Combustion test device and test method for double-component nozzle of engine

Abstract

The invention discloses a combustion test device and test method for a double-component nozzle of an engine, and the device comprises an oxidant filler neck which is communicated with one end of an inner sleeve, and the other end of the inner sleeve is provided with a first nozzle installation hole. An oxidizing agent inlet section of the two-component nozzle is mounted in the first nozzle mounting hole, so that the oxidizing agent filler neck can be communicated with the oxidizing agent inlet section; the inner sleeve is coaxially sleeved with an outer sleeve, the side wall of the outer sleeve is perpendicularly communicated with the fuel filler neck, a cover plate is arranged at the end of the outer sleeve, a second nozzle mounting hole is coaxially formed in the cover plate, and the fuel inlet section of the double-component nozzle is mounted in the second nozzle mounting hole so that the fuel filler neck can be communicated with the fuel holes. According to the engine two-component nozzle testing device, an all-welded inner and outer sleeve structure is adopted, an oxidizing agent and fuel can be simply and effectively prevented from entering the two-component nozzle to be mixed, and the technical problem that in the prior art, in the testing process, fuel is likely to enter an oxidizing agent cavity to cause ablation or explosion can be effectively solved.

Description

Technical Field

[0001] The present invention belongs to the field of liquid rocket engines, relates to a bi-propellant nozzle, and particularly relates to a combustion test device and test method for a bi-propellant nozzle of an engine. Background Art

[0002] The thrust chamber nozzle of a liquid rocket engine is the smallest unit for mixing and burning propellants. The nozzle structure largely determines the combustion completeness and combustion stability of the propellants. Through single-nozzle combustion experiments, the influence of the nozzle on combustion stability can be obtained, so as to select appropriate nozzle structure parameters. The single-nozzle combustion test is carried out at low pressure, and has the characteristics of simple operation, low cost and low danger. Through this test, the correctness of theoretical calculations can be verified, the structure size of the nozzle can be determined, so that the development cost can be reduced, the research and development funds can be reduced, and the development risk can be reduced.

[0003] At present, the injector of the thrust chamber of a liquid rocket engine often uses a bi-propellant nozzle. The thrust chamber of a liquid rocket engine requires the bi-propellant nozzle to have high combustion efficiency and high combustion stability. Therefore, a nozzle combustion test device is needed to evaluate the combustion characteristics of the nozzle and obtain the optimal structure of the bi-propellant nozzle. Summary of the Invention

[0004] Aiming at the deficiencies of the existing technology, the purpose of the present invention is to provide a combustion test device and test method for a bi-propellant nozzle of an engine, so as to solve the technical problem that fuel is likely to enter the oxidizer chamber during the test process, causing ablation or explosion in the prior art.

[0005] In order to solve the above technical problems, the present invention is implemented by adopting the following technical solutions:

[0006] A combustion test device for a bi-propellant nozzle of an engine, including an oxidizer connection nozzle, the oxidizer connection nozzle is connected to one end of an inner sleeve, and the other end of the inner sleeve is provided with a first nozzle installation hole for installing the oxidizer inlet section of the bi-propellant nozzle, so that the oxidizer connection nozzle can be connected to the oxidizer inlet section.

[0007] An outer sleeve is coaxially sleeved outside the inner sleeve. The side wall of the outer sleeve is vertically connected to a fuel connection nozzle. One end of the outer sleeve is closed, and a cover plate is provided at the other end of the outer sleeve. A second nozzle installation hole is coaxially provided on the cover plate for installing the fuel inlet section of the bi-propellant nozzle, so that the fuel connection nozzle can be connected to a plurality of fuel holes provided on the fuel inlet section.

[0008] The present invention also has the following technical features:

[0009] Two support plates are provided on the barrel of the outer sleeve, and the two support plates are symmetrically arranged with the fuel connection nozzle as the axis of symmetry.

[0010] The two support plates are located on the side close to the cover plate between the fuel nozzle and the cover plate.

[0011] The number of the fuel holes is four.

[0012] The present invention also protects a combustion test method for a dual-component nozzle of an engine. The method uses the combustion test device for a dual-component nozzle of an engine according to any one of claims 1 to 4;

[0013] The method specifically includes the following steps:

[0014] Step 1: Taking the dual-component nozzle as the test object, both ends of the dual-component nozzle are open, and the inner end of the oxidant inlet section and the inner end of the fuel inlet section of the dual-component nozzle are coaxially connected through a nozzle housing weld; the outer end of the oxidant inlet section extends into the cylinder body of the inner sleeve, and the outer end of the fuel inlet section is flush with the outer surface of the cover plate;

[0015] Step 2: Passing the oxidant through the oxidant nozzle and into the dual-component nozzle through the inner sleeve;

[0016] Step 3: Passing the fuel through the fuel nozzle, through the outer sleeve and the fuel holes, and into the dual-component nozzle, ensuring that the oxidant in Step 1 enters the dual-component nozzle before the fuel in Step 2;

[0017] Step 4: Mixing the oxidant in Step 1 and the fuel in Step 2 in the dual-component nozzle and then entering the combustion chamber, and performing ignition combustion in the combustion chamber.

[0018] Compared with the prior art, the present invention has the following technical effects:

[0019] (Ⅰ) The combustion test device for a dual-component nozzle of an engine proposed by the present invention adopts a fully welded inner and outer sleeve structure, which can simply and effectively organize the oxidant and fuel to enter the dual-component nozzle for mixing. When the oxidant is oxygen and the fuel is kerosene, the weld position avoids the weak points, can prevent kerosene leakage, and avoid kerosene from entering the oxidant chamber and causing ablation or explosion.

[0020] (Ⅱ) The combustion test device for a dual-component nozzle of an engine proposed by the present invention is applicable to all dual-component nozzles and has universality.

[0021] (Ⅲ) The test method for the combustion test of a dual-component nozzle of an engine proposed by the present invention can prevent the fuel from entering the oxidant chamber during the starting ignition process and avoid deflagration of the fuel in the oxidant chamber. Description of the Drawings

[0022] Figure 1 It is a schematic front view structure diagram of the combustion test device for a dual-component nozzle of an engine.

[0023] Figure 2 It is a schematic side view structure diagram of a combustion test device for a dual-component nozzle of an engine.

[0024] Figure 3 It is a schematic sectional view structure diagram of a combustion test device for a dual-component nozzle of an engine.

[0025] The meanings of each label in the figure are as follows: 1 - oxidizer connection nozzle, 2 - inner sleeve, 3 - first nozzle mounting hole, 4 - dual-component nozzle, 5 - outer sleeve, 6 - fuel connection nozzle, 7 - cover plate, 8 - second nozzle mounting hole, 9 - support plate.

[0026] 401 - oxidizer inlet section, 402 - fuel inlet section, 403 - nozzle housing weld, 404 - fuel holes.

[0027] The following further elaborates on the specific content of the present invention in conjunction with embodiments. Specific Embodiments

[0028] It should be noted that the equipment and components used in the present invention, unless otherwise specified, are all equipment and components known in the prior art. Each component in the present invention is made of stainless steel material.

[0029] Complying with the above technical solutions, the following gives specific embodiments of the present invention. It should be noted that the present invention is not limited to the following specific embodiments, and all equivalent transformations made on the basis of the technical solutions of this application fall within the protection scope of the present invention.

[0030] Embodiment:

[0031] This embodiment proposes a combustion test device for a dual-component nozzle of an engine, including an oxidizer connection 1, as Figures 1 to 3 shown, the oxidizer connection nozzle 1 is connected to one end of the inner sleeve 2, and the other end of the inner sleeve 2 is provided with a first nozzle mounting hole 3 for mounting the oxidizer inlet section 401 of the dual-component nozzle 4, so that the oxidizer connection nozzle 1 can be connected to the oxidizer inlet section 401.

[0032] As Figures 1 to 3 shown, an outer sleeve 5 is coaxially sleeved outside the inner sleeve 2. The side wall of the outer sleeve 5 is vertically connected to the fuel connection nozzle 6. One end of the outer sleeve 5 is closed, and a cover plate 7 is provided at the other end of the outer sleeve 5. A second nozzle mounting hole 8 is coaxially provided on the cover plate 7 for mounting the fuel inlet section 402 of the dual-component nozzle 4, so that the fuel connection nozzle 6 can be connected to a plurality of fuel holes 404 provided on the fuel inlet section 402.

[0033] Specifically, in this embodiment, an oxidizer connection nozzle 1 and an inner sleeve 2 form an oxidizer channel, and a fuel connection nozzle 6 and an outer sleeve 5 form a fuel channel. The oxidizer channel and the fuel channel can separate the oxidizer and the fuel.

[0034] Preferably, in this embodiment, the end faces of the inner sleeve 2 and the outer sleeve 5 are thickened, which can improve the welding quality of the welds between the oxidizer connection nozzle 1 and the inner sleeve 2, and between the fuel connection nozzle 6 and the outer sleeve 5. To reduce the number of welds, the fuel inlet section 402 of the cover plate 7 and the dual-component nozzle 4 can be integrally processed.

[0035] Preferably, in this embodiment, as Figure 1 shown, two support plates 9 are provided on the barrel of the outer sleeve 5, and the two support plates 9 are symmetrically arranged with respect to the fuel connection nozzle 6.

[0036] Preferably, in this embodiment, as Figure 1 shown, the two support plates 9 are located on the side close to the cover plate 7 between the fuel connection nozzle 6 and the cover plate 7.

[0037] Preferably, in this embodiment, the two support plates 9 are 180° apart, and the two support plates 9 are respectively 90° away from the fuel connection nozzle 6. The two support plates 9 are arranged alternately with the fuel connection nozzle 6 and do not interfere with each other. The support plates 9 are used to fix the combustion test device of the engine dual-component nozzle on the combustion chamber.

[0038] Preferably, in this embodiment, the oxidizer inlet section 401 and the fuel inlet section 402 are welded together in sequence, the fuel inlet section 402 and the cover plate 7 are welded together, the oxidizer inlet section 401 and the inner sleeve 2 are welded together, the cover plate 7 and the outer sleeve 5 are welded together, the outer sleeve 5 and the inner sleeve 2 are welded together, the outer sleeve 5 and the fuel connection nozzle 6 are welded together, the inner sleeve 2 and the oxidizer connection nozzle 1 are welded together, and finally the outer sleeve 5 and the two support plates 9 are welded together respectively.

[0039] Preferably, in this embodiment, the number of fuel holes 404 is four.

[0040] Specifically, in this embodiment, a combustion test method for an engine dual-component nozzle. When the combustion test device of the engine dual-component nozzle is working, the method specifically includes the following steps:

[0041] Step 1, taking the dual-component nozzle 4 as the test object, both ends of the dual-component nozzle 4 are open, and the inner ends between the oxidizer inlet section 401 and the fuel inlet section 402 of the dual-component nozzle 4 are coaxially connected through a nozzle housing weld 403; the outer end of the oxidizer inlet section 401 extends into the barrel of the inner sleeve 2, and the outer end of the fuel inlet section 402 is flush with the outer surface of the cover plate 7;

[0042] Step 2: Feed the oxidizer through the oxidizer connection nozzle 1, via the inner sleeve 2, into the dual-component nozzle 4;

[0043] Step 3: Feed the fuel through the fuel connection nozzle 6, via the outer sleeve 5 and the fuel hole 404, into the dual-component nozzle 4, ensuring that the oxidizer in Step 1 enters the dual-component nozzle 4 before the fuel in Step 2;

[0044] Step 4: Mix the oxidizer in Step 1 and the fuel in Step 2 in the dual-component nozzle 4 and then feed them into the combustion chamber. During the experiment, the oxidizer should enter the dual-component nozzle 4 before the fuel. After mixing in the dual-component nozzle 4 and entering the combustion chamber, ignition combustion is carried out.

Claims

1. A combustion test device for a dual-component nozzle of an engine, comprising an oxidant connection nozzle (1), characterized in that, The described oxidizer connection nozzle (1) is connected to one end of the inner sleeve (2). The other end of the inner sleeve (2) is provided with a first nozzle mounting hole (3) for mounting the oxidizer inlet section (401) of the dual-component nozzle (4), so that the oxidizer connection nozzle (1) can be connected to the oxidizer inlet section (401). The outer sleeve (5) is coaxially sleeved outside the inner sleeve (2). The side wall of the outer sleeve (5) is perpendicularly connected to the fuel connection nozzle (6). One end of the outer sleeve (5) is closed, and a cover plate (7) is provided at the other end of the outer sleeve (5). A second nozzle mounting hole (8) is coaxially provided on the cover plate (7) for mounting the fuel inlet section (402) of the dual-component nozzle (4), so that the fuel connection nozzle (6) can be connected to a plurality of fuel holes (404) provided on the fuel inlet section (402).

2. The combustion test device for the dual-component nozzle of the engine according to claim 1, characterized in that, Two support plates (9) are provided on the barrel of the outer sleeve (5), and the two support plates (9) are symmetrically arranged with respect to the fuel connection nozzle (6) as the axis of symmetry.

3. The combustion test device for the dual-component nozzle of the engine according to claim 2, characterized in that, The two support plates (9) are located on the side close to the cover plate (7) between the fuel connection nozzle (6) and the cover plate (7).

4. The combustion test device for the dual-component nozzle of the engine according to claim 1, characterized in that, The number of the fuel holes (404) is four.

5. A combustion test method for a dual-component nozzle of an engine, characterized in that, This method uses the combustion test device for the engine dual-component nozzle as described in any one of claims 1 to 4. This method specifically includes the following steps: Step 1: Taking the dual-component nozzle (4) as the test object, both ends of the dual-component nozzle (4) are open. The inner end of the oxidizer inlet section (401) of the dual-component nozzle (4) is coaxially connected to the inner end of the fuel inlet section (402) through a nozzle housing weld (403). The outer end of the oxidizer inlet section (401) extends into the barrel of the inner sleeve (2), and the outer end of the fuel inlet section (402) is flush with the outer surface of the cover plate (7). Step 2: Introduce the oxidizer into the dual-component nozzle (4) through the oxidizer connection nozzle (1) and the inner sleeve (2). Step 3: Introduce the fuel into the dual-component nozzle (4) through the fuel connection nozzle (6), the outer sleeve (5) and the fuel holes (404), ensuring that the oxidizer in Step 1 enters the dual-component nozzle (4) before the fuel in Step 2. Step 4: Mix the oxidizer in Step 1 and the fuel in Step 2 in the dual-component nozzle (4) and then enter the combustion chamber for ignition and combustion in the combustion chamber.

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