DE1950407C

DE1950407C - Fuel supply system for a rocket engine

Info

Publication number: DE1950407C
Application number: DE19691950407
Authority: DE
Inventors: Michael Dipl.-Ing. 2000 Hamburg Simon
Original assignee: MAN Maschinenfabrik Augsburg Nuernberg AG
Current assignee: MAN AG
Filing date: 1969-10-07
Publication date: 1972-12-28

Description

3 43 4

löst, daß die Turbopumpen und die diese antreiben- ten erreicht. Schließlich wird die Möglichkeit, ohne den Turbinen das Leitungssystem für die abdamp- Vorverbrennung höhere Brennkammerdriicke anzufenden Treibstoffkomponenten mit dem Leitungs- wenden, als Vorteil der Erfindung angesehen,
system für die flüssig zu fördernden Treibstoffkom- Ein Ausführungsbeispiel eines erfindungsgemäßen ponenten derart verbinden, daß die die Turbopum- 5 Treibstoffversorgungssystems für ein Raketentriebpen unmittelbar verlassenden Druckleitungen für die werk wird in der Zeichnung schematisch wiederflüssigen TreibstoSkomponenten in die Leitungen für gegeben. An Hand der folgenden Ausführungen soldie aus den Treibstoffbehältem abdampfenden Treib- len beispielsweise Aufbau und Funktion des Triebstoffkomponenten einmünden, von denen die Lei- werks im Zustand der Schwerelosigkeit erläutert tungen für die dampfförmigen bzw. flüssigen Treib- io werden.triggers that the turbo pumps and those driving them reached. Finally, the possibility, without the turbines, of turning the line system for the exhaust pre-combustion of higher combustion chamber pressures into fuel components with the line is seen as an advantage of the invention,
system for the liquid fuel components to be conveyed. An embodiment of a component according to the invention connect in such a way that the pressure lines for the plant leaving the Turbopum 5 fuel supply system for a rocket engine are shown schematically in the drawing for re-liquid fuel components in the lines for. On the basis of the following explanations, for example, the structure and function of the propellant components flow out from the propellant tanks, of which the propellants in the state of weightlessness are explained and for the vaporous or liquid propellants.

Stoffkomponenten zu der. Regenerativkühlern und Zur Erzeugung eines Hilfsschubes werden die von den diesen nachgeschalteten Turbinen führen, deren den Treibstoffbehältem 14 und 19 durch die Leitun-Austrittsleitungen mit den Einblaskanälen verbunden gen 69, 71 und 70, 72 abdampfenden Treibstoff- sind. komponenten über die Regenerativkühlsysteme 9 Die Erfindung stellt eine sinnvolle Verknüpfung 15 und 8 den Turbinen 67 und 68 zugeführt, in denen des Turbopumpenfördersystems . für den flüssigen sich die hochgespannten und erhitzten Gase ent-Hauptstrom und des Förderstroms für die abdamp- spannen und anschließend in de^ Austrittsleitungen fenden Druckgase dar, ohne daß Brennkammern, 73 und 74 zu den Einbiaskanälen 6 und 7 strömen.
Starter, zusätzliche aufwendige Hilfsleitur.gen und Bei den Vorbeschleunigungsvorgängen sind die Einspritzsysteme notwendig sind. Wie schon im ao Drücke in den Leitungen 69 und 70 so groß, daß Hauptpatent ausführlich besprochen, erlaubt das er- die Rückschlagventile 61 und 62 geöffnet sind, wähfindungsgemäße Treibstoffversorgungssystem im rend df ?. Ventile 63 und 64 in den Leitungen 75 und Gegensatz zu den bekannten Systemen, die flüssig 76 für die flüssig zu fördernden Treibstoffkompo- und/oder dampfförmig aus den Treibstoffbehältem nenten bis zum Erreichen eines bestimmten Druckes abströmenden Treibstoffkomponenten ausschließ- *s infolge der Druckabsenkung in den Behältern 14 !ich in dampfförmigem Zustand in die Brennkammer und 19 geschlossen bleiben. Der Flüssigkeitsspiegel einzuführen. Mit der Erfindung wird also auf ein- in den Treibstoffbehältern nach Erfolge der Vorfache Weise erreicht, daß das beim und nach dem beschleunigung ist schematisch mit 25 und 26 beStart wirksame Treibstoffversorgungssystem, bei dem zeichnet. Der während der Freiflugphase auftretende die dampfförmigen Komponenten aus den Treib- 30 Überdruck in den Treibstoffbehältem ist jeweils stoffbehältern abdampfen (Druckgasfördersystem), strichpunktiert angedeutet und mit 28 und 27 bedie Turbinen antreibt, so daß ein bekannter, als zeichnet.Substance components to the. Regenerative coolers and to generate an auxiliary thrust are fed by the turbines connected downstream of these, whose fuel tanks 14 and 19 are connected to the injection ducts 69, 71 and 70, 72 by evaporating fuel . components via the regenerative cooling systems 9 The invention provides a useful link 15 and 8 supplied to the turbines 67 and 68, in which the turbo pump delivery system. for the liquid, the high-tension and heated gases are ent-main flow and the conveying flow for the evaporation and then compressed gases fending in de ^ outlet lines, without combustion chambers 73 and 74 flowing to the injection ducts 6 and 7.
Starter, additional complex auxiliary lines and the injection systems are necessary for the pre-acceleration processes. As in the ao pressures in lines 69 and 70 so great that the main patent discussed in detail, it allows the check valves 61 and 62 to be open, fuel supply system according to the invention in the rend df? Valves 63 and 64 in the lines 75 and opposed to the known systems, the liquid 76 exclusively for the liquid to be conveyed Treibstoffkompo- and / or vapor from the Treibstoffbehältem components until a certain pressure is flowing fuel components * s as a result of lowering the pressure in the Containers 14! I in the vapor state in the combustion chamber and 19 remain closed. Introduce the liquid level. With the invention it is thus achieved in one way in the fuel tanks after successes that the fuel supply system, which is effective during and after the acceleration, starts schematically with 25 and 26, in which draws. The vaporous components occurring during the free flight phase from the propellant 30 overpressure in the propellant containers is evaporate in each case (compressed gas delivery system), indicated by dash-dotted lines and with 28 and 27 operated turbines drives, so that a well-known one draws as.

Vorbrennkammer ausgebildeter Starter nicht nötig Bei Erreichen des bestimmten durch Druckabfall ist. Wird in den Treibstoffbehältem ein bestimmter sich einstellenden Druckwertes schließen die Ventile Druckwert erreicht, tritt das Treibstoffversorgungs- 35 61 und 62 und öffnen die Ventile 63 und 64, so daß system (Haup^tromfördersystem) in Aktion, bei dem die Treibstoffzufuhr der kaltverfiüssigten Treibstoffdie kalt verflüssigten Treibstoffkomponenten von komponenten von den Böden der Treibstoffbehälter den Pumpen über Regenerativkühlsysteme, in denen 14 und 19 mittels der Turbopumpen 65 und 66 vor sie verdampft werden, über die schon in Drehung sich gehen kann, welche ihrerseits von den Turbinen versetzten Turbinen in die Brennkammer gefördert 40 67 und 68 angetrieben werden. Die Turbopumpen werden. Es werden also die Leitungen für die ab- fördern die Treibstoffkomponenten in die nicht isodampfenden Treibstoffkomponenten und die Leitun- lierten Leitungen 77, 71 (Mündungsstelle Af₃) und gen für die flüssig zu fördernden Treibstoffkompo- 78, 72 (Mündungsstelle M₄) über die Regenerativnenten so miteinander über ein Turbopumpensystem kühlsysteme 9 und 8, in denen die kaltverflüssigten gekoppelt, daß beide Treibstoffkomponenten nach 45 Gase erwärmt und in gasförmigem Zustand übereiner Verdampfung in Regenerativkühlsystemen zum geführt werden, zu den Turbinen 67 und 68. Die Antrieb von Turbopumpea herangezogen und an- Gase werden nach Arbeitsabgabe an den Turbinen schließend in dampfförmigem Zustand in die Brenn- in den Austrittsleitungen 73 und 74 gemeinsam über kammer eingeblasen werden. Neben der allgemeinen die irn Einblaskopf 3 angeordneten Einblaskanäle 6 Leistungssteigerung wird darüber hinaus mit der Er- 50 und 7 dem Brennraum 1 des Triebwerks zugeführt, findung auch eine Verschiebung der Leistungsgrenze, Durch die Förderung reiner Flüssigkeiten aus dem ab der eine an sich bekannte Vorverbrennung vor Treibstoffbehälter kann die hohe Schubleistung für den Antriebsturbinen notwendig ist, zu höheren Wer- das Hauptschubniveau erzeugt werden.Pre-combustion chamber designed starter is not necessary when the pressure drop reaches the specified value. If a certain pressure value that is set in the fuel tank is reached, the valves close pressure value, the fuel supply 35 61 and 62 and open the valves 63 and 64, so that the system (main flow delivery system) in action, in which the fuel supply of the cold liquefied fuel dies Liquefied fuel components from components from the bottoms of the fuel tanks to the pumps via regenerative cooling systems, in which 14 and 19 are vaporized in front of them by means of the turbo pumps 65 and 66, via which they can already start rotating, which in turn conveyed turbines displaced by the turbines into the combustion chamber 40 67 and 68 are driven. The turbo pumps are. The lines for conveying away the fuel components into the non-iso-vaporous fuel components and the lines 77, 71 (opening point Af ₃ ) and for the liquid fuel components to be conveyed 78, 72 (opening point M ₄ ) are therefore used Regenerativnenten so with each other via a turbo pump system cooling systems 9 and 8, in which the cold liquefied coupled that both fuel components are heated after 45 gases and in a gaseous state via evaporation in regenerative cooling systems to the turbines 67 and 68. The drive of Turbopumpea used and on - After the work is done at the turbines, gases are then blown in a vaporous state into the combustion lines in the outlet lines 73 and 74 together via the chamber. In addition to the general increase in performance in the injection ducts 6 arranged in the injection head 3, the invention also supplies the combustion chamber 1 of the engine with a shift in the performance limit, by conveying pure liquids from the pre-combustion, which is known per se The fuel tank can generate the high thrust power required for the drive turbines at higher levels of the main thrust level.

Hierzu 1 Blatt Zeichnungen1 sheet of drawings

Claims

Fuel com- ponents flowing into the fuel tanks

Claim: components which, due to the heat dissipation in the

combustion chamber designed as a regenerative cooler

Evaporate the fuel supply system for a rocket and / or thrust nozzle, one and the same engine, which is used by means of several liquid 5 injection ducts for introducing cryogenic fuel components into the combustion chamber, ie such. This means that a simplified propellant system is operated in the form of liquefied gases at low temperatures, a supply system for a rapidly operational and, for example, liquid oxygen and liquid, powerful liquid rocket engine created - hydrogen, with the prior to the furnace, which, in addition to safe and easy ignitability, starting the engine or immediately thereafter ig optimal inflow conditions and sufficient through the action of the ambient temperature from the mixing of the fuel components a large fuel adjustment range that evaporates from the fuel tanks is ensured,
components after their ignition for thrust In order to further increase the thrust performance of an engine

generation can be used, with both increasing, is additionally suggested in the main patent those before the engine is started or those in the liquid state from the propellant then evaporating fuel compo- nents with outflowing propellant stiff components as well as for those in the course of the furthermore to promote turbo pumps.

Ren start phase in the liquid state from Aus der USA.-Patent 3,094,838 is a

Fuel turbopump delivery system for a rocket drive component following the fuel tanks, which is known because of the heat emission ao work, in which only one fuel component the fuel, designed as a regenerative cooler, is pre-evaporated in a regenerative cooling system Vaporize chamber and / or nozzle, and the gas flow in a drive turbine for the and partially expanded the same injection ducts for introduction into propellant pumps. At the die Serve combustion chamber and to generate sem fuel supply system is therefore one high thrust performance in which the fuel component is in gaseous form and the other Turbopumps are blown into the combustion chamber in a liquid state from the lines leaving the container for fuel delivery: ng are arranged after or injected.

Patent 1 626 101, characterized thereby- The fuel supply system according to the already

net, that the Turbcpumpen (65 and 66) and in the main patent US patent specification, the turbines (6 ^ and 68) 30 3 224 189, which is discussed in the main patent, have a pressurized gas and a main line system (69, 71, 9, 73 and 70, 72, 8, current delivery system, in which lines for 74) for the evaporating fuel components the propellant steaming from the fuel tanks with the line system (75, 77, 71, 9 and 76, material components and lines 78, 72, provided with pumps, 8) for the liquid to be conveyed propellants for the liquid components from the fuel tanks connect in such a way that the turbopumps (65 and 66) provided for the fuel components flowing out are left immediately. Since the phases of the two fuel components are separated in the pressure lines (77 and 78) for the liquid, without being vaporized in a regenerative cooling system before fuel components in the lines (69, 71, via separate injection and 70, 72) for the Fuel containers injection systems are introduced into the combustion chamber (14 and 19) evaporating fuel components, the use of a single injection (opening points M ₃ and M ₄ ) is not possible.

of which the lines (71 and 72) for the Finally is from the U.S. Patent

vaporous or liquid propellant compo- 2 816417 a known fuel supply system, nenten to the regenerative coolers (9 and 8) and in which both liquid fuel components with the downstream turbines (67 and 45) are pumped into the combustion chamber 68), the outlet lines (73, 74) of which are with them. The drive turbines for these pumps the injection ducts (6 and 7) are connected. are tapped from the pump delivery lines

and in pre-combustion chambers of vaporized fuel components driven. After relaxing this

50 vaporous fuel components in the turbines they are diverted into the open, into the atmosphere, so that they are ready for further combustion

The main patent concerns a fuel supply in the rocket combustion chamber. Absystem for a rocket engine, which is seen by means of the fact that in this known propellant several liquid, preferably cryogenic propellant 55 supply system exclusively liquid fuel components, d. H. such in the form of liquefied components in the combustion chamber of the engine Low-temperature gases, for example flowing liquids, must have their own starter, Oxygen and liquid hydrogen, in which the fuel components are pre-burned which must be done before starting the engine or in order to start the turbines immediately then to be displaced by the action of the surrounding rotation.

Vaporize the temperature from the fuel tanks- Object of the present invention is to

the propellant components after their ignition to a simple turbo pump delivery system for the liquid Sch conviction can be used. and for the vapor from the fuel tanks

The invention of the main patent now consists of the outflowing fuel components in the fact that both the door and the GaI; -wtrks D / .w. to combine the propellant which evaporates immediately afterwards in such a way that even higher thrust resistance> i ".
further Siurtpliasc in a liquid state from din.