US3402552A

US3402552A - Liquid injection device

Info

Publication number: US3402552A
Application number: US409251A
Authority: US
Inventors: Bringer Heinz
Original assignee: Etat Francais
Current assignee: Etat Francais
Priority date: 1964-01-29
Filing date: 1964-11-05
Publication date: 1968-09-24
Anticipated expiration: 1985-09-24
Also published as: GB1043020A; FR1391928A; DE1258194B

Description

-B Q I QGS 4' H. BRINGER I 3,402,552

LIQUID INJECTION DEVICE Filed Nov. 5, 1964 United States Patent Office 3,402,552 Patented Sept. 24, 1968 3,402,552 LIQUID INJECTION DEVICE Heinz Bringer, Vernon, France, assignor to Etat Francais (French State) represented by the Minister of Armed Forces, Ministerial Delegation for Armament, Direction of Researches and Manufacture of Armament, Laboratory of Ballistic and Aerodynamic Researches, Vernon, France Filed Nov. 5, 1964, Ser. No. 409,251 Claims priority, application France, Jan. 29, 1964, 961,921 1 Claim. (Cl. 60--39.74)

The present invention is concerned with a liquid injection device, notably for liquid-fuel rocket-type power units utilizing a combustion agent and a fuel, characterized in that it comprises a combustion chamber with injection orifices opening into this chamber in the lateral wall thereof, said injection orifices being grouped by pairs and inclined with respect to the lateral surface of the combustion chamber, with the axes of the two orifices of any pair converging to a point where two jets of the same liquid propellants, whether oxidizer or fuel, are thus caused to meet as they are delivered from said two convergent orifices, so as to atomize these liquids at the point of convergence of these two jets, and that the points of convergence of the axes of the pairs of orifices causing the atomization on the one hand of said fuel and on the other hand of said oxidizer alternate along the wall of the combustion chamber in order to homogenize completely the two atomized propellants.

The liquid injection device according to this invention is capable of producing a uniform and efiicient atomization throughout the chamber, thus ensuring an optimum efiiciency.

Various forms of embodiment of this invention will now be described by way of example with reference to the accompanying drawing, in which:

FIGURE 1 is a longitudinal section showing a liquid injection device constructed according to the teachings of this invention;

FIGURE 2 is a longitudinal section showing an alternate form of embodiment of this device;

FIGURE 3 is a fragmentary developed view showing another form of embodiment of this device.

The liquid injection device illustrated in FIGURE 1, designed for a liquid-fuel rocket-type power unit utilizing as propellants an oxidizer and a fuel, comprises a combustion chamber 1 formed inside a substantially cylindrical member or casing 2 closed by a slightly domed or bulged bottom wall 3. This bottom wall 3 is covered by a cap 4 bearing on an annular shoulder 2a formed on the outer periphery of said casing 2. In the center of this cap 3 a port is formed and has fitted therein the outlet end of a feed pipe 5 supplying one of the propellants, whether oxidizer or fuel, to the device.

The cylindrical casing 2 has longitudinal ducts 6 formed in its wall; these ducts 6 open into the space formed between the dorned bottom wall 3 and the cap 4; they are disposed at regular spaced intervals about the longitudinal axis of the device.

Each longitudinal duct 6 communicates through a pair of

injection orifices

7, 8 with the combustion chamber 1. As shown in FIGURE 1, these

injection orifices

7, 8 converge towards each other and their axes meet at a point A. These orifices lead into a groove 11 of substantially trapezoidal cross-sectional contour, formed in the inner wall 2b of the cylindrical casing 2.

Similarly, the second propellant is atomized in the combustion chamber 1 by means of other pairs of

convergent orifices

12, 13 of which the axes meet at a point B, as shown in the right-hand portion of FIGURE 1. The pairs of

injection orifices

12, 13 are also regularly spaced about the longitudinal axis of the combustion chamber 1, and these pairs of orifices alternate with the aforesaid pairs of

injection orifices

7, 8 injecting the first ergol so that the points of intersection or convergence A and B of the two propellants alternate in a same transverse row in the order A,B,A,B,A,

The various pairs of

orifices

12, 13 maybe connected in various manners to a feed pipe supplying the second propellant. Thus, in FIGURE 1 each pair of

orifices

12, 13 open into a longitudinal blind duct 14 open at the bottom and receiving this second propellant which has cooled the combustion chamber beforehand.

Referring now to the second form of embodiment illustrated in FIGURE 2, wherein the injection device comprises three rows of pairs of

injection orifices

7, 8 on the one hand, and 12, 13 on the other hand, the three pairs of injecting

orifices

7 and 8, 7a and 8a, and 7b and 8b injecting the first propellant have their axes disposed in a same common meridian plane, these six orifices opening, as in the case illustrated in FIGURE 1, into a common longitudinal duct 6 connected to the space formed between the domed bottom 3 and the cap 4. On the other hand, the second propellant is fed in this case according to a different procedure. In fact, it will be seen that the three pairs of

orifices

12 and 13, 12a and 13a, 12b and 13b are connected to

separate ducts

15, 16, 17 and 18 leading into an annular chamber 19 connected to a feed pipe 21 supplying this second propellant. In this case too the first liquid propellant is atomized at the points of intersection A of the axes of the

corresponding injection orifices

7 and 8, 7a and 8a, and 7b and 8b, the second liquid propellant being atomized at points B where the axes of the jets issuing from

orifices

12 and 13, 12a and 13a, and 12b and 13b are caused to converge.

According to a modified form of embodiment of this invention, the pairs of

injection orifices

12 and 13, 12a and 13a, and 12b and 13b delivering the second propellant to the combustion chamber may open directly into a common cavity formed in the outer surface of the cylindrical casing 2, these various cavities communicating in turn with the external annular chamber 19 connected to the feed pipe 21 delivering the second liquid propellant.

The number of pairs of injection orifices such as 7 and 8, 12 and 13 in a same row, and the number of these rows are subordinate, of course, to the desired output and atomization for each liquid propellant.

According to another alternate form of embodiment, all the pairs of orifices of a same row may be used for injecting a same propellant; in other words, this row comprises a succession A, A, A, A, of atomizing points, the pairs of orifices of the adjacent row injecting the other propellant; otherwise stated, this adjacent row provides the succession of points B, B, B, B, In this case, the atomizing points B may be located in the same meridian plane at points A, or the atomizing points B may be disposed in a plane intermediate two adjacent meridian planes containing the atomizing points A.

In a modified form of embodiment illustrated in FIG- URE 3 the injection device comprises three rows of pairs of

injection orifices

7, 8 providing an atomizing point A for one of the propellants and of pairs of

injection orifices

12 and 13 providing an atomizing point B for the other propellant. The pairs of

orifices

7, 8 of these three rows communicate with helical ducts 22 and the pairs of

orifices

12, 13 open into similar helical ducts 23. These

helical ducts

22, 23 alternate in the cylindrical casing 2, as shown in FIGURE 3; they are connected to the relevant feed pipes supplying the two liquid propellants. The arrangement illustrated in FIGURE 3 is such that in each row the atomizing points alternate: A, B, A, B, and on the other hand this alternation A, B is also obtained in the axial or longitudinal direction. In this case each atomizing point A orB is surrounded by four atomizing points of the opposite type, i.e., B or A, and thus the atomized liquid propellants are homogenized in a particularly efiicient manner.

Of course, various modifications and variations may be brought to the forms of embodiment of the invention shown and described herein by Way of example, Without departing from the spirit and scope of the invention as set forth in the appended claim.

What I claim is:

1. Liquid injection device, notably for liquid rockettype power units utilizing an oxidizer and a fuel, which comprises fuel and oxidizer supply means, a combustion chamber having a longitudinal axis, a cylindrical lateral wall and a domed bottom wall defining said combustion chamber, injection orifices formed through said cylindrical lateral Wall and opening into said combustion chamber, said injection orifices being grouped by pairs regularly spaced about the longitudinal axis and inclined with respect to the surface of the combustion chamber, each pair of injection orifices communicating with either the fuel supply means or the oxidizer supply means only, the axes of the two injection orifices of any pair being located in the same meridian plane and converging to an atomizing point where the two jets of the same liquid propellant, whether oxidizer or fuel, issuing from said two convergent orifices, are caused to meet, whereby producing the atomization of said liquid at the point of convergence of the References Cited UNITED STATES PATENTS 2,397,834 4/1946 Bowman 6()--39.74 2,523,656 9/1950 Goddard. 2,555,080 4/1951 Goddard 6039.74 2,602,290 7/1952 Goddard 6039.74 2,763,987 9/1956 Kretschmer 6035.6 3,242,668 3/1966 Ellis 6039.74

OTHER REFERENCES Sutton, F. P.: Rocket Propulsion Elements, second edition, Wiley & Sons, Inc., New York, 1956, pages 207, 208 relied on.

MARTIN P. SCHWADRON, Primary Examiner.

D. HART, Assistant Examiner.

Claims

1. LIQUID INJECTION DEVICE, NOTATABLY FOR LIQUID ROCKETTYPE POWER UNITS UTILIZING AN OXIDIZER AND A FUEL, WHICH COMPRISES FUEL AND OXIDIZER SUPPLY MEANS, A COMBUSTION CHAMBER HAVING A LONGITUDINAL AXIS, A CYLINDRICAL LATERAL WALL AND A DOMED BOTTOM WALL DEFINING SAID COMBUSTION CHAMBER, INJECTION ORIFICES FORMED THROUGH SAID CYLINDRICAL LATERAL WALL AND OPENING INTO SAID COMBUSTION CHAMBER, SAID INJECTION ORIFICES BEING GROUPED BY PAIRS REGULARLY SPACED ABOUT THE LONGITUDINAL AXIS AND INCLINED WITH RESPECT TO THE SURFACE OF THE COMBUSTION CHAMBER, EACH PAIR OF INJECTION ORIFICES COMMUNICATING WITH EITHER THE FUEL SUPPLY MEANS OR THE OXIDIZER SUPPLY MEANS ONLY, THE AXES OF THE TWO INJECTION ORIFICES OF ANY PAIR BEING LOCATED IN THE SAME MERIDIAN PLANE AND COVERGING TO AN ATOMIZING POINT WHERE THE TWO JETS OF THE SAME LIQUID PROPELLANT, WHETHER OXIDIZER OR FUEL, ISSUING FROM SAID TWO CONVERGENT ORIFICES, ARE CAUSED TO MEET, WHEREBY PRODUCING THE ATOMIZATION OF SAID LIQUID AT THE POINT OF CONVERGENCE OF THE TWO JETS, THE POINTS OF INTERSECTION OF THE AXES OF THE PAIRS OF ORIFICES WHICH EFFECT THE ATOMIZATION ON THE ONE HAND OF THE LIQUID FUEL AND ON THE OTHER HAND OF THE LIQUID OXIDIZER ALTERNATING IN A SAME PLANE TRANSVERSE TO THE LONGITUDINAL AXIS OF SAID COMBUSTION CHAMBER IN ORDER PROPERLY TO HOMOGENIZE THE THUS ATOMIZED TWO LIQUID PROPELLANTS, AND SAID ATOMIZING POINTS OF ONE PROPELLANT ALTERNATE WITH THE ATOMIZING POINTS OF THE OTHER PROPELLANT IN THE LONGITUDINAL DIRECTION.