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公开(公告)号：US09115649B2
公开(公告)日：2015-08-25
申请号：US13176473
申请日：2011-07-05
CPC分类号： F02C7/36 , F01D5/141 , F01D15/12 , F01D21/045 , F01D25/34 , F02C7/05 , F02K3/06 , Y02T50/673
摘要： A gas turbine engine includes a spool, a turbine coupled to drive the spool, a propulsor coupled to be rotated about an axis by the turbine through the spool, and a gear assembly coupled between the propulsor and the spool such that rotation of the turbine drives the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extend from the hub. Each of the propulsor blades has a span between a root at the hub and a tip, and a chord between a leading edge and a trailing edge. The chord forms a stagger angle α with the axis, and the stagger angle α is less than 15° at a position along the propulsor blade that is within an inboard 20% of the span.
摘要翻译： 燃气涡轮发动机包括阀芯，联接以驱动阀芯的涡轮机，被连接以通过阀芯绕涡轮机绕轴旋转的推进器，以及联接在推进器和阀芯之间的齿轮组件，使得涡轮机驱动 推进器的速度不同于阀芯。 推进器包括从轮毂延伸的轮毂和一排推杆叶片。 每个推进器叶片具有在轮毂的根部与顶端之间的跨度，以及前缘和后缘之间的弦。 弦与轴线形成交错角α，并且在沿着推进刀片的位置处的交错角α小于15°，该推进角度在跨度的20％内。
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公开(公告)号：US09068460B2
公开(公告)日：2015-06-30
申请号：US13435134
申请日：2012-03-30
摘要： A gas turbine engine case structure includes inner and outer annular case portions radially spaced from one another to provide a flow path and circumferentially arranged airfoils extend radially and interconnect the inner and outer annular case portions. The airfoils include multiple vanes and multiple strut-vanes. Each vane has a vane leading edge. Each strut-vane includes a strut-vane leading edge. The vane leading edges and strut-vane leading edges are aligned in a common plane. The vanes include a first axial length and the strut-vanes include a second axial length that is at least double the first axial length.
摘要翻译： 燃气涡轮发动机壳体结构包括彼此径向间隔开的内部和外部环形壳体部分，以提供流动路径，并且周向布置的翼型件径向延伸并且互连内部和外部环形壳体部分。 翼型件包括多个叶片和多个支柱叶片。 每个叶片都有一个叶片前缘。 每个支柱叶片包括支柱叶片前缘。 叶片前缘和支柱叶片前缘在公共平面对齐。 叶片包括第一轴向长度，支柱叶片包括至少是第一轴向长度的两倍的第二轴向长度。
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公开(公告)号：US20130323012A1
公开(公告)日：2013-12-05
申请号：US13487632
申请日：2012-06-04
IPC分类号： F04D29/56
CPC分类号： F01D11/08 , F02C9/20 , F04D27/004 , F04D27/0246 , F04D29/164 , F04D29/563
摘要： A compressor tip clearance management system includes a compressor section having a low pressure compressor and a high pressure compressor arranged downstream from the low pressure compressor. A variable stator vane is arranged upstream from the high pressure compressor. The variable stator vane is connected to an actuator, and a controller is in communication with the actuator. The controller is configured to provide a command to the actuator to move the variable stator vane in response to a high pressure compressor clearance condition. A high pressure compressor rotor speed is altered, and the high pressure compressor clearance condition is changed to a desired clearance.
摘要翻译： 压缩机顶端间隙管理系统包括压缩机部分，其具有布置在低压压缩机下游的低压压缩机和高压压缩机。 可变定子叶片布置在高压压缩机的上游。 可变定子叶片连接到致动器，并且控制器与致动器连通。 控制器构造成响应于高压压缩机间隙状况向致动器提供命令以移动可变定子叶片。 改变高压压缩机转子速度，将高压压缩机间隙条件改变为期望的间隙。
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公开(公告)号：US08438832B1
公开(公告)日：2013-05-14
申请号：US13407857
申请日：2012-02-29
IPC分类号： F02K3/02
CPC分类号： F01D5/141 , F02C7/36 , F02K3/072 , F05D2220/36 , Y02T50/673
摘要： A turbine engine includes a fan section that rotates about a longitudinal axis and a compressor section. The turbine engine also includes a fan exit stator located between the fan section and the compressor section, the fan exit stator including an airfoil. The airfoil defines an entrance angle with respect to a leading edge of the airfoil and a line parallel to the longitudinal axis, and the airfoil defines an exit angle with respect to a trailing edge of the airfoil and a line parallel to the longitudinal axis. A difference between the entrance angle and the exit angle is between about 45° and about 65°. The turbine engine also includes a turbine section, and a portion of the compressor section is driven by a portion of the turbine section.
摘要翻译： 涡轮发动机包括围绕纵向轴线和压缩机部分旋转的风扇部分。 涡轮发动机还包括位于风扇部分和压缩机部分之间的风扇出口定子，风扇出口定子包括翼型件。 翼型件相对于翼型件的前缘和平行于纵向轴线的线限定入口角，并且翼型件相对于翼型件的后缘和平行于纵向轴线的线限定出口角。 入射角和出射角之间的差异在大约45°和大约65°之间。 涡轮发动机还包括涡轮部分，并且压缩机部分的一部分由涡轮部分的一部分驱动。
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公开(公告)号：US09097133B2
公开(公告)日：2015-08-04
申请号：US13487632
申请日：2012-06-04
CPC分类号： F01D11/08 , F02C9/20 , F04D27/004 , F04D27/0246 , F04D29/164 , F04D29/563
摘要： A compressor tip clearance management system includes a compressor section having a low pressure compressor and a high pressure compressor arranged downstream from the low pressure compressor. A variable stator vane is arranged upstream from the high pressure compressor. The variable stator vane is connected to an actuator, and a controller is in communication with the actuator. The controller is configured to provide a command to the actuator to move the variable stator vane in response to a high pressure compressor clearance condition. A high pressure compressor rotor speed is altered, and the high pressure compressor clearance condition is changed to a desired clearance.
摘要翻译： 压缩机顶端间隙管理系统包括压缩机部分，其具有布置在低压压缩机下游的低压压缩机和高压压缩机。 可变定子叶片布置在高压压缩机的上游。 可变定子叶片连接到致动器，并且控制器与致动器连通。 控制器构造成响应于高压压缩机间隙状况向致动器提供命令以移动可变定子叶片。 改变高压压缩机转子速度，将高压压缩机间隙条件改变为期望的间隙。
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公开(公告)号：US20130192198A1
公开(公告)日：2013-08-01
申请号：US13409305
申请日：2012-03-01
CPC分类号： F04D29/547 , F02K3/04 , F02K3/06 , F04D19/028 , F04D25/045 , F04D29/321 , F04D29/563 , F04D29/682 , F05D2220/3217 , F05D2220/36 , F05D2260/606
摘要： A core flowpath through a low pressure compressor section of a gas turbine engine includes an outer diameter, which has a slope angle relative to an axis defined by the core flowpath. The slope angle is a slope angle that is operable to prevent flow separation of a fluid passing through the core flowpath.
摘要翻译： 通过燃气涡轮发动机的低压压缩机部分的核心流路包括外径，其相对于由芯流动路径限定的轴线具有倾斜角。 斜角是可操作以防止通过芯流动路径的流体的流动分离的倾斜角度。
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7.发明授权公开(公告)号：US08452516B1
公开(公告)日：2013-05-28
申请号：US13446326
申请日：2012-04-13
申请人： Becky E. Rose , Lisa I. Brilliant
发明人： Becky E. Rose , Lisa I. Brilliant
IPC分类号： G06F19/00 , G06G7/70 , F02C7/05 , B64D33/02 , F01D5/14 , F01D5/12 , F01D25/00 , F01D13/02 , F01D17/00 , F03D11/00 , F03B11/00 , F04D29/38 , F01B25/00 , F01B25/02
CPC分类号： B64D45/00 , B64D2033/022 , F01D17/162 , F02C7/05 , F02C9/20 , F04D27/0292 , F04D29/563 , F05D2270/114
摘要： A method of protecting a gas turbine engine according an exemplary aspect of the present disclosure includes, among other things, the steps of determining at least one flight condition of an aircraft and comparing the at least one flight condition to a programmed condition. The method further includes the steps of moving a plurality of inlet vanes of a low pressure compressor from a first position to a second position if the step of comparing the at least one flight condition to the programmed flight condition determines the programmed flight condition are met and deflecting any foreign objects with the plurality of inlet vanes.
摘要翻译： 根据本公开的示例性方面的保护燃气涡轮发动机的方法包括确定飞机的至少一个飞行状况并将至少一个飞行状况与编程状态进行比较的步骤。 该方法还包括以下步骤：如果将至少一个飞行条件与编程的飞行条件进行比较的步骤确定已满足编程的飞行条件，则将低压压缩机的多个入口叶片从第一位置移动到第二位置， 用多个入口叶片偏转任何异物。
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公开(公告)号：US20130259672A1
公开(公告)日：2013-10-03
申请号：US13435134
申请日：2012-03-30
摘要： A gas turbine engine case structure includes inner and outer annular case portions radially spaced from one another to provide a flow path and circumferentially arranged airfoils extend radially and interconnect the inner and outer annular case portions. The airfoils include multiple vanes and multiple strut-vanes. Each vane has a vane leading edge. Each strut-vane includes a strut-vane leading edge. The vane leading edges and strut-vane leading edges are aligned in a common plane. The vanes include a first axial length and the strut-vanes include a second axial length that is at least double the first axial length.
摘要翻译： 燃气涡轮发动机壳体结构包括彼此径向间隔开的内部和外部环形壳体部分，以提供流动路径，并且周向布置的翼型件径向延伸并且互连内部和外部环形壳体部分。 翼型件包括多个叶片和多个支柱叶片。 每个叶片都有一个叶片前缘。 每个支柱叶片包括支柱叶片前缘。 叶片前缘和支柱叶片前缘在公共平面对齐。 叶片包括第一轴向长度，支柱叶片包括至少是第一轴向长度的两倍的第二轴向长度。
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公开(公告)号：US20130011266A1
公开(公告)日：2013-01-10
申请号：US13176473
申请日：2011-07-05
IPC分类号： F01D5/14
CPC分类号： F02C7/36 , F01D5/141 , F01D15/12 , F01D21/045 , F01D25/34 , F02C7/05 , F02K3/06 , Y02T50/673
摘要： A gas turbine engine includes a spool, a turbine coupled to drive the spool, a propulsor coupled to be rotated about an axis by the turbine through the spool, and a gear assembly coupled between the propulsor and the spool such that rotation of the turbine drives the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extend from the hub. Each of the propulsor blades has a span between a root at the hub and a tip, and a chord between a leading edge and a trailing edge. The chord forms a stagger angle α with the axis, and the stagger angle α is less than 15° at a position along the propulsor blade that is within an inboard 20% of the span.
摘要翻译： 燃气涡轮发动机包括阀芯，联接以驱动阀芯的涡轮机，被连接以通过阀芯绕涡轮机绕轴旋转的推进器，以及联接在推进器和阀芯之间的齿轮组件，使得涡轮机驱动 推进器的速度不同于阀芯。 推进器包括从轮毂延伸的轮毂和一排推杆叶片。 每个推进器叶片具有在轮毂的根部与顶端之间的跨度，以及前缘和后缘之间的弦。 弦与轴线形成交错角α，并且在沿着推进刀片的位置处的交错角α小于15°，该推进角度在跨度的20％内。
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