding boundary layer air off the nacelle or another part of the aircraft outer skin and using it as a source of air for the auxiliary compressor. One embodiment includes an air turbine on a common shaft with the auxiliary compressor and a means to direct an unused portion of the airflow form the auxiliary compressor to the air turbine to help power the auxiliary compressor and another embodiment includes a means to direct compressed startling air to the air turbine for on ground and in flight starting of the gas turbine engine through the variable speed drive and a mechanical linkage to the high rotor of the gas turbine engine.
摘要翻译：飞机燃气涡轮发动机设置有通常用于满足客户或飞机放气要求的压缩空气供应系统。压缩空气供应系统包括辅助压缩机，用于从燃气轮机转子的转子机械地驱动系统的装置以及诸如变速驱动器的循环改变装置，用于独立于飞机气体操作辅助压缩机循环涡轮发动机压缩机循环。优选实施例提供了一种用于将边界层空气从机舱或飞行器外皮的另一部分排出并将其用作辅助压缩机的空气源的装置。一个实施例包括在具有辅助压缩机的公共轴上的空气涡轮机和将空气的未使用部分从辅助压缩机引导到空气涡轮机以帮助为辅助压缩机供电的装置，并且另一实施例包括用于引导压缩惊魂通过变速驱动器和通过燃气涡轮发动机的高转子的机械连接而在燃气涡轮发动机的地面和飞行启动中的空气涡轮机。

6. 发明授权

US4230436A Rotor/shroud clearance control system 失效
标题翻译：转子/护罩间隙控制系统
公开(公告)号：US4230436A
公开(公告)日：1980-10-28
申请号：US925352
申请日：1978-07-17
申请人： Samuel H. Davison
发明人： Samuel H. Davison
IPC分类号： F02C7/20 , F01D11/10 , F01D11/24 , F02C7/28 , F01D11/08
CPC分类号： F01D11/24 , Y02T50/671
摘要： Cooling airflow to the shroud support apparatus is varied in response to both rotor speed and elapsed time above a predetermined level by the selective use and mixture of two air sources at different temperatures. For steady-state operation, each of four different operating modes has its prescribed cooling air delivery mode such that, generally, as the engine speed and cycle temperatures increase, so does that of the cooling air. For transient operation, a timer is employed to sequence the desired cooling air delivery modes in such a manner as to maintain optimum rotor-to-shroud clearances during the transient period.
摘要翻译：通过在不同温度下的选择性使用和两种空气源的混合，响应于转子速度和高于预定水平的经过时间，到壳体支撑装置的冷却气流是变化的。对于稳态操作，四种不同操作模式中的每种都具有其规定的冷却空气输送模式，使得通常，随着发动机转速和循环温度的升高，冷却空气的温度也升高。对于瞬态操作，采用定时器来按照期望的冷却空气输送模式进行排序，以便在过渡期间保持最佳的转子到导管间隙。

7. 发明授权

US4928240A Active clearance control 失效
标题翻译：主动间隙控制
公开(公告)号：US4928240A
公开(公告)日：1990-05-22
申请号：US160052
申请日：1988-02-24
申请人： Samuel H. Davison , Kevin H. Kast , Aidan W. Clark
发明人： Samuel H. Davison , Kevin H. Kast , Aidan W. Clark
IPC分类号： F01D11/10 , F01D11/08 , F01D11/24 , F02C7/28 , G01B21/16
CPC分类号： F01D11/24
摘要： The invention relates to a control system which controls the diameter of a turbine shroud which surrounds a turbine in a gas turbine aircraft engine. The invention seeks to minimize the clearance between the turbine rotor and the shroud. Air is bled from the compressor in the engine and ducted to the shroud in order to heat or cool the shroud in order to, respectively, either expand or shrink the shroud to a proper diameter. The air temperature which is required is computed based on compressor speed and other engine parameters, but not upon directly measured rotor temperature, despite the fact that rotor temperature has a significant influence upon rotor diameter, and thus upon shroud diameter needed. Air at two different temperatures is bled from two different compressor stages in the engine and mixed together in a ratio which is determined according to flight conditions, in order to provide air of the required temperature for the shroud, and then ducted to the shroud in order to modify shroud size. Further, during accelerations and decelerations of the engine, a different air temperature is provided, as compared with that provided during steady state operation. In the event that the system just described should fail, back-up systems control shroud diameter. There exist two back-up systems, one for use during steady state, and the other for use during accelerations and decelerations.

8. 发明授权

US4893984A Clearance control system 失效
标题翻译：清关控制系统
公开(公告)号：US4893984A
公开(公告)日：1990-01-16
申请号：US178721
申请日：1988-04-07
申请人： Samuel H. Davison , William F. McGreehan
发明人： Samuel H. Davison , William F. McGreehan
IPC分类号： F01D11/10 , F01D11/24 , F02C7/28
CPC分类号： F01D11/24
摘要： A system for controlling rotor blade tip clearances in a gas turbine engine supplies both heating air and cooling air to the rotor bore. The heating air flow is controlled by a valve and the cooling air flow is not controlled.
摘要翻译：用于控制燃气涡轮发动机中的转子叶片尖端间隙的系统将加热空气和冷却空气提供给转子孔。加热气流由阀控制，冷却空气流不受控制。

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