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91. 发明授权

US09394798B2 Gas turbine engines with turbine airfoil cooling 有权
标题翻译：带涡轮翼型冷却的燃气涡轮发动机
公开(公告)号：US09394798B2
公开(公告)日：2016-07-19
申请号：US13855417
申请日：2013-04-02
申请人： HONEYWELL INTERNATIONAL INC.
发明人： Daniel Cregg Crites , Mark C. Morris , Lorenzo Crosatti , Ardeshir Riahi
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2220/32 , F05D2240/121 , F05D2250/231 , F05D2250/232 , F05D2260/201 , Y02T50/671 , Y02T50/676
摘要： An airfoil for a gas turbine engine is provided. The airfoil includes a body with a leading edge, a trailing edge, a first side wall extending between the leading edge and the trailing edge, and a second side wall extending between the leading edge and the trailing edge. The body defines an interior cavity. The airfoil includes an interior wall disposed within the interior cavity of the body and extending between the first wall and the second wall to define a supply chamber and a leading edge chamber. The interior wall defines a cooling hole with a base portion and a locally extended portion to direct cooling air from the supply chamber to the leading edge chamber such that the cooling air impinges upon the leading edge.
摘要翻译：提供了一种用于燃气涡轮发动机的翼型件。翼型件包括具有前缘的主体，后缘，在前缘和后缘之间延伸的第一侧壁，以及在前缘和后缘之间延伸的第二侧壁。身体定义一个内腔。所述翼型件包括设置在所述主体的内部空腔内并在所述第一壁和所述第二壁之间延伸的内壁，以限定供应室和前缘室。内壁限定具有基部和局部延伸部分的冷却孔，以将冷却空气从供应室引导到前缘室，使得冷却空气撞击前缘。

92. 发明申请

US20160169005A1 GAS TURBINE ENGINE COMPONENT WITH INCREASED COOLING CAPACITY 审中-公开
标题翻译：具有提高冷却能力的气体涡轮发动机部件
公开(公告)号：US20160169005A1
公开(公告)日：2016-06-16
申请号：US14923553
申请日：2015-10-27
申请人： United Technologies Corporation
发明人： San Quach , Christopher King , Thomas N. Slavens
IPC分类号： F01D5/18 , F01D9/04 , F02C3/04 , F01D25/12 , F02C7/18 , F23R3/00 , F01D5/02 , F01D11/08
CPC分类号： F01D5/187 , F01D5/02 , F01D5/186 , F01D9/041 , F01D11/08 , F01D25/12 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2230/10 , F05D2240/12 , F05D2240/30 , F05D2240/307 , F05D2240/35 , F05D2250/231 , F05D2250/232 , F05D2260/202 , F23R3/002 , Y02T50/676
摘要： A cooling circuit for a gas turbine engine comprises a gas turbine engine component having a body with at least one internal cavity defined by a cavity wall. A plurality of cooling holes formed within the cavity wall, wherein each cooling hole is defined by a length extending from a cooling hole inlet to a cooling hole outlet, and wherein the cooling holes are positioned relative to each other such that a minimum allowable ligament distance is maintained between adjacent cooling holes along the entire length of each cooling hole. A gas turbine engine and a method of forming a cooling circuit for a gas turbine engine are also disclosed.
摘要翻译：用于燃气涡轮发动机的冷却回路包括燃气涡轮发动机部件，其具有主体，该主体具有由空腔壁限定的至少一个内部空腔。多个冷却孔形成在空腔壁内，其中每个冷却孔由从冷却孔入口延伸到冷却孔出口的长度限定，并且其中冷却孔相对于彼此定位，使得最小允许韧带距离沿着每个冷却孔的整个长度保持在相邻的冷却孔之间。还公开了一种燃气涡轮发动机和形成燃气涡轮发动机的冷却回路的方法。

93. 发明授权

US09303871B2 Combustor assembly including a transition inlet cone in a gas turbine engine 有权
标题翻译：燃烧器组件包括在燃气涡轮发动机中的过渡入口锥体
公开(公告)号：US09303871B2
公开(公告)日：2016-04-05
申请号：US13927287
申请日：2013-06-26
申请人： Ulrich Woerz
发明人： Ulrich Woerz
IPC分类号： F23R3/00 , F23R3/60 , F01D9/02
CPC分类号： F23R3/002 , F01D9/023 , F05D2250/232
摘要： A combustor assembly defining a main combustion zone where fuel and air are burned to create hot combustion products includes a liner, a transition duct, and a transition inlet cone. The liner defines an interior volume including a first portion of the main combustion zone, and has an inlet and an outlet spaced from the inlet in an axial direction. The transition duct includes an inlet section and an outlet section that discharges gases to a turbine section. The inlet section is adjacent to the outlet of the liner and defines a second portion of the main combustion zone. The transition inlet cone is affixed to the transition duct and includes a frusto-conical portion extending axially and radially inwardly into the main combustion zone. The transition inlet cone deflects combustion products that are flowing in a radially outer portion of the main combustion zone toward a combustor assembly central axis.
摘要翻译：限定燃料和空气燃烧以产生热燃烧产物的主燃烧区的燃烧器组件包括衬套，过渡管道和过渡入口锥体。衬套限定包括主燃烧区域的第一部分的内部容积，并且在轴向方向上具有与入口间隔开的入口和出口。过渡管道包括将气体排放到涡轮机部分的入口部分和出口部分。入口部分邻近衬套的出口并且限定主燃烧区域的第二部分。过渡进口锥体固定在过渡管道上，并且包括沿轴向和径向向内延伸进入主燃烧区的截头圆锥形部分。过渡入口锥体使在主燃烧区域的径向外部部分中流动的燃烧产物朝向燃烧器组件中心轴线偏转。

94. 发明申请

US20160076449A1 AERO ENGINE WITH A BEARING CHAMBER AND AN APPLIANCE FOR INTRODUCING OIL 审中-公开
标题翻译：具有轴承座的AERO发动机和用于介绍油的器具
公开(公告)号：US20160076449A1
公开(公告)日：2016-03-17
申请号：US14847500
申请日：2015-09-08
申请人： Rolls-Royce Deutschland Ltd & Co KG
发明人： Juergen BEIER
IPC分类号： F02C7/06 , F02C3/04
CPC分类号： F02C7/06 , F01D25/18 , F02C3/04 , F05D2250/14 , F05D2250/232 , F05D2260/98 , F16C33/6659 , F16C2360/23
摘要： What is proposed is an aero engine (1) with a bearing chamber (12), which is confined by a first wall area (32) and a second wall area (33) which is embodied so as to be rotatable with respect to the first wall area (32) and in which at least one bearing appliance as well as at least one appliance (38, 39, 40) for introducing oil are arranged. Oil can be introduced into the bearing chamber (12) via at least one appliance (38, 39, 40) for introducing oil substantially against a rotational direction of the first wall area (32) and/or of the second wall area (33) and substantially tangentially to at least one surface (43) of at least one wall area (32, 33) that is facing the bearing chamber (12).
摘要翻译：所提出的是具有轴承室（12）的航空发动机（1），所述轴承室（12）由第一壁区域（32）和第二壁区域（33）限定，所述第一壁区域和第二壁区域被构造成可相对于第一壁区域壁区域（32），并且其中布置有用于引入油的至少一个轴承装置以及至少一个装置（38,39,40）。油可以经由至少一个用于将油基本上抵靠第一壁区域（32）和/或第二壁区域（33）的旋转方向引入的装置（38,39,40）引入到轴承室（12）并且基本切向地相对于面向轴承腔（12）的至少一个壁区域（32,33）的至少一个表面（43）。

95. 发明申请

US20150337678A1 THERMOCOUPLE WITH A VORTEX REDUCING PROBE 有权
标题翻译：具有VORTEX减少探头的热电偶
公开(公告)号：US20150337678A1
公开(公告)日：2015-11-26
申请号：US14286754
申请日：2014-05-23
申请人： Solar Turbines Incorporated
发明人： Rodolfo G. Alonte , Bruno Enriquez Struck
IPC分类号： F01D21/00 , G01M15/14 , G01K7/02
CPC分类号： F01D21/003 , F01D17/085 , F05D2250/14 , F05D2250/231 , F05D2250/232 , F05D2250/241 , G01K1/08 , G01K7/023 , G01K13/02 , G01K2013/024 , G01M15/14
摘要： A sensor assembly for a gas turbine engine is disclosed. The sensor assembly includes a bushing and a probe. The probe includes a body, an anti-vortex tip, and a tip end. The body extends from the bushing and includes a body surface. The body surface is a right circular cylinder with a first diameter. The anti-vortex tip extends from the body and includes an anti-vortex tip surface. The anti-vortex tip surface is a conical surface extending from the body surface to a second diameter at a taper angle from fourteen degrees to sixteen degrees. The tip end extends with a spherical shape from the anti-vortex tip.
摘要翻译：公开了一种用于燃气涡轮发动机的传感器组件。传感器组件包括衬套和探针。探头包括主体，防涡流尖端和尖端。主体从衬套延伸并且包括主体表面。身体表面是具有第一直径的右圆柱体。防涡流尖端从主体延伸并且包括防涡流顶端表面。防旋涡末表面是从十六度到十六度的锥角从体表延伸到第二直径的锥形表面。尖端从抗旋涡末端延伸出球形。

96. 发明申请

US20150267556A1 GAS TURBINE ENGINE 审中-公开
标题翻译：气体涡轮发动机
公开(公告)号：US20150267556A1
公开(公告)日：2015-09-24
申请号：US14630771
申请日：2015-02-25
申请人： ROLLS-ROYCE PLC
发明人： Keith Jeremy Paul THOMAS
IPC分类号： F01D25/04 , F01D21/04
CPC分类号： F01D21/045 , F05D2220/36 , F05D2250/232 , F05D2250/282 , F05D2250/283 , F05D2260/96 , F05D2300/501
摘要： A fan containment system for fitment around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. The fan containment system comprises a fan case having an annular casing element for encircling an array of fan blades. An annular fan track liner is positioned substantially coaxial to the annular casing element, and one or more pockets are provided in a radially outer side of the fan track liner. One or more dampers for damping vibration of the fan track liner are positioned in each of the one or more pockets and are arranged so as to contact the annular casing element.
摘要翻译：一种用于安装在轴向燃气涡轮发动机的轮毂上的径向延伸的风扇叶片阵列周围的风扇容纳系统。风扇容纳系统包括具有用于环绕风扇叶片阵列的环形壳体元件的风扇壳体。环形风扇履带衬板被定位成基本上与环形壳体元件同轴，并且一个或多个袋设置在风扇履带衬板的径向外侧。一个或多个用于阻尼风扇履带衬垫的振动的阻尼器定位在一个或多个袋中的每个中，并且被布置成接触环形壳体元件。

97. 发明申请

US20150218967A1 BIFURCATED DUCTS INCLUDING PLENUMS FOR STABILIZING FLOW THERETHROUGH AND EXHAUST SYSTEMS INCLUDING THE SAME 有权
标题翻译：包括用于稳定流动的整流器和包括其的排气系统的分流管
公开(公告)号：US20150218967A1
公开(公告)日：2015-08-06
申请号：US14174422
申请日：2014-02-06
申请人： HONEYWELL INTERNATIONAL INC.
发明人： Morris Anderson , Yogendra Yogi Sheoran , Doug Hollingshead
IPC分类号： F01D25/30
CPC分类号： B64D33/04 , F01D25/30 , F05D2220/324 , F05D2250/232
摘要： Plenums for bifurcated ducts and bifurcated ducts are provided for stabilizing flow therethrough. The plenum comprises an outer cylindrical body intersected by a pair of exhaust duct stubs that are configured to be coupled to a corresponding pair of exhaust ducts and an inner body. The outer cylindrical body includes an axial rear end portion. The inner body is disposed in the axial rear end portion and increases in diameter in the aft direction. The inner body comprises one of a generally axi-symmetrical inner body or a non-axi-symmetrical inner body. The bifurcated duct comprises the plenum and the pair of exhaust ducts. Exhaust systems are also provided.
摘要翻译：提供用于分叉管道和分叉管道的平板，用于稳定流过其中的流动。增压室包括与一对排气管道短截线相交的外圆柱形体，其被配置为联接到相应的一对排气管道和内部主体。外筒体包括轴向后端部。内体设置在轴向后端部，直径向后方延伸。内部主体包括大致轴对称的内部主体或非轴对称的内部主体中的一个。分叉管道包括增压室和一对排气管道。还提供排气系统。

98. 发明申请

US20150198048A1 METHOD FOR PRODUCING A STATOR BLADE AND STATOR BLADE 审中-公开
标题翻译：用于生产定子叶片和定子叶片的方法
公开(公告)号：US20150198048A1
公开(公告)日：2015-07-16
申请号：US14415480
申请日：2013-07-15
申请人： Siemens Aktiengesellschaft
发明人： Michael Handler
IPC分类号： F01D5/18 , B23P15/04
CPC分类号： F01D5/187 , B23P15/04 , F01D5/147 , F01D5/186 , F01D9/02 , F01D9/065 , F05D2220/30 , F05D2230/12 , F05D2230/13 , F05D2230/60 , F05D2230/90 , F05D2240/81 , F05D2250/232 , F05D2260/20 , F05D2260/202 , Y02T50/673 , Y02T50/676 , Y10T29/49337
摘要： A method for producing a turbine vane with a vane airfoil and a vane root is provided to achieve a higher efficiency for a turbine. The method includes: a) production of a vane airfoil and a vane root as separate parts; b) introduction of a cooling air opening into the vane airfoil; and c) joining the vane airfoil and vane root together after step b).
摘要翻译：提供了一种用于制造具有叶片翼型和叶片根部的涡轮叶片的方法，以实现更高的涡轮效率。该方法包括：a）叶片叶片和叶片根部分为零件制作; b）将冷却空气开口引入叶片翼型件; 和c）在步骤b）之后将叶片翼型件和叶片根部接合在一起。

99. 发明授权

US08997450B2 Filter cartridge assembly for use with turbine engine systems 有权
标题翻译：用于涡轮发动机系统的过滤器滤芯组件
公开(公告)号：US08997450B2
公开(公告)日：2015-04-07
申请号：US12951858
申请日：2010-11-22
申请人： Etienne Rene Jarrier , Charles Brake , Paul Sherwood Bryant
发明人： Etienne Rene Jarrier , Charles Brake , Paul Sherwood Bryant
IPC分类号： F02G3/00 , F02C7/055 , B01D46/00 , B01D46/24
CPC分类号： F02C7/055 , B01D46/002 , B01D46/0024 , B01D46/003 , B01D46/2407 , B01D2265/02 , B01D2275/201 , B01D2279/60 , F05D2250/232 , Y10T29/49826
摘要： A filter cartridge assembly includes a first filter including a first cavity defined therein and a second filter coupled to the first filter. The second filter includes a second cavity defined therein in flow communication with first cavity. The filter cartridge assembly also includes at least one pre-filter extending about the first filter and the second filter such that a third cavity is defined between the at least one pre-filter and at least one of the first filter and the second filter.
摘要翻译：滤芯组件包括第一过滤器，其包括限定在其中的第一空腔和耦合到第一过滤器的第二过滤器。第二过滤器包括与第一空腔流体连通的限定在其中的第二腔。滤芯组件还包括围绕第一过滤器和第二过滤器延伸的至少一个预过滤器，使得在至少一个预过滤器与第一过滤器和第二过滤器中的至少一个之间限定第三腔。

100. 发明申请

US20150093236A1 EXHAUST GAS TURBOCHARGER HAVING GUIDING SCREEN RINGS THAT ARE ROTATABLE RELATIVE TO EACH OTHER 有权
标题翻译：具有相对于其他任何可旋转的导向屏风的排气烟囱
公开(公告)号：US20150093236A1
公开(公告)日：2015-04-02
申请号：US14381271
申请日：2013-02-20
申请人： CONTINENTAL AUTOMOTIVE GMBH
发明人： Holger Faeth , Ralf Boening
IPC分类号： F04D27/00 , F04D17/10
CPC分类号： F04D27/002 , F01D17/14 , F01D17/148 , F02C6/12 , F04D17/10 , F05D2220/40 , F05D2250/232
摘要： An exhaust gas turbocharger includes a turbine housing in which a turbine wheel and a guide apparatus that guides an exhaust gas flow to the turbine wheel are disposed. The guide apparatus has two guide grate or screen rings that are rotatable relative to each other and each of which have guide vanes or blades. Conically running flow channels tapering in the direction of the turbine wheel are formed between the guide grate rings.
摘要翻译：排气涡轮增压器包括涡轮机壳体，其中布置有将废气流引导到涡轮机叶轮的涡轮机叶轮和引导装置。引导装置具有可相对于彼此旋转并且每个具有导向叶片或叶片的两个导向栅格或筛环。引导格栅环之间形成有沿涡轮机叶轮方向逐渐变细的流道。

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