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公开(公告)号：USH1008H
公开(公告)日：1992-01-07
申请号：US737763
申请日：1985-05-28
摘要： In a combustor in which a flow area for fuel and air increases suddenly at dump so as to generate vortices which mix the fuel and air for combustion downstream of the dump, the improvement in which the flow cross section upstream of the dump is noncircular, as triangular or rectangular, causing flow downstream of the dump to be noncoherent so that mixing by the vortices is aperiodic with the result that heat release on mixing is uniform in time and does not drive oscillations in the combustor.
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2.发明授权
公开(公告)号：US5149908A
公开(公告)日：1992-09-22
申请号：US751362
申请日：1991-08-19
IPC分类号： F41A1/04
CPC分类号： F41A1/04
摘要： A regenerative liquid propellant gun and pertains includes a modified contional fixed bolt extending into a conventional combustion chamber of the regenerative liquid propellant gun. The modified fixed bolt of this invention provides for improved operation of the otherwise conventional regenerative liquid propellant gun and has modified end portion embodiments and internal propellant injection passages, all for the purpose of creating turbulent propellant flow.
摘要翻译： 再生式液体推进剂枪包括延伸到再生液体推进剂枪的常规燃烧室中的改进的常规固定螺栓。 本发明的改进的固定螺栓提供了改进的常规再生液体推进剂枪的操作，并且具有改进的端部实施例和内部推进剂注射通道，所有这些都是为了产生湍流推进剂流。
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公开(公告)号：USH1007H
公开(公告)日：1992-01-07
申请号：US737648
申请日：1985-05-24
摘要： In a solid fuel ramjet in which a fluid flow boundary layer extends along aurning fuel grain and receives combustible material liberated from the grain, exciting oscillations in air flowing toward the grain so that oscillations continue in the boundary layer and promote vortices in the layer to mix the air and the combustible material.
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4.发明授权
公开(公告)号：US5361710A
公开(公告)日：1994-11-08
申请号：US138044
申请日：1993-10-07
申请人： Ephraim Gutmark , Klaus C. Schadow , Timothy P. Parr , Donna M. Hanson-Parr , Kenneth J. Wilson , Robert A. Smith , Richard A. Stalnaker
发明人： Ephraim Gutmark , Klaus C. Schadow , Timothy P. Parr , Donna M. Hanson-Parr , Kenneth J. Wilson , Robert A. Smith , Richard A. Stalnaker
CPC分类号： F23C15/00 , F23G5/50 , F23N5/003 , F23N1/02 , F23N2041/18 , Y02T50/677
摘要： An improved method and apparatus for actively controlling a combustion process such as a waste incinerator by means of a spatial and temporal synchronized injection of fuel. The improved method and apparatus employs an active control system which controls the intentional formation of large scale, coherent vortices and the synchronized injection of the fuel supply at various locations relative to the formation of the vortices. The preferred apparatus comprises an actuator or similar structure that is adapted for producing and stabilizing discrete, large scale vortices in a combustion device. In addition, another device controls or modulates the injection of the fuel into the vortices at the optimal location and timing relative to the vortex cycle. As applied to an incinerator, this method can be optimized to ensures that the fuel and waste are introduced into the highest temperature locations, were extended residence times are obtained by trapping the fuel and waste inside the vortices. A high combustion efficiency may also be achieved by actively synchronizing the periodic fuel injection with the formation of the vortices.
摘要翻译： 一种用于通过空间和时间同步喷射燃料主动地控制诸如废物焚化炉的燃烧过程的改进的方法和装置。 改进的方法和装置采用主动控制系统，其控制有意形成大规模相干涡流，并且相对于形成涡流在不同位置同步喷射燃料供应。 优选的装置包括适于在燃烧装置中产生和稳定离散的大尺度涡流的致动器或类似结构。 此外，另一设备在相对于涡流循环的最佳位置和定时处控制或调节燃料喷射到涡流中。 适用于焚烧炉的方法可以优化，以确保将燃料和废物引入最高温度的位置，通过在涡流内捕获燃料和废物获得延长的停留时间。 还可以通过主动地使周期性燃料喷射与涡流的形成同步来实现高燃烧效率。
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公开(公告)号：US5340054A
公开(公告)日：1994-08-23
申请号：US839721
申请日：1992-02-14
CPC分类号： B64C23/06 , Y02T50/162
摘要： The oscillations found to occur in the cavities of an structural frame moving through a fluid are substantially eliminated by the adoption of perturbation elements located at the leading edge of the cavity and reflecting any remaining oscillations out of the cavity at the trailing edge. The perturbation elements may take the form of multiple pins of various shape and geometrical arrangement which prevents the generation and growth of vortices causing acoustic oscillations. The reflection of remaining oscillations out of the cavity may be accomplished by ramping the trailing edge of the cavity.
摘要翻译： 发现发生在移动通过流体的结构框架的空腔中的振荡通过采用位于空腔的前缘处的扰动元件基本上消除，并将任何剩余的振荡反射出在后缘处的空腔。 扰动元件可以采取各种形状和几何布置的多个销的形式，其防止引起声振荡的涡流的产生和生长。 剩余振荡反射出空腔可以通过使空腔的后缘倾斜来实现。
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公开(公告)号：US4957242A
公开(公告)日：1990-09-18
申请号：US180751
申请日：1988-04-12
CPC分类号： B01F5/0256 , B05B7/02 , B01F2005/0017
摘要： The invention is directed to a fluid mixing device in which a jet of firstluid is passed through a nozzle having a conical inlet section and a noncircular, elongated, exit section. The jet of first fluid mixes with a second fluid located downstream of the device. In operation, the intersection of the conical and elongated sections produces axial rotation in the first fluid. Intense, three-dimensional, axial and circumferential vortical structures are created. These structures then interact with the high modes of azimuthal instabilities that are common to the elongated configuration. The jet of first fluid evolves into two secondary jets, generating a double shear layer inside the flow. Highly efficient mixing of the fluids, in both the outside and inside (core) segments of the jet, is achieved within a relatively small mixing space.
摘要翻译： 本发明涉及一种流体混合装置，其中第一流体的射流通过具有锥形入口部分和非圆形，细长的出口部分的喷嘴。 第一流体的射流与位于装置下游的第二流体混合。 在操作中，锥形细长部分的交点在第一流体中产生轴向旋转。 创建了强烈的三维，轴向和圆周涡旋结构。 这些结构然后与细长配置共同的方位不稳定性的高模式相互作用。 第一流体的射流发展成两个二次射流，在流动内部产生双剪切层。 在相对较小的混合空间内实现流体在喷射器的外部和内部（核心）段中的高效混合。
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公开(公告)号：US06601393B2
公开(公告)日：2003-08-05
申请号：US10308985
申请日：2002-12-03
IPC分类号： F02C500
CPC分类号： F23R3/00 , F02C5/00 , F02C9/28 , F05D2220/10 , F05D2260/96 , F23K2900/05003 , F23M20/005 , F23N1/002 , F23N5/16 , F23N2041/20 , F23R2900/00013 , F23R2900/00014 , F23R2900/03281 , Y02T50/677
摘要： This invention relates to air breathing engines, such as ramjets, scramjets and internal combustion, and more particularly to an active combustion control device for a combustor. In more particularity, the present invention relates to a method and apparatus that applies active combustion control technology to advanced propulsion devices and closed-loop fuel injection at sub-harmonic frequencies of the instability frequency of the combustor. The problem of limited actuator frequency response is addressed by injecting fuel pulses at sub-harmonic frequencies of the instability. The fuel may be liquid, solid or gas. To achieve this desired result, a closed loop controller is designed to determine sub-harmonic frequencies using a divider to divide the instability frequency of a combustor, yielding a fraction of the harmonic frequency. Also, this invention also combines open loop injection control with closed loop injection control to obtain enhanced engine performance, which includes extension of the stable combustion zone.
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公开(公告)号：US6101957A
公开(公告)日：2000-08-15
申请号：US330210
申请日：1999-06-11
CPC分类号： F02K9/96 , F02K9/24 , F02K9/38 , F02K9/97 , F23G7/003 , F42B33/067 , F23G2209/16 , Y10S239/07
摘要： An apparatus for the disposal of solid rocket motors which produce exhaustases containing flammable and/or explosive products. The solid rocket motor to be burned is first detachably connected to and inserted in one end of an elongated mixing chamber which has, at an opposite end, a multi-step expansion nozzle. The rocket motor is then ignited and the exhaust gas is passed into the mixing chamber, which is sufficiently large to reduce the velocity of exhaust gases from supersonic to subsonic. Air is injected into the mixing chamber to react with flammable and/or explosive products in the exhaust gases and the resultant mixture is then discharged from the mixing chamber through a multi-step expansion nozzle to expand the gaseous mixture and, at the same time, produce substantial turbulence within the gas mixture which is about six times higher than the turbulence levels produced by a constant area circular nozzle. The expansion nozzle has an inner wall with a stair-step shaped surface, having an aspect ratio of not less than 2 and not greater than 10, to create the increased turbulence levels within the multistep nozzle.
摘要翻译： 一种用于处置固体火箭发动机的装置，其产生含有易燃和/或爆炸产物的废气。 待燃烧的固体火箭发动机首先可拆卸地连接到并插入细长混合室的一端，在另一端具有多级膨胀喷嘴。 然后点火火箭发动机，排气进入混合室，该混合室足够大，以减少从超音速到亚音速的废气速度。 将空气注入到混合室中以与废气中的易燃和/或爆炸产物反应，然后通过多步膨胀喷嘴将所得混合物从混合室排出以膨胀气态混合物，同时， 在气体混合物中产生大大湍流，其比由恒定区域圆形喷嘴产生的湍流水平高大约六倍。 膨胀喷嘴具有具有梯级形状的表面的内壁，其具有不小于2且不大于10的纵横比，以在多步骤喷嘴内产生增加的湍流水平。
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公开(公告)号：US6065688A
公开(公告)日：2000-05-23
申请号：US332013
申请日：1999-06-14
CPC分类号： F23D14/48 , F16K31/004 , F23C2205/00
摘要： The present invention relates to an electric valve capable of producing podic mass-flow modulation of a gaseous, liquid, or mixed-phase medium over wide ranges of frequencies, pressure, and flow rates. Such mass-flow modulation can be used to periodically shed large-scale vortices at the outlet and to manipulate their dynamics allowing the user to actively control fluid mixing and transport further downstream. The device has a piezoelectric wafer that in a relaxed state abuts the upstream end of the outlet tube separating the pressurized fluid in the plenum with the outlet. The device has an apparatus for applying electric field to the wafer, which distorts the wafer and ruptures the seal forming a throat area that controls the fluid mass flux. Due to the fast response of the piezoelectric material to an electric field, the throat area can be modulated rapidly in time making the device operable even at high frequencies. The present invention is particularly useful for actively controlling fuel-air mixing in a combustor. However, it may be utilized in other applications such as in medical drug administration for inhalation therapy.
摘要翻译： 本发明涉及一种能够在宽范围的频率，压力和流速下对气态，液体或混合相介质进行周期性质量流量调制的电动阀。 这种质量流量调制可用于周期性地在出口处流出大尺度的涡流并操纵其动力学，从而允许使用者主动地控制下游的流体混合和输送。 该装置具有处于松弛状态的压电晶片，该压电晶片与出口管的上游端相邻，以将出气口中的加压流体分开。 该装置具有向晶片施加电场的装置，其使晶片扭曲并破裂形成控制流体质量通量的喉部区域的密封。 由于压电材料对电场的快速响应，喉部区域可以在时间上快速调制，使得器件即使在高频也可操作。 本发明对于主动地控制燃烧器中的燃料 - 空气混合特别有用。 然而，它可以用于其它应用，例如用于吸入治疗的药物治疗。
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公开(公告)号：US06640549B1
公开(公告)日：2003-11-04
申请号：US10421186
申请日：2003-04-24
IPC分类号： F02C500
CPC分类号： F02C5/00 , F02K7/02 , F05D2260/96 , F23M20/005 , F23R2900/00013 , F23R2900/03281
摘要： This invention relates to air breathing engines, such as ramjets, scramjets and internal combustion, and more particularly to an active combustion control device for a combustor. In more particularity, the present invention relates to a method and apparatus that applies active combustion control technology to advanced propulsion devices and closed-loop fuel injection at sub-harmonic frequencies of the instability frequency of the combustor. The problem of limited actuator frequency response is addressed by injecting fuel pulses at sub-harmonic frequencies of the instability. The fuel may be liquid, solid or gas. To achieve this desired result, a closed loop controller is designed to determine sub-harmonic frequencies using a divider to divide the instability frequency of a combustor, yielding a fraction of the harmonic frequency. Also, this invention also combines open loop injection control with closed loop injection control to obtain enhanced engine performance, which includes extension of the stable combustion zone.
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