|Publication number||US2709890 A|
|Publication date||Jun 7, 1955|
|Filing date||Mar 26, 1952|
|Priority date||Mar 26, 1952|
|Publication number||US 2709890 A, US 2709890A, US-A-2709890, US2709890 A, US2709890A|
|Inventors||Robert H. Goddard|
|Original Assignee||Esther C Goddard, Daniel And Florence Guggenheim|
|Export Citation||BiBTeX, EndNote, RefMan|
|Patent Citations (7), Referenced by (2), Classifications (14)|
|External Links: USPTO, USPTO Assignment, Espacenet|
June 7, 1955 R. H. GODDARD 2,709,890
MECHANISM FOR INTERMITTENT FEEDING OF COMBUSTION LIQUIDS TO A COMBUSTION CHAMBER IN PROPULSION APPARATUS Filed March 26, 1952 INVENTOR. ROBERT H. GODDARDDECD. ESTHER BY 0. GODDARD, sxccumx.
nited States Patent MECHANISM FOR INTERMITTENT FEEDING OF COMBUSTION LIQUIDS TO A COMBUSTION CHAMBER 1W PROPULSION APPARATUS Robert H. Goddard, deceased, late of Annapolis, Md., by Esther C. Goddard, executrix, Worcester, Mass., assignor of one-half to The Daniel and Florence Guggenheim Foundation, New York, N. Y., a corporation of New York Application March 26, 1952, Serial No. 278,712
1 Claim. (Cl. 6035.6)
This invention relates to propulsion apparatus of the type in which a combustion chamber continuously discharges its exhaust gases through a r-earwardly-open discharge nozzle. When such a combustion chamber is used in aircraft, limitations of weight make it obviously essential that maximum power be developed from the combustion liquids, such as gasoline and liquid oxygen.
This maximum power development depends quite largely on providing a very intimate mixture or inter mingling of the combustion liquids. To the attainment of this desired result, means is herein provided for intermittent or pulsating feeding of each of the combustion liquids.
If the flow interruptions are extremely rapid, the general effect is that of continuous flow, but each stream of liquid tends to break up into many small drops which mix much more easily than when the liquids are fed uniformly and thereby tend to form separate films or layers.
The invention further relates to arrangements and combinations of parts which will be hereinafter described and more particularly pointed out in the appended claim.
Preferred forms of the invention are shown in the drawing, in which Fig. l is a front elevation of mechanism for providing intermittent or pulsating liquid feed;
Fig. 2 is a partial sectional elevation of a modified construction;
Fig. 3 is a front elevation of a construction in which the pulsating waves are produced by turbine action;
Fig. 4 is an enlarged sectional view of one of the turbines shown in Fig. 3;
Fig. 5 is a sectional view indicating the production of waves in the liquid stream by a vibrating reed; and
Fig. 6 is a sectional view showing the interruption of feed as produced by a rapidly rotating bladed rotor.
Referring to Fig. 1, the combustion chamber C is shown as provided with an open discharge nozzle N, both of any usual construction. Feed tubes 10 and 11 are connected into the otherwise closed end of the combustion chamber, and the tube 10 may receive a liquid oxidizer, as oxygen, through a supply pipe 12, while the tube 11 similarly receives a liquid fuel, as gasoline, through a supply pipe 14.
At their outer ends, the tubes 10 and 11 are closed by bellows members 15 and 16. A solenoid 17 may be associated with each bellows member 15 or 16, and the solenoid current may be rapidly interrupted by a magnetic relay 18, which operates a make-and-break switch 19 of any usual type. With this construction, the combustion liquids will be fed under pressure through the pipes 12 and 14 to the tubes 10 and 11, and will be rapidly interrupted or caused to pulsate by the alternate expansion and contraction of the bellows members 15 and 16.
The flow of the liquids to the combustion chamber then also assumes an interrupted or pulsating form which is found to substantially facilitate the breaking-up of the liquid streams into many fine drops.
If the length and diameter of the tubes 10 and 11 are properly selected, standing waves may be produced in the tubes, and the pulsating effect may thus be magnified.
In Fig. 2, the tube 20, corresponding to the tube 11 previously described, receives a combustion liquid under pressure through a supply pipe 21 and is provided with a piston 22 at its outer end. This piston may be intermittently pressed inward against a spring 24 by a rotated cam or eccentric 25. The pulsations thus produced are similar in effect to those produced by the construction shown in Fig. 1.
In Fig. 3, a combustion chamber C2 is provided with a nozzle N2, both of usual construction, and one combustion liquid, as oxygen, is supplied to the chamber C2 through a supply pipe 30, turbine pump P and tube 31, while the other liquid, as gasoline, is supplied from a pipe 33 through a turbine pump P2 and tube 34.
The detailed construction of the turbine pump P2 is shown in Fig. 4, in which a volute casing 36 eccentrically encloses a stator 40 comprising a plurality of fixed vanes 41.
Liquid from the pipe 33 is supplied at the axis of a rotor 45, preferably provided with a series of long vanes 46 and interposed short vanes 47. The vanes or partitions 41, 46 and 47 are of such thickness and spacing that the moving vanes substantially but momentarily close the passages between the stationary vanes 41.
Consequently, the pressure of the liquid fed through the pipe 34 to the cylinder C2 is alternately increased and decreased as the vanes 46 and 47 pass the openings between the stationary vanes 41. if the rotor is rotated at a relatively high speed, the rate of pressure interruption or pulsation will be correspondingly high.
In Fig. 5, a vibrating reed 50 is mounted in a recessed portion 51 in a supply pipe 52. As liquid under pressure flows through this recess, as indicated by the arrows, the reed it will be set in vibration and will produce correspondingly rapid variations in the flow of the liquid out of the recessed portion 51. An interrupted or pulsating flow is thus very simply obtained and with no moving parts except the vibrating reed.
In Fig. 6, a similar result is obtained by rotatably mounting a rotor in an enlarged portion 61 of a supply pipe 62. The rotor is provided with blades 64 which have close clearance in the casing portion 61 and also in the adjacent part of the pipe 62.
As liquid under pressure flows through this device in the direction of the arrows, the rotor 60 will be rotated at a speed definitely related to the rate of travel of the liquid, and the blades 64- will produce irregularities or slight interruptions in the fiow, so that a pulsating'effect is produced.
With each of the constructions herein shown and described, the main purpose of the invention is attained by providing an interrupted or pulsating flow of both liquids to the combustion chamber, at which they arrive in the form of small drops or are otherwise broken up for more effective mixing.
Having thus described the invention and the advantages thereof, it will be understood that the invention is not to be limited to the details herein disclosed, otherwise than as set forth in the claim, but what is claimed is:
In combustion mechanism for propulsion apparatus, a combustion chamber, means to feed a liquid fuel under pressure to said combustion chamber, means to feed a liquid oxidizer under pressure to said combustion chamber, and separate and additional means to impress a pulsating pressure variation on each of said liquids while under otherwise normal and continuous feeding pressure, said additional means comprising a volute casing, a bladed stator within said casing, a bladed rotor within said stator, means to supply a liquid under pressure to the interior of said rotor and means by which said rotor is rotated by said liquid, and the thickness of the blades in said rotor and stator being substantially equal to the spaces between said blades, so that the periods of liquid flow and flow interruption are substantially equal and each of extremely brief duration.
References Qited in the file of this patent UNITED STATES PATENTS 966,124 Rigg Aug. 2, 1910 10 Goddard Apr. 2, 1946 Wells Dec. 7, 1948 Goddard Mar. 29, 1949 Rosenthal Sept. 13, 1949 Goddard Aug. 8, 1950 Goddard Aug 8, 1950
|Cited Patent||Filing date||Publication date||Applicant||Title|
|US966124 *||Oct 14, 1909||Aug 2, 1910||Archie T Rigg||Spray-burner.|
|US2397659 *||Jul 29, 1942||Apr 2, 1946||Daniel And Florence Guggenheim||Control mechanism for rocket apparatus|
|US2455845 *||May 22, 1944||Dec 7, 1948||Wells Edward P||Rocket|
|US2465525 *||Dec 15, 1943||Mar 29, 1949||Daniel And Florence Guggenheim||Reaction combustion chamber for unconfined charges or detonative fuel fed intermittently to the combustion chamber|
|US2481620 *||Feb 8, 1945||Sep 13, 1949||Skiatron Corp||Device for dispensing liquid fuel into combustion air of furnaces|
|US2518001 *||Jul 26, 1946||Aug 8, 1950||Daniel And Florence Guggenheim||Ring valve construction for combustion chambers|
|US2518003 *||Mar 4, 1948||Aug 8, 1950||Daniel And Florence Guggenheim||Ring valve construction for combustion chambers|
|Citing Patent||Filing date||Publication date||Applicant||Title|
|US3001363 *||Mar 4, 1958||Sep 26, 1961||Jr Joseph G Thibodaux||Spherical solid-propellant rocket motor|
|US5800153 *||Sep 20, 1995||Sep 1, 1998||Mark DeRoche||Repetitive detonation generator|
|U.S. Classification||60/39.81, 60/258, 60/915, 431/1, 60/247, 261/DIG.470, 261/DIG.480, 239/381|
|Cooperative Classification||Y10S261/47, Y10S60/915, F02K9/44, Y10S261/48|