-
公开(公告)号：US08453458B2
公开(公告)日：2013-06-04
申请号：US12087778
申请日：2007-01-23
CPC分类号： F02K3/06 , F02K1/08 , Y02T50/671
摘要： Variation in the available mixing plane areas in an exhaust arrangement of a gas turbine engine enables alteration and configuration for better thermal cycle performance of that engine. A shaped centre fairing is associated with an exit nozzle and a bypass duct such that channels between the fairing, nozzle exit and duct can be adjusted to change the available areas. Such variation is achieved by relative axial displacement, typically of the exit nozzle using an appropriate mechanism.
摘要翻译： 在燃气涡轮发动机的排气装置中的可用混合平面区域的变化使得能够改变和构造以获得该发动机的更好的热循环性能。 成形中心整流罩与出口喷嘴和旁路管道相关联，使得整流罩，喷嘴出口和管道之间的通道可以被调节以改变可用区域。 这种变化通过相对的轴向位移来实现，通常使用合适的机构来排出出口。
-
公开(公告)号：US20090158704A1
公开(公告)日：2009-06-25
申请号：US12087778
申请日：2007-01-23
CPC分类号： F02K3/06 , F02K1/08 , Y02T50/671
摘要： Variation in the available mixing plane areas in an exhaust arrangement of a gas turbine engine enables alteration and configuration for better thermal cycle performance of that engine. A shaped centre fairing is associated with an exit nozzle and a bypass duct such that channels between the fairing, nozzle exit and duct can be adjusted to change the available areas. Such variation is achieved by relative axial displacement, typically of the exit nozzle using an appropriate mechanism.
摘要翻译： 在燃气涡轮发动机的排气装置中的可用混合平面区域的变化使得能够改变和构造以获得该发动机的更好的热循环性能。 成形中心整流罩与出口喷嘴和旁路管道相关联，使得整流罩，喷嘴出口和管道之间的通道可以被调节以改变可用区域。 这种变化通过相对的轴向位移来实现，通常使用合适的机构来排出出口。
-
公开(公告)号：US08967967B2
公开(公告)日：2015-03-03
申请号：US13359194
申请日：2012-01-26
CPC分类号： F01D5/022 , B64C11/48 , B64D29/00 , B64D2027/005 , F01D5/143 , F01D5/145 , F02C3/067 , F02K3/072 , F05D2220/324 , F05D2220/325 , F05D2240/14 , F05D2250/70 , Y02T50/66 , Y02T50/671
摘要： The present disclosure relates to a propfan engine comprising: one or more rotor stages comprising a plurality of rotors; and an outer wall comprising an outer profile, at least a portion of the outer profile defining a substantially circular cross-section, wherein the diameter of the substantially circular cross-section increases in the direction of flow over the outer wall and downstream of a leading edge of the rotors, and the diameter increases at substantially all points defining the circumference of the substantially circular cross-section.
摘要翻译： 本公开涉及一种普通发动机，其包括：一个或多个转子级，包括多个转子; 以及外壁，其包括外轮廓，所述外轮廓的至少一部分限定基本上圆形的横截面，其中所述基本圆形横截面的直径在所述外壁上的流动方向上增加，并且在前缘 转子的边缘，并且在限定基本圆形横截面的圆周的基本上所有点处的直径增加。
-
公开(公告)号：US07841185B2
公开(公告)日：2010-11-30
申请号：US11353097
申请日：2006-02-14
申请人： Martyn Richards , Nicholas Howarth
发明人： Martyn Richards , Nicholas Howarth
IPC分类号： F02C6/08
CPC分类号： F02C7/32 , F02C9/18 , F05D2260/96 , F05D2270/051
摘要： Disparities between optimum engine thrust for aircraft operation and power necessary to drive an ancillary machine such an electrical power generator can cause problems within a turbine engine. Clearly, it is necessary to continue developing sufficient electrical power for control and other systems within an aircraft despite aircraft thrust requirements. Previously, some compressed air flow has been bypassed in order to maintain compressor stability, but unfortunately such bypass systems within turbine engines can have a thrust recovery regime such that there is excess thrust in comparison with that actually necessary. In accordance with the present invention, a proportion of the compressed air flow is bled directly through a bleed path to an exhaust nozzle 104 of an engine such that the compressor core can continue to provide work to drive an ancillary machine whilst engine thrust is limited to that actually required, achieving a significant saving in terms of fuel consumption and wear and tear upon brakes, etc under low power operation.
摘要翻译： 飞机运行的最佳发动机推力与驱动诸如发电机的辅助机器所需的动力之间的差异可能导致涡轮发动机内的问题。 显然，尽管有飞机的推力要求，仍然需要为飞机内的控制系统和其他系统继续开发足够的电力。 以前，为了保持压缩机的稳定性，已经绕过一些压缩空气流，但不幸的是，涡轮发动机内的这种旁路系统可以具有推力恢复状态，使得与实际需要相比存在过大的推力。 根据本发明，压缩空气流的一部分直接通过排放通道排放到发动机的排气喷嘴104，使得压缩机芯可以继续提供工作来驱动辅助机器，同时发动机推力被限制到 实际上需要的是，在低功率运行下，在燃油消耗和刹车等磨损方面实现了显着的节省。
-
公开(公告)号：US20050211824A1
公开(公告)日：2005-09-29
申请号：US11036360
申请日：2005-01-18
CPC分类号： B64D33/04 , B64D29/02 , B64D33/02 , B64D2033/0286
摘要： A fan turbine engine arrangement 10 is provided in which a core engine 1 is aligned such that an input 11 of a nacelle 2 is aligned with the upwash of a wing 4 to which the arrangement 10 is secured. The engine 1 drives a fan 14 such that bypass flows 16 produced by the fan 14 are guided by a duct 8 to present a downward component for uplift. The core engine 1 presents its output flow through a nozzle 7 which is aligned with the fundamental axis Y-Y of the engine 1 in such circumstances, the bypass flows cross the core engine 1 flow from the nozzle 7 unless that engine is adjustable during operation in order to maintain alignment dependent upon lift requirements.
摘要翻译： 提供了一种风扇涡轮发动机装置10，其中，核心发动机1对准，使得机舱2的输入端11与安置装置10所固定的机翼4的上洗液对齐。 发动机1驱动风扇14，使得由风扇14产生的旁路流16由导管8引导以呈现用于隆起的向下部件。 核心发动机1通过喷嘴7提供其输出流，喷嘴7在这种情况下与发动机1的基本轴线YY对准，旁路流动从喷嘴7流过核心发动机1，除非发动机在运行期间是可调节的 以保持取决于升力要求的对准。
-
公开(公告)号：US08382430B2
公开(公告)日：2013-02-26
申请号：US12449196
申请日：2008-02-06
IPC分类号： B64C11/48
CPC分类号： B64C11/48 , B64C11/50 , F01D1/24 , F05D2220/324 , F05D2220/325 , F05D2250/30 , F05D2260/96 , F05D2270/01 , Y02T50/66 , Y02T50/672
摘要： A method of operating a contra-rotating propeller engine that preferably comprises a 12 bladed front and a 9 bladed rear propeller. As is conventional, the engine is operated during at least a take-off phase, a cruise phase and an approach phase; during the cruise phase the engine operates with a generally constant propeller tip speed. The method is characterized by the step of operating the engine such that the tip speed of either or both of the propellers, during at least one of take-off, climb or approach, at least 10% greater than cruise tip speed. With a specific front to rear propeller spacing, increasing the tip speed reduces overall noise generated by the propellers.
摘要翻译： 一种操作反转螺旋桨发动机的方法，其优选地包括12个叶片的前部和9个叶片的后部螺旋桨。 如常规的那样，发动机在至少起飞阶段，巡航阶段和进近阶段期间操作; 在巡航阶段，发动机以一般恒定的螺旋桨叶尖速度运转。 该方法的特征在于操作发动机的步骤，使得在至少一个起飞，爬升或接近期间，一个或两个螺旋桨的末端速度比巡航末梢速度大至少10％。 具有特定的前后螺旋桨间距，增加提升速度可以降低螺旋桨产生的总体噪音。
-
公开(公告)号：US20100047068A1
公开(公告)日：2010-02-25
申请号：US12449196
申请日：2008-02-06
CPC分类号： B64C11/48 , B64C11/50 , F01D1/24 , F05D2220/324 , F05D2220/325 , F05D2250/30 , F05D2260/96 , F05D2270/01 , Y02T50/66 , Y02T50/672
摘要： A method of operating a contra-rotating propeller engine that preferably comprises a 12 bladed front and a 9 bladed rear propeller. As is conventional, the engine is operated during at least a take-off phase, a cruise phase and an approach phase; during the cruise phase the engine operates with a generally constant propeller tip speed. The method is characterised by the step of operating the engine such that the tip speed of either or both of the propellers, during at least one of take-off, climb or approach, at least 10% greater than cruise tip speed. With a specific front to rear propeller spacing, increasing the tip speed reduces overall noise generated by the propellers.
摘要翻译： 一种操作反转螺旋桨发动机的方法，其优选地包括12个叶片的前部和9个叶片的后部螺旋桨。 如常规的那样，发动机在至少起飞阶段，巡航阶段和进近阶段期间操作; 在巡航阶段，发动机以一般恒定的螺旋桨叶尖速度运转。 该方法的特征在于操作发动机的步骤，使得在至少一个起飞，爬升或接近期间，一个或两个螺旋桨的末端速度比巡航末梢速度大至少10％。 具有特定的前后螺旋桨间距，增加提升速度可以降低螺旋桨产生的总体噪音。
-
公开(公告)号：US07165744B2
公开(公告)日：2007-01-23
申请号：US11036360
申请日：2005-01-18
IPC分类号： B64D27/00
CPC分类号： B64D33/04 , B64D29/02 , B64D33/02 , B64D2033/0286
摘要： A fan turbine engine arrangement is provided in which a core engine is aligned such that an input of a nacelle is aligned with the upwash of a wing to which the arrangement is secured. The engine drives a fan such that bypass flows produced by the fan are guided by a duct to present a downward component for uplift. The core engine presents its output flow through a nozzle which is aligned with the fundamental axis Y—Y of the engine. In such circumstances, the bypass flows cross the core engine flow from the nozzle unless that engine is adjustable during operation in order to maintain alignment dependent upon lift requirements.
摘要翻译： 提供了一种风扇涡轮发动机装置，其中核心发动机对准，使得机舱的输入与该装置固定到的机翼的上洗液对准。 发动机驱动风扇，使得由风扇产生的旁路流由管道引导以呈现用于隆起的向下部件。 核心发动机通过与发动机的基准轴线Y-Y对准的喷嘴使其输出流动。 在这种情况下，旁路流动从喷嘴流过核心发动机流，除非发动机在运行期间是可调节的，以便根据升力要求保持对准。
-
公开(公告)号：US20060196192A1
公开(公告)日：2006-09-07
申请号：US11353097
申请日：2006-02-14
申请人： Martyn Richards , Nicholas Howarth
发明人： Martyn Richards , Nicholas Howarth
IPC分类号： F02C6/08
CPC分类号： F02C7/32 , F02C9/18 , F05D2260/96 , F05D2270/051
摘要： A Turbine Engine and Method of Operating a Turbine Engine Disparities between optimum engine thrust for aircraft operation and power necessary to drive an ancillary machine such an electrical power generator can cause problems within a turbine engine. Clearly, it is necessary to continue developing sufficient electrical power for control and other systems within an aircraft despite aircraft thrust requirements. Previously, some compressed air flow has been bypassed in order to maintain compressor stability, but unfortunately such bypass systems within turbine engines can have a thrust recovery regime such that there is excess thrust in comparison with that actually necessary. In accordance with the present invention, a proportion of the compressed air flow is bled directly through a bleed path to an exhaust nozzle 104 of an engine such that the compressor core can continue to provide work to drive an ancillary machine whilst engine thrust is limited to that actually required, achieving a significant saving in terms of fuel consumption and wear and tear upon brakes, etc under low power operation.
摘要翻译： 涡轮发动机和涡轮发动机的操作方法飞机运行的最佳发动机推力与驱动辅助机械如发电机所需的动力之间的差异可能导致涡轮发动机内的问题。 显然，尽管有飞机的推力要求，仍然需要为飞机内的控制系统和其他系统继续开发足够的电力。 以前，为了保持压缩机的稳定性，已经绕过一些压缩空气流，但不幸的是，涡轮发动机内的这种旁路系统可以具有推力恢复状态，使得与实际需要相比存在过大的推力。 根据本发明，压缩空气流的一部分直接通过排放通道排放到发动机的排气喷嘴104，使得压缩机芯可以继续提供工作来驱动辅助机器，同时发动机推力被限制到 实际上需要的是，在低功率运行下，在燃油消耗和刹车等磨损方面实现了显着的节省。
-
-
-
-
-
-
-
-
搜索结果
9 条记录 (耗时 0.023 秒)