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1. 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。

2. 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。

3. 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。

4. 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。

5. 发明申请

US20130008170A1 SUBSONIC SWEPT FAN BLADE 有权
标题翻译： SUBSONIC SWPAN风扇叶片
公开(公告)号：US20130008170A1
公开(公告)日：2013-01-10
申请号：US13176540
申请日：2011-07-05
申请人： Edward J. Gallagher , Thomas H. Rogers
发明人： Edward J. Gallagher , Thomas H. Rogers
IPC分类号： F02C1/00 , F01D1/00 , F01D5/14
CPC分类号： F01D5/141 , F05D2220/36 , F05D2240/302 , F05D2240/303 , Y02T50/673
摘要： A gas turbine engine includes a spool, a turbine coupled to drive the spool, a propulsor coupled to be driven at a at a design speed by the turbine through the spool, and a gear assembly coupled between the propulsor and the spool. 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 includes an airfoil body. The leading edge of the airfoil body has a swept profile such that, at the design speed, a component of a relative velocity vector of a working gas that is normal to the leading edge is subsonic along the entire radial 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，被涡轮机通过阀芯以设计速度被联接的推进器，以及耦合在推进器和阀芯之间的齿轮组件。涡轮机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。每个推进器叶片包括翼型体。翼型体的前缘具有扫掠轮廓，使得在设计速度下，与前缘垂直的工作气体的相对速度矢量的分量沿着整个径向跨度是亚音速的。

6. 发明申请

US20130189117A1 ROTOR WITH FLATTENED EXIT PRESSURE PROFILE 有权
标题翻译：具有平稳出口压力配置的转子
公开(公告)号：US20130189117A1
公开(公告)日：2013-07-25
申请号：US13357019
申请日：2012-01-24
申请人： Constantine Baltas , Dilip Prasad , Edward J. Gallagher
发明人： Constantine Baltas , Dilip Prasad , Edward J. Gallagher
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2240/30 , F05D2240/301 , F05D2240/304 , Y02T50/671 , Y02T50/673
摘要： A rotor blade comprises an airfoil extending radially from a root section to a tip section and axially from a leading edge to a trailing edge, the leading and trailing edges defining a curvature therebetween. The curvature determines a relative exit angle at a relative span height between the root section and the tip section, based on an incident flow velocity at the leading edge of the airfoil and a rotational velocity at the relative span height. In operation of the rotor blade, the relative exit angle determines a substantially flat exit pressure ratio profile for relative span heights from 75% to 95%, wherein the exit pressure ratio profile is constant within a tolerance of 10% of a maximum value of the exit pressure ratio profile.
摘要翻译：转子叶片包括从根部到尖端部分径向延伸并且从前缘到后缘的轴向延伸的翼型件，前缘和后缘在它们之间限定曲率。基于在翼型的前缘处的入射流速和在相对跨度高度处的旋转速度，曲率确定根部和尖端部分之间相对跨度高度处的相对出射角。在转子叶片的操作中，相对出口角度确定了从75％到95％的相对跨度高度的基本上平坦的出口压力比分布，其中出口压力比分布是恒定的，在公差范围内的最大值的10％出口压力比。

7. 发明申请

US20130008146A1 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：US20130008146A1
公开(公告)日：2013-01-10
申请号：US13176365
申请日：2011-07-05
申请人： Edward J. Gallagher , Byron R. Monzon
发明人： Edward J. Gallagher , Byron R. Monzon
IPC分类号： F02K3/075 , F01D5/14
CPC分类号： F02K3/06 , F01D17/14 , F02K1/06 , F05D2220/327 , 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 turbine 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 20 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，以及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，使得涡轮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20个推进刀片。

8. 发明授权

US4445258A Method of sealing interfaces of bearing surfaces to steel barrels of piston pumps 失效
标题翻译：将轴承表面的接口密封到活塞泵钢桶的方法
公开(公告)号：US4445258A
公开(公告)日：1984-05-01
申请号：US342943
申请日：1982-01-26
申请人： George R. Caldwell , Edward J. Gallagher
发明人： George R. Caldwell , Edward J. Gallagher
IPC分类号： B22D19/08 , F01B3/00 , F04B1/20 , B22D19/00
CPC分类号： F04B1/2035 , B22D19/08 , F01B3/0052 , F05B2230/41 , F05C2201/0478 , Y10T29/49272
摘要： The method of contemporaneously sealing interfaces of bearing surfaces for valve faces and cylinder linings in a steel rotary cylindrical barrel having a plurality of longitudinal bores extending through the barrel longitudinally from one end to the other, each of the bores having a restricted diameter intermediate portion connecting a valve surface area at one end of the barrel with a cylinder area extending to the other end. An insert of bearing material is placed in both ends of the bore and a cap secured over a lower end adjoining the cylinder bore. A removable carbon hot top is placed over the other end of the barrel. The barrel and its assembly is heated in a metallurgical furnace for 90 minutes at 1925.degree. F., disposed vertically, with the cap at the bottom and is then removed from the furnace and cooled with the cap resting on a bronze pedestal to cause the bearing material to slowly solidify from the bottom up, and to cause gases to rise through the restricted area of the bore as the barrel cools. When the temperature is below 1000.degree. F., the hot top is removed to permit solidification of the bearing material in the upper valve area.
摘要翻译：在具有多个纵向孔的钢旋转圆柱形筒中同时密封用于阀面和气缸衬套的表面的界面的同时密封方法，所述多个纵向孔从一端纵向延伸穿过另一端，每个孔具有限制直径的中间部分连接在桶的一端处的阀表面区域具有延伸到另一端的气缸区域。轴承材料的插入件放置在孔的两端，并且固定在邻近气缸孔的下端上的盖。可移动的碳热顶部放置在桶的另一端上。将桶及其组件在冶金炉中在1925°F加热90分钟，垂直放置，盖子在底部，然后从炉中取出并冷却，盖子搁置在青铜基座上，使轴承材料从底部向上缓慢固化，并且当桶冷却时使气体通过孔的限制区域上升。当温度低于1000°F时，除去热顶以允许轴承材料在上阀区域内固化。

9. 发明申请

US20130014488A1 EFFICIENT, LOW PRESSURE RATIO PROPULSOR FOR GAS TURBINE ENGINES 有权
公开(公告)号：US20130014488A1
公开(公告)日：2013-01-17
申请号：US13484858
申请日：2012-05-31
申请人： Edward J. Gallagher , Byron R. Monzon
发明人： Edward J. Gallagher , Byron R. Monzon
IPC分类号： F02K3/02 , F01D5/02
CPC分类号： F02K3/06 , F01D17/14 , F02K1/06 , F05D2220/327 , 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 turbine 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 20 of the propulsor blades.

10. 发明授权

US09790797B2 Subsonic swept fan blade 有权
公开(公告)号：US09790797B2
公开(公告)日：2017-10-17
申请号：US13176540
申请日：2011-07-05
申请人： Edward J. Gallagher , Thomas H. Rogers
发明人： Edward J. Gallagher , Thomas H. Rogers
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2220/36 , F05D2240/302 , F05D2240/303 , Y02T50/673
摘要： A gas turbine engine includes a spool, a turbine coupled to drive the spool, a propulsor coupled to be driven at a at a design speed by the turbine through the spool, and a gear assembly coupled between the propulsor and the spool. 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 includes an airfoil body. The leading edge of the airfoil body has a swept profile such that, at the design speed, a component of a relative velocity vector of a working gas that is normal to the leading edge is subsonic along the entire radial span.

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