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1. 发明授权

US07549282B2 Multi-slot inter-turbine duct assembly for use in a turbine engine 失效
标题翻译：用于涡轮发动机的多槽涡轮机间导管组件
公开(公告)号：US07549282B2
公开(公告)日：2009-06-23
申请号：US11258547
申请日：2005-10-25
申请人： James Fredric Widenhoefer , Paolo Graziosi , Kevin Richard Kirtley
发明人： James Fredric Widenhoefer , Paolo Graziosi , Kevin Richard Kirtley
IPC分类号： F02C7/00
CPC分类号： F01D5/145 , F02C9/18 , F05D2260/606 , Y02T50/673 , Y10S415/914
摘要： A bypass channel for use in an inter-turbine transition duct assembly of a turbine engine is connected to a suction port disposed upstream of a high-pressure turbine and at least two injection openings disposed downstream of the high-pressure turbine. The flow through the bypass channel is motivated by the natural pressure difference across the high-pressure turbine. The flow out of the at least two injection openings is used to energize the boundary layer flow downstream of the high-pressure turbine in order to allow for the use of a more aggressively expanded inter-turbine duct without boundary layer separation. Methods for optimizing the flow through the turbine engine are also disclosed.
摘要翻译：用于涡轮发动机的涡轮机间过渡管道组件中的旁通通道连接到设置在高压涡轮机上游的吸入口和设置在高压涡轮机下游的至少两个喷射开口。通过旁通通道的流动是由高压涡轮机两端的自然压差引起的。使用至少两个喷射开口的流动来激励高压涡轮机下游的边界层流，以便允许使用更积极地扩展的涡轮机间管道而没有边界层分离。还公开了优化通过涡轮发动机的流量的方法。

2. 发明授权

US07137245B2 High area-ratio inter-turbine duct with inlet blowing 失效
标题翻译：具有入口吹风的高面积比的涡轮机间管道
公开(公告)号：US07137245B2
公开(公告)日：2006-11-21
申请号：US10870884
申请日：2004-06-18
申请人： Paolo Graziosi , Kevin Richard Kirtley
发明人： Paolo Graziosi , Kevin Richard Kirtley
IPC分类号： F02C7/00 , F02C9/18
CPC分类号： F01D5/145 , F01D25/30 , Y02T50/673
摘要： A bypass channel for use in an inter-turbine transition duct of a gas turbine engine is connected to a suction port disposed upstream of a high-pressure turbine and an injection port disposed downstream of the high-pressure turbine. The flow through the bypass channel is motivated by the natural pressure difference across the high-pressure turbine. The flow out of the injection nozzle is used to energize the boundary layer flow downstream of the high-pressure turbine in order to allow for the use of a more aggressively expanded inter-turbine duct without boundary layer separation.
摘要翻译：用于燃气涡轮发动机的涡轮机间过渡管道的旁路通道连接到设置在高压涡轮机的上游的吸入口和设置在高压涡轮机下游的喷射口。通过旁通通道的流动是由高压涡轮机两端的自然压差引起的。喷射出口的流动用于激励高压涡轮机下游的边界层流，以便允许使用更积极扩张的涡轮机间管道，而不需要边界层分离。

3. 发明授权

US06896475B2 Fluidic actuation for improved diffuser performance 失效
标题翻译：用于改进扩散器性能的流体致动
公开(公告)号：US06896475B2
公开(公告)日：2005-05-24
申请号：US10065727
申请日：2002-11-13
申请人： Paolo Graziosi , Richard Edwin Warren, Jr. , Thomas Frank Fric , Ramani Mani , Douglas Carl Hofer
发明人： Paolo Graziosi , Richard Edwin Warren, Jr. , Thomas Frank Fric , Ramani Mani , Douglas Carl Hofer
IPC分类号： F02C7/04 , F01D17/10 , F01D25/30 , F04F5/54 , F15D1/06 , F01D17/14
CPC分类号： F04F5/54 , F01D25/305 , F05D2250/324 , F15D1/06 , Y10S415/914
摘要： A diffuser includes an opening along the diffuser wall for preventing or delaying boundary layer separation of the main flow. The opening may include a curved passageway having a curvature convex relative to the main flow for utilizing the Coanda effect. A gas turbine may include the diffuser with an opening and a centerbody with an opening, each for providing a secondary flow of fluid into the diffuser. The gas turbine may direct fluid from an upstream turbine stage to the opening. A steam turbine may include the diffuser and may situate the opening downstream the diffuser inlet but upstream the location of boundary separation.
摘要翻译：扩散器包括沿着扩散壁的开口，用于防止或延迟主流的边界层分离。开口可以包括弯曲通道，其具有相对于主流的曲率凸起，以利用柯恩达效应。燃气轮机可以包括具有开口的扩散器和具有开口的中心体，每个用于提供流体到扩散器中的二次流。燃气轮机可以将流体从上游涡轮机级引导到开口。蒸汽轮机可以包括扩散器，并且可以将扩散器入口下游的开口定位在边界分离位置的上游。

4. 发明授权

US06655632B1 System and method for actively changing an effective flow-through area of an inlet region of an aircraft engine 有权
标题翻译：用于主动地改变飞机发动机入口区域的有效流通区域的系统和方法
公开(公告)号：US06655632B1
公开(公告)日：2003-12-02
申请号：US10064884
申请日：2002-08-27
申请人： Anurag Gupta , Paolo Graziosi , Ramani Mani
发明人： Anurag Gupta , Paolo Graziosi , Ramani Mani
IPC分类号： B64C2306
CPC分类号： F02C7/042 , B64C23/06 , B64D33/02 , B64D2033/0286 , F02C7/045 , F05D2220/323 , F05D2240/126 , F05D2240/14 , Y02T50/162 , Y02T50/672
摘要： An active effective flow-through area control system includes an upstream wall-flow perturber and a downstream wall-flow perturber situated in an inlet region of an aircraft engine. The downstream wall-flow perturber is positioned downstream from the upstream wall-flow perturber. The upstream and downstream wall-flow perturbers are configured to generate and trap at least one region of separated, vortical flow in the airflow through the inlet region. A method, for actively changing an effective flow-through area of an inlet region of an aircraft engine, includes creating at least one region of separated, vortical flow in an airflow passage defined by the inlet region. The method further includes trapping the region of separated, vortical flow in the airflow passage. The region of separated, vortical flow partially obstructs a main inlet airflow.
摘要翻译：主动的有效流通区域控制系统包括位于飞行器发动机的入口区域中的上游壁流扰流器和下游壁流式扰流器。下游壁流式扰流器位于上游壁流式扰流器的下游。上游和下游壁流扰流器被配置为产生并捕获通过入口区域的气流中分离的涡旋流的至少一个区域。用于主动地改变飞机发动机的入口区域的有效流通区域的方法包括在由入口区域限定的气流通道中产生分离的涡旋流的至少一个区域。该方法还包括将分离的涡旋流的区域截留在气流通道中。分离的涡旋流动区域部分阻碍主入口气流。

5. 发明申请

US20070089422A1 Multi-slot inter-turbine duct assembly for use in a turbine engine 失效
标题翻译：用于涡轮发动机的多槽涡轮机间导管组件
公开(公告)号：US20070089422A1
公开(公告)日：2007-04-26
申请号：US11258547
申请日：2005-10-25
申请人： James Widenhoefer , Paolo Graziosi , Kevin Kirtley
发明人： James Widenhoefer , Paolo Graziosi , Kevin Kirtley
IPC分类号： F02C7/00
CPC分类号： F01D5/145 , F02C9/18 , F05D2260/606 , Y02T50/673 , Y10S415/914
摘要： A bypass channel for use in an inter-turbine transition duct assembly of a turbine engine is connected to a suction port disposed upstream of a high-pressure turbine and at least two injection openings disposed downstream of the high-pressure turbine. The flow through the bypass channel is motivated by the natural pressure difference across the high-pressure turbine. The flow out of the at least two injection openings is used to energize the boundary layer flow downstream of the high-pressure turbine in order to allow for the use of a more aggressively expanded inter-turbine duct without boundary layer separation. Methods for optimizing the flow through the turbine engine are also disclosed.
摘要翻译：用于涡轮发动机的涡轮机间过渡管道组件中的旁通通道连接到设置在高压涡轮机上游的吸入口和设置在高压涡轮机下游的至少两个喷射开口。通过旁通通道的流动是由高压涡轮机两端的自然压差引起的。使用至少两个喷射开口的流动来激励高压涡轮机下游的边界层流，以便允许使用更积极地扩展的涡轮机间管道而没有边界层分离。还公开了优化通过涡轮发动机的流量的方法。

6. 发明授权

US07631483B2 Method and system for reduction of jet engine noise 有权
标题翻译：降低喷气发动机噪音的方法和系统
公开(公告)号：US07631483B2
公开(公告)日：2009-12-15
申请号：US10664695
申请日：2003-09-22
申请人： Ramani Mani , Paolo Graziosi
发明人： Ramani Mani , Paolo Graziosi
IPC分类号： F02K3/02
CPC分类号： F02K3/06 , B64D33/02 , B64D2033/0206 , B64D2033/0286 , F02C7/045 , F05D2250/51 , F05D2260/962
摘要： In an aspect, a method is provided for attenuating jet engine noise. Air velocity, adjacent to an inlet fan duct outer wall, is increased to a greater rate than typical velocity of an operational engine ambient inlet airflow, adjacent to the inlet fan duct outer wall. Boundary layer and associated turbulence is reduced or eliminated. Refraction and absorption of inlet sound into an acoustic liner is optimized. In an aspect, air velocity is increased by injecting air. In an aspect, air velocity is increased by exerting a suction force. In an aspect, a system is provided to attenuate jet engine noise. In an aspect, a fluid duct is provided opening to an inlet fan duct outer wall and to aft of a fan rotor.
摘要翻译：在一方面，提供了一种用于衰减喷气发动机噪声的方法。与入口风扇管道外壁相邻的空气速度增加到比与入口风扇管道外壁相邻的操作的发动机环境入口气流的典型速度更大的速率。边界层和相关的湍流减少或消除。将入口声音的折射和吸收优化到声衬里。在一方面，通过喷射空气来增加空气速度。在一方面，通过施加吸力来增加空气速度。在一方面，提供了一种用于衰减喷气发动机噪声的系统。一方面，流体管道设置成与入口风扇管道外壁和风扇转子的后部相通。

7. 发明申请

US20050060982A1 Method and system for reduction of jet engine noise 有权
标题翻译：降低喷气发动机噪音的方法和系统
公开(公告)号：US20050060982A1
公开(公告)日：2005-03-24
申请号：US10664695
申请日：2003-09-22
申请人： Ramani Mani , Paolo Graziosi
发明人： Ramani Mani , Paolo Graziosi
IPC分类号： B64D33/00 , B64D29/06 , F02C7/045 , F02K3/06 , F02K1/00 , F01N1/00
CPC分类号： F02K3/06 , B64D33/02 , B64D2033/0206 , B64D2033/0286 , F02C7/045 , F05D2250/51 , F05D2260/962
摘要： In an aspect, a method is provided for attenuating jet engine noise. Air velocity, adjacent to an inlet fan duct outer wall, is increased to a greater rate than typical velocity of an operational engine ambient inlet airflow, adjacent to the inlet fan duct outer wall. Boundary layer and associated turbulence is reduced or eliminated. Refraction and absorption of inlet sound into an acoustic liner is optimized. In an aspect, air velocity is increased by injecting air. In an aspect, air velocity is increased by exerting a suction force. In an aspect, a system is provided to attenuate jet engine noise. In an aspect, a fluid duct is provided opening to an inlet fan duct outer wall and to aft of a fan rotor.
摘要翻译：在一方面，提供了一种用于衰减喷气发动机噪声的方法。与入口风扇管道外壁相邻的空气速度增加到比与入口风扇管道外壁相邻的操作的发动机环境入口气流的典型速度更大的速率。边界层和相关的湍流减少或消除。将入口声音的折射和吸收优化到声衬里。在一方面，通过喷射空气来增加空气速度。在一方面，通过施加吸力来增加空气速度。在一方面，提供了一种用于衰减喷气发动机噪声的系统。一方面，流体管道设置成与入口风扇管道外壁和风扇转子的后部相通。

8. 发明授权

US07581692B2 Fluidic chevrons and configurable thermal shield for jet noise reduction 有权
标题翻译：流动人字形和可配置的热屏蔽，用于降低喷射噪音
公开(公告)号：US07581692B2
公开(公告)日：2009-09-01
申请号：US10610718
申请日：2003-06-30
申请人： Paolo Graziosi , Kevin Kirtley , Ramani Mani
发明人： Paolo Graziosi , Kevin Kirtley , Ramani Mani
IPC分类号： B64C1/40
CPC分类号： F02K1/48 , F02K1/34 , F02K1/44 , F02K1/827 , F05D2260/96
摘要： A system for jet engine noise control of a jet engine having a main jet stream exiting an exhaust nozzle and flowing along a jet axis includes a thermal acoustic shield directed at a non-zero angle relative to the jet axis. The thermal acoustic shield may be configurable about the main jet stream. The system may further include at least a fluidic chevron injected at a location relative to the nozzle exit for enhancing mixing in the main jet stream and creating a non-circular jet stream.
摘要翻译：用于具有离开排气喷嘴并沿喷流轴流动的主喷流的喷气发动机的喷气发动机噪声控制系统包括相对于喷射轴线以非零角度定向的热声屏蔽。热声屏蔽可以围绕主喷射流配置。该系统还可以包括至少一个在相对于喷嘴出口的位置处喷射的流体人字形，用于增强主喷射流中的混合并产生非圆形喷射流。

9. 发明申请

US20050279100A1 High area-ratio inter-turbine duct with inlet blowing 失效
标题翻译：具有入口吹风的高面积比的涡轮机间管道
公开(公告)号：US20050279100A1
公开(公告)日：2005-12-22
申请号：US10870884
申请日：2004-06-18
申请人： Paolo Graziosi , Kevin Kirtley
发明人： Paolo Graziosi , Kevin Kirtley
IPC分类号： F01D5/14 , F01D25/30 , F02C7/00
CPC分类号： F01D5/145 , F01D25/30 , Y02T50/673
摘要： A bypass channel for use in an inter-turbine transition duct of a gas turbine engine is connected to a suction port disposed upstream of a high-pressure turbine and an injection port disposed downstream of the high-pressure turbine. The flow through the bypass channel is motivated by the natural pressure difference across the high-pressure turbine. The flow out of the injection nozzle is used to energize the boundary layer flow downstream of the high-pressure turbine in order to allow for the use of a more aggressively expanded inter-turbine duct without boundary layer separation.
摘要翻译：用于燃气涡轮发动机的涡轮机间过渡管道的旁路通道连接到设置在高压涡轮机的上游的吸入口和设置在高压涡轮机下游的喷射口。通过旁通通道的流动是由高压涡轮机两端的自然压差引起的。喷射出口的流动用于激励高压涡轮机下游的边界层流，以便允许使用更积极扩张的涡轮机间管道，而不需要边界层分离。

10. 发明授权

US06851264B2 Self-aspirating high-area-ratio inter-turbine duct assembly for use in a gas turbine engine 失效
标题翻译：用于燃气涡轮发动机的自吸式高面积比的涡轮机间管道组件
公开(公告)号：US06851264B2
公开(公告)日：2005-02-08
申请号：US10279514
申请日：2002-10-24
申请人： Kevin Kirtley , Paolo Graziosi
发明人： Kevin Kirtley , Paolo Graziosi
IPC分类号： F01D9/02 , F01D5/14 , F01D9/04 , F01D9/06 , F01D17/10 , F01D25/30 , F02C9/18 , F02C1/00 , F02C3/04
CPC分类号： F01D5/145 , F01D9/041 , F01D9/06 , F01D17/105 , F01D25/305 , F02C9/18 , F05D2270/17 , Y02T50/671 , Y02T50/673 , Y10S415/914
摘要： In various embodiments, the present invention provides a means for improving gas turbine engine performance by applying fluid flow control to the inter-turbine duct joining a high-pressure turbine spool and an associated low-pressure turbine spool, allowing the low-pressure turbine spool to have a relatively larger diameter than the high-pressure turbine spool. One or more unobstructed fluid flow paths between one or more boundary layer suction ports disposed within the upstream end of the outer-body surface of the inter-turbine duct and the suction side of the associated low-pressure turbine nozzle are provided. Advantageously, the natural static pressure difference between these points results in a self-aspirating assembly. The fluid flow control provided by the respective suction and blowing forces generated allows for a relatively larger diameter low-pressure turbine spool and/or relatively fewer low-pressure turbine nozzles to be used than is possible with conventional systems, assemblies, and methods. Thus, a gas turbine engine weight savings and optimized performance may be achieved.
摘要翻译：在各种实施例中，本发明提供了一种用于通过对连接高压涡轮阀芯和相关联的低压涡轮阀芯的涡轮机间管道施加流体流量控制来改善燃气涡轮发动机性能的装置，允许低压涡轮阀芯具有比高压涡轮阀芯更大的直径。提供了一个或多个设置在涡轮机外管体的外体表面的上游端之间的一个或多个边界层吸入口和相关联的低压涡轮喷嘴的吸入侧之间的无障碍流体流动路径。有利地，这些点之间的天然静压差导致自吸组件。由所产生的相应的吸力和吹力产生的流体流动控制允许比常规系统，组件和方法可能使用相对较大直径的低压涡轮阀芯和/或相对较少的低压涡轮喷嘴。因此，可以实现燃气涡轮发动机的重量节省和优化的性能。

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