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    METHOD FOR CONTROLLING A TRIM-ADJUSTMENT MECHANISM FOR A CENTRIFUGAL COMPRESSOR
    1.
    发明公开
    METHOD FOR CONTROLLING A TRIM-ADJUSTMENT MECHANISM FOR A CENTRIFUGAL COMPRESSOR 审中-公开
    用于控制离心压缩机的调整机构的方法

    公开(公告)号：EP3176440A1

    公开(公告)日：2017-06-07

    申请号：EP16196440.8

    申请日：2016-10-28

    申请人： Honeywell International Inc.

    发明人： HOUST, Vit ,  SMITH, William Joseph

    IPC分类号： F04D27/02

    CPC分类号： F04D29/464 ,  F01D17/165 ,  F02B37/183 ,  F04D25/045 ,  F04D27/0253 ,  F04D29/284 ,  F04D29/4206 ,  F05D2220/40 ,  Y02T10/144

    摘要： A method for controlling an inlet-adjustment mechanism in an air inlet for a compressor so as to switch the mechanism in a binary fashion between two positions P1 and P2 for adjusting a flow area of the inlet. The method includes identifying a threshold line on a compressor map of pressure ratio versus corrected flow rate for the compressor. The threshold line is a line on which the pressure ratio and flow rate of the compressor are the same for the P1 and P2 positions of the inlet-adjustment mechanism at equal speeds. When the operating point of the compressor on the compressor map crosses the threshold line, the inlet-adjustment mechanism is switched from one of its binary positions to the other.

    摘要翻译： 一种用于控制压缩机的空气入口中的入口调整机构的方法，以在二个位置P1和P2之间以二元方式切换机构以调整入口的流动面积。 该方法包括识别压缩机的压力比图上的阈值线，所述压力比针对压缩机的压力比与校正的流量比。 阈值线是在相同速度下压缩机的压力比和流量对于进口调节机构的P1和P2位置相同的线。 当压缩机图上的压缩机的操作点越过阈值线时，进口调节机构从其二进制位置之一切换到另一位置。

    MULTISTAGE RADIAL COMPRESSOR BAFFLE
    3.
    发明公开
    MULTISTAGE RADIAL COMPRESSOR BAFFLE 审中-公开
    多级径向压缩机BAFFLE

    公开(公告)号：EP3043073A1

    公开(公告)日：2016-07-13

    申请号：EP16150106.9

    申请日：2016-01-04

    申请人： Honeywell International Inc.

    发明人： KARES, Vaclav ,  HOUST, Vit ,  LEDNICKY, Ondrej ,  MOKOS, Michal ,  NEJEDLY, Milan ,  OSELJSEK, Zbynek ,  TURECEK, Daniel

    IPC分类号： F04D17/12 ,  F04D29/08 ,  F04D29/10 ,  F04D29/22 ,  F04D29/28

    CPC分类号： F04D29/083 ,  F04D17/12 ,  F04D17/122 ,  F04D29/102 ,  F04D29/2266 ,  F04D29/284 ,  F04D29/44

    摘要： An assembly can include a first radial compressor wheel that has a rotational axis and that includes a hub surface that includes an annular ridge disposed at a radius measured from the rotational axis; a second radial compressor wheel that includes a hub surface; and an annular baffle disposed at least in part between the hub surfaces where the annular baffle includes an outer surface and an inner edge that defines an opening having a central axis where the outer surface includes a surface portion to one side of the inner edge that faces the hub surface of the first radial compressor wheel, where the surface portion includes an annular channel over a radial width measured from the central axis and where the radial width spans the radius of the annular ridge.

    摘要翻译： 一种组件可以包括：第一径向压缩机叶轮，其具有旋转轴线并且包括轮毂表面，该轮毂表面包括以从旋转轴线测量的半径布置的环形脊; 第二径向压缩机叶轮，其包括轮毂表面; 以及环形挡板，其至少部分地设置在轮毂表面之间，其中环形挡板包括外表面和内边缘，内边缘限定具有中心轴线的开口，其中外表面包括表面部分到内边缘的一侧 第一径向压缩机叶轮的轮毂表面，其中表面部分包括在从中心轴线测量的径向宽度上的环形通道，并且其中径向宽度跨越环形脊的半径。

    Functionally asymmetric two-sided turbocharger wheel and diffuser
    5.
    发明公开
    Functionally asymmetric two-sided turbocharger wheel and diffuser 有权
    Turbolader mit einem funktionell asymmetricrischen zweiseitigen Verdichterrad und Diffusor

    公开(公告)号：EP2843236A1

    公开(公告)日：2015-03-04

    申请号：EP14180284.3

    申请日：2014-08-08

    申请人： Honeywell International Inc.

    发明人： HOUST, Vit ,  TURECEK, Daniel ,  KARES, Vaclav ,  NEJEDLY, Milan ,  MOKOS, Michal ,  CHEN, Hua ,  LI, Annie ,  ZHAO, Michael ,  DAI, Wei ,  BERCIANOS, Jose Luis Lazaro

    IPC分类号： F04D17/10 ,  F04D25/02 ,  F04D29/28 ,  F04D29/44 ,  F02C3/08 ,  F02C6/12

    CPC分类号： F01D5/02 ,  F04D17/105 ,  F04D25/024 ,  F04D29/284 ,  F04D29/441 ,  F05D2220/40 ,  F05D2250/73

    摘要： A two-sided turbocharger compressor wheel and a housing forming a diffuser for the compressor. A first side and a second side of the compressor wheel are characterized by different values of a trim and of an annulus area. A first side of the diffuser surrounds the first side of the compressor wheel, and a second side of the diffuser surrounds the second side of the compressor wheel. The first and second sides of the diffuser are characterized by different annulus area ratios. The blades of the first and second sides of the compressor wheel are angularly offset from one another. The compressor wheel is configured for greater flow through the side of the compressor wheel that faces away from a related turbine wheel.

    摘要翻译： 双面涡轮增压器压缩机叶轮和形成用于压缩机的扩散器的壳体。 压缩机叶轮的第一侧和第二侧的特征在于装饰和环形区域的不同值。 扩散器的第一侧围绕压缩机叶轮的第一侧，并且扩散器的第二侧围绕压缩机叶轮的第二侧。 扩散器的第一和第二侧的特征在于不同的环面积比。 压缩机叶轮的第一和第二侧的叶片彼此成角度地偏移。 压缩机叶轮构造成使得流过压缩机叶轮远离相关涡轮机叶轮的侧面更大的流量。

    ADJUSTABLE-INLET RADIAL-RADIAL COMPRESSOR
    7.
    发明公开
    ADJUSTABLE-INLET RADIAL-RADIAL COMPRESSOR 审中-公开
    RADIAL-RADIALVERDICHTER MIT VERSTELLBAREM EINLASS

    公开(公告)号：EP3059452A1

    公开(公告)日：2016-08-24

    申请号：EP16155122.1

    申请日：2016-02-10

    申请人： Honeywell International Inc.

    发明人： NEJEDLY, Milan ,  HOUST, Vit ,  TURECEK, Daniel

    IPC分类号： F04D27/02 ,  F01D17/14 ,  F02C7/042 ,  F04D29/42 ,  F04D29/46

    CPC分类号： F01D17/141 ,  F02C7/042 ,  F04D27/0246 ,  F04D27/0253 ,  F04D29/4213 ,  F04D29/464 ,  F05D2220/40 ,  F05D2260/53 ,  F05D2270/101

    摘要： A radial-radial compressor includes an inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position in the air inlet. The inlet-adjustment mechanism includes a tubular sleeve that is movable in the air inlet with an axial component of movement for adjusting a spacing distance of a trailing edge of the sleeve from an inducer portion of the wheel. In an "on" position the spacing distance is relatively greater, while in the "off" position the spacing distance is relatively smaller and the sleeve therefore reduces an effective inlet area into the inducer portion of the wheel, relative to the effective inlet area in the "on" position.

    摘要翻译： 径向压缩机包括在压缩机的空气入口中的入口调节机构，可操作以在空气入口中的打开位置和关闭位置之间移动。 入口调节机构包括管状套筒，其可在空气入口中以轴向运动分量运动，用于调节套筒的后缘与车轮的导轮部分的间隔距离。 在“开”位置，间隔距离相对较大，而在“关闭”位置，间隔距离相对较小，因此套筒因此相对于有效入口面积减少了进入车轮的导轮部分的有效入口面积 “开”位置。

    TWO-STAGE COMPRESSOR WITH ASYMMETRIC SECOND-STAGE INLET DUCT
    8.
    发明公开
    TWO-STAGE COMPRESSOR WITH ASYMMETRIC SECOND-STAGE INLET DUCT 审中-公开
    具有不对称二级入口管道的两级压缩机

    公开(公告)号：EP3318762A1

    公开(公告)日：2018-05-09

    申请号：EP17199210.0

    申请日：2017-10-30

    申请人： Honeywell International Inc.

    发明人： KARES, Vaclav ,  HOUST, Vit ,  LEDNICKY, Ondrej ,  NEJEDLY, Milan ,  MOKOS, Michal ,  OSLEJSEK, Zbynek ,  TURECEK, Daniel

    IPC分类号： F04D17/12 ,  F01D9/02 ,  F04D25/04 ,  F02C6/12 ,  F04D29/42

    CPC分类号： F04D29/4206 ,  F01D9/026 ,  F01D25/16 ,  F02B37/00 ,  F02C6/12 ,  F04D17/12 ,  F04D25/04 ,  F04D29/285 ,  F04D29/422 ,  F05D2220/40 ,  F05D2240/14 ,  F05D2240/20 ,  F05D2240/50 ,  Y02T10/144

    摘要： A multi-stage compressor for a turbocharger (10) includes a compressor (20) housing that defines an aperture for receiving a compressor wheel (16) for successively compressing air in first and second stages. First- and second-stage inlets (40, 42) are fluidly connected to the aperture in opposite axial directions, and first- and second-stage volutes (46, 48) extend at least partially annularly therearound so that each volute is configured to receive gas flowing generally radially outward from the compressor wheel. First and second passages (58a, 58b) fluidly connect the first-stage volute to the second-stage inlet. The passages approach the second-stage inlet from opposite radially inward directions, and are asymmetric with respect to any orthogonal axes having an origin lying on the turbocharger rotary axis as viewed on a transverse cross-section that is normal to the turbocharger axis.

    摘要翻译： 用于涡轮增压器（10）的多级压缩机包括压缩机（20）外壳，该外壳限定用于接收压缩机叶轮（16）的孔口，用于连续地压缩第一和第二级中的空气。 第一级入口和第二级入口（40,42）在相反的轴向方向上流体地连接到所述孔口，并且第一级和第二级蜗壳（46,48）至少部分地环绕地在其周围延伸，使得每个蜗壳构造成接收 气体通常从压缩机轮径向向外流动。 第一和第二通道（58a，58b）将第一级蜗壳流体连接到第二级入口。 通道从相反的径向向内方向接近第二级入口，并且相对于在垂直于涡轮增压器轴线的横截面上观察时具有位于涡轮增压器旋转轴线上的原点的任何正交轴线不对称。