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公开(公告)号：EP2781759A3
公开(公告)日：2014-12-10
申请号：EP14160312.6
申请日：2014-03-17
CPC分类号： F02K7/08 , B64D41/007 , F04D19/00 , F04D25/0606 , F04D29/644 , H02K5/06
摘要： A ram air fan assembly (10) includes a motor/bearing housing (30) that extends along a horizontal length of the ram air fan assembly (10). An inner housing assembly (32) is in fluid communication with the motor/bearing housing (30) to define a joint (65) The inner housing assembly (32) includes first and second ellipse-shaped slots (58, 58'). The first slot (58') is positioned at a first angle (θ 1 ) with respect to a radial axis of the inner housing assembly (32) that is perpendicular to the horizontal length, and the second slot (58) is positioned at a second angle (θ 2 ) with respect to the radial axis, the second angle (θ 2 ) being different from the first angle (θ 1 ), and each slot (58, 58') extending along a first direction parallel to the horizontal length to define an axial width (wA) and extending along a radial axis to define a radial width (wR) being greater than the axial width (wA).
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公开(公告)号：EP2811169B1
公开(公告)日：2018-11-14
申请号：EP14170804.0
申请日：2014-06-02
发明人： Dorman, David A. , Hipsky, Harold W. , Wierzbowski, Peter A. , Chrabascz, Eric , Cabello, Brian
CPC分类号： F01D9/04 , F04D29/444 , F04D29/681 , F05D2250/52
摘要： A compressor (16) for pressurizing a flow of air within an aircraft includes an inlet (26) providing the flow of air to the compressor (16). An outlet (28) provides the flow of air, after pressurization by the compressor (16), to a chamber of the aircraft. A diffuser assembly (30) is disposed between the inlet (26) and the outlet (28). The diffuser assembly (30) includes one or more vanes (38) at least partially impeding the flow of air through the diffuser assembly (30). A backing plate (32) is included having a surface (44) adjacent to the one or more vanes (38). The surface (44) includes a relief feature (46) that enables air to bypass the one or more vanes (38). The relief feature (46) has an axial depth (D2) of about 0.25% to 2.5% of a width (D5) of a flow path through the diffuser assembly (30) or of about 0.5% to 5% of a thickness (D4) of a flange (52) of the backing plate (32).
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公开(公告)号：EP2781759B1
公开(公告)日：2016-09-28
申请号：EP14160312.6
申请日：2014-03-17
CPC分类号： F02K7/08 , B64D41/007 , F04D19/00 , F04D25/0606 , F04D29/644 , H02K5/06
摘要： A ram air fan assembly (10) includes a motor/bearing housing (30) that extends along a horizontal length of the ram air fan assembly (10). An inner housing assembly (32) is in fluid communication with the motor/bearing housing (30) to define a joint (65) The inner housing assembly (32) includes first and second ellipse-shaped slots (58, 58'). The first slot (58') is positioned at a first angle (¸ 1 ) with respect to a radial axis of the inner housing assembly (32) that is perpendicular to the horizontal length, and the second slot (58) is positioned at a second angle (¸ 2 ) with respect to the radial axis, the second angle (¸ 2 ) being different from the first angle (¸ 1 ), and each slot (58, 58') extending along a first direction parallel to the horizontal length to define an axial width (wA) and extending along a radial axis to define a radial width (wR) being greater than the axial width (wA).
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4.发明公开Centrifugal compressor bladed diffuser with anti-surge clearance between diffuser vane and diffuser wall 审中-公开离心式压缩机与叶片扩压器和Diffusorleitschaufel和扩散器壁之间的泵排量放牧间隙
公开(公告)号：EP2811169A1
公开(公告)日：2014-12-10
申请号：EP14170804.0
申请日：2014-06-02
发明人： Dorman, David A. , Hipsky, Harold W. , Wierzbowski, Peter A. , Chrabascz, Eric , Cabello, Brian
CPC分类号： F01D9/04 , F04D29/444 , F04D29/681 , F05D2250/52
摘要： A compressor (16) for pressurizing a flow of air within an aircraft includes an inlet (26) providing the flow of air to the compressor (16). An outlet (28) provides the flow of air, after pressurization by the compressor (16), to a chamber of the aircraft. A diffuser assembly (30) is disposed between the inlet (26) and the outlet (28). The diffuser assembly (30) includes one or more vanes (38) at least partially impeding the flow of air through the diffuser assembly (30). A backing plate (32) is included having a surface (44) adjacent to the one or more vanes (38). The surface (44) includes a relief feature (46) that enables air to bypass the one or more vanes (38). The relief feature (46) has an axial depth (D2) of about 0.25% to 2.5% of a width (D5) of a flow path through the diffuser assembly (30) or of about 0.5% to 5% of a thickness (D4) of a flange (52) of the backing plate (32).
摘要翻译： 一种用于加压内的空气的流动，以飞机压缩机（16）包括在入口（26）提供的空气流至所述压缩机（16）。 的出口（28）提供的空气的流动，由压缩机（16）到所述飞行器的腔室加压之后。 扩散器组件（30）在入口（26）和所述出口（28）之间设置。 扩散器组件（30）包括一个或多个叶片（38）至少部分地阻碍空气通过扩散器组件（30）的流动。 背板（32）被包括具有表面（44）相邻的一个或多个叶片（38）。 所述表面（44）包括一个释放特征（46）那样使空气绕过一个或多个叶片（38）。 浮雕特征（46）具有在约0.25％的轴向深度（D2），以通过扩散器组件（30）的流路的宽度（D5）的2.5％或约0.5％至厚度为5％（D4 ）背板（32）的一个凸缘（52）的。
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