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71.发明公开
公开(公告)号：EP3115589A1
公开(公告)日：2017-01-11
申请号：EP16178668.6
申请日：2016-07-08
发明人： ADAMS, Paul R. , MAGGE, Shankar S. , STAUBACH, Joseph B. , LORD, Wesley K. , SCHWARZ, Frederick M. , SUCIU, Gabriel L.
摘要： A turbofan engine (20) includes an engine case (22), a gaspath through the engine case (22), a fan (42) having a circumferential array of fan blades, a compressor in fluid communication with the fan (42), a combustor (48) in fluid communication with the compressor, and a turbine in fluid communication with the combustor (48). The turbine has a fan drive turbine section (27) having 3 to 6 blade stages (200, 202, 204). A speed reduction mechanism (46) couples the fan drive turbine section (27) to the fan (42). A bypass area ratio is between 8.0 and 20.0. A ratio of maximum gaspath radius along the fan drive turbine section (27) to maximum radius of the fan (42) is less than 0.50. A ratio of a turbine section airfoil count to the bypass area ratio is between 10 and 170.
摘要翻译： 涡轮风扇发动机（20）包括发动机壳体（22），通过发动机壳体（22）的气路，具有圆周阵列的风扇叶片的风扇（42），与风扇（42）流体连通的压缩机， 与压缩机流体连通的燃烧器（48）和与燃烧器（48）流体连通的涡轮机。 涡轮机具有风扇驱动涡轮部分（27），其具有3至6个叶片级（200,202,204）。 减速机构（46）将风扇驱动涡轮部分（27）连接到风扇（42）。 旁路面积比在8.0和20.0之间。 沿着风扇驱动涡轮部分（27）的最大气路径半径与风扇（42）的最大半径的比值小于0.50。 涡轮机翼型计数与旁路面积比的比值在10和170之间。
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72.发明公开
公开(公告)号：EP3106646A1
公开(公告)日：2016-12-21
申请号：EP16174862.9
申请日：2016-06-16
CPC分类号： F02C7/185 , F01D25/12 , F01P7/02 , F01P11/12 , F02C6/08 , F02C7/14 , F02C9/18 , F02K3/115 , F05D2260/213 , F05D2260/231 , F05D2270/303 , Y02T50/675
摘要： A gas turbine engine (20) includes an engine core (130) defining a primary flowpath, and a nacelle (120; 220; 320) radially surrounding the engine core (130). The nacelle (120; 220; 320) includes at least one bifurcation (112), and a cooled cooling air system (140) including a heat exchanger (142; 240; 348). The heat exchanger (142; 240; 340) is disposed at least partially in the bifurcation (112).
摘要翻译： 燃气涡轮发动机（20）包括限定主流路的发动机芯（130）和径向围绕发动机芯（130）的机舱（120; 220; 320）。 所述机舱（120; 220; 320）包括至少一个分叉（112）和包括热交换器（142; 240; 348）的冷却的冷却空气系统（140）。 热交换器（142; 240; 340）至少部分地设置在分叉（112）中。
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公开(公告)号：EP3071824A1
公开(公告)日：2016-09-28
申请号：EP14864738.1
申请日：2014-09-25
IPC分类号： F02K3/02
摘要： A three-spool turbofan engine (20) has a variable fan nozzle (35). The fan blades have a peak tip radius RT and an inboard leading edge radius RH at an inboard boundary of the flowpath. A ratio of RH to RT is less than about 0.40.
摘要翻译： 根据本公开的示例性方面的涡轮风扇发动机尤其包括具有多个叶片的风扇，并且变速器构造成驱动风扇。 风扇叶片具有峰顶半径RT。 风扇叶片在流路的内侧边界处具有内侧前缘半径RH。 RH与RT的比值小于约0.40。
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74.发明公开GAS TURBINE ENGINE AIRFOIL WITH AUXILIARY FLOW CHANNEL 审中-公开GASTURBINENSCHAUFEL MITZUSÄTZLICHEMSTRÖMUNGSKANAL
公开(公告)号：EP3063374A1
公开(公告)日：2016-09-07
申请号：EP14857657.2
申请日：2014-10-07
CPC分类号： F01D5/147 , F01D5/145 , F01D5/146 , F01D9/041 , F01D17/14 , F01D17/162 , F04D29/563 , F04D29/682 , F04D29/684 , F05D2220/32 , F05D2240/123 , F05D2240/124 , F05D2240/305 , F05D2240/306 , F05D2240/35 , F05D2260/60 , Y02T50/673
摘要： A component for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that includes a pressure side surface and a suction side surface that join together at a leading edge and a trailing edge and a flow channel that extends between the pressure side surface and the suction side surface.
摘要翻译： 根据本公开的示例性方面的用于燃气涡轮发动机的部件包括除了别的以外的翼型件，其包括在前缘和后缘处连接在一起的压力侧表面和吸力侧表面，以及流动 通道，其在压力侧表面和吸力侧表面之间延伸。
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75.发明公开GEARED TURBOFAN WITH HIGH GEAR RATIO AND HIGH TEMPERATURE CAPABILITY 审中-公开GETRIEBE-TURBOFAN-TRIEBWERK MIT HOHEMÜBERSETZUNGSVERHÄLTNISUNDHOCHTEMPERATURSTABILITÄT
公开(公告)号：EP3059393A1
公开(公告)日：2016-08-24
申请号：EP16156289.7
申请日：2016-02-18
CPC分类号： F02C9/18 , F01D5/28 , F01D5/286 , F02C3/10 , F02C7/18 , F02C7/32 , F02C7/36 , F02K3/06 , F05D2220/32 , F05D2220/36 , F05D2240/30 , F05D2300/175 , F05D2300/607 , Y02T50/671
摘要： A gas turbine engine (20; 80; 110) comprises a fan rotor (82) having blades with an outer diameter greater than or equal to 77 inches (196 centimeters) and less than or equal to 135 inches (343 centimeter). The fan rotor (82) has less than or equal to 26 fan blades, and is driven by a fan drive turbine rotor (98) through a gear reduction (83). The gear reduction (83) has a gear ratio of greater than 2.6:1. The fan rotor (82) delivers air into a bypass duct as bypass air, and into a duct leading to a compressor rotor (86, 90) as core air. A ratio of bypass air to the core air is greater than or equal to 12:1. An upstream turbine rotor (88, 92; 96) is upstream of the fan drive turbine rotor (98) and drives a compressor rotor (86, 90). The upstream turbine rotor (88, 92; 96) has at least two stages, and the fan drive turbine rotor (98) has at least three stages. The turbine blades in at least one stage of the fan drive turbine rotor (98) are provided with a performance enhancing feature.
摘要翻译： 燃气涡轮发动机（20; 80; 110）包括具有外径大于或等于77英寸（196厘米）且小于或等于135英寸（343厘米））的叶片的风扇转子（82）。 风扇转子（82）具有小于或等于26个风扇叶片，并由风扇驱动涡轮机转子（98）通过齿轮减速（83）驱动。 齿轮减速装置（83）具有大于2.6:1的传动比。 风扇转子（82）将空气作为旁路空气输送到旁通管道中，并且作为核心空气进入通向压缩机转子（86,90）的管道。 旁路空气与核心空气的比例大于或等于12：1。 上游涡轮转子（88,92; 96）在风扇驱动涡轮转子（98）的上游并驱动压缩机转子（86,90）。 上游涡轮转子（88,92; 96）具有至少两级，并且风扇驱动涡轮转子（98）具有至少三级。 在风扇驱动涡轮转子（98）的至少一个级中的涡轮机叶片具有性能提升特征。
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公开(公告)号：EP3052812A1
公开(公告)日：2016-08-10
申请号：EP14848344.9
申请日：2014-04-02
CPC分类号： F02K3/06 , B64D11/06 , F01D5/06 , F01D5/147 , F01D25/24 , F01D25/30 , F02C3/10 , F04D19/02 , F04D19/026 , F04D19/028 , F04D25/045 , F04D29/321 , F04D29/325 , F04D29/542 , F04D29/563 , F05D2220/327 , F05D2220/36 , F05D2240/30 , F05D2260/40311
摘要： A gas turbine engine has an upstream compressor having an upstream entrance area leading into a first vane upstream of the upstream compressor. A downstream compressor has an exit area at a leading edge of an exit vane for the downstream compressor. The entrance area divided by the exit area is greater than or equal to 13.8 and less than or equal to 15.3.
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77.发明公开GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION 审中-公开GASTURBINENMOTOR MIT EINEM HOCHGESCHWINDIGKEITS-NIEDERDRUCK-TURBINENABSCHNITT
公开(公告)号：EP3034849A1
公开(公告)日：2016-06-22
申请号：EP15199916.6
申请日：2015-12-14
CPC分类号： F02K3/06 , F02C7/36 , F02K3/072 , F05D2260/40311
摘要： A gas turbine engine includes a very high speed low pressure turbine (46) such that a quantity defined by the exit area of the low pressure turbine (46) multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine (54) is at a ratio between about 0.5 and about 1.5.
摘要翻译： 燃气涡轮发动机包括非常高速的低压涡轮机（46），使得由低压涡轮机（46）的出口面积所规定的量乘以低压涡轮机转速的平方，与用于 高压涡轮机（54）的比例为约0.5至约1.5。
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公开(公告)号：EP2994628A2
公开(公告)日：2016-03-16
申请号：EP14829601.5
申请日：2014-04-29
CPC分类号： F01D25/24 , F01D5/02 , F01D5/12 , F01D17/105 , F02C3/107 , F02K3/06 , F04D29/321 , F05D2220/32 , F05D2220/36 , F05D2230/60 , F05D2240/24 , F05D2250/51 , F05D2260/40311 , F16H1/28
摘要： A turbofan engine includes a geared architecture for driving a fan about an axis. The geared architecture includes a sun gear rotatable about an axis, a plurality of planet gears driven by the sun gear and a ring gear circumscribing the plurality of planet gears. A carrier supports the plurality of planet gears. The geared architecture includes a power transfer parameter (PTP) defined as power transferred through the geared architecture divided by gear volume multiplied by a gear reduction ratio and is between about 430 and 645.
摘要翻译： 涡轮风扇发动机包括用于围绕轴驱动风扇的齿轮架构。 齿轮架构包括围绕轴线旋转的太阳齿轮，由太阳齿轮驱动的多个行星齿轮和围绕多个行星齿轮的环形齿轮。 载体支撑多个行星齿轮。 齿轮架构包括功率传递参数（PTP），定义为通过齿轮传动结构传递的功率，齿轮容积乘以齿轮减速比，大约在430和645之间。
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79.发明公开
公开(公告)号：EP2963242A1
公开(公告)日：2016-01-06
申请号：EP15175053.6
申请日：2015-07-02
CPC分类号： F02C7/36 , F01D5/142 , F01D5/225 , F05D2220/327 , F05D2260/40311 , Y02T50/671 , Y02T50/673
摘要： A turbine section (28) for a gas turbine engine (20; 220; 320; 420) includes a fan drive turbine (46) including a fan drive duct (62), the fan drive turbine (46) being configured to drive a fan section (22) through a geared architecture (48) at a speed that is less than an input speed to the geared architecture (48). At least one upstream turbine (54) is configured to drive at least one compressor (44, 52). The at least one upstream turbine (54) includes a turbine duct (60) defining a conical flow path (70) having a conical inlet (75) defined by a first diameter and a conical outlet (77) defined by a second diameter greater than the first diameter. The conical outlet (77) is in fluid communication with the fan drive duct (62) downstream of the conical outlet (77). At least one row of shrouded rotor blades (71) defines at least a portion of the conical flow path (70).
摘要翻译： 一种用于燃气涡轮发动机（20; 220; 320; 420）的涡轮部分（28）包括风扇驱动涡轮机（46），风扇驱动涡轮机（46）包括风扇驱动管道（62），风扇驱动涡轮机（46） （22）通过齿轮架构（48）以小于所述齿轮架构（48）的输入速度的速度。 至少一个上游涡轮机（54）构造成驱动至少一个压缩机（44,52）。 所述至少一个上游涡轮机（54）包括限定具有由第一直径限定的锥形入口（75）和锥形出口（77）的锥形流动路径（70）的涡轮管道（60），所述圆锥形入口由第二直径大于 第一个直径。 锥形出口（77）与锥形出口（77）下游的风扇驱动管道（62）流体连通。 至少一排被覆盖的转子叶片（71）限定了锥形流动路径（70）的至少一部分。
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公开(公告)号：EP2954212A2
公开(公告)日：2015-12-16
申请号：EP14748753.2
申请日：2014-02-04
CPC分类号： F01D25/20 , F01D1/02 , F01D15/10 , F01D15/12 , F01D25/08 , F01D25/125 , F01D25/16 , F01D25/18 , F02C3/107 , F02C7/14 , F05D2220/30 , F05D2260/20 , F05D2260/213 , F05D2260/40311 , F05D2260/98 , Y02T50/676
摘要： A turbine engine system includes a first lubricant circuit, a second lubricant circuit, a plurality of engine stages and a shaft. The first lubricant circuit includes a first turbine engine component that is fluidly coupled with a first lubricant heat exchanger. The second lubricant circuit includes a second turbine engine component that is fluidly coupled with a second lubricant heat exchanger, wherein the second lubricant circuit is fluidly separate from the first lubricant circuit. The first turbine engine component includes a gear train, which connects a first of the engine stages to a second of the engine stages. The second turbine engine component includes a bearing. The shaft is supported by the bearing and connected to one of the engine stages.
摘要翻译： 涡轮发动机系统包括第一润滑油回路，第二润滑油回路，多个发动机级和轴。 第一润滑剂回路包括与第一润滑剂热交换器流体联接的第一涡轮发动机部件。 第二润滑剂回路包括与第二润滑剂热交换器流体联接的第二涡轮发动机部件，其中第二润滑剂回路与第一润滑剂回路流体分离。 第一涡轮发动机部件包括齿轮系，该齿轮系将第一发动机级连接到第二发动机级。 第二涡轮发动机部件包括轴承。 轴由轴承支撑并连接到其中一个发动机级。
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