US2698514A

US2698514A - Rocket motor

Info

Publication number: US2698514A
Application number: US266394A
Authority: US
Inventors: Edwin H Hull; Elizabeth L Winslow
Original assignee: Individual
Current assignee: Individual
Priority date: 1952-01-14
Filing date: 1952-01-14
Publication date: 1955-01-04
Anticipated expiration: 1972-01-04

Description

Jan. 4, 1955 E. H. HULL EI'AL 2,698,514

ROCKET MOTOR Filed Jan. 14, 1952 DISCHARGE.

D/EECT/ON PEEMANGA NATE 5 SOLUTION 9 lNl/E/VTOES E dwin H Hull Arthur F. Winalumglleceused By Eliznhgih I ,.\/\f1'1-Ll511:vv

Adm ini lstrutrix ATTORNEYS United States Patent ROCKET MOTOR Edwin H. Hull, Scotia, N. Y., and Arthur F. Winslow, deceased, late of Scotia, N. Y., by Elizabeth L. Winslow, administratrix, Schenectady, N. Y., assignors to the United States of America Application January 14, 1952, Serial No. 266,394

1 Claim. (Cl. 6035.5)

This invention relates to rockets of the type wherein propulsion is effected by the inter-mixture and reaction of two highly reactant fluids such as hydrogen peroxide and an aqueous solution of permanganate, such as calcium permanganate. The two fluids are intermixed in the reactant chamber wherein the hydrogen peroxide is decomposed into water in the form of steam, and oxygen. Alcohol or furr'ural may also be introduced to combine with the oxygen and supply additional energy to the rearwardly-discharge gaseous reaction products.

Heretofore it has been the practice to direct streams of hydrogen peroxide and permanganate solution into a generally hemispherical cup or chamber in an attempt to obtain thorough mixing of the reactants and consequent smooth and even decomposition. Alternatively, the two streams of liquid, under high pressure, are caused to impinge against an impact plate. This procedure is objectionable because the plates or targets on which the substances impinge, burn out rapidly and cause a failure of the rocket or, at least, inferior performance.

It is an object of the present invention to provide a structure which, while effectively and intimately mixing the propellant reactants, at the same time keeps the surfaces at or on which the intermixture occurs, at a temperature low enough to avoid burn outs and consequent rocket failures. That is, it is the principal object to provide a structure wherein one of the fluids absorbs heat from the reactant surface at such a high rate that the temperature of the surface is maintained below the burnout level.

Another object is the provision of a method whereby two reactant rocket motor fluids may be thoroughly intermixed and reacted without the development of hot spots and burn-outs of the rocket motor.

Other objects and advantages will be apparent from a study of the following description in connection with the drawing.

In the drawing:

Figure 1 shows a cross section through a forward portion of the combustion chamber and reactant back plate.

Figure 2 is a plan view, partly in section, of the porous plate and support therefor, and

Figure 3 is a view looking forwardly along the axis of the motor toward the back plate and showing the porous plate cup support and bracket.

In the drawing, the tubular element 1 forming the reactant chamber has a counterbore forming a shoulder 2 at its forward end. It will be understood that the rearward end of the chamber has means forming the usual venturi orifice, not shown, for the high-velocity discharge of the reactant products.

A back plate or reactant head 3 may be held on shoulder 2 in gas-tight relation therewith by a ring 4 threaded upon tube 1. This plate supports a rearwardly-extending bracket or shelf 5 which is enlarged at its portion adjacent the central longitudinal axis 6 to form a cup 7 having a rim shouldered as at 8. The cup is preferably generally triangular as shown upon Figure 2. Otherwise,

ICC

it may be sector-shaped or circular. The particular shape selected is merely a matter of the most efficient use of the materials required and, possibly, the shape of the spray of one of the reactants from the nozzle, as subsequently described.

A fluid passage 9 is formed within the bracket 5 and extends from a recess 11 in plate 3, to the bottom of cup 7. A fitting 10 aflords means for effecting a coupling with a source of permanganate solution under pressure. A plate or disc 12 of a porous material such as sintered iron or other metal, rests upon shoulder 8 and may be held thereon in any manner such as by peening or by a separable flange, not shown. From Figure 1 it will be noted that a substantial space exists between the bottom of the cup and the under side of plate 12 so that the liquid therein has access to practically the entire surface of the plate.

A passage 13 for a second reactant is provided centrally of back plate 3 and extends from a threaded opening 14 in the forward face of the back plate to a jetforming nozzle 16 which forms a flat jet of fuel directed at a small angle, say 5, downwardly upon, and across plate 12. Alternatively any known insert may be provided in the open end of passage 13 for forming a flat fan-like spray and atomization of the fuel as it emerges. A coupling or fitting 15 is threaded into opening 14 to connect passage 13 to a source of pressure fuel, not shown.

In operation of the motor, permanganate solution is forced under pressure into cup 7 through passage 9, and oozes or percolates through the porous plate 12 over the entire surface thereof. The second reactant, hydrogen peroxide, is forced under pressure through passage 13 and emerges in a fan-like spray or jet which impinges at small angle upon plate 12 over the entire area thereof and wipes or scours off the emerging permanganate solution. As a result, the two fluids are substantially instantaneously and completely mixed and react to form the high temperature gases which in attaining a very high velocity rearwardly, react upon the rocket to impel it forwardly. At the same time, the permanganate solution, in passing through plate 12, cools the same and maintains the temperature thereof below burn-out value.

From the foregoing it will be apparent that numerous changes in shape, form, disposition and interconnection of parts is possible without departure from the basic principles underlying the invention and without altering the manner in which it operates. For these reasons the disclosure should be taken in an illustrative rather than a limiting sense and all modifications within the scope of the subjoined claim are reserved.

We claim:

In a rocket motor component, means forming a reactant chamber including a back plate having a central longitudinal axis, a bracket fixed with said plate and transversely offset from said axis, a cup fixed with said bracket, a flat porous plate secured in the rim of said cup contiguous with said axis and extending parallel and transversely thereof, said plate forming with said cup a closed pressure fluid chamber, conduit means for conducting reactant fluid under pressure to said pressure fluid chamber, nozzle means fixed with said plate in position to discharge a fiat, fan-like spray of a second fluid reactant onto and across the outer surface of said plate at a small angle thereto along said axis and away from said back plate, and second conduit means for conducting a second reactant fluid under pressure to said nozzle means.

References Cited in the file of this patent UNITED STATES PATENTS 2,551,114 Goddard May 1, 1951