Gas generator circulating vacuum type engine

Abstract

The invention discloses a gas generator circulating vacuum type engine, which relates to the technical field of spaceflight and comprises a spray pipe, a turbine pump and a gas generator, a cooling air inlet is formed in the expansion section of the spray pipe; the turbine pump is provided with a volute, and a turbine is arranged in the volute. An outlet of the gas generator is connected with the volute and used for driving a turbine in the volute to rotate, an exhaust pipeline is connected to the volute and communicates with a cooling gas inlet of the spray pipe, a fuel introduction pipeline is further connected to the exhaust pipeline, and fuel is introduced into the exhaust pipeline through the fuel introduction pipeline. The temperature of a medium entering the tail end of the spray pipe for air film cooling can be reduced, the medium flow is increased, the problem that the tail section of the vacuum engine spray pipe is insufficient in cooling can be solved, and the reliability of an engine is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, in particular to a gas generator cycle vacuum type engine. BACKGROUND

[0002] The gas generator cycle vacuum type engine is a kind of liquid rocket engine, which adopts gas generator cycle as the power transmission mode and is optimized in design for the space vacuum environment. The core feature is to realize the gas film cooling of the nozzle in the terminal stage by recycling the turbine exhaust, and to improve the overall efficiency of the engine. Specifically, the turbine exhaust is introduced into the cooling channel on the inner wall of the nozzle expansion section through a special pipeline, and is sprayed out from the micro-holes at a specific angle to form a continuous gas film on the nozzle wall, which isolates the high-temperature gas (2000℃+) from the wall, and the exhaust gas continues to expand in the nozzle to generate additional thrust.

[0003] However, with the continuous improvement of manufacturing process, the expansion ratio of the nozzle of the vacuum type engine can easily reach 100, and the expansion ratio of the gas generator cycle sea level type engine is generally only about 20. Such a high expansion ratio means that a large area of the nozzle needs to be cooled.

[0004] At the same time, the design and production technology of the turbine pump has developed, and the efficiency of the turbine pump has been improved. This reduces the fuel flow required by the turbine pump. The cooling medium at the end of the nozzle of the vacuum type engine is the fuel gas discharged from the turbine pump. Now, the fuel flow of this part is reduced, but the area that needs to be cooled is increasing. Therefore, the end of the nozzle of the gas generator cycle vacuum type engine has the problem of insufficient cooling. SUMMARY

[0005] Therefore, the present application provides a gas generator cycle vacuum type engine to solve the problem of insufficient cooling at the end of the nozzle of the gas generator cycle vacuum type engine.

[0006] The present application provides a gas generator cycle vacuum type engine, comprising: a nozzle, a turbine pump and a gas generator. The expansion section of the nozzle has a cooling gas inlet; The turbine pump has a volute, and the volute has a turbine inside; The outlet of the gas generator is connected with the volute to drive the turbine inside the volute to rotate, the volute is connected with an exhaust pipeline, the exhaust pipeline is in communication with the cooling gas inlet of the nozzle, and the exhaust pipeline is further connected with a fuel introduction pipeline to introduce fuel into the exhaust pipeline.

[0007] Optionally, the outlet of the fuel introduction pipeline is connected with an atomizer. The fuel can be dispersed into small droplets by the atomizer, and the atomized fuel droplets are more uniformly distributed in space.

[0008] Optionally, a flow control device is connected to the fuel introduction pipeline.

[0009] Optionally, the flow control device is a cavitation tube.

[0010] Optionally, the pump body of the turbine pump comprises a fuel pump and an oxidant pump, the outlet of the oxidant pump is connected to the combustion chamber through a first pipeline, and the outlet of the fuel pump is connected to the combustion chamber through a second pipeline.

[0011] Optionally, the fuel introduction pipeline is connected to the second pipeline.

[0012] Optionally, the inlet of the gas generator is communicated with the first pipeline through a third pipeline and communicated with the second pipeline through a fourth pipeline, and valves are respectively arranged on the first pipeline, the second pipeline, the third pipeline and the fourth pipeline.

[0013] Optionally, the fuel introduction pipeline is connected behind the valve.

[0014] Optionally, the fuel introduction pipeline is connected in front of the valve, and a valve is arranged on the fuel introduction pipeline.

[0015] Optionally, a heat exchanger is arranged at the outlet of the volute, and the heat exchanger is connected to the first pipeline.

[0016] The technical scheme of the present application can reduce the temperature of the medium entering the end of the nozzle for film cooling, and increase the flow of the medium, thereby solving the problem of insufficient cooling of the end section of the nozzle of the vacuum-type engine and improving the reliability of the engine. BRIEF DESCRIPTION OF DRAWINGS

[0017] In order to more clearly illustrate the specific embodiments of the present application or the technical scheme in the prior art, the drawings needed in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present application, and those skilled in the art can obtain other drawings according to these drawings without creative labor.

[0018] Figure 1 A front view of a gas generator circulating vacuum-type engine according to an embodiment of the present application is provided.

[0019] Explanation of reference signs: 1, nozzle; 2, turbine pump; 201, volute; 202, fuel pump; 203, oxidant pump; 204, exhaust pipeline; 3. Gas generator; 4. Fuel introduction pipe; 5. Atomizer; 6. Cavitation pipe; 7. First pipe; 8. Second pipe; 9. Third pipe; 10. Fourth pipe; 11. Heat exchanger. DETAILED DESCRIPTION

[0020] In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only some, but not all of the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of the present application.

[0021] In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application. In addition, the terms "first", "second", "third" are only for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0022] In the description of the present application, it should be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connecting", "connecting" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be directly connected, or indirectly connected through an intermediate medium. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0023] In addition, the technical features involved in the different embodiments of the present application described below can be combined with each other as long as they do not conflict with each other.

[0024] After the vacuum engine is started, the thrust chamber will continuously generate high-temperature gas with a temperature exceeding 3000K. In order to avoid the thrust chamber wall being burned out, the upper segment of the thrust chamber adopts regenerative cooling, and the lower segment uses gas film cooling. The gas medium used for gas film cooling is the gas generated by the gas generator, with a temperature of about 800K. After the gas is used to drive the turbine to do work, it will flow into the collector at the nozzle, and then be uniformly sprayed to the inner wall of the nozzle, forming a layer of relatively low-temperature gas film on the inner wall, so as to protect the inner wall of the lower segment of the nozzle.

[0025] However, as the expansion ratio of the nozzle increases, and the turbine pump efficiency improves, the turbine exhaust flow rate decreases, and the existing cooling method is difficult to ensure reliable cooling of the lower nozzle section. Therefore, appropriate measures need to be taken, such as increasing the flow rate of the gas film medium or reducing the medium temperature, to enhance the cooling effect.

[0026] As shown in Figure 1 The gas generator 3 circulating vacuum type engine provided by the embodiment includes a nozzle 1, a turbine pump 2 and a gas generator 3. The nozzle 1 has a cooling gas inlet on the expansion section. The turbine pump 2 has a volute 201 with a turbine inside. The outlet of the gas generator 3 is connected to the volute 201 to drive the turbine inside the volute 201 to rotate. The volute 201 is connected to an exhaust pipe 204, which is in communication with the cooling gas inlet of the nozzle 1. The exhaust pipe 204 is also connected to a fuel introduction pipe 4, through which fuel is introduced into the exhaust pipe 204.

[0027] The gas generator 3 circulating vacuum type engine provided by the embodiment can adapt to the use environment of large nozzle 1, small flow rate and high temperature of the gas film cooling medium. Specifically, by introducing fuel into the exhaust pipe 204, the turbine exhaust gas and the fuel are mixed, and the fuel is gasified after absorbing heat. In this process, the temperature of the turbine exhaust gas is reduced, and the flow rate of the medium is also slightly increased. Subsequently, the part of the gas medium cooled by the fuel flows into the nozzle 1, thereby implementing gas film cooling of the nozzle 1.

[0028] Compared with the improved cooling method, the temperature of the vacuum type engine nozzle gas film cooling medium is significantly reduced, and the flow rate of the medium is also slightly increased. In this way, the cooling effect is enhanced, which can effectively prevent the nozzle 1 from being damaged due to heating, thereby improving the reliability of the engine.

[0029] As shown in Figure 1 In some embodiments, the outlet of the fuel introduction pipe 4 is connected to an atomizer 5. The atomizer 5 is used to atomize the fuel introduced into the exhaust pipe 204, and the atomized fuel can better mix with the turbine exhaust gas.

[0030] As shown in Figure 1 In some embodiments, the fuel introduction pipe 4 is connected to a flow control device for controlling the flow rate of the fuel. Specifically, a cavitation tube 6 can be used to control the flow rate of the fuel. Of course, the above description is not limiting, and in some alternative embodiments, the flow control device can also use other structures, such as a flow regulating valve.

[0031] As shown in Figure 1As shown in the figure, in some embodiments, the pump body of the turbine pump comprises a fuel pump 202 and an oxidant pump 203, the inlet of the oxidant pump 203 is connected with the oxidant storage tank, and the outlet is connected with the combustion chamber through the first pipeline 7 for powering the oxidant delivered to the combustion chamber; the inlet of the fuel pump 202 is connected with the fuel storage tank, and the outlet is connected with the combustion chamber through the second pipeline 8 for powering the fuel delivered to the combustion chamber. In this way, one turbine can drive two pump wheels to rotate, thereby delivering fuel and oxidant to the combustion chamber at the same time. Specifically, the turbine and the two pump wheels are connected through a rotating shaft, and when the turbine is driven to rotate, the two pump wheels can be driven to rotate at the same time.

[0032] As shown in the figure, Figure 1 As shown in the figure, in some embodiments, the fuel introduction pipeline 4 is connected with the second pipeline 8. In this way, the fuel in the second pipeline 8 has a certain power, and part of the fuel can be introduced into the exhaust pipeline 204 through the fuel introduction pipeline 4 without additional power.

[0033] As shown in the figure, Figure 1 As shown in the figure, in some embodiments, the inlet of the gas generator 3 is communicated with the first pipeline 7 through the third pipeline 9 and communicated with the second pipeline 8 through the fourth pipeline 10. In this way, part of the fuel and oxidant is introduced into the gas generator 3 by using the power generated by the pump wheel, thereby saving other power.

[0034] As shown in the figure, Figure 1 As shown in the figure, in some embodiments, valves are respectively arranged on the first pipeline 7, the second pipeline 8, the third pipeline 9 and the fourth pipeline 10. The valves control the opening and closing of the medium in the pipelines.

[0035] As shown in the figure, Figure 1 As shown in the figure, in some embodiments, the fuel introduction pipeline 4 is connected behind the valve. In this way, no valve is arranged on the fuel introduction pipeline 4, and the flow can be controlled only by the cavitation pipeline 6.

[0036] In addition, in some alternative embodiments, the fuel introduction pipeline 4 can also be connected in front of the valve, and in this way, a valve is arranged on the fuel introduction pipeline 4 to prevent fuel from flowing out before the engine starts.

[0037] As shown in the figure, Figure 1 As shown in the figure, in some embodiments, the outlet of the volute 201 is provided with a heat exchanger 11, and the heat exchanger 11 is connected with the first pipeline 7. Through the heat exchanger 11, the gas in the exhaust pipeline 204 is cooled, and the oxidant in the first pipeline 7 is heated at the same time.

[0038] The technical scheme of the embodiment achieves the temperature reduction target of the vacuum engine nozzle film cooling medium, and ensures that the engine nozzle 1 has good cooling effect. At the same time, the scheme has less modification degree to the engine structure, does not need to add additional valves, and has little influence on the engine fuel flow.

[0039] Working principle: The gas generator 3 obtains the oxidant from the first pipeline 7 and the fuel from the second pipeline 8 through the third pipeline 9 and the fourth pipeline 10, combusts to generate high-temperature and high-pressure gas, and drives the turbine in the volute 201 to rotate. The turbine is connected with the pump wheel of the fuel pump 202 and the oxidant pump 203 through a rotating shaft, drives the pump wheel to rotate, realizes the delivery of the fuel and the oxidant to the combustion chamber, maintains the continuous combustion, and provides power for the engine.

[0040] The turbine exhaust gas flows in the exhaust pipeline 204, the fuel introduction pipeline 4 introduces fuel into the turbine exhaust gas, and the atomized fuel is mixed with the turbine exhaust gas. Since the turbine exhaust gas has high temperature, the fuel absorbs heat and gasifies, and in this process, the temperature of the turbine exhaust gas is reduced, and the medium flow is slightly increased, and the gas film cooling medium suitable for nozzle cooling is generated.

[0041] The gas film cooling medium flows into the cooling gas inlet of the divergent section of the nozzle 1, forms a cooling gas film on the inner wall of the nozzle, isolates the high-temperature gas from the inner wall of the nozzle, reduces the temperature of the inner wall of the nozzle, prevents the nozzle 1 from being damaged due to heating, enhances the cooling effect, and improves the reliability of the engine.

[0042] The heat exchanger 11 at the outlet of the volute 201 utilizes the heat of the gas in the exhaust pipeline 204 to heat the oxidant in the first pipeline 7, realizes energy recycling.

[0043] Although the embodiments of the present application are described in combination with the drawings, various modifications and variations can be made by those skilled in the art without departing from the spirit and scope of the present application, and such modifications and variations all fall within the scope defined by the present application.

Claims

1. A gas generator cycle vacuum engine, characterized in that, include: Nozzle (1), turbopump (2) and gas generator (3); The expansion section of the nozzle (1) has a cooling gas inlet; The turbopump (2) has a volute (201) and a turbine is located inside the volute (201); The outlet of the gas generator (3) is connected to the volute (201) to drive the turbine to rotate. An exhaust pipe (204) is connected to the volute (201). The exhaust pipe (204) is connected to the cooling gas inlet of the nozzle (1). A fuel inlet pipe (4) is also connected to the exhaust pipe (204) to introduce fuel into the exhaust pipe (204).

2. The gas generator cycle vacuum engine according to claim 1, characterized in that, The outlet of the fuel inlet pipe (4) is connected to an atomizer (5).

3. The gas generator cycle vacuum engine according to claim 1, characterized in that, A flow control device is connected to the fuel inlet pipe (4).

4. The gas generator cycle vacuum engine according to claim 3, characterized in that, The flow control device is a cavitation pipe (6).

5. The gas generator cycle vacuum engine according to any one of claims 1-4, characterized in that, The pump body of the turbopump (2) includes a fuel pump (202) and an oxidant pump (203). The outlet of the oxidant pump (203) is connected to the combustion chamber through a first pipe (7), and the outlet of the fuel pump (202) is connected to the combustion chamber through a second pipe (8).

6. The gas generator cycle vacuum engine according to claim 5, characterized in that, The fuel inlet pipe (4) is connected to the second pipe (8).

7. The gas generator cycle vacuum engine according to claim 5, characterized in that, The inlet of the gas generator (3) is connected to the first pipe (7) through the third pipe (9) and to the second pipe (8) through the fourth pipe (10). Valves are provided on the first pipe (7), the second pipe (8), the third pipe (9) and the fourth pipe (10).

8. The gas generator cycle vacuum engine according to claim 7, characterized in that, The fuel inlet pipe (4) is connected downstream of the valve.

9. The gas generator cycle vacuum engine according to claim 7, characterized in that, The fuel inlet pipe (4) is connected to the valve in front of the valve, and the valve is provided on the fuel inlet pipe (4).

10. The gas generator cycle vacuum engine according to claim 5, characterized in that, The outlet of the volute (201) is provided with a heat exchanger (11), which is connected to the first pipe (7).

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