JP2004263618A - Injection pipe of combustion apparatus for rocket engine - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide an injection pipe of a combustion apparatus for a rocket engine for eliminating difficulties in manufacturing and setting, and having various injection forms. <P>SOLUTION: The injection pipe 20 is provided with a center cavity 21 opened in a fuel supply side at one end and opened in a combustion chamber side at the other end, an outside space 22 formed outside the center cavity 21 and opened in the fuel supply side at one end, and a plurality of holes arranged in a circumferential direction, formed into an injection port at one end and communicated to the other end of the outside space at the other end. <P>COPYRIGHT: (C)2004,JPO&NCIPI

Description

[0001]
TECHNICAL FIELD OF THE INVENTION
The present invention relates to an injection pipe of a combustion device for a rocket engine.
[0002]
[Prior art]
For example, as shown in Non-Patent Document 1 and FIG. 9, the rocket combustion device includes an injector 1A, a combustion chamber 1B, a nozzle 1C, and the like, and exhausts energy due to a chemical reaction of fuel as a propellant. Thrust is obtained by converting into motion.
[0003]
In the rocket engine combustion device 1, an injector 1 </ b> A including a large number of injection pipes is supplied from a fuel supply device (not shown) to, for example, liquid oxygen (hereinafter referred to as “LOx”) and gaseous hydrogen (hereinafter referred to as “GH 2”). Is injected into a combustion chamber, and LOx and GH2 are finely mixed and burned. This is one of the main factors that determine the performance of a rocket engine.
[0004]
An example of a conventionally used injection tube will be described with reference to FIG.
[0005]
As shown in FIG. 10, the injection tube 10 of the related art forms a central cavity 11 for passing LOx at a speed of 10 to 20 m / S and an annular outer gap 12 for passing GH2 at a speed about 10 times that of LOx. The inner tube 13 and the outer tube 14 have a double-tube annular structure.
[0006]
[Non-patent document 1]
Liquid Oxygen / Hydrogen Testing of a Single Swirl Coaxial Injection Element in a Windowed Combustion Chamber (AIAA 93-1954)
[0007]
[Problems to be solved by the invention]
In the conventional injection tube 10 described above, the annular outer space 12 needs to be very narrow, 0.5 mm or less, and must be concentric with the central cavity 11.
[0008]
It is extremely difficult to manufacture and set such a very narrow annular outer space 12 concentrically with the central cavity 11, and it is possible to eliminate such difficulties in manufacturing and setting and obtain various injection forms. The emergence of possible new injection tubes has been awaited.
[0009]
SUMMARY OF THE INVENTION It is an object of the present invention to provide an injection pipe of a combustion device for a rocket engine, which can eliminate difficulty in manufacturing and setting and can obtain various injection modes.
[0010]
[Means for Solving the Problems]
In order to achieve the above object, the present invention provides an injection pipe of a rocket engine combustion device that injects a propellant supplied from a fuel supply side into a combustion chamber side to burn it.
A central cavity whose one end is open on the fuel supply side and whose other end is open on the combustion chamber side,
An outer space formed outside the central cavity and open at one end on the fuel supply side;
A plurality of holes are provided along the circumferential direction, and one end is provided with an injection port on the combustion chamber side, and the other end is provided with a hole communicating with the other end of the outer space.
[0011]
In the present invention, by adopting a porous structure instead of the conventional double-tube annular structure, the structure is simplified, and it is possible to form the injection port with accuracy by drilling, and in combustion, By flowing LOx passing through the central cavity around GH2 injected from the injection port through the hole, the contact area between GH2 and LOx increases, which promotes atomization and mixing.
[0012]
In the above, the hole may be formed inwardly so as to approach the central cavity. In this case, further, atomization is further promoted by the collision effect of GH2 on LOx, and contact between GH2 and LOx is further increased. It will be stable.
[0013]
In the above, the hole can be formed obliquely so as to rotate along the longitudinal direction. In this case, after further reducing LOx, GH2 and LOx are dispersed by the rotation component toward the outer periphery. Can achieve uniform mixing.
[0014]
In the above, the central cavity can be formed so as to have a taper so that the opening becomes larger as approaching the combustion chamber side. In this case, since the area of the outlet of LOx further expands outward, GH2 and LOx The contact angle is increased, so that the atomization is promoted and the contact is stabilized.
[0015]
In the above, the holes can be formed with different diameters along the circumferential direction, and in this case, the fineness in the circumferential direction and control of the dispersion characteristics can be further achieved.
[0016]
In the above, the central cavity may form a recess on the combustion chamber side. In this case, the recess formed at the outlet of LOx further suppresses attenuation and spread of the injection speed of GH2. And miniaturization is promoted.
[0017]
In the above, the hole may be formed in a plurality of stages along the radial direction, and a recess may be formed on the combustion chamber side of the central cavity. In this case, the recess may be further formed in the recess formed at the outlet of LOx. Since the first stage of miniaturization is performed and the second stage of miniaturization is performed at the outlet, more effective miniaturization and control of mixing GH2 and LOx can be performed.
[0018]
BEST MODE FOR CARRYING OUT THE INVENTION
Hereinafter, an embodiment of an injection pipe of a combustion device for a rocket engine according to the present invention will be described with reference to the drawings.
[0019]
(1st Embodiment)
FIG. 1A is a longitudinal sectional view of the injection pipe of the first embodiment, and FIG. 1B is a front view as viewed from the combustion chamber side. The injection pipe 20 of this embodiment has one end on the fuel supply side. A central cavity 21 opened at the other end side and opened at the combustion chamber side, an outer space 22 formed outside the central cavity 21 and opened at one end side at the fuel supply side, and a plurality of outer gaps are provided along the circumferential direction. On the combustion chamber side, one end forms an injection port 24 and the other end has a hole 23 communicating with the other end of the outer space 22.
[0020]
Here, LOx from a fuel supply device (not shown) is supplied to a central cavity 21, and GH2 is injected from an injection port 24 through a hole 23 through an outer space 22. In the combustion chamber (not shown), LOx and GH2 are finely divided. Combustion.
[0021]
In the present embodiment, a porous structure is used instead of the conventional double-tube annular structure, so that the structure is simplified, and it can be manufactured by drilling from the combustion chamber side, and the processing can obtain accuracy. Thus, it is possible to form an injection port as designed.
[0022]
In the combustion, LOx passing through the central cavity 21 flows around the GH2 injected from the injection port 24 through the hole 23, so that the contact area between the GH2 and the LOx increases, thereby promoting the atomization and mixing. Will be promoted. As a result, good combustion is ensured, and a rocket engine combustion device exhibiting excellent performance is realized.
[0023]
(2nd Embodiment)
FIG. 2A is a longitudinal cross-sectional view of the injection pipe of the second embodiment, and FIG. 2B is a front view as viewed from the combustion chamber side. The injection pipe 30 of this embodiment has one end on the fuel supply side. A central cavity 31 opened at the other end and opened at the combustion chamber side, an outer space 32 formed outside the central cavity 31 and opened at one end at the fuel supply side, and a plurality of outer gaps are provided along the circumferential direction. On the combustion chamber side, one end forms an injection port 34, and the other end communicates with the other end of the outer space 32, and has an inwardly formed hole 33 approaching the central cavity 31.
[0024]
Here, LOx from a fuel supply device (not shown) is supplied to a central cavity 31, and GH2 is injected from an injection port 34 through an inwardly formed hole 33 through an outer space 32, and LOx is injected into a combustion chamber (not shown). And GH2 are finely mixed and burnt.
[0025]
In the present embodiment, similarly to the first embodiment, a porous structure is used instead of the conventional double-tube annular structure, so that the structure is simplified, and it can be manufactured by drilling from the combustion chamber side. Since it is possible to obtain accuracy, it is possible to form an injection port as designed.
[0026]
Further, as in the first embodiment, in combustion, LOx passing through the central cavity 31 flows around the GH2 injected from the injection port 34 through the hole 33, so that the contact area between the GH2 and the LOx is reduced. Thus, the atomization and the mixing are promoted.
[0027]
Further, in this embodiment, since the hole 33 is formed inward so as to approach the central cavity 31, the GH2 injected from the inward jet port 34 collides with LOx coming out of the central cavity 31. Due to the collision impact effect, GH2 and LOx are further atomized, and the contact between GH2 and LOx is stabilized. As a result, good combustion is ensured, and a rocket engine combustion device exhibiting excellent performance is realized.
[0028]
(Third embodiment)
FIG. 3A is a longitudinal sectional view of an injection pipe according to a third embodiment, FIG. 3B is a front view as viewed from a combustion chamber side, and FIG. 4 is a schematic perspective view of the same embodiment. The injection pipe 40 has a central cavity 41 having one end opened on the fuel supply side and the other end opened on the combustion chamber side, and an outer gap formed outside the central cavity 41 and one end opened on the fuel supply side. 42, a plurality of which are provided along the circumferential direction, and one end side forms an injection port 44 on the combustion chamber side, and the other end side communicates with the other end side of the outer space 42 and is slanted so as to turn along the longitudinal direction. And a hole 43 formed.
[0029]
Here, LOx from a fuel supply device (not shown) is supplied to the central cavity 41, and GH2 is also injected from the injection port 44 through the hole 43 through the outer space 42, and LOx and GH2 are finely divided in a combustion chamber (not shown). Combustion.
[0030]
In the present embodiment, similarly to the first embodiment, a porous structure is used instead of the conventional double-tube annular structure, so that the structure is simplified, and it can be manufactured by drilling from the combustion chamber side. Since it is possible to obtain accuracy, it is possible to form an injection port as designed.
[0031]
Further, as in the first embodiment, in combustion, LOx passing through the central cavity 41 flows around the GH2 injected from the injection port 44 through the hole 43, so that the contact area between the GH2 and LOx is reduced. Thus, the atomization and the mixing are promoted.
[0032]
Further, in the present embodiment, since the hole 43 is formed obliquely so as to turn along the longitudinal direction, after making the LOx fine at the ejection port 44 by the turned hole 43, the hole 43 is turned to the outer peripheral side by the turning component. Can achieve uniform mixing of GH2 and LOx. As a result, good combustion is ensured, and a rocket engine combustion device exhibiting excellent performance is realized.
[0033]
(Fourth embodiment)
FIG. 5A is a longitudinal sectional view of the injection pipe of the fourth embodiment, and FIG. 4B is a front view as viewed from the combustion chamber side. The injection pipe 50 of this embodiment has one end on the fuel supply side. A central cavity 51 opened at the other end side and opened at the combustion chamber side, an outer space 52 formed outside the central cavity 51 and opened at one end side at the fuel supply side, and a plurality of outer gaps are provided along the circumferential direction. A hole 53 having one end forming an injection port 54 on the combustion chamber side and the other end communicating with the other end of the outer space 52 is provided, and the combustion chamber side of the central cavity 51 is opened as approaching the combustion chamber side. The taper portion 55 is formed so as to be larger.
[0034]
Here, LOx from a fuel supply device (not shown) is supplied to the central cavity 51, and GH2 is injected from the injection port 54 through the hole 53 through the outer space 52, and the LOx and GH2 are finely divided in the combustion chamber (not shown). Combustion.
[0035]
In the present embodiment, similarly to the first embodiment, a porous structure is used instead of the conventional double-tube annular structure, so that the structure is simplified, and it can be manufactured by drilling from the combustion chamber side. Since it is possible to obtain accuracy, it is possible to form an injection port as designed.
[0036]
Further, in the present embodiment, as in the first embodiment, in combustion, LOx passing through the central cavity 51 flows around the GH2 injected from the injection port 54 through the hole 53, and thereby the GH2 and the GH2 are discharged. The contact area with LOx is increased, and promotion of atomization and mixing are promoted.
[0037]
Further, in the present embodiment, since the central cavity 51 forms the tapered portion 55 so that the opening becomes larger as approaching the combustion chamber side, the area of the outlet of LOx expands outward, so that GH2 and LOx The angle of contact is increased, so that the atomization is promoted and the contact is stabilized. As a result, good combustion is ensured, and a rocket engine combustion device exhibiting excellent performance is realized.
[0038]
(Fifth embodiment)
FIG. 6A is a longitudinal sectional view of an injection pipe according to a fifth embodiment, and FIG. 5B is a front view as viewed from a combustion chamber side. A central cavity 61 opened at the other end side and opened at the combustion chamber side, an outer space 62 formed outside the central cavity 61 and opened at one end side at the fuel supply side, and a plurality of outer gaps are provided along the circumferential direction. A large-diameter hole in which one end forms a large-diameter injection port 64 and a small-diameter injection port 65 on the combustion chamber side, and the other end communicates with the other end of the outer cavity 62 and is formed inward so as to approach the central cavity 61. 63, a small-diameter hole (not shown).
[0039]
Here, LOx from a fuel supply device (not shown) is supplied to the central cavity 61, and GH2 also passes through a large-diameter hole 63 and a small-diameter hole (not shown) through an outer space 62 from a large-diameter injection port 64 and a small-diameter injection port 65. Then, LOx and GH2 are finely mixed and burned in a combustion chamber (not shown).
[0040]
In the present embodiment, similarly to the first embodiment, a porous structure is used instead of the conventional double-tube annular structure, so that the structure is simplified, and it can be manufactured by drilling from the combustion chamber side. Since it is possible to obtain accuracy, it is possible to form an injection port as designed.
[0041]
In the same manner as in the first embodiment, in the combustion, the GH2 injected from the large-diameter injection port 64 and the small-diameter injection port 65 through the large-diameter hole 63 and the small-diameter hole (not shown) passes through the central cavity 61. The flow of LOx increases the contact area between GH2 and LOx, and promotes atomization and mixing.
[0042]
Further, in the present embodiment, since the holes are formed with different diameters along the circumferential direction, it is possible to miniaturize in the circumferential direction and control the dispersion characteristics. As a result, good combustion is ensured, and a rocket engine combustion device exhibiting excellent performance is realized.
[0043]
(Sixth embodiment)
FIG. 7A is a longitudinal sectional view of an injection pipe according to a sixth embodiment, and FIG. 7B is a front view as viewed from a combustion chamber side. A central cavity 71 which is open at the other end and opens at the combustion chamber side is formed, and a recess 75 is formed in the central cavity 71 on the combustion chamber side. Further, an outer space 72 formed outside the central cavity 71 and having one end side opened on the fuel supply side, and a plurality of injection holes 74 formed in the end face of the plurality of recesses 75 provided along the circumferential direction and the other end side formed. A hole 73 communicating with the other end of the outer space 72 is provided.
[0044]
Here, LOx from a fuel supply device (not shown) is supplied to a central cavity 71, and GH2 is injected from an injection port 74 through a hole 73 through an outer space 72, and LOx and GH2 are finely divided in a combustion chamber (not shown). Combustion.
[0045]
In the present embodiment, a porous structure is used instead of the conventional double-tube annular structure, so that the structure is simplified, and it can be manufactured by drilling from the combustion chamber side, and the processing can obtain accuracy. Thus, it is possible to form an injection port as designed.
[0046]
In the combustion, LOx passing through the central cavity 71 flows around the GH2 injected from the injection port 74 through the hole 73, so that the contact area between the GH2 and the LOx increases, which promotes atomization and mixing. Will be promoted.
[0047]
Further, since the recessed portion 75 is formed in the center cavity 71 on the combustion chamber side, the attenuation and spread of the injection speed of the GH2 injected from the injection port 74 can be suppressed in the recessed portion 75, and Promotion is achieved. As a result, good combustion is ensured, and a rocket engine combustion device exhibiting excellent performance is realized.
[0048]
(Seventh embodiment)
FIG. 8A is a longitudinal sectional view of the injection pipe of the seventh embodiment, and FIG. 8B is a front view as viewed from the combustion chamber side. In the injection pipe 80 of this embodiment, one end is located on the fuel supply side. A central cavity 81 opened at the other end and opened at the combustion chamber side, an outer cavity 82 formed outside the central cavity 81 and opened at one end at the fuel supply side, and a plurality of circumferentially provided circumferentially. On the combustion chamber side, one end side has injection ports 84 and 86, and the other end side has holes 83 and 85 formed in two stages in the radial direction communicating with the other end side of the outer space 82. A recess 87 is formed on the combustion chamber side. Here, the holes 83 and 85 are formed alternately in the circumferential direction.
[0049]
Here, LOx from a fuel supply device (not shown) is supplied to a central cavity 81, and GH2 is similarly injected from an injection port 84 through a hole 83 through an outer space 82, and LOx and GH2 are finely divided in a combustion chamber (not shown). Combustion.
[0050]
In the present embodiment, a porous structure is used instead of the conventional double-tube annular structure, so that the structure is simplified, and it can be manufactured by drilling from the combustion chamber side, and the processing can obtain accuracy. Thus, it is possible to form an injection port as designed.
[0051]
In the combustion, LOx passing through the central cavity 81 flows around the GH2 injected from the injection ports 84 and 86 through the holes 83 and 85 formed in two stages in the radial direction, so that the GH2 and the LOx are separated. The contact area increases, and promotion of atomization and mixing are promoted.
[0052]
Further, since the holes 83 and 85 are formed in two stages in the radial direction and the recess 87 is formed on the combustion chamber side of the central cavity 81, the first stage miniaturization is performed at the recess 87 formed at the outlet of LOx. Is performed, and the second-stage refinement is performed at the outlet, so that it is possible to more effectively refine and control the mixing of GH2 and LOx. As a result, good combustion is ensured, and a rocket engine combustion device exhibiting excellent performance is realized.
[0053]
(Other embodiments)
The present invention is not limited to the above and illustrated embodiments, and adoption of the porous structure shown in the first embodiment constitutes a solution means of the present invention, and is shown in the second to seventh embodiments. One or more of the various aspects described above can be implemented in combination, and the degree of freedom of the injection mode can be further increased.
[0054]
【The invention's effect】
As described above, according to the present invention, by adopting a porous structure instead of the conventional double-tube annular structure, the structure can be simplified, and the injection port can be formed with accuracy by drilling. At the same time, in the combustion, LOx flowing through the central cavity flows around the GH2 injected from the injection port through the hole, thereby increasing the contact area between the GH2 and the LOx, thereby promoting the atomization and the mixing. Accordingly, it is possible to provide an injection pipe of a combustion device for a rocket engine in which the degree of freedom of the injection mode is increased.
[Brief description of the drawings]
FIG. 1 is a diagram showing a configuration of an injection pipe of a combustion device for a rocket engine according to a first embodiment of the present invention.
FIG. 2 is a diagram showing a configuration of an injection pipe of a combustion device for a rocket engine according to a second embodiment of the present invention.
FIG. 3 is a diagram showing a configuration of an injection pipe of a rocket engine combustion device according to a third embodiment of the present invention.
FIG. 4 is a schematic perspective view of the embodiment.
FIG. 5 is a diagram showing a configuration of an injection pipe of a combustion device for a rocket engine according to a fourth embodiment of the present invention.
FIG. 6 is a diagram showing a configuration of an injection pipe of a rocket engine combustion device according to a fifth embodiment of the present invention.
FIG. 7 is a diagram showing a configuration of an injection pipe of a rocket engine combustion device according to a sixth embodiment of the present invention.
FIG. 8 is a diagram showing a configuration of an injection pipe of a rocket engine combustion device according to a seventh embodiment of the present invention.
FIG. 9 is a diagram showing a schematic configuration of a rocket engine combustion device.
FIG. 10 is a diagram showing a configuration of an example of an injection pipe of a conventional rocket engine combustion device.
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 1 ... Combustion device for rocket engines, 1A ... Injector, 1B ... Combustion chamber, 1C ... Nozzle, 20, 30, 40, 50, 60, 70, 80 ... Injection pipe, 21, 31, 41, 51, 61, 71 , 81 ... central cavity, 22, 32, 42, 52, 62, 72, 82 ... outer space, 23, 33, 43, 53, 63, 73, 83, 85 ... holes, 24, 34, 44, 54, 64 , 65, 74, 84, 86 ... injection port, 55 ... taper part, 75, 87 ... recess part.

Claims (7)

In an injection pipe of a rocket engine combustion device for injecting fuel supplied from a fuel supply side to a combustion chamber side and burning it,
A central cavity whose one end is open on the fuel supply side and whose other end is open on the combustion chamber side,
An outer space formed outside the central cavity and open at one end on the fuel supply side;
A plurality of holes provided along the circumferential direction, wherein one end of the combustion chamber side has an injection port, and the other end has a hole communicating with the other end of the outer space. The injection pipe of the device. The injection pipe of a combustion device for a rocket engine according to claim 1, wherein the hole is formed inward so as to approach the central cavity. The injection pipe of a combustion device for a rocket engine according to claim 1 or 2, wherein the hole is formed obliquely so as to turn along a longitudinal direction. The injection pipe of a rocket engine combustion device according to any one of claims 1 to 3, wherein the center cavity is tapered so that an opening becomes larger as approaching the combustion chamber side. The injection pipe of a combustion device for a rocket engine according to any one of claims 1 to 4, wherein the holes have different diameters along the circumferential direction. The injection pipe of a combustion device for a rocket engine according to any one of claims 1 to 5, wherein the central cavity has a recess formed on the combustion chamber side. The rocket engine combustion according to any one of claims 1 to 6, wherein the hole is formed in a plurality of stages along a radial direction, and a recess is formed on the combustion chamber side of the central cavity. The injection pipe of the device.

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