@cà 8, M46., f R. H. GODDARD FEEDING DEVICE FOR COMBUSTION CHAMBERS Filed ' OC‘L.' l2, 1942 2,409,036 2,409,036 Patented Oct. 8, 194i@ UNITED STATES PATENT OFFICE 2,409,036 FEEDING DEVICE FOR COMBUSTION y CHAMBERS Robert H. Goddard, Roswell, N. Mex., assignerv of one-halfA to The.v Daniel andFlorence Guggen heim Foundation, New York, N. Y., a corpora tion of NewYork Application October-:12, 1942, SerialNo. 461,670l 5 Claims. (Cl. 1.58--36) l This invention relates to feeding devices par ticularly adapted for use in rocket motors in which~ discharge gases are continuously produced in a combustion chamber and are continuously ejected through a rearwardly directed nozzle, lThe operating conditions in such rocket mo tors are very different from those encountered in oil-burning or gas-burning furnaces. In such furnaces, the combustion space is relatively large and the rate of fuel feed is relatively slow. In a rocket motor, most commonly used in air craft, it is necessary to avoid excessive weight and the motor must be relatively small, with a combustion chamber of limited capacity and to 2 Fig. 1 is a sectional front elevationcff apre ferred construction of feedingî mechanism; _ Fig. 2 is a partial perspective View of» an an nular stationary member forming- part. of thel mechanism shown in Fig. l ; Fig. 3 is a. similar view of an annular rotat ing member used in the preferred construction.; Fig. 4 is .a partial perspective View similar to Fig. 2 but showing a modification- to be> de scribed; and Fig. 5 is a diagrammatic view illustratingv the shiftingl of the locus of impact of the two liq uids under certain operating conditions’. In Figs. 1 to 3 I have shown a modified con struction in which concentric and stationary annular' casing members 60- and 8! are fixed in rapid rate. . the upper end portion 62A of the combustion In order to secure a large power output from chamber of a rocket motor. A» feed pipe 63» for such a, relatively small power unit, it is desir liquid- oxygen is connected to the fixed outer able to use a mixture of. gasoline or other liquid fuel and a liquid oxidizing agent such, as liquid 20 casing 68, and a feed pipe 84 for liquid `fuel is connected to the fixed inner casing lil. At their oxygen, but a mixture of such liquids is very which fuel and an oxidizing agent> are fed at a explosive, and the ignition of any considerable amount of such a mixture produces violent and dangerous combustion. It is the general object of my present inven tion to provide effective combustion for such a mixture of gasoline and liquid oxygen and also lower-ends, theîcasings 68 and 8l are-beveled at their inner and outer edges, as> indicated at 85. and. Bßin Fig. 2 and at 6l and 88 in Fig. l. The beveledÍ inner surface 85> of the fixed outer casing 68 is provided with a series of elongated circumferential slots 18, preferably arranged in staggered relation as best shown in Fig. 2. The to reduce the violence of the combustion reac-A beveled outer surface 88 of the fixed inner tion Without reducing the power output of the apparatus. I also maintain substantially con 30 casing 6| is provided with aV similar series of slots 'Il (Fig. l). tinuous. discharge of combustion gases from the A rotating annular member 'l5 is mounted discharge nozzle. within the outer fixed annular casing 64), anda To the accomplishment of these objects, I corresponding. rotating annular member 16- is provide means for rapidly and periodically vary ing the feed of one or both liquids to they com 35 mounted within the inner fixed annular cas ingßl. bustion chamber, so that combustion takes place The rotating annular member 'l5 is mounted in a rapid succession of relatively small explo at its upper end on balls 'i8 on a fixed ball race'y sions, with the combustion gases produced in 7.9,/ and at its lower end said member is pro a series of closely successive waves. These waves follow each other so rapidly that they inter 40 vided with beveled inner and outerv edge sur faces 88 and 8| (Fig. 3), slidably engaging the mingle in the combustion chamber and produce corresponding.. surfacesl 65- and 66 of the associ a substantially continuous and uniform flow of ated fixed annular casing 88. The inner surface combustion gases through the discharge nozzle. 80 is provided with` a series of staggered slots A more specific object of my inventionl is to provide means for periodically interrupting. the 45 82, arranged to coact with the slots 18. The rotating annular member 15 is of similar flow of each liquid and for more effectively mix construction and, is similarly mounted on balls ing the gasoline and liquid oxygen. I also pro 8% on a fixed ball race 85 in the fixed casingiil. vide means for independently varying the inter Similar beveled surfaces are provided at the vals between feeding occurrences for each liquid. My invention further relates to arrangements 50 lower end of the rotating member 16, and one of these surfaces has staggered slots 88. It will and combinations of parts which will be herein be noted that the slots 10 and 82 of the coact after described and more particularly pointed ing annular members 80 and 15 are directed in out in the appended claims. ward, While the slots 1l and 88 of the coact Preferred forms of the invention are shown ing members 6l and 16 are directed outward. in the drawing, in which 2,409,036 4 The rotating annular member 15 has a rotor ring 90 (Fig. 1) of copper or aluminum, coact ing with a. stator 9| to form an induction motor, and the inner rotating annular member 16 has Y, but the net open slot area will remain approxi mately the same and the flow through the pipes 63 and 64 will be substantially uniform. It is desirable that the frequency of the m0 a. similar rotor ring 92 coacting with a stator 93. tors be such as to produce periodic waves corre sponding to'the dimensions of the combustion chamber. These waves may travel either longi As the movable slots are rotated and inter mittently brought into alignment; with the fixed . slots, jets or slugs of liquid fuel and liquid oxy gen will be fed to the combustion chamber along intersecting paths as indicated in Fig. 1, 10 so that an intimate mixture of the two liquids is quickly attained. This construction has the advantage of delivering both liquids from ex tudinally of the chamber or may expand toward the cylindrical chamber wall. It will be understood that my improved feed ing mechanism, while particularly designed for use with liquids, also possesses similar utility when used with gases. Having thus described my invention and the ad site directions, thus providing a very thoroughly 15 vantages thereof, I do not wish to .be limited to intermingled combustion mixture. the details herein disclosed, otherwise than as Different explosive effects may be obtained by set forth in the claims, but what I claim is: varying the relative speed of the rotating an l. .Feeding mechanism for a combustion cham nular members 'l5 and 16, which varying speeds ber in a rocket motor comprising separate means may be attained by varying the frequencies of to feed liquid fuel and a liquid oxidizing agent the induction motors. to said chamber, and means to quickly and suc In Fig. 4 I have shown a portion of an annu cessively interrupt the feed of :both of said liq lar casing lill*i having slots 'l0a arranged in a uids as they enter said chamber and to simulta somewhat different and less staggered rela neously shift the locus of delivery of said liquids. tion. With this construction and with a similar 2. Feeding mechanism for a `combustion cham arrangement of slots in the associated rotating ber in a rocket motor comprising concentric fixed member, the feed will be more definitely inter annular casings mounted on said combustion tended coaxial annular passages and in oppo mittent while the arrangement previously de chamber and projecting therein and having slots scribed shifts the admission area up and down in their lower end portions, means to feed fluid between the upper and lower rows of slots. 30 fuel and a fluid oxidizing agent to said concentric All forms of my invention as above described fixed casings, rotatable annular members mount thus provide very simple and effective means for ed within said fixed casings and having slots in periodically feeding liquids to a combustion their lower end portions coacting with said first chamber in separated portions, so that the com named slots to provide fluid passages when bustion, while substantially continuous, neverthe 35 aligned therewith, and means to rotate said annu less takes place at slightly spaced intervals. The intervals are, however, too short to completely extinguish the flame. Dangerous explosions of large amounts of the combustion mixture are thus lar members. . 3. The combination in a feeding mechanism as set forth in claim 2, in which the fluid passages of the outer pair of ñxed and rotating annular avoided. 40 members are directed toward the axis of said ro By changing the relative locations of the ad tating members and the fluid passages in the in mission slots in the construction shown in Fig. 1 ner pair of fixed and rotating annular members and as illustrated in Figs. 2 and 4, both the ad are directed away from said axis. mission timing and the admission locus may be 4. Feeding mechanism for a combustion cham varied. By varying the frequencies, further var ber in a rocket motor comprising concentric fixed iations in feed and proportionate mixture may annular casings mounted on said combustion be obtained. chamber and projecting therein and having slots 'I'he change in locus of admission and impact in their lower end portions, means to feed fluid of the two liquids, when using the stationary an fuel and a fluid oxidizing agent to said concentric nular casing (il)a (Fig. 4) with the rotating mem 50 fixed casings, rotatable annular members mount ber l5 and a corresponding stationary casing 6|a ed within said fixed casings and having slots in with the inner rotating member 16, is illustrated their lower end portions coacting with said first diagrammatically in Fig. 5. named slots to provide fluid passages when It is assumed that the stationary casings and aligned therewith, and each rotatable member rotating members are so disposed angularly that having a ring of conductive metal and constitut a lower slot 'llla in the casing Sl'la will be opened ing the rotor of an induction motor by which said simultaneously with an upper slot 1 Ib in the cas member is rotated. . ing Sla, and that an upper slot 10b in the casing 5. Feeding mechanism for a combustion cham 60a will :be opened simultaneously with a lower ber in a rocket motor comprising separate means slot 'Ha in the casing 6in. 60 to feed liquid fuel and a liquid oxidizing agent With the slot ‘Illa and ‘Ilb open, the impact of to said chamber, and rapidly rotated valve ele the jets or sprays will occur at the locus X, while ments effective to shift the locus of delivery of with the slots 10b and 'Ha open, the impact will both of said liquids to said chamber and of im occur at the locus Y. As one pair of slots is pact of said liquids Within said chamber succes gradually closed and the other pair of slots is sively and repeatedly during each rotation of simultaneously and gradually opened, the locus said elements. of impact will shift back and forth between X and ROBERT H. GODDARD.