LIQUID FUEL ROCKET ENGINE

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 within a fuel cooling jacket of a fuel combustor means with an expansion pressure of thus-gasified fuel being adapted to en­ ergize the booster means, and the gasified fuel is sent to the fuel combustor means so as to be combusted therein to pro­ duce a combustion gas to be discharged outwardly serving as a propulsive effort of the rocket engine. An expansion nozzle cooling jacket means is arranged around the circum­ ference of a high expansion nozzle. 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 for driving the booster means. The remaining major part of gasified fuel from the combustor cooling jacket means is fed directely into the combustor means, so that it may be combusted to be discharged as pro­ pulsive force so pressure loss of the gasified fuel is held to a minimum, while establishing a potential energy made avail­ able for driving the booster means.

Description: The present invention relates to a rocket engine using a liquid fuel, according to the pre-characterizing part of claim 1. In the art of rocket engine, there is generally know a liquid fuel rocket engine of expander cycle type. Now, reference is made to a typical basic construction of this type rocket engine as shown in FIG. 2, which is constructed such that a propellant 1, for example liquid hydrogen, is pressurized to a desired pressure level by means of a fuel pressure booster 3, which is a fuel pump, and wherein a second propellant 2, for example liquid oxygen which is an oxidizing agent reacting with the first propellant 1 to be deflagrated together, is pressurized to a certain desired pressure by means of another pressure booster 4 for an oxidizing agent, which is an oxidizer pump. With this construction, thus-boosted propellant (liquid oxygen) 2 is then directed to a combustor 6. On the other hand, it is also constructed that thus-boosted propellant (liquid hydrogen), 1 is directed through a combustor cooling jacket 7 being arranged circumferentially around the combustor 6 so as to cool-off the same, and then is redirected to a booster driving unit 5 such as a gas turbine and the like mechanism, which is driven in rotation with this propellant, from which it is further directed to the combustor 6. In this combustor 6, the propellants 1 and 2 react with each other to be combusted or deflagrated together to produce a high pressure gas stream, which is to be released outwardly through an expansion nozzle 8 so as to generate a great propulsive force of a rocket engine. The propellant 1 boosted in pressure by means of the fuel booster 3 gains a temperature rise while cooling-off the combustor 6, also having a concurrent pressure rise. With thus-gained pressure of the propellant 1, the booster driving unit 5 is driven in rotation, accordingly. The driving power from the booster driving unit 5 is adapted to drive each of the fuel and oxidizer boosters 3 and 4 in rotating motion by may of a gear transmission 10. According to the conventional rocket engine construction wherein the propellant 1 gaining heat from part of the heat as generated from the combustor 6 is adapted to be a driving medium for the fuel and oxidizer boosters 3 and 9, it has generally been arranged such that the whole quantity of the propellant 1 with heat gains is directed to use as the driving fluid for the both fuel boosters 3 and 4. Also, it is the common practice in the conventional arrangement of a rocket engine that heat as generated from the combustor 6 is absorbed by cooling the same with the liquid phase propellant, and this is the so-called regeneration-cooling system. In such arrangement that the whole quantity of the propellant 1 which is once used for the purpose of cooling of the combustor is adapted as the driving medium for the fuel and oxidizer boosters 3 and 4, however, it is essentially required that the fuel booster 3 for that propellant 1 should be designed with a substantial capacity which is large enough to compensate for a loss in pressure as generated while passing through the combustor cooling jacket 7, plus an inevitable pressure drop as encountered in the driving of the booster driving unit 5, and so it is consequently required to employ a large capacity booster unit to counter such losses in pressures, accordingly. In coping with such undesirable problems, there is proposed a countermeasure in design as typically shown in FIG. 3 such that a subcombustor 11 which is adapted as a drive source for the fuel booster 3 to introduce part of the propellants 1 and 2 thereinto so as to be combusted therein and have thus-produced combustion gas made available for energizing the fuel booster, which is of the so-called gas generation cycle system. With such a construction, however, it brings such drawback that the entire system may inevitably turn out to be complex in construction, and thus resulting in a substantial increase in weight and hence reduction in the reliability of the system. In this arrangement as shown in FIG. 3, there is seen provided a high expansion nozzle cooling jacket designated at the reference numeral 9 defined extensively around a high-expansion nozzle 8 and adapted to pass a coolant therethrough in such a manner that part of the propellant 1 from the combustor cooling jacket 7 is introduced as a coolant of the high expansion nozzle 8 through the high expansion nozzle cooling jacket 9, and that that propellant is then discharged outwardly to the atmosphere. With this gas generation cycle system, it would become complex in construction with the addition of the subcombustor 11, which would then bring disadvantages such that it has an increased weight and hence a reduction in reliability of the system, and consequently, it would be desirable to attain an efficnent solution for overcoming such inevitable problems particalur to the conventional construction. FR-A-2 531 141, from which the present invention starts out in its pre-characterizing part shows a liquid fuel rocket engine, where liquid hydrogen is fed to a rocket engine and acts as a cooling medium for the combustion chamber and af­ ter having cooled the combustion chamber the now heated hy­ drogen is divided into two streams, the main stream thereof being fed into the combustion chamber to react there with e. g. liquid oxygen for combustion purposes and the remaining (smaller) stream is fed to a high expansion nozzle in order to cool also the high expansion nozzle. After having cooled the high expansion nozzle, the now additional heated up hy­ drogen is fed to booster driving means, e. g. a gas turbine, by means of which a fuel booster or hydrogen booster and an oxidizer booster or oxygen booster are driven. In view of this state of the art, it is the object of the present invention to increase the propellant agency of the hydrogen when driving the booster driving means without in­ creasing complexity and/or weight of the entire liquid fuel rocket engine. A solution of this object is achieved by the features of claim 1. According to the invention, the cooling arrangement for the expansion nozzle comprises upflow and downflow sections with respect to the flow direction of the combustion gas along the surface of the high expansion nozzle, by means of which the fuel or hydrogen, respectively, having cooled the combustion jacket is let downstream and upstream perpendi­ cular to the circumference of the high expansion nozzle and then afterwards the fuel or hydrogen, respectively, is let to the booster driving means. This arrangement at the high expansion nozzle jacket is cal­ led "down-up-pass system" in the following. As in the generic art according to FR-A-2 531 141 the coo­ ling fuel or hydrogen is let to the high expansion jacket cooling system only in a downward stream direction, the heat absorbing efficiency of the hydrogen is rather low, so that the driving capability of the hydrogen for the booster dri­ ving means is also comparatively low. In contrary thereto by means of the down-up pass system according to the present invention, the heat absorption efficiency of the high expan­ sion nozzle is improved in comparison to the single down pass system according to FR-A-2 531 141. Owing to the increase in the cooling efficiency, the amount of the propellant which is directed to the expansion nozzle can be minimized to the effect that the amount of propellant directed to the combustor increases in turn. Also the tempe­ rature of the propellant heated at the nozzle becomes higher and thus the output of the driving unit and rocket engine itself are improved. In other words, for the same output the weight of the engine can be reduced since the nozzle cooling jacket can be made shorter. According to this advantageous construction of a rocket engine propellant booster of the present invention, as summarized above, there is attained an advantageous effect such that only a minor part of propellant required specifically for the driving of the propellant booster in rocket engine system out of the total quantity thereof boosted by the booster and with a moderate temperature rise as gained from the cooling of the combustor is then reheated to a desired level by utilizing the heat of a nozzle arrangement, which is part of the combustor, so as to obtain a substantial increase in its thermal energy to such an extent as made available as a medium for energizing the propellant booster. With this improvement in construction, therefore, there is no need for a subcombustor arrangement as required in the conventional rocket engine propellant booster, hence without any further components required in construction, and so there is naturally attainable advantageous effects such as a light weight and hence a less production cost, yet with a substantial improvement in reliability, accordingly. Additional features and advantages of the invention will how become more apparent to those skilled in the art upon consideration of the following detailed description of a preferred embodiment exemplifying the best mode of carrying out the invention as presently perceived. The detailed description refers particularly to the accompanying drawings, in which like parts are designated at like reference numerals. In the drawings; FIG. 1 is a schematic view showing the general construction of a liquid fuel rocket engine system by way of a preferred embodiment of the present invention; and FIGS. 2 and 3 are similar schematic views showing the typical constructions of conventional rocket engine system, respectively. Referring firstly to FIG. 1, there is shown in schematic view the general construction of an improved liquid fuel rocket engine system according to the invention. In this figure, there are seen provided a propellant or liquid hydrogen fed through a feed line designated at the reference numeral 1, another propellant or liquid oxygen (oxidizer) fed through a feed line designated at 2, a propellant or liquid fuel booster at 3 adapted to boost up the pressure of the propellant 1, an oxidizer booster at 4 adapted to boost up the pressure of the propellant 2, booster driving units 5 adapted to drive such propellant boosters 3, 4 in operative rotating motion, for example, gas turbines or the like, a liquid fuel combustor at 6, a combustor cooling racket at 7 extending around the circumference of the combustor 6, and a high-expansion nozzle at 8 provided on the side of propelling gas jet outlet. Also, on the circumference of the divergent extension of the high expansion nozzle 8, there is provided a high expansion nozzle cooling jacket 9 which is adapted to take-off part of the propellant 1 cooled off while passing through the combustor cooling jacket 7 and adapted to reheat thus-branched propellant 1 with heat conducted from the high expansion nozzle 8. According to this liquid fuel booster system of the invention, it is notable that the propellant 1 is firstly boosted to a specified pressure level by way of the fuel booster 3, thereafter it is directed to pass through the combustor cooling jacket 7 in line of the booster system, where it effects the cooling of the combustor 6 while passing therethrough. Then, the propellant 1 which gains a temperature rise while cooling the combustor 6 is redirected partly to the nozzle cooling jacket 9 on one hand, and the remaining or the major part of the propellant 1 is fed to the combustor 6 on the other hand, where it reacts with the high pressure propellant (the oxidizer) 2 fed concurrently thereinto so that it is combusted or deflagrated with the propellant 2 and produces a large volume of combustion gas, and then thus-produced combustion gas is discharged outwardly by way of the high expansion nozzle 8, thus producing a great thrust or propulsive effort of the rocket engine system. That minor part of the propellant 1 which gains a temperature rise while passing through the high expansion nozzle cooling jacket 9 is given an increase in volume, hence with an increased pressure in the confined space from such heat and is redirected over to the booster driving units 5, where it is made available for the energizing of the same with thus-increased pressure. The present construction according to the invention may result in an advantageous effect in operation, as follows. By way of this preferred embodiment of the invention, the propellant comprises a fuel component or liquid hydrogen and an oxidizer component or liquid oxygen, which components are designed to be pressurized to a specified pressure level by means of each of the boosters 3 and 4 in the engine system, respectively. It is arranged that the whole quantity of liquid hydrogen under pressure is directed passing through the combustor cooling jacket 7, with which the combustor 6 is cooled off. With this arrangement, the propellant 1 or liquid hydrogen is caused to be heated up to 140°K. After having passed through the combustor cooling jacket 7 with the the combustor 6 cooled off, major part of liquid hydrogen is then redirected into the combustor 6 so that it is reacted with liquid oxygen to be combusted therein, thus forming a large volume of combustion gas, and thus producing a great propulsive effort for the rocket engine. On the other hand, minor part of liquid hydrogen which has passed through the combustor cooling jacket 7 is directed into the high expansion nozzle cooling jacket 9 for cooling off the high expansion nozzle 8, thus gaining a temperature rise up to approximately 600°K, and thus having a further increase in pressure. Consequently, with thus-obtained potential energy in the form of increased pressure of liquid hydrogen heated to that temperature being directed to the booster driving units 5, it is now made available to have these booster driving units energized further in acceleration, thus producing an output increased accordingly. Now, referring to FIG. 3 which shows a typical construction of the conventional gas-generation cycle type rocket engine, on which the present invention is based, the following is a review in comparison of this conventional construction with the preferred embodiment of the invention shown above. According to this typical example of the conventional propellelant booster system with the employment of a subcombustor 11 as shown in FIG. 3, it is noted that liquid hydrogen having cooled the high expansion nozzle 8 is then redirected into the high expansion nozzle cooling jacket 9, and thereafter it is merely discharged outwardly. In this respect, liquid hydrogen serves as a coolant alone, and therefore its potential energy as attained in the form of increased pressure is left unused to practice at all. More specifically, it is arranged such that minor parts of the propellants 1 and 2 are introduced into the subcombustor 11 for the purpose of energizing the boosters 3 and 4, and there is generated a gas at the temperature of approximately 850°K, which is made available for the driving of the boosters 3 and 4. In other words, the subcombustor 11 is added into the system on purpose to produce the additional energy for energizing the boosters 3 and 4. In contrast, it is advantageous according to the present invention that the potential energy of liquid hydrogen as gained from the cooling of the high expansion nozzle 8, which was heretofore exhausted in waste, is utilized with intention as a potential power source for driving the boosters in the system. More specifically, it is constructed in constrast from the conventional construction such that liquid hydrogen having passed the high expansion nozzle cooling jacket 9 is redirected for reuse into the booster driving units 5, instead of being exhausted in waste, and for this arrangement, it will do whith ease only by a slight rectification of the high expansion nozzle cooling jacket 9 to the reduction to practice of the present invention, accordingly. Now, without the subcombustor 11 adopted, and without any particular means to accompany therewith in the system, it is naturally possible to have such advantageous effect of affording a light weight and a simpler construction of the system. In addition, by virtue of the advantage that the driving medium made available for the booster driving units 5 has a lower temperature in comparison with the conventional system that uses the combustion gas from the subcombustor 11, it is advantageous that the operating conditions of the booster driving units 5 may be relieved accordingly, thus ensuring a longer service life and a higher reliability in operation of the rocket engine. Furthermore, since the propellant or liquid hydrogen which is preliminarily placed under a certain level of pressure by the booster 3 and the combustor cooling jacket 7 while passing therethrough has its potential energy in the form of pressure further increased by heat absorbed from the high expansion nozzle 8 while passing therethrough, thus affording a higher energy potential, though it has a relatively low temperature, in comparison with the combustion gas produced in the subcombustor 11 in the conventional arrangement. With such advantages of the present invention that may contribute much to the utility of waste heat from the combustor 6, there is afforded a substantial improvement in the rocket engine system which is adaptable to an upper stage module for the space shuttle craft and the like application, accordingly. While the present invention has been described in detail by way of a specific preferred embodiment thereof, it is to be understood that the present invention is not intended to be restricted to the details of the specific constructions shown in the preferred embodiment, but to the contrary, the present invention can of course be practiced in many other arrangement to an equal advantageous effect in accordance with the foregoing teachings without any restriction thereto and without departing from the invention. According to the present invention, there is attained an improved liquid fuel rocket engine wherein the propellant can efficiently be raised up to a specified high pressure level with a simple rectification in construction to provide a reserve of pressure available for the driving of the propellant (liquid fuel) booster, without the use of an undesired subcombustor. Also, there is provided a relatively simple construction of a liquid fuel rocket engine with a light weight and hence a less production cost, yet with a high reliability in operation.

Claims: 1. A liquid fuel rocket engine having a fuel booster means (3) for boosting the pressure of a fuel compo­ nent, an oxidizer booster means (4) for boosting the pressure of an oxidizer component, booster driving means (5) for energizing said two booster means, a combustor means (6) wherein said boosted fuel and oxidizer components are put into combustion to pro­ duce a combustion gas to be discharged outwardly, a combustor cooling jacket means (7) mounted operati­ vely around the circumference of said combustor means, a high expansion nozzle means (8) extending from said combustor means (6), and a high expansion nozzle cooling jacket means (9) disposed operatively around the circumference (9) of said high expansion nozzle means (8), wherein an outlet from said fuel booster means (3) is connected operatively to an inlet of said combustor cooling jacket means (7), an outlet from said combustor cooling jacket means (7) is connected operatively to a fuel inlet of said combustor means (6) and to an inlet of said high expan­ sion nozzle cooling jacket means (9), and an outlet from said high expansion nozzle cooling jacket means (9) is connected operatively to an inlet of said booster driving means (5), respectively, characterized in that said high expansion nozzle cooling jacket means (9) com­ prises an arrangement of upflow and downflow sec­ tions with respect to the flow direction of the combustion gas along the surface of said high expansion nozzle means (8), said upflow and downflow sections being connected to each other at the wider side of the high expansion nozzle said outlet from said combustor cooling jacket means (7) being connected to the downflow sections, and the outlets from said upflow sections being connec­ ted to an inlet of said booster driving means (5). 2. The liquid fuel rocket engine as claimed in claim 1, wherein said high expansion nozzle cooling jacket means (9) is adapted to serve as a heat exchanger means mounted operatively around the circumference of said high expansion nozzle means (8) and wherein said fuel component is reheated by said high expansion nozzle cooling jacket means (9) while passing therethrough and is fed into said booster driving means (5), whereby said fuel booster means (3) and said oxidi­ zer booster means (4) are energized. 3. A liquid fuel rocket engine as claimed in claim 2, wherein an outlet from said booster driving means (5) for driving said fuel booster means (3) is con­ nected operatively to an inlet of said booster dri­ ving means (5) for driving said oxidizier booster means (4). 4. A liquid fuel rocket engine as claimed in claim 2 or 3, wherein said booster driving means (5) are a gas turbine means.

Inventors: KAKUMA, YOJIRO C/O NAGOYA AIRCRAFT WORKS,, KISHIMOTO, KENJI C/O NAGOYA AIRCRAFT WORKS, KOYARI, YUKIO C/O NAT. SPACE DEVELOPMENT AGENCY, SOGAME, EIJI C/O NAT. SPACE DEVELOPMENT AGENCY
Applicants: MITSUBISHI JUKOGYO KABUSHIKI KAISHA, NATIONAL SPACE DEVELOPMENT
Application year: 1987
Main classification: F02K9
IPC codes: F02K9