Integrated structure of turbine pump, main valve and fuel gas generator

Abstract

The integrated structure of the turbine pump, the main valve and the fuel gas generator comprises the turbine pump, the turbine pump is of a barrel-shaped structure with the two ends open, the first end of the turbine pump is a first medium inlet, and the second end of the turbine pump is connected with a fuel gas generator flange; a movable valve element is installed in an inner channel between the turbine pump and the fuel gas generator. When the valve element moves to the first position, the inner channel is closed. When the valve element moves to the second position, the inner channel is opened; the structures of the turbine pump, the main valve and the fuel gas generator are improved, the improved turbine pump and the fuel gas generator are in flange connection, the main valve is installed in an internal channel of the turbine pump and the fuel gas generator, the integrated structure of the turbine pump, the main valve and the fuel gas generator is achieved, pipeline connection is avoided, and the space size and the assembly difficulty are reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of supplementary combustion cycle liquid rocket engines, and in particular relates to an integrated structure of a turbo pump, a main valve and a gas generator. Background Art

[0002] The regenerative cycle liquid rocket engine can be divided into three types: oxygen-rich cycle, fuel-rich cycle and full-flow regenerative cycle.

[0003] The oxygen-rich cycle uses an oxygen-rich generator, and there are two options: one is that all the oxidant first cools the thrust chamber, and then all enters the generator and mixes with a small amount of fuel to burn, generating oxygen-rich combustion gas to drive the turbine, and then burns with a large amount of fuel in the thrust chamber; the other is that the thrust chamber is cooled by fuel, and then the fuel and the oxygen-rich combustion gas after the driving turbine rotates are burned in the thrust chamber.

[0004] The fuel-rich cycle is similar to the oxygen-rich cycle and uses a fuel-rich generator. There are also two options: one is that all the fuel first cools the thrust chamber, and then all enters the generator and mixes with a small amount of oxidant to burn, generating fuel-rich combustion gas to drive the turbine, and then burns with a large amount of oxidant in the thrust chamber; the other is that the thrust chamber is cooled by oxidant, and then the oxidant and the fuel-rich combustion gas after the driving turbine rotates burn in the thrust chamber.

[0005] The full-flow regenerative combustion cycle uses an oxygen-rich generator and a fuel-rich generator to provide the gas for driving the turbine to the oxygen-rich turbopump and the fuel-rich turbopump respectively, and then transports the gas to the thrust chamber for combustion. This cycle has good combustion stability and the highest performance. There are also two options for the full-flow regenerative combustion cycle, namely using oxidant to cool the thrust chamber or using fuel to cool the thrust chamber.

[0006] The structure of the above-mentioned regenerative cycle liquid rocket engine is relatively complex. The turbine pump, main valve and gas generator are connected by pipelines, mainly including the medium pipeline between the pump outlet and the main valve, the medium pipeline between the main valve and the gas generator, the gas pipeline between the gas generator and the turbine, and the main valve control gas pipeline. These pipelines have different shapes and sizes, complex spatial layout, and require a device to fix the pipeline during installation. As a result, the regenerative cycle engine system has a complex structure, large spatial dimensions, a large number of parts, high assembly difficulty, and low structural reliability. Summary of the invention

[0007] The purpose of the present invention is to provide an integrated structure of a turbo pump, a main valve and a gas generator, which can avoid the use of pipeline connections and reduce the difficulty of engine assembly.

[0008] The present invention adopts the following technical solution: an integrated structure of a turbine pump, a main valve and a gas generator, comprising a turbine pump, the turbine pump being a barrel-shaped structure with openings at both ends, a first end of which is a first medium inlet, and a second end of which is flange-connected to the gas generator;

[0009] A movable valve core is installed in the internal passage between the turbine pump and the gas generator; when the valve core moves to a first position, the internal passage is closed; when the valve core moves to a second position, the internal passage is opened.

[0010] Further, the turbine pump comprises an outer casing, in which an inner casing is coaxially arranged;

[0011] The inner casing is tubular, a first end of which extends radially outward to form an annular plate, and a second end of which extends outward from a second end of the outer casing;

[0012] The outer shell corresponding to the position of the annular plate expands radially outward, and a first medium speed reduction flow channel is formed between the annular plate and the outer shell.

[0013] Furthermore, a first diffuser blade and a second diffuser blade are sequentially installed in the first medium velocity reduction flow channel.

[0014] Furthermore, the valve core includes an inner ring body and an outer ring body, the inner ring body and the outer ring body are connected by connecting ribs, and adjacent connecting ribs have flow holes;

[0015] A disc spring is installed between the end surface of the inner ring body and the gas generator;

[0016] The outer ring surface of the outer ring body is sealed and connected to the outer shell, and the inner ring surface is sealed and connected to the gas generator.

[0017] Furthermore, a first pressure chamber is formed between the end surface of the outer ring body, the inner wall surface of the outer shell and the gas generator;

[0018] A groove is provided inwardly on the outer ring surface of the outer ring body, and a second pressure chamber is formed between the groove and the outer shell. A control air inlet is provided on the outer shell, and the control air inlet is communicated with the second pressure chamber.

[0019] Furthermore, the gas generator includes an annular mixing chamber, a top plate of the mixing chamber is provided with a liquid inlet, and the liquid inlet is opposite to the flow hole;

[0020] A side plate is arranged downwardly on the outer side of the top plate, and a first medium channel is formed between the side plate and the outer shell of the gas generator;

[0021] A partition is provided between the side plate and the mixing chamber, a combustion chamber is formed between the partition and the side plate, and the combustion chamber and the mixing chamber are connected through the space between the partition and the top plate;

[0022] The combustion chamber is communicated with a second medium inlet which is provided on the shell of the gas generator.

[0023] Furthermore, a stationary blade cascade is provided at the outlet of the mixing chamber.

[0024] Furthermore, a main shaft is coaxially installed in the inner shell, a second end of the main shaft is located in the gas generator, a turbine rotor is installed on the second end of the main shaft, and blades of the turbine rotor are located at the outlet of the mixing chamber.

[0025] Furthermore, a first bearing and a second bearing are installed between the main shaft and the inner housing at intervals.

[0026] Furthermore, a first sealing device is provided between the main shaft and the inner housing.

[0027] The beneficial effects of the present invention are as follows: the present invention improves the structures of the turbine pump, the main valve and the gas generator. The improved turbine pump and the gas generator are flange-connected, and the main valve is installed in the internal channels of the two, thereby realizing an integrated structure of the three, avoiding connecting pipelines, and reducing the space size and assembly difficulty. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 A schematic diagram of the structure of a turbine pump housing in an embodiment of the present invention;

[0029] Figure 2 A schematic diagram of the combination of a turbine pump housing and a valve core in an embodiment of the present invention;

[0030] Figure 3 It is a schematic diagram of the top view of the valve core in an embodiment of the present invention;

[0031] Figure 4 It is a schematic diagram of the combination of a turbine pump housing, a valve core and a gas generator in an embodiment of the present invention;

[0032] Figure 5 Schematic diagram of the flow paths of various media in the embodiment of the present invention;

[0033] Figure 6 This is a schematic diagram of the structure after the turbine rotor is installed in an embodiment of the present invention;

[0034] Figure 7 It is a schematic structural diagram of another embodiment of the present invention.

[0035] Among them: 100. Turbine pump;

[0036] 110. Liquid inlet; 120. Inner shell; 130. Outer shell; 140. First diffuser blade; 150. Second diffuser blade; 160. Control gas inlet; 170. Connecting part;

[0037] 200. valve core; 210. flow hole; 220. connecting rib; 230. inner ring body; 240. outer ring body;

[0038] 300. Gas generator; 310. Liquid inlet; 320. First medium channel; 330. Second medium inlet; 340. Mixing chamber; 350. Combustion chamber; 360. Stationary blade cascade; 370. Gas outlet;

[0039] 400. Disc spring;

[0040] 500. Turbine rotor; 510. First bearing; 520. Inducer; 530. Centrifugal wheel; 540. First sealing device; 550. Second bearing; 560. Second sealing device. DETAILED DESCRIPTION

[0041] The present invention is described in detail below with reference to the accompanying drawings and specific embodiments.

[0042] The present invention discloses an integrated structure of a turbine pump, a main valve and a gas generator, such as Figure 3 As shown, the turbine pump 100 is a barrel-shaped structure with two ends open, a first end of which is a first medium inlet 110, and a second end is flange-connected to a gas generator 300; Figure 1 The figure shows the connection flange at the end of the outer shell 130, that is, the connection part 170. A movable valve core 200 is installed in the internal passage between the turbo pump 100 and the gas generator 300; when the valve core 200 moves to the first position, the internal passage is closed; when the valve core moves to the second position, the internal passage is opened.

[0043] The present invention improves the structure of the turbine pump 100, the main valve and the gas generator 300. The improved turbine pump and the gas generator are flange-connected, and the main valve is installed in the internal channels of the two, thereby realizing an integrated structure of the three, avoiding connecting pipelines, and reducing space size and assembly difficulty.

[0044] In one embodiment, Figure 1 As shown, the turbine pump 100 includes an outer shell 130, in which an inner shell 120 is coaxially arranged; the inner shell 120 is tubular, a first end of which radially extends outward to form an annular plate, and a second end extends out of the second end of the outer shell 130; the outer shell 130 corresponding to the position of the annular plate expands radially outward, and a first medium speed reduction flow channel is formed between the annular plate and the outer shell 130. By designing the expansion section of the annular plate and the outer shell 130, the first medium can be reduced in speed along the flow channel after entering, thereby increasing the static pressure.

[0045] In addition, the first medium deceleration flow channel is sequentially installed with a first diffuser blade 140 and a second diffuser blade 150. More specifically, the upper and lower parts of the expansion section correspond to the two end surfaces of the annular plate, respectively, so that the first diffuser blade 140 and the second diffuser blade 150 can be installed between the annular plate and the expansion section. In other words, the design purpose of the annular plate is to provide a flow path for the first medium to decelerate and increase pressure.

[0046] The present invention eliminates the traditional spiral volute and diffuser pipe, and completes the guiding and pressurizing functions through the flow channel in the shell and two rows of radial diffuser blades, thereby greatly reducing the radial size of the engine.

[0047] As a specific implementation method, Figure 2 and Figure 3 As shown, the valve core 200 includes an inner ring body 230 and an outer ring body 240, and the inner ring body 230 and the outer ring body 240 are connected by connecting ribs 220, and adjacent connecting ribs 220 have flow holes 210; when the valve core 200 moves downward, the top of the outer ring body 240 is separated from the bottom surface of the annular plate. At this time, the first medium enters between the valve core 200 and the inner shell 120, and due to the high pressure of the first medium inlet 110, the first medium will continue to move downward through the flow hole 210.

[0048] According to different media, the seal between the valve core 200 and the turbine pump housing can be a non-metallic seal or a metal seal. When a metal seal is selected, processes such as grinding and electroplating are required.

[0049] More specifically, a disc spring 400 is installed between the end surface of the inner ring body 230 and the gas generator 300; the outer ring surface of the outer ring body 240 is sealedly connected to the outer shell 130, and the inner ring surface is sealedly connected to the gas generator 300. A first pressure chamber is formed between the end surface of the outer ring body 240, the inner wall surface of the outer shell 130 and the gas generator; a groove is formed inwardly on the outer ring surface of the outer ring body 240, and a second pressure chamber is formed between the groove and the outer shell 130, and a control gas inlet 160 is formed on the outer shell 130, and the control gas inlet 160 is connected to the second pressure chamber.

[0050] Through the design of the first pressure chamber and the second pressure chamber, the movement of the valve core 200 can be controlled by the pressure difference and the force of the disc spring.

[0051] In one embodiment, Figure 4 As shown, the gas generator 300 includes an annular mixing chamber 340, and a liquid inlet 310 is provided on the top plate of the mixing chamber 340, and the liquid inlet 310 is opposite to the flow hole 210. Through the arrangement of the liquid inlet 310, most of the first medium can enter the mixing chamber 340, and a small part of the first medium can enter the combustion chamber 350 along the first medium channel 320.

[0052] Specifically, a side plate is arranged downwardly on the outer side of the top plate, and a first medium channel 320 is formed between the side plate and the outer shell of the gas generator 300; a partition is arranged between the side plate and the mixing chamber 340, and a combustion chamber 350 is formed between the partition and the side plate, and the combustion chamber 350 and the mixing chamber 340 are connected through the space between the partition and the top plate; the combustion chamber 350 is connected to the second medium inlet 330, and the second medium inlet is opened on the outer shell of the gas generator 300. A stationary blade cascade 360 ​​is arranged at the outlet of the mixing chamber 340. Moreover, a vertical plate is also provided on the inner side of the gas generator 300, and the vertical plate is fixedly and sealedly connected to the outer periphery of the inner shell 120 to prevent the first medium from directly leaking to the gas outlet 370.

[0053] The vertical plates, top plates, side plates and partition plates in this embodiment are all annular plates. Through these designs, a medium flow channel can be established in the gas generator 300 to achieve combustion, mixing and acceleration.

[0054] In one embodiment, Figure 6 As shown, a main shaft is coaxially installed in the inner casing 120, and the second end of the main shaft is located in the gas generator 300. A turbine rotor 500 is installed on the second end of the main shaft, and the blades of the turbine rotor 500 are located at the outlet of the mixing chamber 340. A first bearing 510 and a second bearing 550 are installed between the main shaft and the inner casing 120. A first sealing device 540 is provided between the main shaft and the inner casing 120.

[0055] In addition, the first end of the main shaft is located inside the outer shell 130, close to the first medium inlet 110, and the induction wheel 520 and the centrifugal wheel 530 are installed in sequence in the part between the first medium inlet 110 and the annular plate to realize the acceleration, pressurization and guidance of the first medium, so that the first medium can smoothly enter the deceleration and pressurization flow channel. Moreover, in order to further increase the sealing performance, a second sealing device 560 can be added between the end of the inner shell 120 and the main shaft. Depending on the different media, the first sealing device 540 can be a floating ring seal or a labyrinth seal, and the second sealing device 560 can be an end face seal or a leather cup seal. In order to adapt to the system characteristics of low pressure ratio and large flow of the regenerative cycle, the turbine is designed as a low reaction force structure.

[0056] In another embodiment, Figure 7 As shown, the first medium inlet 110 may also be opened along the radial direction of the outer shell 130, so that other structures can be designed at the end of the outer shell 130 to facilitate overall technical innovation.

[0057] Regarding the medium flow path in the present invention, Figure 5As shown, the first medium enters the turbo pump 100 from the first medium inlet 110, and then moves toward the outer shell 130 under the action of the inducer 520 and the centrifugal wheel 530. Then, when the first medium passes between the annular plate and the expansion section of the outer shell 130 in sequence, it is decelerated and pressurized under the action of the first diffuser blade 140 and the second diffuser blade 150.

[0058] At this time, high-pressure gas will rush into the control gas inlet 160. Under the action of the high-pressure gas, the pressure of the second pressure chamber is much greater than the pressure of the first pressure chamber and the elastic force of the disc spring 400, so that the valve core 200 moves toward the gas generator 300 under the action of pressure, and the first medium continues to move forward from the channel between the outer ring body 240 and the annular plate.

[0059] When the first medium moves to the liquid inlet hole 310, most of the first medium enters the mixing chamber 340 from the liquid inlet hole 310, and a small part of the first medium enters the combustion chamber along the first medium channel 320, and is mixed and burned with the second medium entering from the second medium inlet 330. After combustion, the high-pressure gas enters the mixing chamber 340 through the channel between the partition and the top plate, and the high-pressure gas is mixed with the first medium entering through the liquid inlet hole 310 to form high-pressure combustion gas and is accelerated to be discharged through the stationary blade cascade 360.

[0060] Driven by the high-pressure and high-speed combustion gas discharged from the stationary blade cascade 360 ​​, the turbine rotor 500 rotates, thereby driving the inducer 520 and the centrifugal wheel 530 to rotate.

[0061] As a specific embodiment, the structure is applied to an oxygen-rich supplementary combustion cycle liquid oxygen / kerosene engine, the first medium may be liquid oxygen, and the second medium may be kerosene.

[0062] The structure is applied to an oxygen-rich supplementary combustion cycle liquid oxygen / methane engine, wherein the first medium may be liquid oxygen and the second medium may be methane.

[0063] The structure can also be applied to a full-flow staging cycle liquid oxygen / methane engine, where the first medium is liquid oxygen and the second medium is methane.

[0064] In summary, the integrated structure of the present invention is applicable to the oxygen-rich regenerative cycle oxidant path of the fuel-cooled thrust chamber, the fuel path of the fuel-rich regenerative cycle of the oxidant-cooled thrust chamber, and the medium path of the full-flow regenerative cycle that does not require cooling of the thrust chamber. Through the new structural layout and the integrated design of the internal flow channel, the turbo pump 100, the main valve and the gas generator 300 are integrated into one, and there is no need for pipeline connection between the three, which simplifies the engine structure, reduces the engine space size, reduces the number of parts, reduces the difficulty of assembly, and improves the reliability of the engine structure itself.

[0065] The gas generator 300 is designed as an annular structure, surrounding the outside of the inner casing of the turbine pump, which greatly saves the axial layout space of the engine. The stationary blade cascade 360 ​​is set at the outlet of the combustion chamber of the gas generator 300, which accelerates the gas and blows the turbine rotor 500 to rotate, eliminating the gas pipeline between the gas generator 300 and the turbine pump 100, making the overall structure of the engine more compact. The gas after driving the turbine is discharged through the outlet flange and finally reaches the thrust chamber for secondary combustion.

Claims

1. An integrated structure of a turbo pump, a main valve and a gas generator, characterized in that: The turbine pump (100) is a barrel-shaped structure with openings at both ends, a first end of the turbine pump (100) being a first medium inlet (110), and a second end being flange-connected to a gas generator (300); A movable valve core (200) is installed in the internal passage between the turbine pump (100) and the gas generator (300); when the valve core (200) moves to a first position, the internal passage is closed; when the valve core moves to a second position, the internal passage is opened.

2. The integrated structure of a turbo pump, a main valve and a gas generator as claimed in claim 1, characterized in that: The turbine pump (100) comprises an outer casing (130), wherein an inner casing (120) is coaxially arranged in the outer casing (130); The inner shell (120) is tubular, with a first end extending radially outward to form an annular plate, and a second end extending out of the second end of the outer shell (130); The outer shell (130) corresponding to the position of the annular plate expands radially outward, and a first medium speed reduction flow channel is formed between the annular plate and the outer shell (130).

3. The integrated structure of a turbo pump, a main valve and a gas generator as claimed in claim 2, characterized in that: A first diffuser blade (140) and a second diffuser blade (150) are sequentially installed in the first medium velocity reduction flow channel.

4. The integrated structure of a turbo pump, a main valve and a gas generator as claimed in claim 2, characterized in that: The valve core (200) comprises an inner ring body (230) and an outer ring body (240), wherein the inner ring body (230) and the outer ring body (240) are connected via connecting ribs (220), and adjacent connecting ribs (220) have flow holes (210); A disc spring (400) is installed between the end surface of the inner ring body (230) and the gas generator (300); The outer ring surface of the outer ring body (240) is sealedly connected to the outer shell (130), and the inner ring surface is sealedly connected to the gas generator (300).

5. The integrated structure of a turbo pump, a main valve and a gas generator as claimed in claim 4, characterized in that: A first pressure chamber is formed between the end surface of the outer ring body (240), the inner wall surface of the outer shell (130) and the gas generator; The outer ring surface of the outer ring body (240) is provided with a groove inwardly, and a second pressure chamber is formed between the groove and the outer shell (130). The outer shell (130) is provided with a control air inlet (160), and the control air inlet (160) is connected to the second pressure chamber.

6. The integrated structure of a turbo pump, a main valve and a gas generator as claimed in claim 5, characterized in that: The gas generator (300) comprises an annular mixing chamber (340), a top plate of the mixing chamber (340) is provided with a liquid inlet (310), and the liquid inlet (310) is opposite to the flow hole (210); A side plate is arranged downwardly on the outer side of the top plate, and a first medium channel (320) is formed between the side plate and the outer shell of the gas generator (300); A partition is provided between the side plate and the mixing chamber (340), a combustion chamber (350) is formed between the partition and the side plate, and the combustion chamber (350) and the mixing chamber (340) are connected via a space between the partition and the top plate; The combustion chamber (350) is in communication with a second medium inlet (330), and the second medium inlet is provided on the outer shell of the gas generator (300).

7. The integrated structure of a turbo pump, a main valve and a gas generator as claimed in claim 6, characterized in that: The outlet of the mixing chamber (340) is provided with a stationary blade cascade (360).

8. The integrated structure of a turbo pump, a main valve and a gas generator as claimed in claim 7, characterized in that: A main shaft is coaxially mounted in the inner casing (120), a second end of the main shaft is located in the gas generator (300), a turbine rotor (500) is mounted on the second end of the main shaft, and blades of the turbine rotor (500) are located at the outlet of the mixing chamber (340).

9. The integrated structure of a turbo pump, a main valve and a gas generator as claimed in claim 8, characterized in that: A first bearing (510) and a second bearing (550) are installed between the main shaft and the inner housing (120) at intervals.

10. An integrated structure of a turbo pump, a main valve and a gas generator as claimed in claim 9, characterized in that: A first sealing device (540) is provided between the main shaft and the inner housing (120).

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