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1. 发明申请

US20130011266A1 FAN STAGGER ANGLE FOR DIRT REJECTION 有权
标题翻译：风扇防护角风扇角
公开(公告)号：US20130011266A1
公开(公告)日：2013-01-10
申请号：US13176473
申请日：2011-07-05
申请人： Edward J. Gallagher , Becky E. Rose , Lisa I. Brilliant
发明人： Edward J. Gallagher , Becky E. Rose , Lisa I. Brilliant
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。

2. 发明授权

US09115649B2 Fan stagger angle for dirt rejection 有权
标题翻译：风扇交错角度排污
公开(公告)号：US09115649B2
公开(公告)日：2015-08-25
申请号：US13176473
申请日：2011-07-05
申请人： Edward J. Gallagher , Becky E. Rose , Lisa I. Brilliant
发明人： Edward J. Gallagher , Becky E. Rose , Lisa I. Brilliant
IPC分类号： F02C7/36 , F01D15/12 , F01D25/34 , F02C7/05 , F02K3/06
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。

3. 发明授权

US08452516B1 Variable vane scheduling based on flight conditions for inclement weather 有权
标题翻译：基于恶劣天气的飞行条件的可变叶片调度
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。

4. 发明授权

US08438832B1 High turning fan exit stator 有权
标题翻译：高转向风扇出口定子
公开(公告)号：US08438832B1
公开(公告)日：2013-05-14
申请号：US13407857
申请日：2012-02-29
申请人： Lisa I. Brilliant , Becky E. Rose , Yuan Dong , Stanley J. Balamucki
发明人： Lisa I. Brilliant , Becky E. Rose , Yuan Dong , Stanley J. Balamucki
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。

5. 发明申请

US20130192198A1 COMPRESSOR FLOWPATH 审中-公开
标题翻译：压缩机流量
公开(公告)号：US20130192198A1
公开(公告)日：2013-08-01
申请号：US13409305
申请日：2012-03-01
申请人： Lisa I. Brilliant , Becky E. Rose , Yuan Dong , Stanley J. Balamucki
发明人： Lisa I. Brilliant , Becky E. Rose , Yuan Dong , Stanley J. Balamucki
IPC分类号： F02K3/04 , F04D29/52
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。

6. 发明申请

US20130008144A1 EFFICIENT, LOW PRESSURE RATIO PROPULSOR FOR GAS TURBINE ENGINES 有权
标题翻译：高效的，用于气体涡轮发动机的低压比推进器
公开(公告)号：US20130008144A1
公开(公告)日：2013-01-10
申请号：US13176255
申请日：2011-07-05
申请人： Edward J. Gallagher , Jun Jiang , Becky E. Rose , Jason Elliott , Anthony R. Bifulco
发明人： Edward J. Gallagher , Jun Jiang , Becky E. Rose , Jason Elliott , Anthony R. Bifulco
IPC分类号： F02K3/00
CPC分类号： F04D29/321 , F02C7/36 , F02K3/06 , F02K3/075 , F04D25/022 , F04D25/024 , F05B2220/306 , F05D2260/4031
摘要： A gas turbine engine includes a spool, a turbine coupled to drive the spool and a propulsor that is coupled to be driven by the turbine through the spool. A gear assembly is coupled between the propulsor and the spool such that rotation of the spool drives the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extends from the hub. The row includes no more than 16 of the propulsor blades.
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和被涡轮机通过阀芯驱动的推进器。齿轮组件联接在推进器和阀芯之间，使得阀芯的旋转以与卷轴不同的速度驱动推进器。推进器包括从轮毂延伸的轮毂和一排推杆叶片。该行包括不超过16个推进刀片。

7. 发明授权

US09121412B2 Efficient, low pressure ratio propulsor for gas turbine engines 有权
标题翻译：燃气轮机的高效，低压比推进器
公开(公告)号：US09121412B2
公开(公告)日：2015-09-01
申请号：US13176255
申请日：2011-07-05
申请人： Edward J. Gallagher , Jun Jiang , Becky E. Rose , Jason Elliott , Anthony R. Bifulco
发明人： Edward J. Gallagher , Jun Jiang , Becky E. Rose , Jason Elliott , Anthony R. Bifulco
IPC分类号： F04D29/32 , F02K3/06 , F02K3/02 , F04D25/02 , F02C7/36 , F02K3/075
CPC分类号： F04D29/321 , F02C7/36 , F02K3/06 , F02K3/075 , F04D25/022 , F04D25/024 , F05B2220/306 , F05D2260/4031
摘要： A gas turbine engine includes a spool, a turbine coupled to drive the spool and a propulsor that is coupled to be driven by the turbine through the spool. A gear assembly is coupled between the propulsor and the spool such that rotation of the spool drives the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extends from the hub. The row includes no more than 16 of the propulsor blades.
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和被涡轮机通过阀芯驱动的推进器。齿轮组件联接在推进器和阀芯之间，使得阀芯的旋转以与卷轴不同的速度驱动推进器。推进器包括从轮毂延伸的轮毂和一排推杆叶片。该行包括不超过16个推进刀片。

8. 发明授权

US07963742B2 Variable compressor stator vane having extended fillet 有权
标题翻译：可变压缩机定子叶片具有延伸的圆角
公开(公告)号：US07963742B2
公开(公告)日：2011-06-21
申请号：US11590297
申请日：2006-10-31
申请人： Brian E. Clouse , Paul W. Baumann , Becky E. Rose , Mark E. Simonds
发明人： Brian E. Clouse , Paul W. Baumann , Becky E. Rose , Mark E. Simonds
IPC分类号： F04D29/56 , F03B3/18
CPC分类号： F01D5/147 , F01D5/16 , F01D17/162
摘要： An example variable stator vane assembly includes at least one button, a vane airfoil adjacent to the button, and a fillet defined between the button and the airfoil. In one example, the fillet defines a constant radius and extends beyond the button at least greater than a distance of 60% of a length of an overhang portion of the vane airfoil.
摘要翻译：示例性可变定子叶片组件包括至少一个按钮，与按钮相邻的叶片翼型件和在按钮和翼型之间限定的圆角。在一个示例中，圆角限定了恒定的半径，并且延伸超过按钮至少大于叶片翼型的突出部分的长度的60％的距离。

9. 发明申请

US20080101935A1 Variable compressor stator vane having extended fillet 有权
标题翻译：可变压缩机定子叶片具有延伸的圆角
公开(公告)号：US20080101935A1
公开(公告)日：2008-05-01
申请号：US11590297
申请日：2006-10-31
申请人： Brian E. Clouse , Paul W. Baumann , Becky E. Rose , Mark E. Simonds
发明人： Brian E. Clouse , Paul W. Baumann , Becky E. Rose , Mark E. Simonds
IPC分类号： F01D11/00
CPC分类号： F01D5/147 , F01D5/16 , F01D17/162
摘要： An example variable stator vane assembly includes at least one button, a vane airfoil adjacent to the button, and a fillet defined between the button and the airfoil. In one example, the fillet defines a constant radius and extends beyond the button at least greater than a distance of 60% of a length of an overhang portion of the vane airfoil.
摘要翻译：示例性可变定子叶片组件包括至少一个按钮，与按钮相邻的叶片翼型件和在按钮和翼型之间限定的圆角。在一个示例中，圆角限定了恒定的半径，并且延伸超过按钮至少大于叶片翼型的突出部分的长度的60％的距离。

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