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    TURBINE HOUSING WITH DIVIDING VANES IN VOLUTE
    1.
    发明申请
    TURBINE HOUSING WITH DIVIDING VANES IN VOLUTE 审中-公开
    具有分体积的涡轮机外壳

    公开(公告)号：US20160024999A1

    公开(公告)日：2016-01-28

    申请号：US14653946

    申请日：2013-12-02

    Applicant: BORGWARNER INC.

    Inventor： David G. Grabowska ,  Adam R. Reinke

    IPC: F02B37/24 ,  F02M25/07 ,  F01D25/24 ,  F01D17/14 ,  F01D5/02 ,  F01D9/02

    CPC classification number: F02B37/24 ,  F01D5/02 ,  F01D9/02 ,  F01D17/14 ,  F01D17/148 ,  F01D17/18 ,  F01D25/24 ,  F02B37/22 ,  F02M26/10 ,  Y02T10/144

    Abstract: A turbocharger turbine (10) having a turbine wheel (12) and a turbine housing (14) with a volute (20). The turbine housing (14) has dividing vanes (24) in the curved portion (22) of the volute (20) for use with a turbine (10) as mixed-flow or axial-flow. A valve (36) controls exhaust gas flow to one or both of an outer volute portion (26) and an inner volute portion (28) formed on each side of the dividing vanes (24).

    Abstract translation: 具有涡轮机叶轮（12）的涡轮增压器涡轮机（10）和具有蜗壳（20）的涡轮机壳体（14）。 涡轮壳体（14）在蜗壳（20）的弯曲部分（22）中具有与涡轮机（10）一起用作混合流动或轴向流动的分隔叶片（24）。 阀（36）控制排气流到形成在分隔叶片（24）的每一侧的外蜗壳部分（26）和内蜗壳部分（28）中的一个或两个。

    MIXED-FLOW TURBOCHARGER WITH VARIABLE TURBINE GEOMETRY
    2.
    发明申请
    MIXED-FLOW TURBOCHARGER WITH VARIABLE TURBINE GEOMETRY 审中-公开
    具有可变涡轮几何的混合流量涡轮增压器

    公开(公告)号：US20150016968A1

    公开(公告)日：2015-01-15

    申请号：US14374393

    申请日：2013-01-28

    Applicant: BorgWarner Inc.

    Inventor： David G. Grabowska ,  Jaroslaw Kierat ,  Olgierd Urbanczyk ,  Andrzej Mazurek

    IPC: F04D29/56 ,  F02B37/22

    CPC classification number: F04D29/563 ,  F01D17/165 ,  F02B37/22 ,  F02B37/24 ,  F05D2220/40 ,  F05D2250/314 ,  Y02T10/144

    Abstract: A turbocharger (10) including variable turbine geometry has a turbine wheel (24) with a turbine axis of rotation (R1) that extends in an axial direction. The turbocharger (10) also has a plurality of guide vanes (34) that is selectively movable between a range of angular positions. Each one of the guide vanes (34) is supported for pivotal movement about a guide vane axis of rotation (R2) and each guide vane axis of rotation (R2) is non-parallel to the turbine axis of rotation (R1).

    Abstract translation: 包括可变涡轮机几何形状的涡轮增压器（10）具有涡轮机叶轮（24），其具有在轴向方向上延伸的涡轮机旋转轴线（R1）。 涡轮增压器（10）还具有多个导向叶片（34），其能够在一定范围的角位置之间移动。 导向叶片（34）中的每一个被支撑以围绕导向叶片旋转轴线（R2）枢转运动，并且每个导向叶片旋转轴线（R2）不平行于涡轮机旋转轴线（R1）。

    COMPRESSOR RECIRCULATION INTO ANNULAR VOLUME
    4.
    发明申请
    COMPRESSOR RECIRCULATION INTO ANNULAR VOLUME 审中-公开

    公开(公告)号：US20190055952A1

    公开(公告)日：2019-02-21

    申请号：US16166439

    申请日：2018-10-22

    Applicant: BorgWarner Inc.

    Inventor： Paul K. Anschel ,  David G. Grabowska ,  Brock Fraser

    IPC: F04D27/02 ,  F02M26/06 ,  F01D17/10 ,  F01D17/16 ,  F02M26/09 ,  F02M26/19 ,  F02B37/16 ,  F01D9/02 ,  F02C6/12

    Abstract: To solve the problems of compressor wheel blade flow separation causing surge type noises when an exhaust gas recirculation (EGR) duct introduces into the compressor exhaust gases to be returned to the engine, the exhaust gas is fed into an annular volume, defined between inner and outer walls or an annular transition cavity shaped as a radially expanded, axially flattened cylindrical space in the compressor inlet, so that the generally unidirectional radial flow from an EGR duct is re-directed and organized as it is turned from generally radial to generally axial, merging with the general inlet flow and presenting the compressor wheel with airflow of “circumferentially uniform” flow velocity.

    METHODS AND STRUCTURE FOR REDUCING LOSSES IN 90 DEGREE WASTE GATES FOR TURBOCHARGERS
    5.
    发明申请
    METHODS AND STRUCTURE FOR REDUCING LOSSES IN 90 DEGREE WASTE GATES FOR TURBOCHARGERS 审中-公开
    用于减少90度瓦斯凿岩机损失的方法和结构

    公开(公告)号：US20150345375A1

    公开(公告)日：2015-12-03

    申请号：US14653463

    申请日：2013-12-02

    Applicant: BORGWARNER INC.

    Inventor： David G. Grabowska

    IPC: F02B37/18 ,  F04D29/28 ,  F04D29/42 ,  F16K1/16 ,  F04D17/10

    CPC classification number: F02B37/183 ,  F02B37/12 ,  F04D17/10 ,  F04D29/284 ,  F04D29/4206 ,  F16K1/16 ,  Y02T10/144

    Abstract: A turbocharger (10) has an improved wastegate valve assembly (45) wherein a port-controlling valve body (44) includes flow formations which serve to reduce exhaust gas flow in non-optimal directions transverse to an optimal flow direction in the direction of a wastegate passage (26). These flow formations serve to optimize or maximize the flow of exhaust gas in the optimal or primary flow direction as the exhaust gas flow turns through a turn angle (47) from an inlet direction (29) to the optimal flow direction.

    Abstract translation: 涡轮增压器（10）具有改进的废气门阀组件（45），其中端口控制阀体（44）包括流动结构，其用于减少横向于最佳流动方向的非最佳方向上的排气流动 废气通道（26）。 当废气流从入口方向（29）转换到最佳流动方向转动角（47）时，这些流动结构用于优化或最大化最佳或主流动方向上的废气流。

    TURBOCHARGER SHROUD WITH CROSS-WISE GROOVES AND TURBOCHARGER INCORPORATING THE SAME
    6.
    发明申请
    TURBOCHARGER SHROUD WITH CROSS-WISE GROOVES AND TURBOCHARGER INCORPORATING THE SAME 有权
    涡轮增压器与具有相同功能的交叉瓦楞车和涡轮增压器

    公开(公告)号：US20150118079A1

    公开(公告)日：2015-04-30

    申请号：US14395281

    申请日：2013-04-11

    Applicant: BorgWarner Inc.

    Inventor： Stephanie Dextraze ,  David G. Grabowska

    IPC: F01D5/14 ,  F04D25/04 ,  F04D29/28 ,  F01D5/04 ,  F04D17/10

    CPC classification number: F01D5/143 ,  F01D5/048 ,  F01D5/145 ,  F01D5/146 ,  F01D5/20 ,  F01D11/02 ,  F04D17/10 ,  F04D25/04 ,  F04D29/162 ,  F04D29/284 ,  F04D29/4206 ,  F04D29/526 ,  F04D29/685 ,  F05D2220/40 ,  Y10S415/914

    Abstract: A turbocharger (5) comprising a housing (10) including a compressor shroud (14) and a turbine shroud (12). A compressor wheel (18) is disposed in the compressor shroud (14) and includes a plurality of compressor blades (45, 46). Each compressor blade (45, 46) includes a leading edge (50, 51) and a compressor shroud contour edge (54, 55), wherein each compressor shroud contour edge (54, 55) is in close confronting relation to the compressor shroud (14). A turbine wheel (16) is disposed in the turbine shroud (12) and includes a plurality of turbine blades (26). Each turbine blade (26) includes a leading edge (30) and a turbine shroud contour edge (34), wherein each turbine shroud contour edge (34) is in close confronting relation to the turbine shroud (12). At least one of the compressor shroud (14) and turbine shroud (12) includes a plurality of grooves (70, 72) extending cross-wise with respect to the corresponding compressor or turbine shroud contour edges (34, 54, 55).

    Abstract translation: 一种涡轮增压器（5），包括包括压缩机罩（14）和涡轮罩（12）的壳体（10）。 压缩机叶轮（18）设置在压缩机罩（14）中并且包括多个压缩机叶片（45,46）。 每个压缩机叶片（45,46）包括前缘（50,51）和压缩机护罩轮廓边缘（54,55），其中每个压缩机护罩轮廓边缘（54,55）与压缩机护罩处于紧密的相对关系 14）。 涡轮机叶轮（16）设置在涡轮机罩（12）中并且包括多个涡轮机叶片（26）。 每个涡轮机叶片（26）包括前缘（30）和涡轮机护罩轮廓边缘（34），其中每个涡轮机护罩轮廓边缘（34）与涡轮机护罩（12）处于紧密相对的关系。 压缩机护罩（14）和涡轮机护罩（12）中的至少一个包括相对于相应的压缩机或涡轮机护罩轮廓边缘（34,54,55）横向延伸的多个槽（70,72）。

    Compressor recirculation into annular volume
    7.
    发明授权
    Compressor recirculation into annular volume 有权

    公开(公告)号：US11261873B2

    公开(公告)日：2022-03-01

    申请号：US16166439

    申请日：2018-10-22

    Applicant: BorgWarner Inc.

    Inventor： Paul K. Anschel ,  David G. Grabowska ,  Brock Fraser

    IPC: F04D27/02 ,  F01D9/02 ,  F01D17/10 ,  F01D17/16 ,  F02C6/12 ,  F02B37/16 ,  F02M26/06 ,  F02M26/09 ,  F02M26/19

    Abstract: To solve the problems of compressor wheel blade flow separation causing surge type noises when an exhaust gas recirculation (EGR) duct introduces into the compressor exhaust gases to be returned to the engine, the exhaust gas is fed into an annular volume, defined between inner and outer walls or an annular transition cavity shaped as a radially expanded, axially flattened cylindrical space in the compressor inlet, so that the generally unidirectional radial flow from an EGR duct is re-directed and organized as it is turned from generally radial to generally axial, merging with the general inlet flow and presenting the compressor wheel with airflow of “circumferentially uniform” flow velocity.

    FLINGER OIL SEAL AND TURBOCHARGER INCORPORATING THE SAME
    8.
    发明申请
    FLINGER OIL SEAL AND TURBOCHARGER INCORPORATING THE SAME 审中-公开
    飞机油封和涡轮增压器同时进行

    公开(公告)号：US20150125263A1

    公开(公告)日：2015-05-07

    申请号：US14399985

    申请日：2013-05-01

    Applicant: BorgWarner Inc.

    Inventor： David G. Grabowska

    IPC: F04D29/051 ,  F04D17/10 ,  F02M25/07

    CPC classification number: F04D29/051 ,  F01D11/003 ,  F01D25/18 ,  F02B39/14 ,  F02M26/04 ,  F04D17/10 ,  F04D25/024 ,  F04D29/102 ,  F05D2220/40 ,  F05D2240/55 ,  F05D2240/70 ,  F16J15/164

    Abstract: A compressor oil seal comprising a thrust bearing (59) adapted for insertion into a turbocharger housing cavity (33), concentric with the turbocharger's compressor wheel shaft (11). An insert (360) is adapted for insertion into the cavity (33) adjacent the thrust bearing (59), wherein the thrust bearing (59) and insert (360) are configured to provide an oil drain cavity (35) therebetween. The oil seal also includes an oil flinger (340) that includes a flinger flange (382) and a sleeve portion (383) extending therefrom. The flinger flange (382) extends between the thrust bearing (59) and the insert (360). A plurality of spiral vane segments (74) are circumferentially spaced about the flinger flange (382). Each spiral vane segment (74) extends arcuately from a first end (372) to a second end (373). The spiral vane segments (74) are disposed between the flinger flange (382) and the insert (360). The spiral vane segments (74) may extend into a recess (363) formed into the insert (360), and the recess (363) may include at least one discharge port (370).

    Abstract translation: 一种压缩机油封，包括适于插入与涡轮增压器的压缩机叶轮轴（11）同心的涡轮增压器容纳空腔（33）中的推力轴承（59）。 插入件（360）适于插入靠近推力轴承（59）的空腔（33）中，其中推力轴承（59）和插入件（360）构造成在其间提供排油腔（35）。 所述油封还包括一个油喷溅器（340），其包括一个抛油环凸缘（382）和一个从其延伸的套筒部分（383）。 挡板凸缘（382）在止推轴承（59）和插入件（360）之间延伸。 多个螺旋叶片段（74）围绕抛光轮凸缘（382）周向隔开。 每个螺旋叶片段（74）从第一端（372）到第二端（373）呈弧形延伸。 螺旋叶片段（74）设置在抛光轮凸缘（382）和插入件（360）之间。 螺旋叶片段（74）可以延伸到形成到插入件（360）中的凹槽（363）中，并且凹部（363）可以包括至少一个排出口（370）。

    TURBOCHARGER BLADE WITH CONTOUR EDGE RELIEF AND TURBOCHARGER INCORPORATING THE SAME
    9.
    发明申请
    TURBOCHARGER BLADE WITH CONTOUR EDGE RELIEF AND TURBOCHARGER INCORPORATING THE SAME 审中-公开
    具有轮廓边缘的涡轮叶片和与其同时进行的涡轮增压器

    公开(公告)号：US20150086395A1

    公开(公告)日：2015-03-26

    申请号：US14395251

    申请日：2013-04-09

    Applicant: BorgWarner Inc.

    Inventor： Stephanie Dextraze ,  David G. Grabowska

    IPC: F04D25/04 ,  F04D29/30 ,  F04D17/10 ,  F02B37/00 ,  F01D5/04

    CPC classification number: F04D25/045 ,  F01D5/048 ,  F02B37/00 ,  F04D17/10 ,  F04D25/024 ,  F04D29/162 ,  F04D29/284 ,  F04D29/30 ,  F04D29/4206 ,  F04D29/685 ,  F05D2220/40 ,  F05D2240/127 ,  F05D2250/192 ,  F05D2250/60 ,  F05D2260/941

    Abstract: A turbocharger (5) comprising a housing (10) including a compressor shroud (14) and a turbine shroud (12). The turbocharger (5) further comprises compressor wheel (18) and a turbine wheel (16). The compressor wheel (18) includes a compressor hub (44) and a plurality of compressor blades (45, 46) extending radially from the compressor hub (44). Each compressor blade (45, 46) includes a leading edge (50, 51), a trailing edge (52, 53), and a compressor shroud contour edge (54, 55) extending therebetween. The turbine wheel (16) includes a turbine hub (24) and a plurality of turbine blades (26) extending radially from the turbine hub (24). Each turbine blade (26) including a leading edge (30), a trailing edge (32), and a turbine shroud contour edge (34) extending therebetween. At least one of the compressor and turbine blades includes an edge relief (40, 60, 61) formed along at least a portion of the corresponding compressor or turbine shroud contour edge.

    Abstract translation: 一种涡轮增压器（5），包括包括压缩机罩（14）和涡轮罩（12）的壳体（10）。 涡轮增压器（5）还包括压缩机叶轮（18）和涡轮机叶轮（16）。 压缩机叶轮（18）包括压缩机毂（44）和从压缩机毂（44）径向延伸的多个压缩机叶片（45,46）。 每个压缩机叶片（45,46）包括前缘（50,51），后缘（52,53）和在它们之间延伸的压缩机护罩轮廓边缘（54,55）。 涡轮机叶轮（16）包括涡轮机毂（24）和从涡轮机毂（24）径向延伸的多个涡轮叶片（26）。 每个涡轮叶片（26）包括前缘（30），后缘（32）和在它们之间延伸的涡轮机护罩轮廓边缘（34）。 压缩机和涡轮机叶片中的至少一个包括沿着相应的压缩机或涡轮机护罩轮廓边缘的至少一部分形成的边缘浮雕（40,60,61）。

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