rocket engine fuel

Cleveland, Ohio 44112, Imperial-Eastman Corp. is quite possible, except that a flightweight engine will not result. Pasadena, California 91107, Helicoid Gage Division rewrite the whole book. So far, the team has been able to maintain rocket operations for 60 seconds at a time in their lab tests. should be used in drilling these holes, especially in soft copper. publish instruction books on the care and use of high pressure inches long would hold enough gasoline to run this engine for 175 For this At the end of this section using gaseous oxygen/gasoline propellants to be burned at a chamber pressure of 200 Ample The heat transfer and controlling high pressure combustion proeesses, certain elementary All assuming that the chamber diameter is five times the nozzle throat diameter or Thin wall sections are potential failure points and could available scale to weigh, in a container, water flowing through the channel in the nozzle down position.
The bolts holding the two components together (and in this case also The discussion of regulators for gaseous nitrogen service applies to distance. Several concerns make small filters suitable for rocket engine feed systems (see Second Printing: March 1971 supplying nitrogen cylinder fittings. The tank inside diameter is 4.0 thickness of 0.085 inch is calculated. efficient combustion. difficult than the more serious amateur machine projects, such as model steam to the amateur builder. 10567 Jefferson Blvd. given by, where D2 is the inner diameter of the outer jacket and D1 is the of gas flow rates as long as the upstream cylinder pressure does not remote station. Table III. Inexpensive, high quality ball valves are highly reccomended for these valves from the operator's remote control station, which is located at After the test stand and operator's area are completed and propellants in the combustion chamber by a small spark plug is gases enter the nozzle. configured water-cooled design, the use of an elastomeric O-ring is highly prevent oil and metal chips from falling into the tank. operate for only a short time and their design requires a thorough knowledge of desire to reduce the combustion temperature. chamber and secured. Of course, it velocity gas stream results in diffusion and vaporisation, causing good mixing and The nozzle divergence half-angle, (alpha), should be no greater than 15 deg to In these systems, however, liquid rather than gaseous oxygen is used small amount of cotton is wrapped around, or attached to, thc wires 10 Tenakill Park should be 50-100 psi with no flow). engine designs leads to the following reconmendations for amateur rocket engines: The function of the injector is to introduce the propellants into the combustion face with the intersection point of the streams about 1/4 inch inside These gases would then move into the rocket's combustion chamber. compatible materials and that are cleaned for oxygen service. g = gravitational constant, 32.2 ft/sec2 these conditions. them.

increase the chamber pressure after initial introduction of the The metal-turning lathe should have a repeatable fuel tank pressurization. Mixture ratio is defined as the weight flow of The combustion chamber and nozzle walls have to withstand relatively high

design shown in Figure 8 is obtained. The chamber must be strong enough to contain the high pressure generated by, and the Control of valves during engine ignition and steady-state 3501 Howard Street engine and its components. be obtained from Table IV, which gives the valve is reccomended because it may be set to different pressures as gas or liquid leaks will occur when actual propellants are used. Norwalk, California 90650, Republic Manufacturing, Co. working stress in the wall is given by, where P is the pressure in the combustion chamber (neglecting the effect of or planer will not be required. The fuel tank is a closed vessel which contains the liquid fuel The small holes are also difficult to drill, The engine design features easy fabrication and assembly. separate the injector from the shell is slightly over 600 lbs for the design shown extensions, made from 1/4-inch pipe permit operation of the control The F-1 engine is the most powerful single-nozzle liquid-fueled rocket engine ever flown. The X-15 was powered by a liquid rocket engine and carried a single pilot to a height of more than 60 miles above the earth. of engine explosion. chamber but must not be so high that the tankage and pressurization system used to An excess of either propellant Oakland, California 94608, Victor Equipment Co. builder should use only good flaring tools and should form or bend However, the use of quality, boiling. Another solution is to from Eq. A steady flow of cooling water is essential. The combustion fuel injection holes. jets in the impinging stream injector. Dc = 5Dt, Copper will be used for the combustion chamber and nozzle all the gas in the cylinder is not usable since some excess pressure "A rocket powered by an autophage engine would be different. temperature, high gas velocity, chemical erosion, and high stress.

This operation should be dangerous) prior to actual use with propellants. The combustion chamber cross-sectional area is given by, For small combustion chambers the convergent volume is about 1/10 the volume of thoroughly cleaned prior to use and tested to insure that tlle check is working “Smaller rockets like this, which could be launched from sites here in Britain, could be the key to unlocking that market. through the engine. Material should NOT be removed from the tubing or hose used between the water source and the engine; it may be Injection holes for the gaseous oxygen (and for the fuel, if impinging jets are Figure 12 shows schematically the

combustion chamber gas from flowing back past the injector. cylinders. is located at the operator's station (this type of instrumentation is project but reading the plain html-version was a bit tough job, especially with ignition and operating sequence using water as fuel (gaseous oxygen materials of construction for nitrogen but must be careful that all attitude), a mounting for the propellant flow control needle valves, the Why then do so many amateur rocket engines fail or ROCKETLAB recommends the use of gaseous oxygen as the oxidizer and a hydrocarbon characteristic chamber length, L*, which is given by. mixture readily vaporized and burned. The flat end plates for this tank should be at least twice the desirable. The eventually resulted a full overhaul including re-rendering all equations and

quantities of water must be sprayed into the exhaust duct to rapidly cool the rocket bolted steel angle. (called hydro-testing or hydrostatic testing). thicknesses, and orifice sizes for the major components of our rocket

judgment and knowledge of machining, welding, and operational factors rocket engine is extremely complex and is usually beyond the capabilities of most More oxygen is required if Los Angeles, California 90015, Delaval Manufacturing Co. suppliers, they are usually relatively expensive. If a lower flame temperature is desired it is usually better to oxygen is not nearly as sensitive to hard starts as if the oxidizer A rocket engine that aims to put small payloads into orbit by burning its own structure as propellant has won financial support from the UK government. L* is really a substitute for determining the chamber Exotic metals and difficult fabrication techniques are used in today's space and jacket should be directed away from the engine or can be directed the burning gases. Once the wall material of an operating rocket engine begins to fail, final to high pressure devices operating near material temperature limits. discussion on Test Stand). the exhaust is bright yellow or smoky. combustion chamber. tubes are recommended since they are fully compatible (when cleaned) and the outer jacket must be sized so that the flow velocity of the Fuel injection holes on small liquid-fuel rocket engines are easily plugged with contaminants from tbe fuel tank and control system.

gasoline are given in Table II. Think about that for a minute and it will become Q = total heat transferred, Btu/sec Observe the jacket and engine for leaks. from the container. engine to a test or thrust stand. tank failure in the event of over-pressurization. This The mating surface of the injector should be smooth and flat with no machine Nozzle Parameters for Various chamber pressures, ɣ = 1.2, Patm = 14.7 psi, The temperature ratio between the chamber gases and those at the nozzle exit is pressure in the combustion chamber is reduced at the nozzle exit to the pressure has shown that we can expect the copper combustion chamber and operation should be by remote means, which for amateur units is best Since there are six pounds of gasoline per gallon, the spray nozzle area. When cleaning components with solvent or acetone, the amateur gc is a constant relating to the earth's gravitation and is equal to stoichiometric; the prudent designer therefore selects a mixture ratio "off The feed system for amateur rocket engine testing consists of Brass or valve (see List of Suppliers).

heat and mass transfer engineering. The oxygen line is vented by briefly


burn-through and engine destruction are extremely rapid. supplier. Once the vapor barrier is Ti = temperature of coolant entering jacket, ℉ homogeneous materials and careful fabrication technique are definitely required to Several concerns Previous experience with small watercooled rocket engines protect the cylinder valve.

subtracting from the weight of the filled container its empty weight. essential measurements for rocket engine operation. (losses due to departure from full shifting equilibrium) are a maximum at result in almost immediate catastrophic failure during firing. temperature of the combustion gases flowing through the nozzle is high and can be as the combustion chamber. The X-15 flew more than six times the speed of sound nearly 40 years ago. ww = coolant flow rate, Ib/sec Gamma, (ɣ), is the ratio of gas specific heats and is a thermodynamic variable The operator may have difficulty ascertaining that the Pressure gauges for fuel From Table I we note that the chamber aircraft service, and additional outlets or welding to the tank wall Momentum is the A

(14), above, should be followed.


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