Gas-liquid injector and gas-liquid rocket

Abstract

The present invention discloses a gas-liquid injector, comprising: a pintle-type inner nozzle, a ceramic sleeve, and an outer nozzle. The inner nozzle of the present invention serves as a discharge anode, and the outer nozzle serves as a cathode, generating a high-temperature environment to gasify the liquid fuel, and the combustible gas and the combustion-supporting gas move in opposite directions and collide to be fully mixed, thereby achieving the most efficient gaseous mixed combustion; the present invention abuts the first flange with a convex ring at the upper end of the outer nozzle, the ceramic sleeve and the inner nozzle abut the second flange, and tightens the long bolts to fix the second flange and the first flange, so that the injector is fixed and formed as a whole, so the present invention has a relatively simple structure, and the installation process is relatively simplified, avoiding redundant design.

Description

Technical Field

[0001] The invention relates to a rocket injector. Background Art

[0002] In liquid rockets and gas-liquid rocket engines, the injector is a device that organizes the atomization and mixing of the propellant. After efficient atomization and mixing, the propellant produces efficient and stable combustion in the combustion chamber, then expands and accelerates in the nozzle, and then is ejected at the nozzle outlet as a high-speed jet to form a driving force for the rocket to fly. Therefore, the structural quality of the injector directly determines the performance of the rocket engine. Traditional liquid rocket engine injectors are generally composed of dozens or hundreds of nozzle units, which are usually pintle type, centrifugal type, direct current type or mutual impact type nozzles, etc., and often have the disadvantages of complex structure, high production cost, and long manufacturing cycle. And the function is single, only liquid propellant or gas-liquid mixing, so the present invention makes improvements to the injector, has diversified performance, and has a simple structure and is easy to install. Summary of the invention

[0003] In order to overcome the above-mentioned shortcomings, the present invention aims to provide a technical solution that can solve the above-mentioned problems.

[0004] A gas-liquid injector, comprising: a pintle-type inner nozzle, a ceramic sleeve, and an outer nozzle; the inner nozzle is used to transport liquid fuel, and a tangential spray hole is provided at the lower end thereof; the upper end of the ceramic sleeve is coaxially sleeved on a limit ring in the middle section of the inner nozzle; a cavity for transporting gas is formed between the lower end of the ceramic sleeve and the lower end of the inner nozzle; a tangential air inlet is also provided at the lower end of the ceramic sleeve, and the air outlet direction of the air inlet is opposite to the injection direction of the spray hole, and the bottom of the ceramic sleeve is connected to the top of the outer nozzle; the inner nozzle is electrically connected to the positive electrode of a high-voltage power supply, and the outer nozzle is electrically connected to the negative electrode of the high-voltage power supply;

[0005] Preferably, the outer circumference of the middle section of the inner nozzle is a large diameter end, and the outer circumference of the lower end is a small diameter end;

[0006] Preferably, a step is provided on the inner circumference of the ceramic sleeve, and the step limits the downward movement of the upper end of the nozzle;

[0007] Preferably, the inner nozzle and the outer nozzle are both made of stainless steel;

[0008] Preferably, the top end of the inner nozzle is sealed and connected to the fuel storage chamber of the rocket through a fuel pipe;

[0009] Preferably, an annular first flange is provided on the outer side of the upper end of the outer nozzle, and the first flange is folded along the circumference;

[0010] Preferably, a second flange is provided above the ceramic sleeve and the inner nozzle, and the second flange is sealed and connected to the first flange fold by long bolts to form an oxidant chamber;

[0011] Preferably, the second flange is a ceramic structure;

[0012] The present invention also provides a gas-liquid rocket, comprising the gas-liquid injector described in any one of the above.

[0013] Compared with the prior art, the advantages of the present invention are:

[0014] The inner nozzle of the present invention serves as a discharge anode and the outer nozzle serves as a cathode, generating a high temperature environment to gasify the liquid fuel. The combustible gas and the combustion-supporting gas move in opposite directions and collide with each other to be fully mixed, thereby achieving the most efficient gaseous mixed combustion.

[0015] The present invention has a convex ring at the upper end of the outer nozzle abutting against the first flange, a ceramic sleeve and an inner nozzle abutting against the second flange, and tightening long bolts to fix the second flange and the first flange, so that the injector is fixed as a whole. Therefore, the present invention has a relatively simple structure and a simplified installation process, avoiding redundant design.

[0016] Additional aspects and advantages of the present invention will be given in part in the following description and in part will be obvious from the following description, or will be learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0018] Figure 1 It is a structural schematic diagram of the present invention.

[0019] Figure 2 yes Figure 1 Section view along line AA.

[0020] Figure 3 yes Figure 1 Sectional view along the BB line. DETAILED DESCRIPTION

[0021] The technical solutions in the embodiments of the present invention are described clearly and completely below. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0022] In the description of the present invention, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. indicate directions or positional relationships based on the directions or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, they cannot be understood as limitations on the present invention.

[0023] In addition, in the description of the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", etc. should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, it can also be the internal communication of two components, it can be a wireless connection, or it can be a wired connection. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0024] In addition, the technical features involved in the different embodiments of the present invention described later can be combined with each other as long as they do not conflict with each other.

[0025] See also Figure 1-2 In an embodiment of the present invention, a gas-liquid injector includes: a pintle type inner nozzle 1, a ceramic sleeve 2, and an outer nozzle 3; the pintle type inner nozzle 1 is mainly used for injecting liquid fuel, the outer nozzle 3 is mainly used for injecting combustion-supporting gas, such as oxidant or air, and the ceramic sleeve 2 is mainly used for insulation between the above two.

[0026] As a further explanation of the present invention, the inner nozzle 1 serves as a discharge anode and the outer nozzle 3 serves as a cathode. When the inner nozzle 1 is connected to a high voltage power supply, the inner nozzle 1 is at a high potential, and a radial strong electric field is formed between the inner nozzle 1 and the outer nozzle 3, so that the gas molecules are ionized, ions and free electrons are generated, and a high-heat plasma is formed.

[0027] As a further illustration of the present invention, plasma discharge generates high temperature, causing the temperature of the inner nozzle 1 to rise sharply. The liquid fuel inside the inner nozzle 1 can absorb the heat of the inner nozzle 1, causing the inner nozzle 1 to cool down quickly, effectively preventing the inner nozzle 1 from ablation.

[0028] At the same time, the heat vaporizes part of the fuel. When the gas-liquid mixed fuel is ejected from the tangential nozzle hole 11, it hits the inner wall of the outer nozzle 3, cooling the outer nozzle 3 and effectively preventing the outer nozzle 3 from ablation. In addition, the plasma heat promotes the full vaporization of the fuel.

[0029] As a further illustration of the present invention, Figure 2 As shown, the upper end of the ceramic sleeve 2 is coaxially sleeved on the limiting ring 12 at the middle end of the inner nozzle 1, and the cavity for conveying the combustion-supporting gas formed between the lower end of the ceramic sleeve 2 and the lower end of the inner nozzle 1 provides a specific space for the flow of the combustion-supporting gas. Figure 3 As shown, the tangential air inlet 21 at the lower end of the ceramic sleeve 2 is opened along the tangential direction of the circumference of the ceramic sleeve 2, so that the combustion-supporting gas has a tangential velocity and kinetic energy when entering, thereby forming a cyclone state when entering the ceramic sleeve 2.

[0030] As a further illustration of the present invention, Figure 2 and Figure 3 As shown, the cyclone direction is opposite to the fuel injection direction, and the two form a certain collision, thereby promoting the full mixing of the combustion-supporting gas and the gaseous fuel. The mixed gas of the combustion-supporting gas and the gaseous fuel is ejected from the outer nozzle 3 and enters the combustion chamber.

[0031] The mixed combustion of the combustible gas and the combustion-supporting gas is the most complete and efficient mixed combustion mode. It can be seen that the present invention has the advantage of efficient gas mixed combustion.

[0032] As a further explanation of the present invention, the outer circumference of the limiting ring 12 in the middle section of the inner nozzle 1 is a large diameter end, and the outer circumference of the lower end is a small diameter end. The inner circumference of the ceramic sleeve 2 is provided with a step 22, which limits the limiting ring 12 of the inner nozzle 1, effectively preventing the inner nozzle 1 from moving downward during operation. Under the complex working conditions of high temperature, high pressure and airflow impact generated by combustion, the displacement change of the inner nozzle 1 due to force can be avoided, and the stability of the internal structure of the injector can be maintained.

[0033] The inner nozzle 1 and the outer nozzle 3 are both made of stainless steel.

[0034] The top end of the inner nozzle 1 is sealed and connected to the fuel storage chamber of the rocket through a fuel pipe.

[0035] like Figure 1-Figure 2 As shown, an annular first flange 4 is provided on the outer side of the upper end of the outer nozzle 3, and the first flange 4 is folded along the circumference. A second flange 5 is provided above the ceramic sleeve 2 and the inner nozzle 1, and the second flange 5 is sealed and connected to the folded edge of the first flange 4 by long bolts 6 to form an oxidant chamber 8, and the oxidant chamber is connected to the oxygen storage chamber through an oxygen pipe.

[0036] As a further illustration of the present invention, the convex ring 31 at the upper end of the outer nozzle 3 abuts against the first flange 4, the ceramic sleeve 2 and the inner nozzle 1 abut against the second flange 5, and the long bolts 6 are tightened to fix the second flange 5 and the first flange 4, so that the injector is fixed as a whole.

[0037] Therefore, compared with the prior art, the present invention is simpler in structure and installation process, and avoids redundant design.

[0038] The present invention also provides a gas-liquid rocket, comprising the gas-liquid injector.

[0039] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above and that the present invention can be implemented in other specific forms without departing from the spirit or essential features of the present invention. Therefore, the embodiments should be considered exemplary and non-restrictive in all respects, and the scope of the present invention is defined by the appended claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims be included in the present invention.

Claims

1. A gas-liquid injector, comprising: Pintle type inner nozzle, ceramic sleeve, outer nozzle, characterized by: The interior of the inner nozzle is used to transport liquid fuel, and a tangential spray hole is provided at the lower end thereof; The upper end of the ceramic sleeve is coaxially sleeved on the limiting ring in the middle section of the inner nozzle, the outer circumference of the middle section of the inner nozzle is the large diameter end, and the outer circumference of the lower end is the small diameter end. The inner circumference of the ceramic sleeve is provided with a step, which limits the downward movement of the upper end of the nozzle; An annular first flange is provided on the outer side of the upper end of the outer nozzle, and the first flange is folded along the circumference. A second flange is provided above the ceramic sleeve and the inner nozzle, and the second flange is sealed and connected to the folded edge of the first flange by long bolts to form an oxidant chamber; the convex ring at the upper end of the outer nozzle abuts against the first flange, the ceramic sleeve and the inner nozzle abut against the second flange, and the long bolts are tightened to fix the second flange and the first flange, so that the injector is fixed and formed as a whole; A cavity for conveying gas is formed between the lower end of the ceramic sleeve and the lower end of the inner nozzle; a tangential air inlet is also provided at the lower end of the ceramic sleeve, and the air outlet direction of the air inlet is opposite to the injection direction of the nozzle, and the bottom of the ceramic sleeve is connected to the top of the outer nozzle; The inner nozzle is electrically connected to the positive electrode of the high voltage power supply, and the outer nozzle is electrically connected to the negative electrode of the high voltage power supply.

2. The gas-liquid injector according to claim 1, characterized in that: The inner nozzle and the outer nozzle are both made of stainless steel.

3. The gas-liquid injector according to claim 1, characterized in that: The top end of the inner nozzle is sealed and connected to the fuel storage chamber of the rocket through a fuel pipe.

4. The gas-liquid injector according to claim 1, characterized in that: The second flange is a ceramic structure.

5. A gas-liquid rocket, characterized in that: A gas-liquid injector comprising the gas-liquid injector according to any one of claims 1-4.

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