Engine and liquid rocket

Abstract

The invention belongs to the technical field of aerospace machinery, and particularly relates to an engine and a liquid rocket. The invention provides an engine. The engine comprises a pre-pressing pump, a fuel pump, an oxidizing agent pump, a fuel gas generator and a main turbine. The pre-pressing pump comprises an oxidizing agent pre-pressing turbine pump, the oxidizing agent pre-pressing turbine pump is arranged at the front end of the oxidizing agent pump, and an oxidizing agent sequentially passes through the oxidizing agent pre-pressing turbine pump and the oxidizing agent pump. The invention further provides a liquid rocket comprising the engine. According to the technical scheme, through pressurization of the pre-pressing pump, the pressure requirement of an inlet of the engine pump is lowered, the pressurization pressure is further lowered, and therefore a lighter and thinner wall thickness can be selected, and the weight is lowered; meanwhile, the rotating speed of the main turbine is increased after the pressure is increased, and the working efficiency is improved; the technical defects that in the prior art, a fuel gas generator circulating rocket engine is large in storage tank weight, low in load and low in turbine efficiency are overcome.

Description

Technical Field

[0001] The present application belongs to the field of aerospace mechanical technology, and in particular relates to an engine and a liquid rocket. Background Art

[0002] Liquid rocket engines generally refer to pump-pressure liquid rocket engines, and their circulation modes are divided into closed cycle and open cycle. Closed cycle mainly refers to regenerative cycle rocket engines, and open cycle refers to gas generator cycle rocket engines. Among them, gas generator cycle engines generally do not have a pre-pressure turbo pump, and the pressure provided by the rocket tank must meet the engine pump inlet requirements.

[0003] In the prior art, since the gas generator cycle engine is not equipped with a pre-pressure turbopump system, the pressure of the rocket tank must meet the normal working conditions of the engine, and the rocket tank pressure must not be lower than a certain lower limit. The higher tank pressure leads to: increased tank wall thickness, increased tank weight and reduced rocket payload; at the same time, the gas generator cycle engine is not equipped with a pre-pressure turbopump system, which reduces the pump speed. The lower speed leads to lower turbine efficiency, and at the same time, the size of the turbopump becomes larger, which increases the overall size of the engine.

[0004] Therefore, developing an engine and a liquid rocket to solve the technical defects of the gas generator cycle rocket engine in the prior art, such as heavy tank weight, low load and low turbine efficiency, has become an urgent problem to be solved by technical personnel in this field. Summary of the invention

[0005] Based on this, it is necessary to provide an engine and a liquid rocket to address the technical defects of the gas generator cycle rocket engine in the existing technology, such as heavy tank weight, low load and low turbine efficiency.

[0006] The present application provides an engine, the engine comprising: a pre-pressure pump, a fuel pump, an oxidant pump, a gas generator and a main turbine, the fuel pump and the oxidant pump are respectively connected to the gas generator, the gas generator generates gas to drive the main turbine; The pre-pressure pump comprises: an oxidant pre-pressure turbine pump, the oxidant pre-pressure turbine pump is arranged at the front end of the oxidant pump, and the oxidant passes through the oxidant pre-pressure turbine pump and the oxidant pump in sequence.

[0007] In one of the embodiments, the pre-pressure pump further includes: a fuel pre-pressure turbine pump, wherein the fuel pre-pressure turbine pump is disposed at the front end of the fuel pump, and the fuel passes through the fuel pre-pressure turbine pump and the fuel pump in sequence.

[0008] In one of the embodiments, the engine further comprises: a heat exchanger, wherein the heat exchanger is disposed before the air inlet of the pre-pressure pump.

[0009] In one embodiment, the engine further includes: a first oxidizer valve, a second oxidizer valve and a thrust chamber, wherein one end of the first oxidizer valve and the second oxidizer valve are respectively connected to the oxidizer pump, the other end of the first oxidizer valve is connected to the thrust chamber, and the other end of the second oxidizer valve is connected to the gas generator.

[0010] In one of the embodiments, the engine further comprises: a cavitation tube, one end of which is connected to the oxidant pump, and the other end of which is connected to the oxidant pre-pressure turbine pump.

[0011] In one embodiment, the engine further includes: a first fuel valve and a second fuel valve, wherein one end of the first fuel valve and the second fuel valve are respectively connected to the fuel pump, the other end of the first fuel valve is connected to the thrust chamber, and the other end of the second fuel valve is connected to the gas generator.

[0012] The present application also provides a liquid rocket, which includes an engine as described in any one of the above.

[0013] In summary, the present application provides an engine, which includes: a pre-pressure pump, a fuel pump, an oxidant pump, a gas generator and a main turbine, wherein the fuel pump and the oxidant pump are respectively connected to the gas generator, and the gas generator generates gas to drive the main turbine; the pre-pressure pump includes: an oxidant pre-pressure turbine pump, and the oxidant pre-pressure turbine pump is arranged at the front end of the oxidant pump, and the oxidant passes through the oxidant pre-pressure turbine pump and the oxidant pump in sequence. The present application also provides a liquid rocket including the above engine. In the technical solution provided by the present application, the pressure requirement at the inlet of the engine pump is reduced by the boosting of the pre-pressure pump, and the boosting pressure is further reduced, so that a thinner wall thickness can be selected, and the weight can be reduced; at the same time, after the pressure is increased, the speed of the main turbine increases, and the working efficiency is improved. The engine and the liquid rocket provided by the present application solve the technical defects of the gas generator cycle rocket engine in the prior art, that is, the tank weight is large, the load is low, and the turbine efficiency is low. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the embodiments of the present application 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 embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying any creative work.

[0015] Figure 1In the technical solution provided in the embodiment of the present application, a structural schematic diagram of an engine; Among them, there are an oxidizer pre-pressure turbine pump 1, a fuel pre-pressure turbine pump 2, a gas check valve 3, a thrust chamber 4, a second oxidizer valve 5, a second fuel valve 6, a gas generator 7, a first oxidizer valve 8, a first fuel valve 9, an oxidizer pump 10, a fuel pump 11, a main turbine 12, a gas nozzle 13, a heat exchanger 14 and a cavitation tube 15. DETAILED DESCRIPTION

[0016] The embodiments of the present application provide an engine and a liquid rocket for solving the technical defects of the gas generator cycle rocket engine in the prior art, such as heavy tank weight, low load and low turbine efficiency.

[0017] In order to make the above-mentioned purposes, features and advantages of the present application more obvious and easy to understand, the specific implementation methods of the present application are described in detail below in conjunction with the accompanying drawings. In the following description, many specific details are set forth to facilitate a full understanding of the present application. However, the present application can be implemented in many other ways different from those described herein, and those skilled in the art can make similar improvements without violating the connotation of the present application, so the present application is not limited by the specific embodiments disclosed below.

[0018] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0019] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of this application, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0020] In this application, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like 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 an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0021] In the present application, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0022] It should be noted that when an element is referred to as being "fixed to" or "disposed on" another element, it may be directly on the other element or there may be a central element. When an element is considered to be "connected to" another element, it may be directly connected to the other element or there may be a central element at the same time. The terms "vertical", "horizontal", "upper", "lower", "left", "right" and similar expressions used herein are for illustrative purposes only and do not represent the only implementation method.

[0023] See also Figure 1 The embodiment of the present application provides an engine, comprising: a pre-pressure pump, a fuel pump 11, an oxidant pump 10, a gas generator 7 and a main turbine 12. The fuel pump 11 and the oxidant pump 10 are respectively connected to the gas generator 7, and the gas generator 7 generates fuel gas to drive the main turbine 12; the pre-pressure pump comprises: an oxidant pre-pressure turbine pump 1, the oxidant pre-pressure turbine pump 1 is arranged at the front end of the oxidant pump 10, and the oxidant passes through the oxidant pre-pressure turbine pump 1 and the oxidant pump 10 in sequence. The engine provided by the embodiment of the present application solves the technical defects of the gas generator 7 cycle rocket engine in the prior art, such as heavy tank weight, low load and low turbine efficiency.

[0024] In the technical solution provided in the embodiment of the present application, the oxidant is pressurized by the oxidant pre-pressure turbine pump 1, and the pressurized oxidant enters the gas generator 7 through the oxidant pump 10 to mix with the fuel, and after ignition, the main turbine 12 is driven to operate through the gas generator 7.

[0025] In the present application, the oxidant is pre-pressurized by the oxidant pre-pressure turbine pump 1, which can effectively reduce the oxidant pressure requirement at the inlet of the oxidant pump 10. Accordingly, due to the pressure reduction, the wall thickness requirement for the outer wall of the engine is also reduced accordingly, and the overall weight of the engine can also be reduced accordingly. Further, the engine load can be effectively increased.

[0026] At the same time, due to the increase in pressure, the rotation speed of the main turbine 12 can increase accordingly, which helps to improve the working efficiency of the main turbine 12, and further reduce the volume of the main turbine 12. The volume of the engine can also be reduced synchronously, making it easier to assemble the engine.

[0027] To further optimize the technical solution, a pre-pressure pump provided in an embodiment of the present application further includes: a fuel pre-pressure turbine pump 2, which is arranged at the front end of the fuel pump 11, and the fuel passes through the fuel pre-pressure turbine pump 2 and the fuel pump 11 in sequence. The fuel is pre-pressurized synchronously by the fuel pre-pressure turbine pump 2, which cooperates with the oxidant pre-pressure turbine pump 1, further effectively reducing the wall thickness requirement for the outer wall of the engine, effectively reducing the overall weight of the engine, and at the same time is conducive to improving the working efficiency of the main turbine 12.

[0028] An engine provided in an embodiment of the present application further includes: a heat exchanger 14, which is arranged in front of the air inlet of the pre-pressure pump. After the oxidant passes through the heat exchanger 14, the liquid oxidant absorbs heat and becomes gaseous, and then enters the oxidant pre-pressure turbine pump 1 and the gas generator 7 in sequence to drive the main turbine 12 to do work; the oxidant after doing work can re-enter the oxidant pre-pressure pump for secondary use. After the oxidant is heated by the heat exchanger 14, the liquid and gaseous oxidants can be compatible in the oxidant pre-pressure turbine pump 1, which can effectively reduce the sealing requirements for the oxidant pre-pressure turbine pump 1, simplify the design of the sealing structure, and effectively improve the safety performance; at the same time, compared with the liquid oxidant, the gaseous oxidant has a strong working capacity, and the working fluid flow of the main turbine 12 will be greatly reduced, which is conducive to reducing the weight and volume of the oxidant pre-pressure turbine and its pipeline system. The oxygen after doing work returns to the engine again, avoiding the loss of the engine specific impulse performance.

[0029] The gas nozzle 13 is used to control the flow of the gas. Since the temperature of the gas is relatively high, it is cooled by the heat exchanger 14. While cooling the gas, the temperature of the heat exchanger 14 is increased, which can be used to increase the temperature of the oxidant. The cooled gas enters the fuel pre-pressure turbine through the gas check valve 3, and drives the main turbine 12 to do work after passing through the fuel pre-pressure turbine pump 2 and the gas generator 7 in sequence. After the fuel is cooled by the heat exchanger 14, the cooled gas and the fuel can be compatible in the fuel pre-pressure turbine pump 2, which can effectively reduce the sealing requirements for the fuel pre-pressure turbine pump 2, simplify the design of the sealing structure, and effectively improve the safety performance; at the same time, the gas has a strong working capacity and only requires a small amount of gas flow, which is conducive to reducing the weight and volume of the fuel pre-pressure turbine pump 2 and its pipeline system. The gas after work returns to the engine again, avoiding the loss of the engine's specific impulse performance.

[0030] The gas is cooled in the heat exchanger 14 to release heat, and the oxidant is heated in the heat exchanger 14 to absorb heat. In actual application, the heat released by the gas is greater than the heat absorbed by the oxidant. The heat exchanger 14 is additionally provided with a refrigerant supplement structure to effectively cool the gas.

[0031] To further optimize the technical solution, an engine provided in an embodiment of the present application further includes: a first oxidant valve 8, a second oxidant valve 5 and a thrust chamber 4, one end of the first oxidant valve 8 and the second oxidant valve 5 are respectively connected to the oxidant pump 10, the other end of the first oxidant valve 8 is connected to the thrust chamber 4, and the other end of the second oxidant valve 5 is connected to the gas generator 7. When the engine is assembled to the installation system, the thrust chamber 4 can provide thrust for driving, thereby broadening the application scenarios of the engine.

[0032] Correspondingly, an engine provided by the present application also includes: a first fuel valve 9 and a second fuel valve 6, one end of the first fuel valve 9 and the second fuel valve 6 are respectively connected to the fuel pump 11, the other end of the first fuel valve 9 is connected to the thrust chamber 4, and the other end of the second fuel valve 6 is connected to the gas generator 7.

[0033] In order to better utilize the oxidant and avoid oxidant waste, an engine provided in an embodiment of the present application further includes: a cavitation tube 15, one end of the cavitation tube 15 is connected to the oxidant pump 10, and the other end of the cavitation tube 15 is connected to the oxidant pre-compression turbine pump 1. The oxidant in the cavitation tube 15 can be refluxed for secondary or even multiple utilizations. The engine provided by the above technical solution has the advantages of light weight and small size. At the same time, the main turbine 12 of the engine has high working efficiency and can be installed in a liquid rocket. In view of this, the present application also provides a liquid rocket, which includes the above engine.

[0034] In summary, the present application provides an engine, which includes: a pre-pressure pump, a fuel pump, an oxidant pump, a gas generator and a main turbine, wherein the fuel pump and the oxidant pump are respectively connected to the gas generator, and the gas generator generates gas to drive the main turbine; the pre-pressure pump includes: an oxidant pre-pressure turbine pump, and the oxidant pre-pressure turbine pump is arranged at the front end of the oxidant pump, and the oxidant passes through the oxidant pre-pressure turbine pump and the oxidant pump in sequence. The present application also provides a liquid rocket including the above engine. In the technical solution provided by the present application, the pressure requirement at the inlet of the engine pump is reduced by the boosting of the pre-pressure pump, and the boosting pressure is further reduced, so that a thinner wall thickness can be selected, and the weight can be reduced; at the same time, after the pressure is increased, the speed of the main turbine increases, and the working efficiency is improved. The engine and the liquid rocket provided by the present application solve the technical defects of the gas generator cycle rocket engine in the prior art, that is, the tank weight is large, the load is low, and the turbine efficiency is low.

[0035] The technical features of the above-mentioned embodiments can be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above-mentioned embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification. At the same time, other implementation methods can be derived from the above-mentioned embodiments, so that structural and logical replacements and changes can be made without departing from the scope of this disclosure.

[0036] The above-described embodiments only express several implementation methods of the present application, and the descriptions thereof are relatively specific and detailed, but they cannot be construed as limiting the scope of the patent application. It should be pointed out that, for a person of ordinary skill in the art, several variations and improvements can be made without departing from the concept of the present application, and these all belong to the protection scope of the present application. Therefore, the protection scope of the patent application shall be subject to the attached claims.

Claims

1. An engine, characterized in that: The engine comprises: a pre-pressure pump, a fuel pump, an oxidant pump, a gas generator and a main turbine, wherein the fuel pump and the oxidant pump are respectively connected to the gas generator, and the gas generator generates gas to drive the main turbine; The pre-pressure pump comprises: an oxidant pre-pressure turbine pump, the oxidant pre-pressure turbine pump is arranged at the front end of the oxidant pump, and the oxidant passes through the oxidant pre-pressure turbine pump and the oxidant pump in sequence.

2. The engine according to claim 1, characterized in that The pre-pressure pump further includes: a fuel pre-pressure turbine pump, which is arranged at the front end of the fuel pump, and the fuel passes through the fuel pre-pressure turbine pump and the fuel pump in sequence.

3. The engine according to claim 1 or 2, characterized in that: The engine further comprises: a heat exchanger, which is arranged in front of the air inlet of the pre-pressure pump.

4. The engine according to any one of claims 1 to 3, characterized in that: The engine also includes: a first oxidant valve, a second oxidant valve and a thrust chamber, wherein one end of the first oxidant valve and the second oxidant valve are respectively connected to the oxidant pump, the other end of the first oxidant valve is connected to the thrust chamber, and the other end of the second oxidant valve is connected to the gas generator.

5. The engine according to claim 3, characterized in that The engine further comprises: a cavitation tube, one end of which is connected to the oxidant pump, and the other end of which is connected to the oxidant pre-compression turbine pump.

6. The engine according to claim 4 or 5, characterized in that: The engine further includes: a first fuel valve and a second fuel valve, wherein one end of the first fuel valve and the second fuel valve are respectively connected to the fuel pump, the other end of the first fuel valve is connected to the thrust chamber, and the other end of the second fuel valve is connected to the gas generator.

7. A liquid rocket, characterized in that: The liquid rocket comprises the engine according to any one of claims 1 to 6.

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