公开(公告)号：US5077968A

公开(公告)日：1992-01-07

申请号：US505738

申请日：1990-04-06

Applicant: Bruce R. Branstrom

Inventor： Bruce R. Branstrom

IPC: F01D1/20 ,  F01D1/24 ,  F01D15/08 ,  F02K9/48 ,  F04D9/04 ,  F04D13/04 ,  F04D13/12

CPC classification number: F04D9/04 ,  F01D1/20 ,  F01D1/24 ,  F01D15/08 ,  F02K9/48 ,  F04D13/04 ,  F04D13/12

Abstract: First turbine stage 14 rotates at low speed, doing moderate work, and driving a low pressure pump (22). Second turbine stage 16 rotates at high speed, doing a major portion of the work, and drives a high pressure pump (28). The low speed pump is compatible with suction requirements, and the second turbine stage does the substantial work at high efficiency.

Abstract translation: 第一涡轮级14以低速旋转，进行适度的作业，并驱动低压泵（22）。 第二涡轮级16高速旋转，进行大部分工作，驱动高压泵（28）。 低速泵与吸力要求相兼容，第二台涡轮级能高效率地进行实质性的工作。

公开(公告)号：US4998410A

公开(公告)日：1991-03-12

申请号：US403278

申请日：1989-09-05

Applicant: Aurelio Martinez-Leon ,  Christopher M. Erickson ,  Pei-Shiun Chen

Inventor： Aurelio Martinez-Leon ,  Christopher M. Erickson ,  Pei-Shiun Chen

IPC: F02K9/48

CPC classification number: F02K9/48

Abstract: A thrust engine is disclosed in the form of a hybrid staged combustion-expander topping cycle engine. The engine comprises a mixed cycle, one cycle being an expander cycle (14) operating at low temperatures and the other being a staged combustion cycle (12) operating at a higher temperature. A portion of liquid hydrogen from a fuel pump (16) is passed in heat exchange relation with the engine nozzle (22) for cooling same and heating the hydrogen, and the heated hydrogen is passed to an oxidizer turbine (28) for driving a liquid oxygen pump (81). Another portion of the liquid hydrogen from the fuel pump is passed in heat exchange relation with the engine thrust chamber (21) and combustor (20), and a portion of the resulting heated hydrogen is introduced, together with a portion of the pressurized liquid oxygen from the liquid oxygen pump, into a preburner (20) for combustion therein, and passage of the combustion gasses to a fuel turbine (26) for driving the fuel pump. A portion of the liquid hydrogen discharged from heat exchange relation with the thrust chamber and combustor is introduced into the combustor, together with a portion of the liquid oxygen discharged from the liquid oxygen pump, for combustion and passage of the combustion gases to the thrust chamber and expansion in the nozzle. The combustion gases discharged from the fuel turbine are mixed with the hydrogen gases discharged from the oxidizer turbine, and such mixture is also introduced into the combustor.

Abstract translation: 推力发动机以混合分段燃烧 - 膨胀机顶部循环发动机的形式被公开。 发动机包括混合循环，一个循环是在低温下运行的膨胀器循环（14），另一个是在较高温度下运行的分段燃烧循环（12）。 来自燃料泵（16）的液体氢气的一部分与发动机喷嘴（22）以热交换的方式通过，用于冷却，并且加热氢气，并且加热的氢气被传送到用于驱动液体的氧化剂涡轮机（28） 氧气泵（81）。 来自燃料泵的液态氢的另一部分与发动机推力室（21）和燃烧器（20）以热交换的方式通过，一部分加热的氢气与一部分加压液氧 从液氧泵输入到用于燃烧的预燃机（20）中，并且将燃烧气体通过燃料涡轮机（26）以驱动燃料泵。 从与推力室和燃烧器的热交换关系排出的液体氢的一部分与从液氧泵排出的一部分液氧一起引入燃烧器中，用于燃烧和通过燃烧气体到推力室 并在喷嘴中膨胀。 从燃料涡轮排出的燃烧气体与从氧化剂涡轮机排出的氢气混合，并且这种混合物也被引入燃烧器。

公开(公告)号：US4901525A

公开(公告)日：1990-02-20

申请号：US165765

申请日：1988-03-09

Applicant: John H. Beveridge ,  William H. Knuth

Inventor： John H. Beveridge ,  William H. Knuth

IPC: F02K9/48

CPC classification number: F02K9/48

Abstract: A bi-propellant self-contained propulsion system is provided for powering rockets. A plurality of turbopump assemblies are provided to take liquid propellants from low pressure storage tanks to a substantially higher pressure thrust chamber. Substantially all of the liquid propellants are pressurized and gasified within the plurality of turbopumps. Substantially all of the gasified propellants are then used to drive the turbopumps that pressurize the liquid propellants. Gasification preferably occurs within a preburner internal to the turbopump assembly that combines a small portion of one of the propellants with a substantial portion of the other. The proportions are selected so that gasification of all of the propellants is ensured yet relatively low preburner temperatures are maintained. A multi-stage pintle assembly may be provided to vary the exit-to-throat area ratio of the nozzle. The total thrust and the mixture ratio may be controlled by shutting down some of the turbopumps. Actuation of the pintle is preferably coordinated with the shutting down of turbopumps to maintain a relatively constant thrust chamber pressure. A nozzle skirt insert is provided to enhance the low altitude performance of the rocket engine and the high altitude performance of the rocket engine.

Abstract translation: 提供双推进剂独立式推进系统，用于为火箭提供动力。 提供了多个涡轮泵组件，以将液体推进剂从低压储罐中吸取到基本上较高压力的推力室。 基本上所有的液体推进剂在多个涡轮泵内被加压和气化。 然后基本上将所有气化的推进剂用于驱动对液体推进剂加压的涡轮泵。 气化优选地在涡轮泵组件内部的预燃室内发生，其将一部分推进剂中的一部分与另一个的大部分组合。 选择比例使得所有推进剂的气化得到确保，同时维持相对较低的预燃室温度。 可以提供多级枢栓组件以改变喷嘴的出口与喉部面积比。 总推力和混合比可以通过关闭一些涡轮泵来控制。 枢轴的致动优选与关闭涡轮泵相配合，以保持相对恒定的推力室压力。 提供喷嘴裙插入件以增强火箭发动机的低空性能和火箭发动机的高空性能。

公开(公告)号：US4879874A

公开(公告)日：1989-11-14

申请号：US182938

申请日：1988-04-18

Applicant: Yukio Koyari ,  Eiji Sogame ,  Kanji Kishimoto ,  Yojiro Kakuma

Inventor： Yukio Koyari ,  Eiji Sogame ,  Kanji Kishimoto ,  Yojiro Kakuma

IPC: F02K9/46 ,  F02K9/48 ,  F02K9/64

CPC classification number: F02K9/48 ,  F02K9/64

Abstract: The present invention is related to a liquid fuel rocket engine of the type that a liquid fuel is boosted in pressure by way of a booster means. Thus boosted liquid fuel is gasified with a fuel cooling jacket of a fuel combustor means with an expansion pressure of thus gasified fuel being adapted to energize the booster means, and the gasified fuel is sent to the fuel combustor means so as to be combusted therein to produce a combustion gas to be discharged outwardly serving as a propulsive effort of the rocket engine, wherein there is mounted an expansion nozzle cooling jacket means around the circumference of a high expansion nozzle means of the combustor means, wherein part of the gasified fuel from the combustor cooling jacket means is directed into the expansion nozzle cooling jacket means to be reheated therein resulting in an increased potential energy to be utilized as a potential energy for driving the booster means, and wherein the remaining major part of gasified fuel from the combustor cooling jacket means is fed intact into the combustor means, not utilized to energize the booster means, so that it may be combusted to be discharged as propulsive force, whereby a pressure loss of the gasified fuel is held to a minimum, while establishing a potential energy made available for driving the booster means.

Abstract translation: 本发明涉及一种液体燃料火箭发动机，其中液体燃料通过增压装置在压力下升压。 因此，用燃料燃烧器装置的燃料冷却套将这种增压的液体燃料气化，其膨胀压力由此被气化的燃料适用于对增压装置通电，气化的燃料被送到燃料燃烧器装置以便在其中燃烧， 产生燃烧气体作为火箭发动机的推进力向外排出，其中在燃烧器装置的高膨胀喷嘴装置的周围安装有膨胀喷嘴冷却套装置，其中部分来自燃烧器的气化燃料 燃烧器冷却套管装置被引导到膨胀喷嘴冷却套装置中，以在其中再加热，从而增加了用作驱动升压装置的势能的势能，并且其中来自燃烧器冷却套的气化燃料的剩余主要部分 装置被完整地供给到燃烧器装置中，不用于对增压装置通电，从而可燃烧 作为推进力排出，由此气化燃料的压力损失保持最小，同时建立可用于驱动升压装置的势能。

公开(公告)号：US4223530A

公开(公告)日：1980-09-23

申请号：US944750

申请日：1978-09-22

Applicant: Erich Kirner ,  Helmut Dederra

Inventor： Erich Kirner ,  Helmut Dederra

IPC: F02K9/46 ,  F02K9/48 ,  F02K9/64 ,  F02K9/97 ,  F02K9/02

CPC classification number: F02K9/48 ,  F02K9/972

Abstract: A method of operating a liquid fuel rocket engine having at least first and second propellant component pumps, driven by a gas turbine which is connected to discharge its turbine propulsion gases through a secondary thrust nozzle, includes a main engine having a combustion chamber with a thrust nozzle, an initial expansion portion with an expansion corresponding to ground pressure and a final expansion portion connected to the initial expansion portion and terminating in a thrust discharge operating substantially at vacuum and with means for circulating at least one propellant component through cooling channels of the walls of both expansion portions, comprises, directing a first component into the combustion chamber, and directing at least a first portion of a second propellant component into the walls of the initial expansion portion and then into the combustion chamber and directing a second portion of the second propellant component into the walls of the final expansion portion so that they are heated therein and, thereafter, directing the heated propellant component gases into the turbine. The liquid fuel rocket engine for operation in outer space, comprises, wall means defining a combustion chamber having an injection head and a thrust nozzle part with a narrow neck portion, an initial expanding portion and a final expanding portion which terminates in a thrust discharge.

Abstract translation: 一种操作液体燃料火箭发动机的方法，所述液体燃料火箭发动机具有至少第一和第二推进剂组分泵，所述推进剂组分泵由燃气轮机驱动，燃气轮机连接以通过次级推力喷嘴排出其涡轮机推进气体，包括具有推力的燃烧室的主发动机 喷嘴，具有对应于地面压力的膨胀的初始膨胀部分，以及连接到初始膨胀部分的终止膨胀部分，并终止基本上在真空下运行的推力排放，以及用于使至少一个推进剂部件通过壁的冷却通道循环的装置 两个膨胀部分包括：将第一部件引导到燃烧室中，并将第二推进剂组分的至少第一部分引导到初始膨胀部分的壁中，然后进入燃烧室，并引导第二部分的第二部分 推进剂组分进入最终膨胀部分的壁 它们在其中被加热，然后将加热的推进剂组分气体引导到涡轮机中。 用于在外部空间操作的液体燃料火箭发动机包括限定具有喷射头和具有窄颈部的推力喷嘴部分的燃烧室的壁装置，初始膨胀部分和终止于推力排放的最终膨胀部分。

公开(公告)号：US4171615A

公开(公告)日：1979-10-23

申请号：US545793

申请日：1966-04-21

Applicant: Warner L. Stewart ,  Ambrose Ginsburg ,  Melvin J. Hartmann

Inventor： Warner L. Stewart ,  Ambrose Ginsburg ,  Melvin J. Hartmann

IPC: F02K9/46 ,  F02K9/48 ,  F02K9/02

CPC classification number: F02K9/46 ,  F02K9/48

Abstract: A rocket propellant feed system utilizing a bleed turbopump to supercharge a topping turbopump. The bleed turbopump is of a low pressure type to meet the cavitation requirements imposed by the propellant storage tanks. The topping turbopump is of a high pressure type and develops 60 to 70 percent of the pressure rise in the propellant.

Abstract translation: 火箭推进剂进料系统利用排放涡轮泵对顶部涡轮泵进行增压。 排气涡轮泵是低压型，以满足推进剂储罐施加的空化要求。 顶部涡轮泵是高压型，并且在推进剂中产生60％至70％的压力升高。

公开(公告)号：US3788069A

公开(公告)日：1974-01-29

申请号：US3788069D

申请日：1972-08-18

Applicant: MESSERSCHMITT BOELKOW BLOHM

Inventor： SCHMIDT G

IPC: F02K9/48 ,  F02K9/88 ,  F02K9/02

CPC classification number: F02K9/88 ,  F02K9/48 ,  F42B10/663

Abstract: A liquid fueled rocket engine of the so-called main current type in which combustion gases are generated in a precombustion chamber and directed in series to a fuel component pump drive turbine and to a main combustion chamber for generating thrust gases, includes one or more control nozzles or control nozzle groups which are connected to receive the exhaust gases from the turbine with the addition of small partial amounts of a propellant component.

Abstract translation: 一种所谓的主电流型液体燃料火箭发动机，其中燃烧气体在预燃室中产生并串联连接到燃料部件泵驱动涡轮机和主燃烧室产生推力气体，包括一个或多个控制 喷嘴或控制喷嘴组，其连接以接收来自涡轮机的废气，同时添加少量的推进剂组分。

公开(公告)号：US3349566A

公开(公告)日：1967-10-31

申请号：US38974464

申请日：1964-08-14

Applicant: BRISTOL SIDDELEY ENGINES LTD

Inventor： RALPH TYRRELL ALBERT ,  HUNT MICHAEL S

IPC: F02K9/48

CPC classification number: F02K9/48

公开(公告)号：US3306038A

公开(公告)日：1967-02-28

申请号：US38969464

申请日：1964-08-14

Applicant: BRISTOL SIDDELEY ENGINES LTD

Inventor： NIGEL FERRIMAN VICTOR

IPC: F02K9/44 ,  F02K9/48 ,  F02K9/56

CPC classification number: F02K9/48 ,  F02K9/44 ,  F02K9/563

公开(公告)号：US3269317A

公开(公告)日：1966-08-30

申请号：US26155863

申请日：1963-02-21

Applicant: UNITED AIRCRAFT CORP

Inventor： FRANK LATTANZIO ,  REICHENBACHER FRANK W

IPC: F01D15/08 ,  F02K9/48 ,  F04D13/02 ,  F04D13/04

CPC classification number: F02K9/48 ,  F01D15/08 ,  F04D13/02 ,  F04D13/04