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1. 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。

2. 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。

3. 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。

4. 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。

5. 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。

6. 发明授权

US3937590A Acoustic duct with peripherally segmented acoustic treatment 失效
标题翻译：具有外围SEGMENTED ACOUSTIC TREATMENT的耳塞
公开(公告)号：US3937590A
公开(公告)日：1976-02-10
申请号：US503031
申请日：1974-09-03
申请人： Ramani Mani
发明人： Ramani Mani
IPC分类号： F01N1/06 , F01N1/24 , F02C7/045 , G10K11/16 , F04D29/66
CPC分类号： F02C7/045 , Y02T50/671 , Y10T137/0536
摘要： An acoustic duct such as a jet engine fan duct is lined with numerous peripherally spaced, longitudinally extending strips of sound-absorbing material which are effective to scatter spinning mode acoustic pressure fields to higher order, attenuating modes for improved noise suppression. These strips can be alternated with other strips having a different acoustical impedance, or combined with a longitudinally segmented treatment.

7. 发明授权

US4449358A Method and apparatus for promoting a surge condition in a gas turbine 失效
标题翻译：用于促进燃气轮机中的喘振状况的方法和装置
公开(公告)号：US4449358A
公开(公告)日：1984-05-22
申请号：US286431
申请日：1981-07-24
申请人： Ramani Mani
发明人： Ramani Mani
IPC分类号： F02C9/28 , F02C9/00 , F04D27/02
CPC分类号： F02C9/00 , F04D27/02
摘要： A surge condition in a stalled gas turbine engine is promoted by modulating a time-varying component of an operating parameter of the gas turbine engine, such as the fuel flow to the combustor plenum of the engine, substantially in phase with a time-varying component of the pressure in the combustor plenum, thereby allowing normal operation of the engine to resume during the surge condition by eliminating the stall-inducing agent.
摘要翻译：通过调节燃气涡轮发动机的运行参数的时变分量，例如到发动机的燃烧室增压室的燃料流量，与时变分量基本上同相，来促进停滞的燃气涡轮发动机中的喘振状况的燃烧室增压室中的压力，从而通过消除失速诱导剂，允许发动机在喘振状态期间恢复正常运行。

8. 发明授权

US06618693B2 Method and apparatus for non-intrusive monitoring of rotating components 有权
公开(公告)号：US06618693B2
公开(公告)日：2003-09-09
申请号：US09863020
申请日：2001-05-23
申请人： Philip Lynn Andrew , Ramani Mani , Hyoun-Woo Shin
发明人： Philip Lynn Andrew , Ramani Mani , Hyoun-Woo Shin
IPC分类号： G06F1500
CPC分类号： F01D21/003 , F04D27/001 , F05D2270/1024 , F05D2270/114 , F05D2270/301 , Y02T50/67
摘要： A non-intrusive method of monitoring the integrity of a rotating member comprising mounting at least one sensor in a stationary frame of reference in a casing over the rotating member, measuring the pressure field of the rotating member, comparing the measured pressure field with a corresponding reference pressure field, identifying variations in the measured pressure field, the variations indicative of a fault in the rotating member, and generating an output indicative of an identified fault.

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