Combustion chamber air exhaust circulation liquid rocket engine

Abstract

The invention discloses a combustion chamber air exhaust circulation liquid rocket engine. The combustion chamber air exhaust circulation liquid rocket engine comprises a combustion chamber, a turbine pump and a plurality of injectors installed in the combustion chamber. The injector is composed of a shell, an inner nozzle, a ceramic pipe and an outer nozzle, wherein the inner nozzle, the ceramic pipe and the outer nozzle are coaxially arranged. A middle partition plate in the shell of the injector divides an inner cavity of the shell into an oxygen cavity and a fuel cavity. According to the injector, multiple functions of premixing, pre-combustion, air exhaust and high-temperature gas cooling are integrated and matched with one another, the performance of a liquid rocket engine is improved from multiple aspects, and a powerful guarantee is provided for efficient and stable operation of a rocket.

Description

Technical Field

[0001] The present invention relates to rockets. Background Art

[0002] The main components of the existing gas generator cycle liquid rocket engine are: gas generator and accessories, combustion chamber and turbo pump. The gas generator is equivalent to a small liquid rocket engine, which requires special valves, pipelines, injectors, combustion chambers and igniters, etc. The structure is complex and the reliability is poor.

[0003] The invention patent with application number 202211018754.0 abandoned the gas generator and made further improvements, directly taking out the gas from the combustion chamber to drive the turbine. The current technical problems encountered are how to cool the gas so as not to affect the turbine, and how to make the fuel entering the combustion chamber fully burn to increase the rocket's specific impulse. Summary of the invention

[0004] In order to overcome the above-mentioned shortcomings, the present invention aims to provide a technical solution that can solve the above-mentioned problems.

[0005] A combustion chamber exhaust cycle liquid rocket engine, comprising a combustion chamber, a turbopump and a plurality of injectors installed in the combustion chamber; the injector is composed of a shell and a coaxially arranged inner nozzle, a ceramic tube and an outer nozzle, and the middle partition in the injector shell divides the shell cavity into an oxygen cavity and a fuel cavity; the upper end of the inner nozzle is arranged in the oxygen cavity, and the lower end of the inner nozzle passes through the middle partition and extends into the fuel cavity, and the upper end of the inner nozzle is provided with a first tangential hole; the ceramic tube sleeve is arranged on the limit ring of the middle section of the inner nozzle, and the tube wall of the ceramic tube is provided with a second tangential hole opposite to the first tangential hole; the outer nozzle is arranged on the bottom surface of the shell and extends to the combustion chamber, and the bottom end of the ceramic tube abuts the outer nozzle; the inner nozzle and the outer nozzle are both made of stainless steel, and are respectively connected to the positive and negative electrodes of a high-voltage power supply; Preferably, the injector further comprises a spiral exhaust pipe, which is arranged in the oxygen chamber and the fuel chamber of the shell, and the exhaust end of the spiral exhaust pipe extends into the combustion chamber; Preferably, the upper end of the outer nozzle is contracted, and the lower end is expanded; Preferably, the turbo pump comprises an oxygen pump, a fuel pump and a turbine pipe, and the jet end of the spiral exhaust pipe extends into the turbine pipe; Preferably, the oxygen pump is connected to the oxygen chamber of the injector through an oxygen pipe, the fuel pump is connected to the fuel chamber of the injector through a fuel pipe, and the oxygen pipe is also directly connected to the combustion chamber through an oxygen manifold.

[0006] Compared with the prior art, the advantages of the present invention are: the injector of the present invention integrates multiple functions of premixing, precombustion, air extraction and cooling of high-temperature gas, which cooperate with each other, improve the performance of liquid rocket engines in many aspects, and provide a strong guarantee for the efficient and stable operation of the rocket.

[0007] 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

[0008] 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.

[0009] Figure 1 It is a structural schematic diagram of the present invention.

[0010] Figure 2 It is a schematic cross-sectional view of the injector of the present invention. DETAILED DESCRIPTION

[0011] 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.

[0012] 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.

[0013] 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.

[0014] 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.

[0015] See also Figure 1 In an embodiment of the present invention, a combustion chamber exhaust cycle liquid rocket engine includes a combustion chamber 1, a turbopump 2, and a plurality of injectors 3 installed in the combustion chamber 1; like Figure 2 As shown, the injector 3 includes the following structure: The housing is used to divide the inner cavity of the injector 3 housing into an oxygen cavity 32 and a fuel cavity 33 through a middle partition 31, so as to ensure that the fuel and the oxidant are in a mutually isolated state before entering the nozzle; An inner nozzle 34 is used to inject an oxidant so that the oxidant is mixed with the fuel; Ceramic tube 35, having high temperature resistance, heat insulation and insulating properties; The outer nozzle 36 cooperates with the inner nozzle 34 to spray fuel, and collides and mixes with the oxidant sprayed from the inner nozzle 34, thereby improving the mixing effect and mixing uniformity of the propellant.

[0016] The upper end of the inner nozzle 34 is arranged in the oxygen chamber 32, and the lower end of the inner nozzle 34 passes through the middle partition 31 and extends into the fuel chamber 33. A first tangential hole 341 is provided at the upper end of the inner nozzle 34. When the oxidant passes through the inner nozzle 34, the first tangential hole 341 allows the oxidant to enter the inner nozzle 34 at a certain angle, thereby forming a rotating flow inside the nozzle.

[0017] The ceramic tube 35 is sleeved on the limiting ring 342 in the middle section of the inner nozzle 34. The wall of the ceramic tube 35 is provided with a second tangential hole 351 opposite to the first tangential hole 341. When the fuel passes through the gap between the ceramic tube 35 and the inner nozzle 34, the second tangential hole 351 will cause the fuel to produce a rotating flow in the opposite direction to the rotation direction of the oxidant, and the fuel will cool the outer nozzle 36 at the same time.

[0018] The inner nozzle 34 and the outer nozzle 36 are both made of stainless steel and are connected to the positive and negative electrodes of a high-voltage power supply, respectively. When the high-voltage power supply is turned on, a strong electric field is formed between the inner nozzle 34 and the outer nozzle 36. Under the action of this strong electric field, the gas and liquid in the fuel or oxidant are rapidly heated.

[0019] When the oxidant is ejected from the inner nozzle 34, it collides with the fuel rotating in the opposite direction in the outer nozzle 36. The collision of the two with opposite rotation directions produces a strong stirring effect, which improves the mixing efficiency and uniformity of the oxidant and the fuel. The mixed propellant ignites in the outer nozzle 36 under the action of the strong electric field.

[0020] The outer nozzle 36 adopts a Laval tube design, which accelerates the burning and expanding high-temperature gas at its contraction end to reach the speed of sound, and makes the high-temperature gas reach supersonic speed at its expansion end and sprays it into the main combustion chamber 1.

[0021] The injector 3 also includes a spiral exhaust pipe 37, the exhaust end of which sucks high-temperature gas from the combustion chamber 1 into the spiral exhaust pipe 37. Since the temperature of the gas exhausted in the exhaust pipe is relatively high, and the oxidant or fuel is usually at a relatively low temperature, the oxidant in the oxygen chamber 32 or the fuel in the fuel chamber 33 is vaporized into oxygen or fuel gas after absorbing the heat of the spiral exhaust pipe 37, thereby cooling the high-temperature gas in the spiral exhaust pipe 37 to prevent the high-temperature gas from burning the turbine.

[0022] The turbo pump 2 comprises an oxygen pump 21 , a fuel pump 22 and a turbine pipe 23 , and the jet end of the spiral exhaust pipe 37 extends into the turbine pipe 23 .

[0023] The oxygen pump 21 is connected to the oxygen chamber 32 of the injector 3 through an oxygen pipe, and the fuel pump 22 is connected to the fuel chamber 33 of the injector 3 through a fuel pipe.

[0024] The working principle of the present invention is as follows: When the engine is started, part of the oxidant and fuel are respectively delivered to the oxygen chamber 32 and the fuel chamber 33 of the injector 3 by the turbo pump 2, while most of the oxidant is directly input into the combustion chamber 1 through the oxygen manifold. After the oxidant enters the oxygen chamber 32, it enters the inner nozzle 34 at a certain angle through the first tangential hole 341, forming a rotating flow, and then ejects from the lower end of the inner nozzle 34; the fuel is introduced into the gap between the ceramic tube 35 and the inner nozzle 34 in the fuel chamber 33 by the second tangential hole 351. The second tangential hole 351 causes the fuel to produce a rotating flow in the opposite direction of the oxidant's rotation. When the reverse rotating flows of the oxidant and the fuel meet in the outer nozzle 36, a strong collision and mixing occurs; when a high voltage is applied to the inner nozzle 34, the inner nozzle 34 discharges to pre-ignite the propellant mixture, generating a relatively low temperature rich fuel gas; the rich fuel gas is ejected into the combustion chamber 1 at a high speed under the action of the Laval tubular outer nozzle 36, mixed with another large part of the oxidant and fully burned, and the high-temperature gas after the afterburning is ejected through the nozzle to generate thrust.

[0025] The spiral exhaust pipe 37 extracts high-temperature gas to drive the turbine pump 2. The spiral exhaust pipe 37 is arranged in the oxygen chamber 32 and the fuel chamber 33 of the shell. The high-temperature gas is cooled by the oxidant in the oxygen chamber 32 and the fuel in the fuel chamber 33 and then transported to the turbine pipe 23, so as to prevent the turbine from being damaged due to high temperature, thereby enhancing the reliability and service life of the engine; and the spiral shape of the exhaust pipe prolongs the movement path of the high-temperature gas in the injector 3 shell, and the heat of the high-temperature gas is effectively transferred to the oxidant and the fuel, and the oxidant and the fuel are vaporized at the same time.

[0026] 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 chamber-exhaust cycle liquid rocket engine comprising a combustion chamber, a turbopump, and a plurality of injectors mounted within the combustion chamber, characterized in that: The injector is composed of a shell and a coaxially arranged inner nozzle, a ceramic tube, and an outer nozzle. The middle partition in the injector shell separates the shell cavity into an oxygen cavity and a fuel cavity. The upper end of the inner nozzle is arranged in the oxygen chamber, and the lower end of the inner nozzle extends into the fuel chamber through the middle partition plate, and the upper end of the inner nozzle is provided with a first tangential hole; The ceramic tube is sleeved on the limiting ring in the middle section of the inner nozzle, and a second tangential hole is provided on the wall of the ceramic tube in the opposite direction to the first tangential hole; The outer nozzle is arranged on the bottom surface of the shell and extends to the combustion chamber, and the bottom end of the ceramic tube abuts the outer nozzle; the inner nozzle and the outer nozzle are both made of stainless steel and are respectively connected to the positive and negative poles of the high-voltage power supply.

2. The combustion chamber exhaust cycle liquid rocket engine according to claim 1, characterized in that: The injector further comprises a spiral exhaust pipe, which is arranged in the oxygen chamber and the fuel chamber of the shell, and the exhaust end of the spiral exhaust pipe extends into the combustion chamber.

3. The combustion chamber exhaust cycle liquid rocket engine according to claim 2, characterized in that: The upper end of the outer nozzle is in a contracted shape, and the lower end thereof is in an expanded shape.

4. The combustion chamber exhaust cycle liquid rocket engine according to claim 3, characterized in that: The turbo pump comprises an oxygen pump, a fuel pump and a turbine pipe, and the jet end of the spiral exhaust pipe extends into the turbine pipe.

5. The combustion chamber exhaust cycle liquid rocket engine according to claim 4, characterized in that: The oxygen pump is communicated with the oxygen cavity of the injector through an oxygen pipe, the fuel pump is communicated with the fuel cavity of the injector through a fuel pipe, and the oxygen pipe is also directly communicated with the combustion chamber through an oxygen manifold.

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