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1. 发明授权

US5308169A Bearing system for turbocharger 失效
标题翻译：涡轮增压器轴承系统
公开(公告)号：US5308169A
公开(公告)日：1994-05-03
申请号：US984186
申请日：1992-11-20
申请人： Glenn L. Baker , David R. Engle , Roger Williams
发明人： Glenn L. Baker , David R. Engle , Roger Williams
IPC分类号： F02B39/14 , F01D25/16 , F16C17/04 , F04B17/00
CPC分类号： F16C17/04 , F01D25/168 , F16C33/1075 , F16C2360/24
摘要： A thrust bearing for a turbocharger includes a main body portion which defines a central bore for receipt of a thrust collar, an oil reservoir in the shape of a blind, oblong slot disposed in the main body portion and an oil passageway connecting the oil reservoir with the central bore. As oil is drained from the turbocharger by a siphoning action as the engine oil level drops, oil which is stored in the oil reservoir will remain and after the engine has completely stopped this stored oil is available to drain into the interface between the thrust collar and central bore of the thrust bearing in order to provide lubricating oil to this interface upon restart of the engine. Oil is also provided by the reservoir to the turbine and compressor journal bearings where it is held in small clearances on the inner and outer surfaces of the journal bearings.
摘要翻译：用于涡轮增压器的止推轴承包括主体部分，其限定用于接收止推环的中心孔，设置在主体部分中的盲孔长椭圆形状的储油器以及将油槽与中心孔。当发动机油位下降时，通过虹吸作用将油从涡轮增压器排出，储存在储油器中的油将保留，并且在发动机完全停止后，储存的油可用于排入推力轴环和推力轴承的中心孔，以便在发动机重起时向该界面提供润滑油。油也由油箱提供给涡轮机和压缩机轴颈轴承，其中轴颈轴承的内表面和外表面上保持小间隙。

2. 发明申请

US20120189433A1 VARIABLE GEOMETRY TURBINE 有权
标题翻译：可变几何涡轮
公开(公告)号：US20120189433A1
公开(公告)日：2012-07-26
申请号：US13237473
申请日：2011-09-20
申请人： Glenn L. Baker , Gary Beshears , Timothy James William Proctor , John Frederick Parker , John Michael Bywater
发明人： Glenn L. Baker , Gary Beshears , Timothy James William Proctor , John Frederick Parker , John Michael Bywater
IPC分类号： F04D29/46 , F04D27/00
CPC分类号： F01D17/14 , F01D17/167 , F05D2220/40
摘要： A variable geometry turbine comprising: a housing; a turbine wheel supported in the housing for rotation; an annular inlet passage defined between respective inlet surfaces defined by an annular nozzle ring and a facing annular shroud; the nozzle ring can vary the size of the inlet passage; a circumferential array of inlet vanes; the shroud covering the opening of a shroud cavity defined by the housing inlet passage and inboard of the shroud, and defining a circumferential array of slots, the slots and shroud cavity being configured to receive said vanes accommodating movement of the nozzle ring; wherein the annular shroud comprises an outer flange, the outer flange defining a circumferential groove for receiving a retaining ring for securing the shroud in the opening of the shroud cavity and defined on an inboard side by a flange wall; wherein an annular flange rim extends axially inboard from said flange wall.
摘要翻译：一种可变几何涡轮，包括：壳体; 支撑在壳体中用于旋转的涡轮机叶轮; 环形入口通道限定在由环形喷嘴环和面向环形罩限定的相应入口表面之间; 喷嘴环可以改变入口通道的尺寸; 入口叶片的圆周阵列; 所述护罩覆盖由所述壳体入口通道和所述护罩的内侧限定的护罩腔的开口，并且限定狭槽的圆周阵列，所述狭槽和护罩腔被构造成容纳所述叶片容纳所述喷嘴环的运动; 其中所述环形护罩包括外凸缘，所述外凸缘限定圆周槽，用于接收用于将所述护罩固定在所述护罩腔的开口中并由凸缘壁在内侧限定的保持环; 其中环形凸缘边缘从所述凸缘壁轴向向内延伸。

3. 发明授权

US06408624B1 System for controlling transient compressor surge in a turbocharged internal combustion engine 有权
标题翻译：用于控制涡轮增压内燃机瞬时压缩机喘振的系统
公开(公告)号：US06408624B1
公开(公告)日：2002-06-25
申请号：US09771754
申请日：2001-01-29
申请人： Martin T. Books , Glenn L. Baker
发明人： Martin T. Books , Glenn L. Baker
IPC分类号： F02D2300
CPC分类号： F02D23/02 , F02D41/0007 , F02D2200/0406 , F02D2200/0414 , Y02T10/144
摘要： A system and method are provided for avoiding transient compressor surge in a turbocharged internal combustion engine. The system includes a control circuit responsive to at least one engine operating parameter to determine a minimum fueling limit that is generally higher under certain engine operating conditions than the default engine fueling value. Under such conditions, the minimum fueling limit is used to establish a lower limit of fuel supplied to the engine in order to avoid turbocharger transient compresser surge conditions. In one embodiment, the at least one engine operating parameter includes intake manifold air pressure, and in an alternative embodiment, the at least one engine operating parameter further includes intake manifold air temperature. In either case, the at least one engine operating parameter also preferably includes engine speed.
摘要翻译：提供了一种用于避免涡轮增压内燃机中的瞬时压缩机喘振的系统和方法。该系统包括响应于至少一个发动机操作参数的控制电路，以确定在某些发动机操作条件下比默认发动机加油值通常更高的最小加油极限。在这种条件下，最小燃油限制用于建立供应给发动机的燃料的下限，以避免涡轮增压器瞬时压缩机浪涌状况。在一个实施例中，所述至少一个发动机操作参数包括进气歧管空气压力，并且在替代实施例中，所述至少一个发动机操作参数还包括进气歧管空气温度。在任一种情况下，至少一个发动机操作参数也优选地包括发动机转速。

4. 发明授权

US06220234B1 Coated compressor diffuser 有权
标题翻译：涂层压缩机扩散器
公开(公告)号：US06220234B1
公开(公告)日：2001-04-24
申请号：US09357090
申请日：1999-07-19
申请人： Glenn L. Baker , Paul D. Free
发明人： Glenn L. Baker , Paul D. Free
IPC分类号： F02B3344
CPC分类号： F04D25/04 , F02C7/04 , F04D29/023 , F05D2300/43 , F05D2300/437 , F05D2300/611 , Y10S415/915 , Y10T29/49236 , Y10T29/49238 , Y10T29/4932
摘要： A coating for a portion of the flowpath of a diffuser of a centrifugal compressor. The coating covers a portion of the diffuser against which flows high velocity air from the compressor blades. The coating is a smooth, tenacious, heat-resistant powder paint that reduces the aerodynamic drag of the diffuser walls on the high velocity air thus increasing the efficiency of the compressor.
摘要翻译：用于离心压缩机的扩散器的一部分流路的涂层。该涂层覆盖扩散器的一部分，该部分流过来自压缩机叶片的高速空气。该涂层是光滑，耐用的耐热粉末涂料，其降低了高速空气上扩散壁的气动阻力，从而提高了压缩机的效率。

5. 发明授权

US5199261A Internal combustion engine with turbocharger system 失效
标题翻译：具有涡轮增压器系统的内燃机
公开(公告)号：US5199261A
公开(公告)日：1993-04-06
申请号：US925320
申请日：1992-08-04
申请人： Glenn L. Baker
发明人： Glenn L. Baker
IPC分类号： F02B37/013 , F02B37/18
CPC分类号： F02B37/18 , F02B37/004 , F02B37/013 , F02B39/16 , Y02T10/144
摘要： The present invention relates to an internal combustion engine and more particularly to an internal combustion engine which includes a turbocharger system having at least one smaller exhaust gas turbocharger and at least one larger exhaust gas turbocharger, as well as means for controlling the exhaust gas and intake air flow to the respective turbochargers. The turbochargers and control means are interconnected to provide pressurized intake air throughout the entire operating range of the internal combustion engine, while effectively bypassing the smaller exhaust gas turbocharger during operating conditions which produce high exhaust gas volumes. The operating characteristics of this turbocharger system are matched with the operating range of an internal combustion engine to provide improved performance, efficiency, transient response and reliability, while reducing maintenance and undesirable emissions.
摘要翻译：内燃机技术领域本发明涉及一种内燃机，更具体地涉及一种内燃机，其包括具有至少一个较小排气涡轮增压器和至少一个较大排气涡轮增压器的涡轮增压器系统，以及用于控制废气和进气空气流到相应的涡轮增压器。涡轮增压器和控制装置相互连接以在内燃机的整个工作范围内提供加压进气，同时在产生高排气量的运行条件期间有效地绕过较小排气涡轮增压器。该涡轮增压器系统的操作特性与内燃机的工作范围相匹配，以提供改进的性能，效率，瞬态响应和可靠性，同时减少维护和不期望的排放。

6. 发明授权

US08979485B2 Variable geometry turbine 有权
标题翻译：可变几何涡轮机
公开(公告)号：US08979485B2
公开(公告)日：2015-03-17
申请号：US13237473
申请日：2011-09-20
申请人： Glenn L. Baker , Gary Beshears , Timothy James William Proctor , John Frederick Parker , John Michael Bywater
发明人： Glenn L. Baker , Gary Beshears , Timothy James William Proctor , John Frederick Parker , John Michael Bywater
IPC分类号： F01D17/14 , F01D17/16
CPC分类号： F01D17/14 , F01D17/167 , F05D2220/40
摘要： A variable geometry turbine comprising: a housing; a turbine wheel supported in the housing for rotation; an annular inlet passage defined between respective inlet surfaces defined by an annular nozzle ring and a facing annular shroud; the nozzle ring can vary the size of the inlet passage; a circumferential array of inlet vanes; the shroud covering the opening of a shroud cavity defined by the housing inlet passage and inboard of the shroud, and defining a circumferential array of slots, the slots and shroud cavity being configured to receive said vanes accommodating movement of the nozzle ring; wherein the annular shroud comprises an outer flange, the outer flange defining a circumferential groove for receiving a retaining ring for securing the shroud in the opening of the shroud cavity and defined on an inboard side by a flange wall; wherein an annular flange rim extends axially inboard from said flange wall.
摘要翻译：一种可变几何涡轮，包括：壳体; 支撑在壳体中用于旋转的涡轮机叶轮; 环形入口通道限定在由环形喷嘴环和面向环形罩限定的相应入口表面之间; 喷嘴环可以改变入口通道的尺寸; 入口叶片的圆周阵列; 所述护罩覆盖由所述壳体入口通道和所述护罩的内侧限定的护罩腔的开口，并且限定槽的圆周阵列，所述槽和护罩腔被构造成容纳所述叶片容纳所述喷嘴环的运动; 其中所述环形护罩包括外凸缘，所述外凸缘限定圆周槽，用于接收用于将所述护罩固定在所述护罩腔的开口中并由凸缘壁在内侧限定的保持环; 其中环形凸缘边缘从所述凸缘壁轴向向内延伸。

7. 发明授权

US06202413B1 Multiple nozzle ejector for wastegated turbomachinery 有权
标题翻译：用于废水涡轮机的多喷嘴喷射器
公开(公告)号：US06202413B1
公开(公告)日：2001-03-20
申请号：US09244048
申请日：1999-02-04
申请人： Glenn L. Baker , Gregory H. Henderson , P. Douglas Free
发明人： Glenn L. Baker , Gregory H. Henderson , P. Douglas Free
IPC分类号： F02D2300
CPC分类号： F02C3/32 , F01N5/04 , F02B37/025 , F02B37/18 , F05D2220/40 , F05D2260/601 , Y02T10/144 , Y02T10/16
摘要： An improved wastegated turbocharger including ejector nozzles such that the bypassed exhaust flow re-enters the main exhaust flow at a predetermined pitch angle and yaw angle so as to create a drop in turbine back pressure. The exhaust gas turbocharger includes a turbine housing having a turbine chamber, an exhaust housing portion, and an exhaust gas inlet to said turbine chamber wherein a turbine wheel is rotatably mounted in the turbine chamber and is rotatably responsive to exhaust gas flow from the exhaust gas inlet. In one embodiment, an outlet insert is provided which is rigidly attached to the exhaust housing portion and extends toward the turbine chamber thereby defining a bypass chamber and providing an exhaust gas outlet. A bypass flow passage which fluidly connects the exhaust gas inlet with the bypass chamber is also provided. The outlet insert includes a plurality of ejector nozzles for directing exhaust flow from the bypass chamber to the exhaust gas outlet. In another embodiment, an ejector nozzle ring with plurality of ejector nozzles is positioned between the turbine chamber and the outlet insert.
摘要翻译：一种改进的废气涡轮增压器，包括喷射器喷嘴，使得旁路废气流以预定的俯仰角和偏航角度重新进入主排气流，以便产生涡轮机背压的下降。排气涡轮增压器包括涡轮壳体，其具有涡轮室，排气容纳部分和到所述涡轮室的排气入口，其中涡轮机叶轮可旋转地安装在涡轮机室中并且可旋转地响应于来自废气的废气流进口。在一个实施例中，提供出口插入件，其刚性地附接到排气容纳部分并且朝向涡轮室延伸，从而限定旁路室并提供废气出口。还提供了将废气入口与旁路室流体连接的旁通流路。出口插入件包括多个喷射器喷嘴，用于将排气流从旁路室引导到废气出口。在另一个实施例中，具有多个喷射器喷嘴的喷射器喷嘴环位于涡轮室和出口插入件之间。

8. 发明授权

US6123061A Crankcase ventilation system 失效
标题翻译：曲轴箱通风系统
公开(公告)号：US6123061A
公开(公告)日：2000-09-26
申请号：US805935
申请日：1997-02-25
申请人： Glenn L. Baker , David M. Ruch , John M. Partridge , Brett Herrick
发明人： Glenn L. Baker , David M. Ruch , John M. Partridge , Brett Herrick
IPC分类号： F02B33/36 , F01M13/00 , F01M13/02 , F02B37/00 , F02M25/06
CPC分类号： F01M13/021 , F01M13/025 , F01M2013/0055 , F01M2013/0438
摘要： A closed crankcase ventilation system for a turbocharger internal combustion engine which uses differential pressure between the turbo compressor inlet and the crankcase to force blow-by gases through a separation device. The zone of low pressure of the turbo compressor inlet is located at the innermost diameter of the compressor inlet shroud. The difference between the pressure in the compressor inlet and the crankcase creates a vacuum which pulls gas from the crankcase into the ventilation system. The ventilation system includes a high restriction separator for removing oil from the blow-by gases. A control valve bypasses the separation device when insufficient pressure differential exists to drive the separator. Additionally, a system for ventilating crankcase gases from a crankcase of the engine includes a first flow passage communicating between the crankcase and a turbocharger of the engine, an high restriction separator positioned in the flow passage for separating air contaminant mixtures from crankcase gases, a first connection for connecting a first end of the flow passage to the crankcase, a second connection for connecting a second end of the flow passage to a predetermined point of the turbocharger, a second flow passage communicating between the first flow passage and an intake manifold of the engine, and a bypass flow passage for bypassing the separator. In this case, the crankcase gases are directed through the separator during heavy load, light load and idle operating conditions when sufficient vacuum exists to draw the crankcase gases through the coalescing filter and through the bypass flow passage when a sufficient vacuum is not present.
摘要翻译：一种用于涡轮增压器内燃机的闭合曲轴箱通风系统，其使用涡轮压缩机入口和曲轴箱之间的压差来迫使窜气通过分离装置。涡轮压缩机入口的低压区位于压缩机入口护罩的最内径。压缩机入口和曲轴箱之间的压力之差产生了将气体从曲轴箱吸入通风系统的真空。通风系统包括用于从窜气中除去油的高限制分离器。当存在不足的压差来驱动分离器时，控制阀旁路分离装置。此外，用于从发动机的曲轴箱通风曲轴箱气体的系统包括在曲轴箱和发动机的涡轮增压器之间连通的第一流动通道，位于流动通道中的用于将空气污染物混合物与曲轴箱气体分离的高限制分离器，第一用于将流路的第一端连接到曲轴箱的连接件，用于将流动通道的第二端连接到涡轮增压器的预定点的第二连接件，在第一流动通道和第一流动通道之间连通的第二流动通道发动机和用于绕过分离器的旁通流路。在这种情况下，当存在足够的真空时，当不存在足够的真空时，曲轴箱气体在重负载，轻负载和怠速运行条件下被引导通过聚结过滤器和通过旁路流动通道的曲轴箱气体。

9. 发明授权

US5406795A Exhaust manifold to turbine casing flanges 失效
标题翻译：涡轮机壳法兰的排气歧管
公开(公告)号：US5406795A
公开(公告)日：1995-04-18
申请号：US183842
申请日：1994-01-21
申请人： Jonathan H. Raub , Glenn L. Baker
发明人： Jonathan H. Raub , Glenn L. Baker
IPC分类号： F01N13/08 , F01D9/02 , F01N13/10 , F02B37/00 , F02B37/02 , F02B39/00 , F02B67/10 , F02B33/44
CPC分类号： F02B67/10 , F01D9/026 , F01N13/107 , F02B37/00 , F02B37/02 , F02B37/025 , Y02T10/144
摘要： An internal combustion engine has a turbocharger inlet flange mounted to the outlet flange of the exhaust manifold of the engine. The exhaust gas flow out of the manifold is through two ports having a centrally located guide wall directing flow from the manifold out the flange into the turbocharger inlet. The two ports are trapezoidal in shape with a short common dividing wall which, for each port, blends at a short radius into two diverging straight walls, one at each end of the common wall, and which blend from their ends into the outer wall of the port, resulting in trapezoidal port shape. The inlet flange of the turbocharger casing has ports matching and in registry with the two ports of the exhaust manifold flange.
摘要翻译：内燃机具有安装在发动机的排气歧管的出口法兰上的涡轮增压器入口法兰。从歧管流出的废气通过具有居中定位的导向壁的两个端口，其引导从歧管流出法兰进入涡轮增压器入口。两个端口的形状为梯形，具有短的公共分隔壁，对于每个端口，其在短半径处混合成两个发散的直壁，一个在公共壁的每个端部处，并且从其端部共混到外壁端口，形成梯形端口形状。涡轮增压器壳体的入口法兰具有匹配并与排气歧管法兰的两个端口对准的端口。

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