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1. 发明授权

US10618018B2 Low wear radial flow impeller device and system 有权
公开(公告)号：US10618018B2
公开(公告)日：2020-04-14
申请号：US15164349
申请日：2016-05-25
申请人： SPX FLOW, INC.
发明人： Richard Kehn
IPC分类号： B01F7/00 , F04D29/24 , F04D29/66 , B01J19/00 , F04D29/043 , F04D29/22
CPC分类号： B01F7/00383 , B01J19/0066 , F04D29/043 , F04D29/22 , F04D29/242 , F04D29/669 , B01F2215/0431 , F05D2250/72 , F05D2250/75
摘要： A radial impeller includes a hub, a disk, and a plurality of blades. The disk is affixed to the hub. The disk has a disk plane defined by the disk. Each blade of the plurality of blades is affixed to the disk. Each blade includes a “C” shaped body portion and an upper and lower horizontal extension. The upper horizontal extension extends along an upper plane parallel to the disk plane. The lower horizontal extension extends along a lower plane parallel to the disk plane.

2. 发明申请

US20180195438A1 FUEL DISTRIBUTION DEVICE, GAS TURBINE ENGINE AND MOUNTING METHOD 审中-公开
公开(公告)号：US20180195438A1
公开(公告)日：2018-07-12
申请号：US15323125
申请日：2015-07-01
申请人： Nuovo Pignone S.r.l
发明人： Simone CHECHI
IPC分类号： F02C7/22 , F23K5/06
CPC分类号： F02C7/222 , F02C7/228 , F05D2220/32 , F05D2230/60 , F05D2240/35 , F05D2240/40 , F05D2250/51 , F05D2250/52 , F05D2250/72 , F23K5/06 , F23R3/283
摘要： A fuel distribution device is provided wherein an axis is defined. The device comprises a body housing a distribution path for fuel; the distribution path has one inlet and a plurality of outlets; the inlet is located on the external surface of the body at an end of an inlet branch of the distribution path; the plurality of outlets are located on the external surface of the body at ends of a corresponding plurality of outlet branches of the distribution path; the inlet branch and the outlet branches are fluidly connected to a distribution space; and the outlet branches are arranged radially.

3. 发明申请

US20160376903A1 REVERSIBLE BLADE ROTOR SEAL WITH PROTRUSIONS 有权
标题翻译：可逆刀片转子密封件
公开(公告)号：US20160376903A1
公开(公告)日：2016-12-29
申请号：US14748876
申请日：2015-06-24
申请人： United Technologies Corporation
发明人： Christopher Corcoran , Daniel A. Snyder
IPC分类号： F01D11/00 , F02C7/18 , F16J15/02 , F01D5/08
CPC分类号： F01D11/006 , F01D5/081 , F01D5/22 , F01D5/3015 , F01D11/008 , F02C7/18 , F05D2220/32 , F05D2240/24 , F05D2240/55 , F05D2250/72 , F05D2260/20 , F16J15/02 , Y02T50/676
摘要： A sealing structure for a gas turbine engine includes a rotor that has a rim with slots and a cooling passage. The rotor is rotatable about an axis. First and second blades are arranged in the slots and respectively including first and second shelves facing one another within a pocket that is in fluid communication with the cooling passage. The first and second shelves form an opening. A reversible seal is arranged within the pocket and has a body that is configured for operative association with the first and second blades in any of four orientations to seal the opening in a first condition. The seal includes first and second protrusions respectively extending from first and second faces opposing one another. The first protrusions supported on the rim in a first condition.
摘要翻译：用于燃气涡轮发动机的密封结构包括具有带槽的轮辋和冷却通道的转子。转子可绕轴线转动。第一和第二叶片布置在槽中并且分别包括在与冷却通道流体连通的凹穴内彼此面对的第一和第二搁架。第一和第二个货架形成一个开口。可口密封件布置在口袋内，并且具有构造成与四个取向中的任何一个中的第一和第二刀片操作关联的主体，以在第一状态下密封开口。密封件包括分别从相对的第一和第二面延伸的第一和第二突起。在第一状态下，第一凸起支撑在轮辋上。

4. 发明申请

US20130175015A1 DOUBLE-JET TYPE FILM COOLING STRUCTURE 有权
标题翻译：双盖型薄膜冷却结构
公开(公告)号：US20130175015A1
公开(公告)日：2013-07-11
申请号：US13636667
申请日：2011-03-02
申请人： Ryozo Tanaka , Masahide Kazari , Takao Sugimoto , Karsten Kusterer , Dieter Bohn , Anas Elyas
发明人： Ryozo Tanaka , Masahide Kazari , Takao Sugimoto , Karsten Kusterer , Dieter Bohn , Anas Elyas
IPC分类号： F28F3/12
CPC分类号： F28F3/12 , F01D5/186 , F05D2250/14 , F05D2250/72 , F05D2260/202 , F23R3/06
摘要： Provided is a film cooling structure capable of suppressing a cooling medium film from being separated from a wall surface, to increase a film efficiency on the wall surface and thereby-cool the wall surface effectively. One or more pairs of injection holes are formed on a wall surface facing a passage of high-temperature gas to inject a cooling medium to the passage. A single supply passage is formed inside the wall to supply the cooling medium to the injection holes. A separating section is provided between the injection holes in a location forward relative to rear ends of the injection holes to separate the cooling medium into components flowing to the injection holes. An injection direction of the cooling medium is inclined relative to a gas flow direction so that the cooling medium forms swirl flows that push the cooling medium against the wall surface.
摘要翻译：提供一种能够抑制冷却介质膜与壁面分离的膜冷却结构，提高壁面的膜效率，从而有效地冷却壁面。在面向高温气体通道的壁面上形成一对或多对喷射孔，以向通道注入冷却介质。在壁内形成单个供应通道以将冷却介质供应到喷射孔。在喷射孔之间的相对于喷射孔的后端的位置处的喷射孔之间设置有分离部分，以将冷却介质分离成流入喷射孔的部件。冷却介质的喷射方向相对于气体流动方向倾斜，使得冷却介质形成将冷却介质推向壁面的涡流。

5. 发明申请

US20110185699A1 GAS TURBINE ENGINE STEAM INJECTION MANIFOLD 有权
标题翻译：气体涡轮发动机蒸汽喷射喷嘴
公开(公告)号：US20110185699A1
公开(公告)日：2011-08-04
申请号：US12696241
申请日：2010-01-29
申请人： Allen Michael Danis , Steven Marakovits , Edward Joseph Stiftar
发明人： Allen Michael Danis , Steven Marakovits , Edward Joseph Stiftar
IPC分类号： F02C7/00
CPC分类号： F02C3/305 , F05D2240/35 , F05D2250/312 , F05D2250/711 , F05D2250/72 , F05D2270/082 , F23L7/005 , F23R3/16 , F23R3/50
摘要： A gas turbine engine steam injector includes an annular steam injection manifold aftwardly bounded by an aft manifold wall having steam injection holes disposed therethrough and located axially aft and radially inwardly of a diffuser outlet. An outer baffle wall around manifold has a curved convex surface which may generally conform to a streamline emanating from outlet. Holes may be circumferentially evenly distributed and non-uniformally sized around the aft manifold wall. Hollow struts extend between radially outer and inner bands of a diffuser and a steam supply header in steam supply communication with a fluid passage of at least one of the struts having a passage outlet open to steam cavity within cavity casing located inwardly of inner band. Openings are disposed in an aft cavity wall between cavity and the injector. Passages may be in only a non-uniformally distributed portion of the struts that may be adjacent to each other.
摘要翻译：燃气涡轮发动机蒸汽喷射器包括由后排管壁构成的环形蒸气喷射歧管，所述后部歧管壁具有穿过其设置的蒸汽喷射孔并且位于扩散器出口的轴向向后和径向向内。歧管周围的外部挡板壁具有弯曲的凸形表面，该凸形表面通常可符合从出口发出的流线。孔可以在后部歧管壁周围沿周向均匀分布和不均匀的尺寸。空心支柱在扩散器的径向外部和内部带之间延伸，并且与至少一个支柱的流体通道的蒸汽供应连通的蒸汽供应头部具有在位于内部带内侧的腔体壳体内的通向蒸气腔的通道出口。开口设置在腔和注射器之间的后空腔壁中。通道可以仅在可以彼此相邻的支柱的非均匀分布的部分中。

6. 发明公开

US20240060430A1 GAS TURBINE ENGINE 审中-公开
公开(公告)号：US20240060430A1
公开(公告)日：2024-02-22
申请号：US17889927
申请日：2022-08-17
申请人： General Electric Company
发明人： William Joseph Bowden , Keith Edward James Blodgett
IPC分类号： F01D25/24 , F01D25/28
CPC分类号： F01D25/24 , F01D25/28 , F05D2220/323 , F05D2240/14 , F05D2250/72 , F05D2250/38 , F05D2260/30
摘要： A gas turbine engine defining a radial direction, an axial direction, a circumferential direction, and a longitudinal axis is provided. The gas turbine engine includes: a fan rotatable about the longitudinal axis; a turbomachine; and a housing surrounding the turbomachine and having an upper outer surface portion and a lower outer surface portion, the housing defining a first distance extending radially from the longitudinal axis to a first point located at the upper outer surface portion, the housing further defining a second distance extending radially from the longitudinal axis to a second point located at the lower outer surface portion, and the second distance is greater than the first distance.

7. 发明申请

US20180355754A1 SPLINE FOR A TURBINE ENGINE 审中-公开
公开(公告)号：US20180355754A1
公开(公告)日：2018-12-13
申请号：US15441569
申请日：2017-02-24
申请人： General Electric Company
发明人： Robert Charles Groves, II , David Scott Stapleton
IPC分类号： F01D25/12 , F01D11/00 , F01D11/08
CPC分类号： F01D25/12 , F01D11/005 , F01D11/08 , F05D2220/323 , F05D2240/11 , F05D2240/55 , F05D2240/57 , F05D2250/12 , F05D2250/182 , F05D2250/294 , F05D2250/72 , F05D2260/201 , F05D2270/112
摘要： A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge spanning to an aft edge to define an axial direction and a set of confronting seal channels formed in each of the confronting end faces with a spline seal located within the confronting seal channels.

8. 发明申请

US20170175626A1 GAS TURBINE ENGINE WITH MINIMIZED INLET DISTORTION 审中-公开
公开(公告)号：US20170175626A1
公开(公告)日：2017-06-22
申请号：US14974112
申请日：2015-12-18
申请人： United Technologies Corporation
发明人： Yuan J. Qiu , Amr Ali , Steven H. Zysman
IPC分类号： F02C7/04 , F02K3/06 , F04D29/38 , F04D29/52 , F02C3/04 , F04D19/00
CPC分类号： F02C7/04 , F02C3/04 , F02C7/045 , F02K3/06 , F04D19/002 , F04D29/384 , F04D29/522 , F05D2220/32 , F05D2240/30 , F05D2250/314 , F05D2250/713 , F05D2250/72 , F05D2260/96
摘要： A gas turbine engine comprises a nacelle and a fan rotor carrying a plurality of fan blades. The nacelle is formed with droop such that one portion extends axially further from the fan blades than does another portion. The nacelle has inner periphery that is substantially axially symmetric about a center axis of the rotor from either a throat of the nacelle at a substantially bottom dead center location, or a point of inflection at which the inner periphery of the nacelle at substantially bottom dead center merges a convex portion into a concave portion.

9. 发明申请

US20160201486A1 Extruded profile for manufacturing a blade of an outlet guide vane 有权
标题翻译：用于制造出口导叶片的叶片的挤压型材
公开(公告)号：US20160201486A1
公开(公告)日：2016-07-14
申请号：US14595094
申请日：2015-01-12
申请人： MTU Aero Engines AG
发明人： Andreas HARTUNG , Frank STIEHLER , Martin PERNLEITNER
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , B21C23/16 , F01D5/141 , F05D2220/3215 , F05D2230/24 , F05D2230/61 , F05D2240/12 , F05D2250/70 , F05D2250/713 , F05D2250/72 , F05D2250/73 , F05D2250/75 , Y02T50/673
摘要： An extruded profile for manufacturing a blade of an outlet guide vane of a turbine engine. A cross-sectional area has an axial length LAX and a thickness D/LAX relative to the axial length LAX. A cross-sectional area has an at least nearly axisymmetric leading edge region, a first transition region having a varying relative thickness D/LAX. A first constant region has a relative thickness D/LAX at least substantially constant and, relative to a leading edge of the extruded profile, begins at the closest at 10% LAX and ends at the furthest at 50% LAX. A second transition region has a varying relative thickness D/LAX and, relative to the leading edge of the extruded profile, begins at the closest at 30% LAX and ends at the furthest at 90% LAX. A second constant region has a relative thickness D/LAX at least substantially constant and an axial length X of 40% LAX at most; and an at least nearly axisymmetric trailing edge region.
摘要翻译：用于制造涡轮发动机的出口导叶的叶片的挤压型材。截面积相对于轴向长度LAX具有轴向长度LAX和厚度D / LAX。横截面积具有至少近似轴对称的前缘区域，具有变化的相对厚度D / LAX的第一过渡区域。第一恒定区域具有至少基本恒定的相对厚度D / LAX，并且相对于挤出型材的前缘开始于最接近的10％LAX处，并且在最远处以50％LAX结束。第二过渡区域具有变化的相对厚度D / LAX，并且相对于挤出型材的前缘开始于最接近的30％LAX处，并且在90％LAX处最远。第二恒定区域的相对厚度D / LAX至少基本上恒定，轴向长度X至多为40％LAX; 以及至少近似轴对称的后缘区域。

10. 发明申请

US20160115796A1 TURBINE BLADE COOLING STRUCTURE 有权
标题翻译：涡轮叶片冷却结构
公开(公告)号：US20160115796A1
公开(公告)日：2016-04-28
申请号：US14944441
申请日：2015-11-18
申请人： KAWASAKI JUKOGYO KABUSHIKI KAISHA , B&B AGEMA GmbH
发明人： Tomoki TANIGUCHI , Ryozo TANAKA , Takeshi HORIUCHI , Takao SUGIMOTO , Masahide KAZARI , Karsten KUSTERER , Dieter BOHN , Gang LIN
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/303 , F05D2250/141 , F05D2250/15 , F05D2250/231 , F05D2250/25 , F05D2250/312 , F05D2250/314 , F05D2250/72 , F05D2260/201 , F05D2260/2212 , F05D2260/2214
摘要： In a structure for internally cooling a turbine blade, a cooling medium passage is provided in the turbine blade. The cooling medium passage has a shape in which a plurality of cylindrical spaces, each having substantially cylindrical shape, extending in parallel with each other partially overlap each other. A cooling medium supply passage that supplies a cooling medium to the cooling medium passage is connected to a portion of the cooling medium passage that includes a peripheral wall, in a direction that forms an acute angle with respect to a longitudinal direction of the cooling medium passage.
摘要翻译：在用于内部冷却涡轮机叶片的结构中，在涡轮机叶片中设置有冷却介质通道。冷却介质通道具有彼此平行延伸的多个圆柱形状的多个圆柱形空间部分地彼此重叠的形状。将冷却介质供给到冷却介质通路的冷却介质供给通路与包括周壁的冷却介质通路的相对于冷却介质通路的长度方向成锐角的方向连接。

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