公开(公告)号：US06598385B1

公开(公告)日：2003-07-29

申请号：US09195792

申请日：1998-11-19

申请人： Stephen G. Abel ,  Donald J. Christensen

发明人： Stephen G. Abel ,  Donald J. Christensen

IPC分类号： F02K952

CPC分类号： B64G1/26 ,  B64G1/402 ,  F02K9/805 ,  F16K31/42

摘要： A multi-stage pilot valve is disclosed for selectively supplying a working fluid to and venting from a reaction jet main stage actuation chamber. In a preferred embodiment of the invention, the pilot valve comprises a solenoid actuated ball and socket flapper valve having a pressure inlet, an exhaust outlet and a service port. The first stage service port is in fluid communication with a second stage actuation chamber. A piston disposed in the second stage actuation chamber operatively engages a ball member of a ball-and-seat type valve comprising the second stage valve. The second stage valve also comprises a pressure inlet, an exhaust outlet and a service port. The piston and ball are sized relative to each other such that when the second stage actuation chamber is pressurized by the first stage, the force is sufficient to seat the ball against the second stage pressure inlet. This shuts off the flow of high pressure gases to the second stage service port and permits the second stage service port to vent through the exhaust port. When the second stage actuation chamber is vented by the first stage valve, the pressure acting on the ball is sufficient to seat the ball against the second stage exhaust outlet. This opens the second stage pressure inlet to permit high pressure gases to enter the second stage service port. The bi-directional movement of the ball member of the second stage valve is accomplished entirely by fluid pressure, thus enabling a fast responding, high flow rate regulation of the hot gases using low electrical power and eliminating the use of springs or other resilient members that would be of dubious reliability operating in a hot gas environment.

摘要翻译： 公开了一种多级先导阀，用于选择性地将工作流体供应到反应喷射主级致动室并从反应喷射主级致动室排出。 在本发明的优选实施例中，先导阀包括具有压力入口，排气出口和服务端口的电磁致动的球窝挡板阀。 第一级服务端口与第二级致动室流体连通。 设置在第二级致动室中的活塞可操作地接合包括第二级阀的球座型阀的球形构件。 第二级阀还包括压力入口，排气出口和服务口。 活塞和球的尺寸相对于彼此大小，使得当第二级致动室被第一级加压时，该力足以使球抵靠第二级压力入口。 这样可以将高压气体的流动关闭到第二级服务端口，并允许第二级服务端口通过排气口排出。 当第二级致动室由第一级阀排气时，作用在球上的压力足以使球抵靠第二级排气出口。 这打开第二级压力入口以允许高压气体进入第二级服务口。 第二级阀的球构件的双向运动完全由流体压力实现，从而能够使用低电功率快速响应，高流量调节热气体，并且消除使用弹簧或其它弹性构件 在热气体环境中运行可靠的可靠性。

公开(公告)号：US06370867B1

公开(公告)日：2002-04-16

申请号：US07637845

申请日：1991-01-07

申请人： Richard James Schnoor

发明人： Richard James Schnoor

IPC分类号： F02K952

CPC分类号： F02K9/58 ,  F02K9/52

摘要： A throttleable rocket injector assembly is disclosed wherein the flow of oxidizer into each of the oxidizer injectors is simultaneously regulated by a mechanical assembly mounted entirely within the oxidizer chamber.

摘要翻译： 公开了一种可节约的火箭喷射器组件，其中氧化剂流入每个氧化剂喷射器的流动同时由完全安装在氧化器室内的机械组件调节。

公开(公告)号：US06212878B1

公开(公告)日：2001-04-10

申请号：US09410872

申请日：1999-10-01

申请人： Alexei Pogosovich Adzhian ,  Vladimir Jurievich Bogushev ,  Alexandr Mikhailovich Samsonov ,  Jury Anatolievich Tjurin

发明人： Alexei Pogosovich Adzhian ,  Vladimir Jurievich Bogushev ,  Alexandr Mikhailovich Samsonov ,  Jury Anatolievich Tjurin

IPC分类号： F02K952

CPC分类号： F02K9/42 ,  F02K9/52 ,  F02K9/60 ,  F23L2900/07004 ,  F23R3/286 ,  Y02E20/344

摘要： The invention relates to the field of power machine building and may be used in mixing devices of gas generators for driving gas turbines, in particular, for liquid-propellant rocket engines. A gas generator comprises a cover with a hole, a bottom with a mixing chamber, a housing with an axial duct communicating with the hole in the cover. The housing is fastened in the cover hole and/or in the mixing chamber of the bottom. Grooves are made uniformly along the circumference of the cross section of the housing in the bottom and/or on the housing. The hole in the cover and the axial duct are designed to supply propellant, and the space between the cover and the bottom and the grooves in the bottom and/or on the housing are designed to supply an oxidizer. A propellant space is made in the cover, and the axial duct communicates through the propellant space with the hole in the cover by means of tangential propellant supply holes. An annular oxidizer duct and a cylindrical mixing chamber are additionally made in the module housing. The annular oxidizer duct is placed concentrically to the axial duct and communicates coaxially with the cylindrical mixing chamber, and by tangential oxidizer supply holes communicates with the space between the cover and the bottom.

摘要翻译： 本发明涉及动力机械制造领域，并且可以用于用于驱动燃气轮机的燃气发生器的混合装置，特别是用于液体推进剂火箭发动机。一种气体发生器，包括具有孔的盖，具有混合的底部 室，具有与盖中的孔连通的轴向管道的壳体。 外壳固定在底盖的盖孔和/或混合室中。 槽沿着壳体的底部和/或壳体的横截面的圆周均匀地制成。 盖和轴向管道中的孔被设计成供应推进剂，并且盖和底部之间的空间以及底部和/或壳体上的槽设计成供应氧化剂。 在盖子上形成推进剂空间，并且轴向管道通过切向推进剂供应孔与推进剂空间与盖中的孔连通。 在模块壳体中另外制造环形氧化器管道和圆柱形混合室。 环形氧化器管道同心地放置在轴向管道上并与圆柱形混合室同轴地连通，切向氧化剂供应孔与盖和底部之间的空间连通。

公开(公告)号：US06502385B2

公开(公告)日：2003-01-07

申请号：US09817499

申请日：2001-03-26

申请人： Dietrich Haeseler ,  Thomas Ruff

发明人： Dietrich Haeseler ,  Thomas Ruff

IPC分类号： F02K952

CPC分类号： B01F5/0453 ,  B01F2215/0086 ,  F02K9/52

摘要： An injection element for a combustion component running on two propellants, includes a first, central injection channel, which is connectable to a first propellant supply for a first propellant, and a second injection channel, which annularly surrounds the first injection channel. The second injection channel is connectable to a second propellant supply for a second propellant. The injection element includes a third injection channel, which annularly surrounds the second injection channel and which is in fluid communication with the first injection channel.

摘要翻译： 用于在两个推进剂上运行的燃烧部件的喷射元件包括可连接到第一推进剂的第一推进剂供应的第一中心喷射通道和环形地围绕第一喷射通道的第二喷射通道。 第二喷射通道可连接到用于第二推进剂的第二推进剂供应。 注射元件包括第三注入通道，其环形地围绕第二注入通道并与第一注射通道流体连通。

公开(公告)号：US06185927B1

公开(公告)日：2001-02-13

申请号：US08995563

申请日：1997-12-22

申请人： Constant J. Chrones ,  Gordon A. Dressler

发明人： Constant J. Chrones ,  Gordon A. Dressler

IPC分类号： F02K952

CPC分类号： F02K9/52

摘要： A tripropellant coaxial pintle injector for a rocket engine which enables smooth transitioning between two types of propellants that are adapted to be alternatively mixed with a third type of propellant in a combustion chamber of a rocket engine. The tripropellant coaxial injector includes a pintle for expelling a first propellant into a combustion chamber in a generally radial direction and two or more concentric metering sleeves which define orifices for expelling two or more different propellants into the combustion chamber in an axial direction thus, such a configuration allows for alternative mixing of two propellants with a third propellant in the combustion chamber of a rocket engine.

摘要翻译： 一种用于火箭发动机的三介质同轴枢轴喷射器，其能够在适合于与火箭发动机的燃烧室中的第三类型推进剂交替混合的两种类型的推进剂之间平稳过渡。 所述三介质同轴喷射器包括用于将第一推进剂沿大体径向排出到燃烧室中的枢栓和两个或更多个同心计量套筒，所述两个或更多个同心计量套筒限定用于沿轴向排出两个或更多个不同推进剂进入燃烧室的孔， 配置允许两个推进剂与火箭发动机的燃烧室中的第三推进剂的混合。