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公开(公告)号：US09341082B2
公开(公告)日：2016-05-17
申请号：US14003180
申请日：2012-03-02
CPC分类号： F01D25/24 , B64D33/04 , F02K1/00 , F02K1/82 , F05D2250/71 , F05D2250/711 , Y02T50/671
摘要： A turbine engine pipe having a longitudinal axis, which, at an upstream end thereof, includes an outer wall and a core, only an upstream portion of which is surrounded by the outer wall. The boundary between the upstream portion and a downstream portion is defined by the intersection between the core and the surface formed by bisectors of acute angles formed by straight lines perpendicular to the outer wall and straight lines perpendicular to an outer surface of the core passing through the downstream end of the outer wall. The outer surface of the downstream portion of the core has a sharply curved convex region close to the boundary, the region having a radius of curvature in a radial plane of less than 30 times the radius of the core at the boundary, and a first slightly curved region between the boundary and the sharply curved convex region.
摘要翻译： 一种具有纵向轴线的涡轮发动机管道，其在其上游端包括外壁和芯部，只有其上游部分被外壁包围。 上游部分和下游部分之间的边界由芯和由垂直于外壁的直线形成的锐角的平分线形成的表面和垂直于芯的外表面的直线形成的表面之间的交点限定， 外壁的下游端。 芯的下游部分的外表面具有接近边界的急剧弯曲的凸起区域，该区域在径向平面中的曲率半径小于边界处的芯的半径的30倍，并且第一稍微 边界与锐曲的凸区域之间的弯曲区域。
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公开(公告)号：US20160123230A1
公开(公告)日：2016-05-05
申请号：US14897138
申请日：2014-06-13
发明人： Michael R. Thomas
CPC分类号： F02C7/185 , F02K3/115 , F05D2250/61 , F05D2250/71 , F05D2260/213 , F28D1/0358 , F28D9/0025 , F28D9/02 , F28F3/02 , F28F3/025 , Y02T50/675
摘要： A plate/fin heat exchanger includes multiple stacked panels defining a curvature. Each of the panels has a first corrugated sheet defining a first set of passages and a second corrugated sheet defining a second set of passages. Each of the corrugated sheets includes multiple aligned corrugations, and the corrugations of the first corrugated sheet are not aligned with the corrugations of the second corrugated sheet. Each of the corrugations has a corrugation height defined as a length of said corrugation tangential to a curvature of the plate/fin heat exchanger, and wherein each of the first corrugated sheets includes axially aligned corrugations defining a wedge shaped radial cross section.
摘要翻译： 板/翅片热交换器包括限定曲率的多个堆叠板。 每个面板具有限定第一组通道的第一波纹板和限定第二组通道的第二波纹板。 每个波纹片包括多个对准的波纹，并且第一波纹片的波纹不与第二波纹片的波纹对准。 每个波纹具有限定为与板/翅片式热交换器的曲率相切的所述波纹的长度的波纹高度，并且其中每个第一波纹片包括限定楔形径向横截面的轴向对准的波纹。
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公开(公告)号：US20160084162A1
公开(公告)日：2016-03-24
申请号：US14493758
申请日：2014-09-23
发明人： Farid ABRARI , Peter TOWNSEND
IPC分类号： F02C7/055
CPC分类号： F02C7/055 , F02K3/06 , F05D2240/307 , F05D2250/182 , F05D2250/51 , F05D2250/71
摘要： An inlet for a turbofan engine, including an inlet wall surrounding an inlet flow path. The inlet wall extends axially from an upstream end to a downstream end adjacent the fan. The inlet wall has a shape defining a plurality of teeth circumferentially spaced around the inlet. The teeth extend axially and project radially inwardly toward the central longitudinal axis. A central portion of the inlet flow path has a cross-sectional dimension measured diametrically between opposed teeth, the cross-sectional dimension varying along the axial direction. The central portion defines a geometric throat at a minimum value of the cross-sectional dimension. The inlet wall is shaped so that the geometric throat is axially spaced from the upstream end and the downstream end. A gas turbine engine and a method of shielding tips of fan blades from impact by an object having a predetermined minimum dimension are also discussed.
摘要翻译： 涡扇发动机的入口，包括围绕入口流动路径的入口壁。 入口壁从上游端轴向延伸到与风扇相邻的下游端。 入口壁具有限定围绕入口周向间隔开的多个齿的形状。 齿沿轴向延伸并朝向中心纵向轴线径向向内突出。 入口流动路径的中心部分具有在相对的齿之间径向测量的横截面尺寸，横截面尺寸沿轴向方向变化。 中心部分以横截面尺寸的最小值限定几何喉部。 入口壁的形状使得几何喉部与上游端和下游端轴向间隔开。 还讨论了燃气涡轮发动机和屏蔽风扇叶片尖端的方法不受具有预定最小尺寸的物体的冲击。
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公开(公告)号：US20160061218A1
公开(公告)日：2016-03-03
申请号：US14778317
申请日：2014-03-18
申请人： Snecma
发明人： Damien Cellier
CPC分类号： F04D29/384 , F01D5/141 , F04D29/324 , F04D29/544 , F04D29/563 , F05D2250/71 , Y02T50/673
摘要： The invention relates to a compressor blade, defined at each one of the points of its surface by a sweep angle and a dihedral angle, comprising: a root, a tip, the distance between the root and the tip, measured along an axis referred to as the radial axis, perpendicular to an axis of rotation of the compressor, being referred to as radial height (h), a zone, between the root and the tip, of which a first portion has a strictly positive leading edge dihedral angle, and a second portion has a strictly negative leading edge dihedral angle, the zone of maximum dihedral angle being, along the radial axis, between r=0.25 h and r=0.7 h.
摘要翻译： 本发明涉及一种压缩机叶片，其在其表面的每个点处被限定为扫掠角和二面角，包括：根部，尖端，根部和尖端之间的距离，沿着所指的轴线 作为垂直于压缩机的旋转轴线的径向轴线被称为径向高度（h），根部和尖端之间的区域，第一部分具有严格正的前缘二面角，以及 第二部分具有严格负的前缘二面角，沿着径向轴的最大二面角的区域在r = 0.25h和r = 0.7h之间。
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公开(公告)号：US09243511B2
公开(公告)日：2016-01-26
申请号：US14189081
申请日：2014-02-25
发明人： Ching-Pang Lee , Kok-Mun Tham , Gm Salam Azad
IPC分类号： F01D11/12
CPC分类号： F01D11/122 , F01D5/02 , F01D5/12 , F01D11/14 , F01D25/24 , F01D25/246 , F05D2220/30 , F05D2230/10 , F05D2230/60 , F05D2240/24 , F05D2250/182 , F05D2250/183 , F05D2250/282 , F05D2250/294 , F05D2250/71 , Y10T29/49236
摘要： Turbine and compressor casing abradable component embodiments for turbine engines, with zig-zag pattern abradable surface ridges and grooves. Some embodiments include distinct forward upstream and aft downstream composite multi orientation groove and vertically projecting ridges planform patterns, to reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. Ridge or rib embodiments have first lower and second upper wear zones. The lower zone optimizes engine airflow characteristics while the upper zone is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone.
摘要翻译： 用于涡轮发动机的涡轮机和压缩机壳体可磨损部件实施例，具有锯齿形图案可磨损的表面脊和凹槽。 一些实施方案包括明显的前向上游和后向下游复合多取向凹槽和垂直突出的脊平台形图案，以减少，重定向和/或阻挡下游进入凹槽的叶片尖端气流泄漏，而不是从涡轮叶片翼型件到高压侧。 脊或肋实施例具有第一下部和第二上部耐磨区域。 下部区域优化发动机气流特性，同时优化上部区域以通过比下部区域更容易磨损来最小化叶片尖端间隙和磨损。
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公开(公告)号：US09212565B2
公开(公告)日：2015-12-15
申请号：US13799613
申请日：2013-03-13
申请人： EcoServices, LLC
CPC分类号： F01D25/002 , F02C7/1435 , F05D2250/71 , F05D2260/30 , F16L33/00 , F16L37/00
摘要： A retention system includes a structure clamp to connect the retention system to another structure; and a manifold clamp connected to the structure clamp, the manifold clamp including a trough to receive a pipe, a plurality of tube clamps with split cylinders extending through the trough, a collar to clamp around the pipe, and a spring to bias the trough from the collar.
摘要翻译： 保持系统包括用于将保持系统连接到另一结构的结构夹具; 以及连接到所述结构夹具的歧管夹具，所述歧管夹具包括用于容纳管道的槽，具有延伸穿过所述槽的分离缸的多个管夹，围绕所述管夹紧的套环以及用于将所述槽偏置 衣领。
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公开(公告)号：US20150354362A1
公开(公告)日：2015-12-10
申请号：US14624240
申请日：2015-02-17
发明人： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
CPC分类号： F04D29/384 , F01D5/141 , F02C3/04 , F02C3/14 , F02C7/36 , F02K3/04 , F04D29/325 , F05D2220/36 , F05D2240/35 , F05D2250/71 , F05D2250/713 , F05D2250/75 , F05D2260/4031 , F05D2270/3013 , Y02T50/672 , Y02T50/673
摘要： An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a total chord length and a span position and corresponds to a curve that has an increasing total chord length from the 0% span position to a first peak. The first peak occurs in the range of 45-65% span position, and the curve either remains generally constant or has a decreasing total chord length from the first peak to the 100% span position. The total chord length is at the 0% span position in the range of 8.2-10.5 inches (20.8-26.7 cm).
摘要翻译： 用于涡轮发动机的翼型包括压力和吸力侧，其在径向方向上从内部流动路径位置处的0％跨度位置延伸到翼型端部处的100％跨度位置。 翼型具有总弦长和跨度位置之间的关系，并且对应于从0％跨度位置到第一峰具有增加的总弦长的曲线。 第一个峰出现在45-65％跨度位置的范围内，并且该曲线或者保持一般恒定或具有从第一峰到100％跨度位置的总弦长减小。 总和弦长度在8.2-10.5英寸（20.8-26.7厘米）范围内的0％跨度位置。
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公开(公告)号：US09194239B2
公开(公告)日：2015-11-24
申请号：US13508689
申请日：2011-01-19
申请人： Koichiro Iida
发明人： Koichiro Iida
CPC分类号： F01D5/225 , F05D2250/71 , Y02T50/671 , Y02T50/673
摘要： A rotor blade includes a blade main body having a proximal end connected to the blade root, and a tip shroud connected to a tip end of the blade main body so as to constitute a part of an annular shroud, a tip end side of a leading edge of the blade main body is made continuous to an outside surface of the tip shroud via a curved portion curved toward a trailing edge, fillets are provided between the tip end of the blade main body and an inside surface of the tip shroud, and the curved portion is located closer to the leading edge than the fillets, whereby the turbine rotor blade and the turbo machine can realize weight reduction and suppress performance degradation.
摘要翻译： 转子叶片包括具有连接到叶片根部的近端的叶片主体和连接到叶片主体的顶端以构成环形护罩的一部分的尖端罩，前端的前端侧 叶片主体的边缘经由弯曲部分向后缘弯曲而与尖端护罩的外表面连续，在刀片主体的末端和尖端护罩的内表面之间设置有圆角， 弯曲部分位于比圆角更靠近前缘的位置，由此涡轮转子叶片和涡轮机可实现重量减轻并抑制性能下降。
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39.发明授权Seal assembly including grooves in an aft facing side of a platform in a gas turbine engine 有权密封组件包括在燃气涡轮发动机中的平台的面向后方的槽公开(公告)号：US09181816B2
公开(公告)日：2015-11-10
申请号：US14189227
申请日：2014-02-25
发明人： Ching-Pang Lee , Kok-Mun Tham , Eric Schroeder , Erik Johnson , Dustin Muller , Steven Coppess , Manjit Shivanand , Kahwai G. Muriithi
CPC分类号： F01D11/001 , F01D11/02 , F05D2240/80 , F05D2250/37 , F05D2250/38 , F05D2250/71 , F05D2260/14
摘要： A seal assembly between a disc cavity and a hot gas path in a gas turbine engine includes a stationary vane assembly and a rotating blade assembly axially upstream from the vane assembly. A platform of the blade assembly has a radially outwardly facing first surface, an axially downstream facing second surface defining an aft plane, and a plurality of grooves extending into the second surface such that the grooves are recessed from the aft plane The grooves are arranged such that a circumferential space is defined between adjacent grooves During operation of the engine, the grooves impart a circumferential velocity component to purge air flowing out of a disc cavity through the grooves to guide the purge air toward a hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path.
摘要翻译： 燃气涡轮发动机中的盘腔和热气路之间的密封组件包括固定叶片组件和在叶片组件的轴向上游的旋转叶片组件。 叶片组件的平台具有径向向外的第一表面，限定了后平面的轴向下游的第二表面，以及延伸到第二表面中的多个凹槽，使得凹槽从后平面凹陷。凹槽被布置成 在相邻槽之间限定周向空间在发动机工作期间，槽赋予圆周速度分量，以通过槽吹扫从盘腔流出的空气，以将吹扫空气引向热气路径，使得吹扫空气流动 相对于热气体流过热气体路径的方向在期望的方向上。
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40.发明申请Blade Retaining Ring for an Internal Shroud of an Axial-Flow Turbomachine Compressor 有权用于轴流式涡轮机压缩机内部护罩的叶片固定环公开(公告)号：US20150308277A1
公开(公告)日：2015-10-29
申请号：US14695292
申请日：2015-04-24
申请人： Techspace Aero S.A.
发明人： Damien Verhelst
CPC分类号： F01D9/04 , F01D9/042 , F01D11/001 , F01D11/122 , F01D25/005 , F04D19/007 , F04D29/164 , F05D2250/71 , F05D2260/30 , F05D2260/36 , F05D2300/171 , F05D2300/43 , F05D2300/437 , F05D2300/501
摘要： The present application relates to a stator of a low-pressure compressor of an axial-flow turbomachine. The stator includes an annular row of stator blades including radial extremities which pass through the openings of an internal shroud, and which include radial retaining slots having tapers formed by hooks. The stator also includes a ring for retaining the blades on the internal shroud. The ring is curved circumferentially in order to be inserted into a plurality of retaining slots and exhibits the form of a strip having an arched transversal profile which is in abutment against the tapers, in such a way as to maintain the ring in the interior of the slots. The shroud includes an annular layer of abradable material made from silicone, which encloses the ring in such a way as to block the curvature of the arched profile of the ring in order to prevent it from disengaging from the tapers of the slots.
摘要翻译： 本申请涉及一种轴流式涡轮机的低压压缩机的定子。 定子包括环形排的定子叶片，其包括通过内部罩的开口的径向末端，并且包括具有由钩形成的锥形的径向保持槽。 定子还包括用于将叶片保持在内部护罩上的环。 环是周向弯曲的，以便插入到多个保持狭槽中并呈现出具有拱形横截面的条带的形状，该横向轮廓与锥形物抵接，以将环保持在内部的内部 插槽 护罩包括由硅树脂制成的可磨损材料的环形层，其围绕环以这种方式封闭环的拱形轮廓的曲率，以防止其与槽的锥形脱离。
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