公开(公告)号：US09482277B2

公开(公告)日：2016-11-01

申请号：US14584505

申请日：2014-12-29

Applicant: Hamilton Sundstrand Corporation

Inventor： David A. Dorman ,  Peter A. Wierzbowski

IPC: F16C32/06 ,  F16C33/12 ,  F16C17/02

CPC classification number: F16C33/124 ,  F16C17/024 ,  F16C32/0603 ,  F16C32/0607 ,  F16C33/1005 ,  F16C33/121 ,  F16C2204/44 ,  F16C2223/70 ,  F16C2360/44 ,  F16C2380/26

Abstract: An air bearing shaft for a cabin air compressor includes a first edge and a second edge, a surface extending between the first edge and the second edge, and chrome plating on the surface between the first edge and the second edge. L1 is a first distance from the first edge of the air bearing shaft to a first end of the chrome plating. L2 is a second distance from the first edge of the air bearing shaft to a second end of the chrome plating.

Abstract translation: 用于机舱空气压缩机的空气轴承轴包括第一边缘和第二边缘，在第一边缘和第二边缘之间延伸的表面以及在第一边缘和第二边缘之间的表面上的镀铬。 L1是从空气轴承轴的第一边缘到镀铬的第一端的第一距离。 L2是从空气轴承轴的第一边缘到镀铬的第二端的第二距离。

公开(公告)号：US20160186806A1

公开(公告)日：2016-06-30

申请号：US14584505

申请日：2014-12-29

Applicant: Hamilton Sundstrand Corporation

Inventor： David A. Dorman ,  Peter A. Wierzbowski

IPC: F16C33/12 ,  F16C17/02

CPC classification number: F16C33/124 ,  F16C17/024 ,  F16C32/0603 ,  F16C32/0607 ,  F16C33/1005 ,  F16C33/121 ,  F16C2204/44 ,  F16C2223/70 ,  F16C2360/44 ,  F16C2380/26

Abstract: An air bearing shaft for a cabin air compressor includes a first edge and a second edge, a surface extending between the first edge and the second edge, and chrome plating on the surface between the first edge and the second edge. L1 is a first distance from the first edge of the air bearing shaft to a first end of the chrome plating. L2 is a second distance from the first edge of the air bearing shaft to a second end of the chrome plating.

Abstract translation: 用于机舱空气压缩机的空气轴承轴包括第一边缘和第二边缘，在第一边缘和第二边缘之间延伸的表面以及在第一边缘和第二边缘之间的表面上的镀铬。 L1是从空气轴承轴的第一边缘到镀铬的第一端的第一距离。 L2是从空气轴承轴的第一边缘到镀铬的第二端的第二距离。

公开(公告)号：US20150345506A1

公开(公告)日：2015-12-03

申请号：US14291226

申请日：2014-05-30

Applicant: HAMILTON SUNDSTRAND CORPORATION

Inventor： David A. Dorman ,  Craig M. Beers ,  Peter A. Wierzbowski

IPC: F04D29/46

CPC classification number: F04D29/462 ,  F04D29/624

Abstract: A cover plate for use in a cabin air compressor is a generally cylindrical body with 19 holes extending through the body and an inner bore defining an inner diameter centered on a center axis. The body has a thickness in a dimension measured perpendicular to the central axis. The inner diameter is 14.840 inches (37.693 centimeters) plus/minus .005 inch (0.013 centimeter). A diffusor housing, a cabin air compressor and a method of replacing a cover plate are also disclosed.

Abstract translation: 用于机舱空气压缩机的盖板是大致圆柱形的主体，其具有延伸穿过主体的19个孔和限定以中心轴线为中心的内径的内孔。 主体具有垂直于中心轴测量的尺寸的厚度。 内径为14.840英寸（37.693厘米）加/减.005英寸（0.013厘米）。 还公开了扩散器壳体，机舱空气压缩机和更换盖板的方法。

公开(公告)号：US20140356124A1

公开(公告)日：2014-12-04

申请号：US13909377

申请日：2013-06-04

Applicant: Hamilton Sundstrand Corporation

Inventor： David A. Dorman ,  Harold W. Hipsky ,  Peter A. Wierzbowski ,  Eric Chrabascz ,  Brian Cabello

IPC: F01D9/04

CPC classification number: F01D9/04 ,  F04D29/444 ,  F04D29/681 ,  F05D2250/52

Abstract: A compressor for pressurizing a flow of air within an aircraft including an inlet providing the flow of air to the compressor. An outlet provides the flow of air, after pressurization by the compressor, to a chamber of the aircraft. A diffuser assembly is disposed between the inlet and the outlet. The diffuser assembly includes one or more vanes at least partially impeding the flow of air through the diffuser assembly. A backing plate is included having a surface adjacent to the one or more vanes. The surface includes a relief feature that enables air to bypass the one or more vanes. The relief feature has an axial depth of about 0.25% to 2.5% of a width of a flow path through the diffuser assembly or of about 0.5% to 5% of a thickness of a flange of the backing plate. A method of operating a compressor is also included.

Abstract translation: 一种用于对飞行器内的空气流进行加压的压缩机，包括提供空气流到压缩机的入口。 出口在压缩机加压之后提供空气流到飞行器的腔室。 扩散器组件设置在入口和出口之间。 扩散器组件包括一个或多个叶片，其至少部分地阻碍通过扩散器组件的空气流。 背板包括具有邻近一个或多个叶片的表面。 表面包括使空气绕过一个或多个叶片的浮雕特征。 浮雕特征具有通过扩散器组件的流动通道的宽度的约0.25％至2.5％的轴向深度或背衬板的凸缘的厚度的约0.5％至5％。 还包括操作压缩机的方法。

公开(公告)号：US09568018B2

公开(公告)日：2017-02-14

申请号：US14291226

申请日：2014-05-30

Applicant: HAMILTON SUNDSTRAND CORPORATION

Inventor： David A. Dorman ,  Craig M. Beers ,  Peter A. Wierzbowski

IPC: F04D29/46 ,  F04D29/62

CPC classification number: F04D29/462 ,  F04D29/624

Abstract: A cover plate for use in a cabin air compressor is a generally cylindrical body with 19 holes extending through the body and an inner bore defining an inner diameter centered on a center axis. The body has a thickness in a dimension measured perpendicular to the central axis. The inner diameter is 14.840 inches (37.693 centimeters) plus/minus .005 inch (0.013 centimeter). A diffusor housing, a cabin air compressor and a method of replacing a cover plate are also disclosed.

Abstract translation: 用于机舱空气压缩机的盖板是大致圆柱形的主体，其具有延伸穿过主体的19个孔和限定以中心轴线为中心的内径的内孔。 主体具有垂直于中心轴测量的尺寸的厚度。 内径为14.840英寸（37.693厘米）加/减.005英寸（0.013厘米）。 还公开了扩散器壳体，机舱空气压缩机和更换盖板的方法。

公开(公告)号：US08979026B2

公开(公告)日：2015-03-17

申请号：US13909377

申请日：2013-06-04

Applicant: Hamilton Sundstrand Corporation

Inventor： David A. Dorman ,  Harold W. Hipsky ,  Peter A. Wierzbowski ,  Eric Chrabascz ,  Brian Cabello

IPC: B64D11/00 ,  F01D9/04

CPC classification number: F01D9/04 ,  F04D29/444 ,  F04D29/681 ,  F05D2250/52

Abstract: A compressor for pressurizing a flow of air within an aircraft including an inlet providing the flow of air to the compressor. An outlet provides the flow of air, after pressurization by the compressor, to a chamber of the aircraft. A diffuser assembly is disposed between the inlet and the outlet. The diffuser assembly includes one or more vanes at least partially impeding the flow of air through the diffuser assembly. A backing plate is included having a surface adjacent to the one or more vanes. The surface includes a relief feature that enables air to bypass the one or more vanes. The relief feature has an axial depth of about 0.5% to 2.5% of a width of a flow path through the diffuser assembly or of about 0.5% to 5% of a thickness of a flange of the backing plate. A method of operating a compressor is also included.

Abstract translation: 一种用于对飞行器内的空气流进行加压的压缩机，包括提供空气流到压缩机的入口。 出口在压缩机加压之后提供空气流到飞行器的腔室。 扩散器组件设置在入口和出口之间。 扩散器组件包括一个或多个叶片，其至少部分地阻碍通过扩散器组件的空气流。 背板包括具有邻近一个或多个叶片的表面。 表面包括使空气绕过一个或多个叶片的浮雕特征。 浮雕特征具有通过扩散器组件的流动通道的宽度的约0.5％至2.5％的轴向深度或背衬板的凸缘的厚度的约0.5％至5％。 还包括操作压缩机的方法。