公开(公告)号：US6082635A

公开(公告)日：2000-07-04

申请号：US848851

申请日：1997-05-02

Applicant: John M. Seiner ,  Mikhail M. Gilinsky

Inventor： John M. Seiner ,  Mikhail M. Gilinsky

IPC: B64D33/04 ,  F02K1/46 ,  F02K1/48 ,  B63H11/10

CPC classification number: F02K1/46 ,  B64D33/06 ,  F02K1/48 ,  F05D2250/611

Abstract: A nozzle having an undulating surface for enhancing the mixing of a primary flow with a secondary flow or ambient air, without requiring an ejector. The nozzle includes a nozzle structure and design for introducing counter-rotating vorticity into the primary flow either through (i) internal surface corrugations where an axisymmetric line through each corrugation is coincident with an axisymmetric line through the center of the flow passageway or (ii) through one or more sets of alternating convexities and cavities in the internal surface of the nozzle where an axisymmetric line through each convexity and cavity is coincident with an axisymmetric line through the center of the flow passageway, and where the convexities contract from the entrance end towards the exit end. Exit area mixing is also enhanced by one or more chevrons attached to the exit edge of the nozzle. The nozzle is ideally suited for application as a jet engine nozzle. When used as a jet engine nozzle, noise suppression with simultaneous thrust augmentation/minimal thrust loss is achieved.

Abstract translation: 喷嘴具有起伏的表面，用于增强主流与二次流或环境空气的混合，而不需要喷射器。 喷嘴包括喷嘴结构和用于通过（i）内表面波纹将反向旋转涡度引入主旋流的设计，其中通过每个波纹的轴对称线与通过流动通道的中心的轴对称线重合，或（ii） 通过喷嘴内表面中的一组或多组交替的凸起和空腔，其中通过每个凸起和空腔的轴对称线与通过流动通道的中心的轴对称线重合，并且凸起从入口端朝向 出口端 出口区域混合也通过一个或多个附着在喷嘴出口边缘的人字形增强。 该喷嘴非常适合用作喷气式发动机喷嘴。 当用作喷气发动机喷嘴时，实现了具有同时推力增加/最小推力损失的噪声抑制。

公开(公告)号：US07475550B2

公开(公告)日：2009-01-13

申请号：US11769539

申请日：2007-06-27

Applicant: John M. Seiner

Inventor： John M. Seiner

IPC: F02C1/00

CPC classification number: F02C7/24 ,  F02K1/12 ,  F02K1/1223 ,  F02K1/1269 ,  F02K1/48 ,  F02K1/805 ,  F02K1/822 ,  F02K1/827 ,  F05D2250/13 ,  F05D2250/14 ,  F05D2250/23 ,  F05D2250/324 ,  F05D2250/61 ,  F05D2250/611 ,  F05D2260/96 ,  Y02T50/671 ,  Y02T50/675

Abstract: A method and device to reduce the noise produced by jet aircraft engines and/or other supersonic nozzles involves the use of corrugated engine seals (30) for the secondary internal divergent flaps (14) of the nozzle (10). Such corrugated seals (30) serve not only to eliminate shock-generated noise, but also generate a counter-rotating vorticity to force low speed mixing of surrounding ambient air with the high-speed jet exhaust. Lower exhaust velocities, combined with reduced levels of the turbulent Reynolds shear stress, lead to reduction of turbulence-generated noise, including Mach wave emission.

Abstract translation: 用于减少由喷气式飞行器发动机和/或其它超音速喷嘴产生的噪声的方法和装置涉及使用用于喷嘴（10）的次级内部发散翼片（14）的波纹发动机密封件（30）。 这种波纹密封件（30）不仅用于消除冲击产生的噪声，而且还产生反向旋转的涡流，以迫使周围环境空气与高速喷射式排气的低速混合。 较低的排气速度，结合湍流雷诺剪切应力水平的降低，导致湍流产生的噪声减少，包括马赫波发射。

公开(公告)号：US5924632A

公开(公告)日：1999-07-20

申请号：US850572

申请日：1997-05-02

Applicant: John M. Seiner ,  Mikhail M. Gilinsky

Inventor： John M. Seiner ,  Mikhail M. Gilinsky

IPC: B64D33/04 ,  F02K1/46 ,  F02K1/48 ,  B64C1/38

CPC classification number: F02K1/48 ,  B64D33/06 ,  F02K1/46 ,  F05D2250/611

Abstract: A nozzle arrangement includes a nozzle and a centerbody. The longitudinal axis of the centerbody is coaxially aligned with the nozzle. The centerbody has a free end portion shaped to create vortices in exhaust exiting the exit area. The vortices enhance mixing action in the exhaust and reduce exhaust noise while augmenting thrust.

Abstract translation: 喷嘴装置包括喷嘴和中心体。 中心体的纵向轴线与喷嘴同轴对准。 中心体具有形状的自由端部，以在离开出口区域的排气口中产生涡流。 涡流增强排气中的混合动作，并减少排气噪声，同时增加推力。

公开(公告)号：US07240493B2

公开(公告)日：2007-07-10

申请号：US10999449

申请日：2004-11-30

Applicant: John M. Seiner

Inventor： John M. Seiner

IPC: F02K1/34

CPC classification number: F02C7/24 ,  F02K1/12 ,  F02K1/1223 ,  F02K1/1269 ,  F02K1/48 ,  F02K1/805 ,  F02K1/822 ,  F02K1/827 ,  F05D2250/13 ,  F05D2250/14 ,  F05D2250/23 ,  F05D2250/324 ,  F05D2250/61 ,  F05D2250/611 ,  F05D2260/96 ,  Y02T50/671 ,  Y02T50/675

Abstract: A method and device to reduce the noise produced by jet aircraft engines and/or other supersonic nozzles involves the use of corrugated engine seals (30) for the secondary internal divergent flaps (14) of the nozzle (10). Such corrugated seals (30) serve not only to eliminate shock-generated noise, but also generate a counter-rotating vorticity to force low speed mixing of surrounding ambient air with the high-speed jet exhaust. Lower exhaust velocities, combined with reduced levels of the turbulent Reynolds shear stress, lead to reduction of turbulence-generated noise, including Mach wave emission.

Abstract translation: 用于减少由喷气式飞行器发动机和/或其它超音速喷嘴产生的噪声的方法和装置涉及使用用于喷嘴（10）的次级内部发散翼片（14）的波纹发动机密封件（30）。 这种波纹密封件（30）不仅用于消除冲击产生的噪声，而且还产生反向旋转的涡流，以迫使周围环境空气与高速喷射式排气的低速混合。 较低的排气速度，结合湍流雷诺剪切应力水平的降低，导致湍流产生的噪声减少，包括马赫波发射。

公开(公告)号：US5579999A

公开(公告)日：1996-12-03

申请号：US408333

申请日：1995-03-22

Applicant: John M. Seiner ,  Roy S. Baty

Inventor： John M. Seiner ,  Roy S. Baty

IPC: F02K1/00 ,  F02K1/40 ,  B63H11/00

CPC classification number: F02K1/00 ,  F02K1/40 ,  F05D2250/14

Abstract: A method of forming a shock-free supersonic elliptic nozzle, in which the nozzle to be designed is divided into three sections, a circular-to-elliptic section which begins at a circular nozzle inlet, an elliptic subsonic section downstream from the circular-to-elliptic section and a supersonic section downstream from the elliptic subsonic section. The maximum and minimum radii for each axial point in the circular-to-elliptic section and the elliptic subsonic section are then separately determined, the maximum and minimum radii being the radii for the widest part of an elliptic cross-section and the narrowest part of the elliptic cross-section, respectively. The maximum and minimum radii for each axial point in the supersonic section are determined based on the Method of Characteristics, Then, each of the three sections are based on the maximum and minimum radii for each axial point in the section. The resulting nozzle is acoustically superior.

Abstract translation: 一种形成无冲击超音速椭圆形喷嘴的方法，其中待设计的喷嘴分为三个部分，圆形至椭圆形部分，其从圆形喷嘴入口开始，椭圆形亚音速部分从圆形到 椭圆形部分和椭圆形亚音速部分下游的超音速部分。 然后分别确定圆形到椭圆形截面和椭圆形亚音速部分中每个轴向点的最大和最小半径，最大和最小半径是椭圆截面最宽部分的半径，最小半径 椭圆截面。 基于特征方法确定超声部分中每个轴向点的最大和最小半径，然后，三个部分中的每一个基于该部分中每个轴向点的最大和最小半径。 所得到的喷嘴在声学上是优越的。