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1.发明授权
公开(公告)号：US5255513A
公开(公告)日：1993-10-26
申请号：US730152
申请日：1991-07-12
CPC分类号： F02K7/10 , Y02T50/671
摘要： A scramjet engine is disclosed which is effective for use in a hypersonic aircraft as an aircraft-integrated scramjet engine. The engine includes a first surface having an aft facing step, and a cowl upper surface spaced from the first surface to define an integrated inlet-combustor therebetween. A method of operating the engine includes injecting fuel into the inlet-combustor at the step for mixing fuel with supersonic airflow for generating supersonic combustion gases in the inlet-combustor. In the preferred embodiment of the invention, the fuel is injected to create a fluid boundary defining a subsonic fuel zone and a supersonic fluid zone. The fluid boundary is variable and eliminates start and unstart problems requiring variable inlet geometry in a conventional scramjet engine.
摘要翻译： 公开了一种有效用于超音速飞机作为飞行器集成的冲击式发动机的冲击式发动机。 发动机包括具有向后的台阶的第一表面和与第一表面间隔开的整流罩上表面，以在它们之间限定一体的入口 - 燃烧器。 一种操作发动机的方法包括将燃料与用于在入口 - 燃烧器中产生超音速燃烧气体的超音速气流混合的步骤将燃料喷入入口 - 燃烧器。 在本发明的优选实施例中，喷射燃料以产生限定亚音速燃料区域和超音速流体区域的流体边界。 流体边界是可变的，并且消除了在常规冲击式喷气发动机中需要可变入口几何形状的起动和不起动问题。
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公开(公告)号：US5085048A
公开(公告)日：1992-02-04
申请号：US486640
申请日：1990-02-28
CPC分类号： F02K7/10 , Y02T50/671
摘要： A scramjet engine is disclosed which is effective for use in a hypersonic aircraft as an aircraft-integrated scamjet engine. The engine includes a first surface having an aft facing step, and a cowl upper surface spaced from the first surface to define an integrated inlet-combustor therebetween. Means for injecting fuel into the inlet-combustor at the step are provided for mixing fuel with supersonic airflow for generating supersonic combustion gases in the inlet-combustor. In the preferred embodiment of the invention, the fuel injecting means is effective for injecting fuel to create a fluid boundary defining a subsonic fuel zone and a supersonic fluid zone. The fluid boundary is variable and eliminates start and unstart problems requiring variable inlet geometry in a conventional scramjet engine.
摘要翻译： 公开了一种有效用于超音速飞机作为飞行器集成的scamjet发动机的冲击式发动机。 发动机包括具有后向后台阶的第一表面和与第一表面间隔开的整流罩上表面，以在它们之间限定一体的入口 - 燃烧器。 提供了在步骤中将燃料喷入入口 - 燃烧器的装置，用于将燃料与用于在入口 - 燃烧器中产生超音速燃烧气体的超音速气流混合。 在本发明的优选实施例中，燃料喷射装置有效地喷射燃料以产生限定亚音速燃料区和超音速流体区的流体边界。 流体边界是可变的，并且消除了在常规冲击式喷气发动机中需要可变入口几何形状的起动和不起动问题。
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公开(公告)号：US5397077A
公开(公告)日：1995-03-14
申请号：US205967
申请日：1994-03-03
IPC分类号： B64D33/02
CPC分类号： B64D33/02 , B64D2033/026 , Y10T137/0536
摘要： An inlet bleed system for a supersonic aircraft engine having a longitudinally downstream extending inlet bounded by a boundary wall that in part defines a supersonic flowpath through the inlet, a transversely extending boundary layer scoop extends into a boundary layer region of the flowpath and has an upstream facing bleed aperture, and a shock generating means for generating a shockwave in a supersonic flow in the flowpath such that the shockwave passes through the bleed aperture. One embodiment provides a scoop which extends a height above the wall such that it is operable to scoop off no more than a sufficient amount of a boundary layer flow that would exist in the boundary region and be momentum deficient relative to predetermined conditions that would exist downstream of the scoop under supersonic operating conditions. Another embodiment provides for the scoop to be disposed a throat section of the inlet wherein the aperture located is just upstream of the normal shock location.
摘要翻译： 一种用于超音速飞行器发动机的入口泄放系统，其具有由边界壁限定的纵向下游延伸的入口，其部分地限定通过入口的超音速流动路径，横向延伸的边界层勺延伸到流动路径的边界层区域中，并且具有上游 以及用于在流路中以超音速流动产生冲击波的冲击产生装置，使得冲击波穿过排放孔。 一个实施例提供了一种在壁上方延伸高度的勺子，使得其可操作地铲除不超过足够量的边界层中存在的边界层流动并且相对于将存在于下游的预定条件而动量不足 的勺子在超音速操作条件下。 另一个实施例提供了将勺放置在入口的喉部，其中所述孔位于恰好正常冲击位置的上游。
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4.发明授权Scramjet combustor having a two-part, aft-facing step with primary and secondary fuel injector discharge orifices 失效Scramjet燃烧器具有具有初级和次级燃料喷射器排出孔的两部分的向后的步骤
公开(公告)号：US5546745A
公开(公告)日：1996-08-20
申请号：US266069
申请日：1994-06-27
CPC分类号： F02K7/14
摘要： A flight vehicle scramjet combustor is provided having two spaced-apart, generally opposing, and generally longitudinally extending walls extending forward and aft. One of the walls includes a generally aft-facing step, a forward wall portion extending generally longitudinally forward of the step, and an aft wall portion extending generally longitudinally aft of the step. The step further includes a first section and an interconnected second section, where in the first section is attached to the forward wall portion and the second section is attached to the aft wall portion. The second section includes a main or primary fuel injector discharge orifice and a plurality of secondary fuel injector discharge orifices positioned adjacent thereto, the primary and secondary fuel injector discharge orifices each having a fuel discharge axis aligned generally perpendicular to the second section which projects both generally toward the other of the walls and longitudinally aft.
摘要翻译： 提供了一种飞行车辆冲击式喷气燃烧器，其具有向前和向后延伸的两个间隔开的，大致相对的并且大致纵向延伸的壁。 其中一个壁包括大体上朝后的台阶，大体上纵向前延伸的前壁部分以及大致纵向后延伸的后壁部分。 该步骤还包括第一部分和互连的第二部分，其中第一部分附接到前壁部分，第二部分附接到后壁部分。 第二部分包括主燃料喷射器排出孔和与其相邻设置的多个次燃料喷射器排放孔，主燃料喷射器和辅助燃料喷射器排出孔各自具有大致垂直于第二部分排列的燃料排出轴， 朝向另一个墙壁并纵向后方。
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公开(公告)号：US5082206A
公开(公告)日：1992-01-21
申请号：US223826
申请日：1988-07-25
CPC分类号： F02C7/04 , B64C30/00 , B64D33/02 , B64D2033/026
摘要： A hypersonic inlet and a hypersonic engine and flight vehicle having such an inlet. The three-dimensionally-swept inlet has an upper member with a caret-shaped lower surface portion producing a two-dimensional wedge flow below such lower surface portion. The inlet also has a lower member having two inverted and transposed semi-caret-shaped upper surface portions producing a two-dimensional wedge flow above such upper surface portions. An inlet aft portion connects together the upper and lower members and has an orifice defining the engine inlet throat which at least partially receives the two-dimensional flows.
摘要翻译： 超音速进气口和超音速发动机和具有这种入口的飞行器。 三维扫描入口具有上部构件，其具有插入符号下表面部分，在该下表面部分下方产生二维楔形流。 入口还具有下部构件，其具有两个倒置和转置的半插入形状的上表面部分，在上表面部分上方产生二维楔形流。 入口后部将上部构件和下部构件连接在一起，并且具有限定发动机入口喉部的孔，其至少部分地接收二维流。
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公开(公告)号：US5349815A
公开(公告)日：1994-09-27
申请号：US750343
申请日：1991-08-27
CPC分类号： F02K7/10
摘要： A flight vehicle scramjet combustor. The combustor, in its "2-D" and annular embodiments, has two spaced-apart, generally opposing, and longitudinally extending walls. One wall includes a generally aft-facing step having a first section and an interconnected second section, a forward wall portion attached to the first section, and an aft wall portion attached to the second section. The second section includes a fuel injector discharge orifice having a fuel discharge axis which is aligned generally perpendicular to the second section and which projects both generally towards the other wall and longitudinally aft. The combustor has a cylindrical embodiment which includes a cylindrical wall having a step and fuel injector discharge orifice similar those of the "2-D" and annular combustor embodiments.
摘要翻译： 一个飞行器的喷气式燃烧器。 燃烧器在其“2-D”和环形实施例中具有两个间隔开的，大致相对的和纵向延伸的壁。 一个壁包括具有第一部分和相互连接的第二部分的总体后向的台阶，附接到第一部分的前壁部分和附接到第二部分的后壁部分。 第二部分包括具有燃料排放轴线的燃料喷射器排出孔，燃料排放轴线大致垂直于第二部分排列，并且大致朝向另一壁并纵向后方突出。 燃烧器具有圆柱形实施例，其包括具有类似于“2-D”和环形燃烧器实施例的台阶和燃料喷射器排出孔的圆柱形壁。
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公开(公告)号：US5301901A
公开(公告)日：1994-04-12
申请号：US10963
申请日：1993-01-29
CPC分类号： F02C7/042 , B64D33/02 , B64D2033/026 , F05D2220/80 , Y10T137/0536
摘要： An aircraft engine two-dimensional inlet system of the present invention provides a telescoping two-dimensional centerbody that is referred to as a wedge. The telescoping wedge may be of a fixed wedge angle design or a variable wedge angle design. The present invention contemplates single and multi-wedge angle designs of the fixed or variable intermediate wedge angle types having more than one ramp angle. The telescoping wedge has at least one upper and lower pair of longitudinally adjacent wedge forward and aft walls that overlap to form an aft facing step and are in controlled sliding engagement.
摘要翻译： 本发明的飞机发动机二维入口系统提供了称为楔形物的伸缩二维中心体。 伸缩楔可以是固定的楔角设计或可变的楔角设计。 本发明考虑了具有多于一个斜坡角的固定或可变中间楔角类型的单楔形和多楔形角度设计。 伸缩楔具有至少一个上下一对纵向相邻的楔形前后壁重叠以形成向后的台阶并处于受控的滑动接合。
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公开(公告)号：US5280705A
公开(公告)日：1994-01-25
申请号：US902260
申请日：1992-06-22
摘要： To promote fuel and air mixing combustor of a scramjet engine, fuel is injected as a succession of pulses into the airstream flowing through the combustor. By controlling the duty cycle and flow rate of the fuel pulses, increased fuel penetration and mixing efficiency are obtained with an overall fuel flow schedule comparable to steady state fuel injection. With sequential pulsed operation of plural, variously located fuel injectors in phased relation, the combustor remains in a transient state to enhance mixing and to spread out the combustor heat load.
摘要翻译： 为了促进冲击式发动机的燃料和空气混合燃烧器，将燃料作为一连串的脉冲喷射到流过燃烧器的气流中。 通过控制燃料脉冲的占空比和流量，可以获得与稳态燃料喷射相当的总体燃料流程图，从而提高燃料渗透和混合效率。 通过多个相继的脉冲操作，各种定位的燃料喷射器处于相位关系，燃烧器保持在过渡状态，以增强混合并扩展燃烧器的热负荷。
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