公开(公告)号：US20120272663A1

公开(公告)日：2012-11-01

申请号：US13096295

申请日：2011-04-28

申请人： Zaher Milad Moussa ,  David Paul Miller ,  David Vickery Parker

发明人： Zaher Milad Moussa ,  David Paul Miller ,  David Vickery Parker

IPC分类号： F02C3/04 ,  F01D9/04

CPC分类号： F04D29/285 ,  F01D5/146 ,  F02C3/08 ,  F04D29/30 ,  F04D29/444 ,  F05D2220/40

摘要： A compressor assembly for a gas turbine engine includes rotatable impeller with forward and aft ends, including: an annular hub defining a generally concave-curved cross-sectional inner flowpath surface at its radially outer periphery, the inner flowpath surface extending between an inlet and an exit; an annular array of airfoil-shaped inducer blades extending radially outward from the inner flowpath surface near the forward end; and an annular array of exducer blades extending outward from the inner flowpath surface, the array of exducer blades axially spaced apart from the array of inducer blades; a non-rotating shroud assembly surrounding the impeller and including a convex-curved outer flowpath surface, wherein the inner and outer flowpath surfaces cooperate to define a primary flowpath past the blades and the stator vanes; and an annular array of airfoil-shaped stator vanes extending radially inward from the outer flowpath surface into a space between the inducer and exducer blades.

摘要翻译： 一种用于燃气涡轮发动机的压缩机组件包括具有前端和后端的可旋转叶轮，包括：环形毂，在其径向外周边限定大体上为凹曲面的横截面内流道表面，内流道表面在进口和 出口; 从靠近前端的内部流路表面径向向外延伸的翼型形状的叶片的环形阵列; 以及从所述内部流路表面向外延伸的所述驱动器叶片的环形阵列，所述驱动器叶片阵列与所述诱导叶片阵列轴向间隔开; 围绕所述叶轮并且包括凸曲面的外部流动路径表面的非旋转罩组件，其中所述内部和外部流动路径表面协作以限定通过所述叶片和所述定子叶片的主要流路; 以及从外部流路表面径向向内延伸到引导器和驱动器叶片之间的空间中的翼型定子叶片的环形阵列。

公开(公告)号：US07798777B2

公开(公告)日：2010-09-21

申请号：US11611558

申请日：2006-12-15

申请人： Zaher Milad Moussa ,  Caroline Curtis Granda ,  Robert Albert Walter

发明人： Zaher Milad Moussa ,  Caroline Curtis Granda ,  Robert Albert Walter

IPC分类号： F03D11/00

CPC分类号： F04D29/441

摘要： A compressor assembly for a gas turbine engine is provided. The compressor assembly includes a rotating impeller including an inlet, an outlet, and a body extending therebetween. The compressor assembly further includes a non-rotating impeller shroud. The body and the shroud define an impeller chamber including a radially inner surface and a radially outer surface. The radially inner surface includes an arcuate flow surface. The flow surface includes a first portion and a second portion extending downstream from the first portion. The impeller chamber includes a variable area wherein a first cross-sectional area is defined between the radially outer surface and the first portion, and a second cross-sectional area is defined downstream from the first cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. A method of operating the compressor assembly is also included.

摘要翻译： 提供了一种用于燃气涡轮发动机的压缩机组件。 压缩机组件包括旋转叶轮，其包括入口，出口和在其间延伸的主体。 压缩机组件还包括不旋转的叶轮罩。 主体和护罩限定了包括径向内表面和径向外表面的叶轮室。 径向内表面包括弧形流动表面。 流动表面包括第一部分和从第一部分下游延伸的第二部分。 叶轮室包括可变区域，其中在径向外表面和第一部分之间限定第一横截面积，并且第二横截面面积被限定在第一横截面积的下游。 第一截面积大于第二横截面积。 还包括操作压缩机组件的方法。

公开(公告)号：US20080145213A1

公开(公告)日：2008-06-19

申请号：US11611558

申请日：2006-12-15

申请人： Zaher Milad Moussa ,  Caroline Curtis Granda ,  Robert Allbert Walter

发明人： Zaher Milad Moussa ,  Caroline Curtis Granda ,  Robert Allbert Walter

IPC分类号： F04D29/40

CPC分类号： F04D29/441

摘要： A compressor assembly for a gas turbine engine is provided. The compressor assembly includes a rotating impeller including an inlet, an outlet, and a body extending therebetween. The compressor assembly further includes a non-rotating impeller shroud. The body and the shroud define an impeller chamber including a radially inner surface and a radially outer surface. The radially inner surface includes an arcuate flow surface. The flow surface includes a first portion and a second portion extending downstream from the first portion. The impeller chamber includes a variable area wherein a first cross-sectional area is defined between the radially outer surface and the first portion, and a second cross-sectional area is defined downstream from the first cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. A method of operating the compressor assembly is also included.

摘要翻译： 提供了一种用于燃气涡轮发动机的压缩机组件。 压缩机组件包括旋转叶轮，其包括入口，出口和在其间延伸的主体。 压缩机组件还包括不旋转的叶轮罩。 主体和护罩限定了包括径向内表面和径向外表面的叶轮室。 径向内表面包括弧形流动表面。 流动表面包括第一部分和从第一部分下游延伸的第二部分。 叶轮室包括可变区域，其中在径向外表面和第一部分之间限定第一横截面积，并且第二横截面面积被限定在第一横截面积的下游。 第一截面积大于第二横截面积。 还包括操作压缩机组件的方法。

公开(公告)号：US06540481B2

公开(公告)日：2003-04-01

申请号：US09826113

申请日：2001-04-04

申请人： Zaher Milad Moussa ,  Gilbert John Laidlaw ,  David John Tapparo

发明人： Zaher Milad Moussa ,  Gilbert John Laidlaw ,  David John Tapparo

IPC分类号： F01D904

CPC分类号： F04D29/681 ,  F01D5/145 ,  F01D9/045 ,  F04D29/441 ,  F04D29/444 ,  F05D2240/128 ,  F05D2250/52 ,  Y02T50/673

摘要： A diffuser for a centrifugal compressor in which the diffuser has a plurality of passageways that each include a diffuser inlet region, a diffuser throat region, and a diffusion region. Within the diffuser inlet region are positioned pairs of opposed ridges that disrupt the boundary layer growth and minimize aerodynamic blockage at the throat region. The diffusion region includes a first diffusion region downstream of the throat region and that has a first area expansion ratio, and the second diffusion region that includes flow dividers to allow a total area expansion rate within the second diffusion region that is about twice that of the area expansion rate in the first diffusion region.