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1. 发明申请

US20190048724A1 LOW-NOISE AIRFOIL FOR AN OPEN ROTOR 审中-公开
公开(公告)号：US20190048724A1
公开(公告)日：2019-02-14
申请号：US15675239
申请日：2017-08-11
申请人： General Electric Company
发明人： Daniel Lawrence Tweedt
IPC分类号： F01D5/14 , F01D5/16 , B64C21/00
CPC分类号： F01D5/141 , B64C11/18 , B64C21/00 , F01D5/142 , F01D5/16 , F05D2220/36 , F05D2240/301 , F05D2240/302 , F05D2240/303 , F05D2240/304 , F05D2240/305 , F05D2240/306 , F05D2250/70 , F05D2260/96
摘要： An airfoil section of a blade for an open rotor includes: a pressure side and a suction side, the pressure side and the suction side intersecting at a leading edge and a trailing edge, wherein a chord of the airfoil section is defined as a straight-line distance between the leading edge and the trailing edge; the airfoil section has a meanline defined midway between the pressure side and the suction side; and the meanline is shaped such that, in the presence of predetermined transonic or supersonic relative velocity conditions, maximum and minimum ideal Mach numbers on the suction side will lie within a 0.08 band, between 25% and 80% percent of the chord.

2. 发明申请

US20130149100A1 GAS TURBINE ENGINE 有权
标题翻译：气体涡轮发动机
公开(公告)号：US20130149100A1
公开(公告)日：2013-06-13
申请号：US13542674
申请日：2012-07-06
申请人： SHAWN P. LAWLOR , WILLIAM BYRON ROBERTS, II
发明人： SHAWN P. LAWLOR , WILLIAM BYRON ROBERTS, II
IPC分类号： F01D9/00
CPC分类号： F01D9/00 , F01D1/026 , F01D1/10 , F01D1/16 , F01D5/02 , F01D9/047 , F02C3/00 , F02C3/04 , F02C3/06 , F02C3/14 , F02C7/00 , F02C7/22 , F02C9/16 , F02C9/18 , F04D21/00 , F05D2220/3216 , F05D2220/3218 , F05D2220/3219 , F05D2240/128 , F05D2240/30 , F05D2240/301 , F05D2240/302 , F05D2240/35 , Y02E20/14
摘要： A gas turbine engine with a compressor rotor having compressor impulse blades that delivers gas at supersonic conditions to a stator. The stator includes a one or more aerodynamic ducts that each have a converging portion and a diverging portion for deceleration of the selected gas to subsonic conditions and to deliver a high pressure oxidant containing gas to flameholders. The flameholders may be provided as trapped vortex combustors, for combustion of a fuel to produce hot pressurized combustion gases. The hot pressurized combustion gases are choked before passing out of an aerodynamic duct to a turbine. Work is recovered in a turbine by expanding the combustion gases through impulse blades. By balancing the axial loading on compressor impulse blades and turbine impulse blades, asymmetrical thrust is minimized or avoided.
摘要翻译：具有压缩机转子的燃气涡轮发动机具有压缩机脉冲叶片，其将超声波条件下的气体输送到定子。定子包括一个或多个空气动力学管道，每个空气动力学管道具有会聚部分和发散部分，用于将选定气体减速至亚音速条件并将含有气体的高压氧化剂输送到火焰持有器。火焰保持器可以被设置为被捕获的涡流燃烧器，用于燃烧燃料以产生热的加压燃烧气体。热的加压燃烧气体在从空气动力学管道流出到涡轮机之前被阻塞。通过将燃烧气体膨胀通过脉冲叶片在涡轮机中恢复工作。通过平衡压缩机脉冲叶片和涡轮脉冲叶片上的轴向载荷，可以最小化或避免非对称推力。

3. 发明授权

US07753652B2 Aero-mixing of rotating blade structures 有权
标题翻译：旋转叶片结构的气动混合
公开(公告)号：US07753652B2
公开(公告)日：2010-07-13
申请号：US11639962
申请日：2006-12-15
申请人： Frank Truckenmueller , Heinrich Stueer , Harry F. Martin , Lewis Gray
发明人： Frank Truckenmueller , Heinrich Stueer , Harry F. Martin , Lewis Gray
IPC分类号： B63H1/16
CPC分类号： F01D5/141 , F01D5/142 , F01D5/16 , F05D2240/302 , Y10S416/05
摘要： An array of blades for use in a turbomachine is provided comprising a plurality of blades mounted to a rotor disk. A plurality of first blades form a first set of blades and a plurality of second blades form a second set of blades. A blade-to-blade flow field defined between successive ones of the first set of blades is interrupted by the second set of blades to form an asymmetric blade-to-blade flow field around the array of blades. The trailing edges of the second set of blades are positioned forwardly from a line connecting the trailing edges of the first set of blades such that shock forces in the flow field around the array of blades will generally impinge on a stable region of the first set of blades.
摘要翻译：提供了一种用于涡轮机的叶片阵列，其包括安装到转子盘上的多个叶片。多个第一叶片形成第一组叶片，并且多个第二叶片形成第二组叶片。在第一组叶片中的连续的叶片之间限定的叶片到叶片的流场被第二组叶片中断，以形成围绕叶片阵列的不对称叶片到叶片的流场。第二组叶片的后缘从连接第一组叶片的后缘的线向前定位，使得在叶片阵列周围的流场中的冲击力通常将撞击第一组叶片的稳定区域刀片。

4. 发明申请

US20080145228A1 Aero-mixing of rotating blade structures 有权
标题翻译：旋转叶片结构的气动混合
公开(公告)号：US20080145228A1
公开(公告)日：2008-06-19
申请号：US11639962
申请日：2006-12-15
申请人： Frank Truckenmueller , Heinrich Stueer , Harry F. Martin , Lewis Gray
发明人： Frank Truckenmueller , Heinrich Stueer , Harry F. Martin , Lewis Gray
IPC分类号： F01D5/10
CPC分类号： F01D5/141 , F01D5/142 , F01D5/16 , F05D2240/302 , Y10S416/05
摘要： An array of blades for use in a turbomachine is provided comprising a plurality of blades mounted to a rotor disk. A plurality of first blades form a first set of blades and a plurality of second blades form a second set of blades. A blade-to-blade flow field defined between successive ones of the first set of blades is interrupted by the second set of blades to form an asymmetric blade-to-blade flow field around the array of blades. The trailing edges of the second set of blades are positioned forwardly from a line connecting the trailing edges of the first set of blades such that shock forces in the flow field around the array of blades will generally impinge on a stable region of the first set of blades.
摘要翻译：提供了一种用于涡轮机的叶片阵列，其包括安装到转子盘上的多个叶片。多个第一叶片形成第一组叶片，并且多个第二叶片形成第二组叶片。在第一组叶片中的连续的叶片之间限定的叶片到叶片的流场被第二组叶片中断，以形成围绕叶片阵列的不对称叶片到叶片的流场。第二组叶片的后缘从连接第一组叶片的后缘的线向前定位，使得在叶片阵列周围的流场中的冲击力通常将撞击第一组叶片的稳定区域刀片。

5. 发明授权

US06837679B2 Gas turbine engine 有权
标题翻译：燃气轮机
公开(公告)号：US06837679B2
公开(公告)日：2005-01-04
申请号：US10240107
申请日：2000-12-22
申请人： Satoshi Kawarada , Toyotaka Sonoda
发明人： Satoshi Kawarada , Toyotaka Sonoda
IPC分类号： F01D5/14 , F01D9/02
CPC分类号： F01D5/141 , F01D5/145 , F05D2240/302 , F05D2250/711 , F05D2250/712 , Y02T50/671 , Y02T50/673
摘要： A gas turbine engine has, in a cross section in the axial direction of an annular inner peripheral wall connected to a blade main body of a turbine blade, a concave part and a convex part on the front edge side and the rear edge side. The concave part has a negative curvature and is concave toward the axis, and the convex part has a positive curvature and is convex away from the axis. The flow rate on the upper face of the blade main body can be reduced in the concave part on the front edge side, thus suppressing generation of a shock wave, and the flow rate can be increased in the convex part on the rear edge side following the concave part, thus smoothly changing the flow rate on the upper face of the blade main body and thereby minimizing the pressure loss. In this way, the thickness of the blade main body can be reduced while ensuring the performance of the gas turbine engine, thereby contributing to a reduction in weight.
摘要翻译：燃气涡轮发动机在连接到涡轮叶片的叶片主体的环形内周壁的轴向的横截面中，在前边缘侧和后边缘侧具有凹部和凸部。凹部具有负曲率并且朝向轴线凹入，并且凸部具有正曲率并且远离轴凸出。在前边缘侧的凹部中能够减小叶片主体的上表面的流量，抑制冲击波的产生，并且能够使后边缘侧的凸部的流量增大凹部，从而平滑地改变叶片主体的上表面上的流量，从而使压力损失最小化。以这种方式，可以在确保燃气轮机的性能的同时减小叶片主体的厚度，从而有助于减轻重量。

6. 再颁专利

USRE38040E1 Swept turbomachinery blade 有权
标题翻译：扫涡轮机叶片
公开(公告)号：USRE38040E1
公开(公告)日：2003-03-18
申请号：US09343736
申请日：1999-06-30
申请人： David A. Spear , Bruce P. Biederman , John A. Orosa
发明人： David A. Spear , Bruce P. Biederman , John A. Orosa
IPC分类号： F01D514
CPC分类号： F01D5/16 , F01D5/141 , F04D21/00 , F04D29/324 , F04D29/384 , F04D29/386 , F05D2220/327 , F05D2240/302 , F05D2250/70 , F05D2250/711 , F05D2250/712 , F05D2250/713
摘要： A swept turbomachinery blade for use in a cascade of such blades is disclosed. The blade (12) has an airfoil (22) uniquely swept so that an endwall shock (64) of limited radial extent and a passage shock (66) are coincident and a working medium (48) flowing through interblade passages (50) is subjected to a single coincident shock rather than the individual shocks. In one embodiment of the invention the forwardmost extremity of the airfoil defines an inner transition point (40) located at an inner transition radius rt-inner. The sweep angle of the airfoil is nondecreasing with increasing radius from the inner transition radius to an outer transition radius rt-outer, radially inward of the airfoil tip (26), and is nonincreasing with increasing radius between the outer transition radius and the airfoil tip.
摘要翻译：公开了一种用于这种叶片级联的扫掠式涡轮机叶片。叶片（12）具有独特地扫过的翼型件（22），使得有限径向范围的端壁冲击（64）和通道冲击（66）重合，并且流经叶片间通道（50）的工作介质（48）以单一的同时震惊而不是个别的冲击。在本发明的一个实施例中，翼型件的最前端限定位于内部过渡半径rt-内部的内部转变点（40）。翼型的扫掠角度随着从内部过渡半径到外部过渡半径rt-半径的增加而减小，这在外部过渡半径（外部过渡半径）外部，在翼型端部（26）的径向内侧，并且随着外部过渡半径和翼型尖端之间的半径的增加而增加。

7. 发明授权

US4835958A Process for directing a combustion gas stream onto rotatable blades of a gas turbine 失效
标题翻译：将燃烧气体流引导到燃气轮机的可旋转叶片上的过程
公开(公告)号：US4835958A
公开(公告)日：1989-06-06
申请号：US170647
申请日：1988-03-16
申请人： Ivan G. Rice
发明人： Ivan G. Rice
IPC分类号： F01D5/18 , F01K23/10 , F02C6/00 , F02C6/18 , F02C7/16
CPC分类号： F01D5/185 , F01D5/187 , F01K23/103 , F02C6/003 , F02C6/18 , F02C7/16 , F05D2240/302 , F05D2250/25 , F05D2260/202 , F05D2260/2322 , Y02E20/16 , Y02T50/673 , Y02T50/676
摘要： A process for producing work comprises passing a combustion gas stream through a gas nozzle which directs the steam onto the rotatable blades of an expansion turbine. The trailing edge of the air-foil shaped vanes which form the gas nozzle is cooled by passing coolant steam through the interior of said vanes and passing said steam through a plurality of said spaced steam nozzles contained at the trailing edge of the vanes. Disruption of the laminar steam film on the surfaces of the nozzle ensures increased heat transfer.
摘要翻译：用于生产作业的方法包括使燃烧气流通过气体喷嘴，气体喷嘴将蒸汽引导到膨胀涡轮机的可旋转叶片上。通过使冷却剂蒸汽通过所述叶片的内部并使所述蒸汽通过包含在叶片的后缘处的多个所述间隔开的蒸汽喷嘴来冷却形成气体喷嘴的气翼形叶片的后缘。喷嘴表面上的层状蒸汽膜的破坏确保了热传递的增加。

8. 发明授权

US3692425A Compressor for handling gases at velocities exceeding a sonic value 失效
标题翻译：用于处理超过声码的速度的压缩机
公开(公告)号：US3692425A
公开(公告)日：1972-09-19
申请号：US3692425D
申请日：1969-01-02
申请人： GEN ELECTRIC
发明人： ERWIN JOHN R
IPC分类号： F01D5/14 , F04D21/00 , F04D29/32 , F04D29/58 , F04D29/38
CPC分类号： F04D29/321 , F01D5/146 , F04D21/00 , F04D29/324 , F05D2240/302 , Y02T50/673 , Y10S415/914 , Y10S416/50
摘要： In the fan portion of a turbofan engine, rotor blades comprise a primary cambered airfoil and an auxiliary airfoil. Where air flow exceeds a sonic velocity relative to the blades, the throat section between adjacent blades positions the normal air shock wave on the auxiliary airfoil. Each auxiliary airfoil forms a nozzle in combination with the pressure surface of its adjacent primary airfoil. This minimizes energy losses normally associated with such normal shock waves riding on the suction surfaces of cambered airfoils in regions of relatively thick boundary layer air. Lateral struts projecting from the primary airfoil, and used to position the auxiliary airfoil, create oblique shock waves which weaken the normal shock wave and minimize energy losses associated with a normal shock wave''s effect of distributing boundary layer air on an airfoil surface. These features are also effective in reducing the generation of noise.
摘要翻译：在涡扇发动机的风扇部分中，转子叶片包括初级弧形翼型件和辅助翼型件。当空气流相对于叶片超过声速时，相邻叶片之间的喉部将正常的空气冲击波定位在辅助翼型上。每个辅助翼型件与其相邻的主翼面的压力表面组合形成喷嘴。这最大限度地减少了在相对厚的边界层空气的区域中骑乘在弧形翼型件的吸力表面上的正常冲击波通常相关联的能量损失。从主翼面突出并用于定位辅助翼型的横向支柱产生倾斜的冲击波，这削弱了正常的冲击波，并使与正常冲击波在翼型表面上分配边界层空气的效果相关联的能量损失最小化。这些功能也有效减少了噪音的产生。

9. 发明授权

US3156407A Supersonic compressors 失效
标题翻译：超音速压缩机
公开(公告)号：US3156407A
公开(公告)日：1964-11-10
申请号：US82516659
申请日：1959-07-06
申请人： COMMISSARIAT ENERGIE ATOMIQUE
发明人： FERNAND BOURQUARD
IPC分类号： F04D21/00
CPC分类号： F04D21/00 , F05D2240/302

10. 发明授权

US2935246A Shock wave compressors, especially for use in connection with continuous flow engines for aircraft 失效
标题翻译：冲击波压缩机，特别适用于飞机连续流量发动机
公开(公告)号：US2935246A
公开(公告)日：1960-05-03
申请号：US16541050
申请日：1950-06-01
申请人： ONERA (OFF NAT AEROSPATIALE)
发明人： MAURICE ROY
IPC分类号： F01D5/14 , F04D19/02 , F04D21/00 , F04D29/68
CPC分类号： F04D21/00 , F01D5/146 , F04D19/024 , F04D29/682 , F04D29/684 , F05D2240/302 , F05D2250/70 , Y02T50/673

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