A gas hydraulic servo system with power optimization function

Abstract

The present invention discloses a gas hydraulic servo system, which includes a gas source, a turbine pump and an oil source assembly. The gas source is used to deliver gas to the turbine pump to drive the turbine pump to suck oil from the oil source assembly. The gas hydraulic servo system satisfies at least one of the following: the turbine pump is provided with a nozzle, and the nozzle is used to accelerate the delivered gas at the front end of the turbine of the turbine pump. The nozzle is detachable from the turbine pump, so as to adjust the degree of gas acceleration by adjusting the throat diameter of the nozzle; the turbine pump is provided with an annular member, and the annular member surrounds the outer periphery of the turbine of the turbine pump. The annular member is detachable from the turbine pump, so as to adjust the gas flow rate between the annular member and the turbine by adjusting the gap between the annular member and the turbine; a throttle ring is arranged at the gas outlet end of the turbine pump, and the throttle ring is detachable from the turbine pump, so as to adjust the exhaust back pressure of the turbine pump by adjusting the inner diameter of the throttle ring. The present invention has been tested in application practice and achieved the purpose of optimizing and adjusting the power.

Description

Technical Field

[0001] The present application relates to the technical field of gas hydraulic servo, in particular to a gas hydraulic servo system with power optimization function. Background Art

[0002] This technology takes the currently widely used aerospace gas hydraulic servo technology as the application background. Aerospace servo technology is a technology for thrust vector control of rocket or missile engine nozzles. When a rocket needs to adjust its attitude or control its direction during flight, the servo actuator in the servo system provides thrust and swings the engine nozzle according to the control instruction requirements, thereby achieving the control of the rocket's flight attitude and direction. Gas hydraulic servo technology is an energy system with a solid gas source as the primary energy source, a hypersonic turbopump as the core energy conversion unit, and an oil source assembly composed of check valves, relief valves, various fluid connectors and booster components as the main component system. During operation, the solid gas source is ignited to generate high-temperature and high-pressure gas. After the high-temperature and high-pressure gas is led to the hypersonic turbopump, it is expanded and accelerated through a supersonic nozzle and then drives the turbopump to rotate at high speed. The pump impeller in the turbopump sucks hydraulic oil from the oil source assembly, rotates at high speed and pressurizes it, and then is delivered to various fluid connectors through the relief valve and check valve in sequence for external output. In a gas hydraulic servo system, its externally output hydraulic power is mainly determined by two parts. The solid gas source determines the total input power level, and the turbopump determines the conversion power efficiency and the total hydraulic power output externally. The design of the solid gas source is highly matched with the supersonic nozzle in the turbopump. Once the design is completed, its output power level and working duration are determined, and the output power cannot be adjusted without changing the design scheme; the turbopump is also designed according to its highest working efficiency point and output power level. Theoretically, if the output power is to be adjusted, the design scheme has to be adjusted; the design of the oil source assembly determines the total capacity of the working medium in the energy system.

[0003] After the gas hydraulic servo energy system is designed, it is very difficult for its output power to be consistent with the actual working demand power of the servo actuator. If the output power of the energy system is higher than the actual demand, the excess energy will be converted into heat energy and consumed through the relief valve in the energy system, which will cause the overall temperature of the entire energy system to continuously rise during operation, affecting the working reliability of the system; if the output power of the energy system is lower than the actual demand during operation, the system performance cannot be fully released, affecting its function. Thus, it can be seen that after the energy system is designed and processed and assembled, it is still necessary to optimize and adjust the output power of the energy system within a certain range according to the actual demand without changing the design scheme and the main structure of the product. Summary of the Invention

[0004] Based on such requirements, the present invention proposes a solution that is both convenient and feasible and has the least impact on the overall system scheme and structure: namely, at the beginning of the design scheme, the intake air scheme of the supersonic nozzle is installed by inlaying on the housing in the turbine pump design scheme, and a ring-shaped structure covering the outermost edge of the turbine is inlaid in the turbine cover design. At the same time, a throttle ring is installed at the tail of the gas exhaust channel on the turbine cover.

[0005] In the actual use process, the system output power can be optimized and adjusted in three ways: 1) By modifying or replacing the supersonic nozzle to adjust the throat diameter of the nozzle, so as to adjust the pressure of the solid gas source combustion chamber, and then adjust the gas output power; 2) By adjusting the inner diameter size of the ring-shaped part in the turbine cover to adjust the tip clearance of the turbine blades, so as to adjust the working efficiency of the turbine pump to achieve the optimization and adjustment of the output power; 3) Adjust the inner diameter of the throttle ring at the tail of the gas exhaust channel to achieve the purpose of adjusting the exhaust back pressure of the turbine pump, and finally achieve the optimization and adjustment of the system output power. The above invention methods have been tested in application practice and have fully achieved the purpose of optimizing and adjusting the power.

[0006] In a first aspect, a gas hydraulic servo system is provided, including a gas source, a turbine pump, and an oil source assembly. The gas source is used to supply gas to the turbine pump to drive the turbine pump to suck oil from the oil source assembly. The gas hydraulic servo system satisfies at least one of the following:

[0007] The turbine pump is provided with a nozzle, and the nozzle is used to expand and accelerate the conveyed gas at the front end of the turbine of the turbine pump. The nozzle can be detached from the turbine pump, so as to adjust the throat diameter of the nozzle, the gas acceleration degree, and the gas flow rate;

[0008] The turbine pump is provided with a ring-shaped part, and the ring-shaped part surrounds the outer periphery of the turbine of the turbine pump. The ring-shaped part can be detached from the turbine pump, so as to adjust the gas flow rate between the ring-shaped part and the turbine by adjusting the gap between the ring-shaped part and the turbine;

[0009] A throttle ring is arranged at the gas outlet end of the turbine pump, and the throttle ring can be detached from the turbine pump, so as to adjust the exhaust back pressure of the turbine pump by adjusting the inner diameter of the throttle ring.

[0010] In combination with the first aspect, in some implementation manners of the first aspect, the adjustment center value of the throat diameter is 3-6 mm, and the throat diameter varies within the range of ±5-30% of the adjustment center value.

[0011] In combination with the first aspect, in certain implementations of the first aspect, the turbo pump includes a housing, the housing includes a first cavity and a second cavity, the second cavity is located on the side of the first cavity close to the turbine, the first cavity is used to accommodate the nozzle, and the inner cavity of the nozzle communicates with the second cavity.

[0012] In combination with the first aspect, in certain implementations of the first aspect, the housing satisfies at least one of the following:

[0013] The wall thickness ratio of the first cavity to the second cavity is 0.4 to 0.6;

[0014] The inner diameter dimension of the second cavity matches the opening dimension of the nozzle facing the turbine.

[0015] In combination with the first aspect, in certain implementations of the first aspect, the gap between the annular member and the turbine is the turbine tip clearance Δh, the adjustment center value of the turbine tip clearance Δh is 0.4 to 1 mm, and the turbine tip clearance Δh varies within the range of ±5 to 40% of the adjustment center value.

[0016] In combination with the first aspect, in certain implementations of the first aspect, the turbo pump includes a housing and a turbine cover assembled with each other, the housing has a gas passage leading to the turbine, and the turbine cover is used to accommodate the turbine; wherein,

[0017] An annular groove is provided on the side of the turbine cover facing the housing, the annular groove corresponds to the position of the turbine, and the annular member abuts against the inner wall of the annular groove.

[0018] In combination with the first aspect, in certain implementations of the first aspect, the adjustment center value of the inner diameter of the throttle ring is 35 to 50 mm, and the inner diameter varies within the range of ±10 to 30% of the adjustment center value.

[0019] In combination with the first aspect, in certain implementations of the first aspect, the turbo pump includes a turbine cover, the turbine cover is used to accommodate the turbine, the turbine cover further has a gas exhaust passage, the gas from the turbine is discharged through the gas exhaust passage, and the throttle ring is provided at the outlet of the gas exhaust passage.

[0020] In combination with the first aspect, in certain implementations of the first aspect, the outlet diameter of the gas exhaust passage is larger than the inner diameter of the throttle ring.

[0021] In a second aspect, a design method for a gas hydraulic servo system is provided, characterized in that the method is applied to the gas hydraulic servo system in any one of the implementations in the first aspect as described above; the method includes:

[0022] Replace or adjust at least one of the following according to the adjustment amount of the output power of the energy system: the nozzle, the annular member, and the throttle ring.

[0023] In combination with the second aspect, in some implementations of the second aspect, the method includes: satisfying at least one of the following when the adjustment amount increases:

[0024] The throat diameter of the nozzle after replacement or adjustment is smaller than that before replacement;

[0025] The inner diameter of the annular member after replacement or adjustment is smaller than that before replacement;

[0026] The inner diameter of the throttle ring after replacement or adjustment is larger than that before replacement.

[0027] Compared with the prior art, the solution provided by this application includes at least the following beneficial technical effects:

[0028] 1) A larger throat diameter can reduce the pressure and flow rate of the gas generated by the gas source to reduce the gas output power, and a smaller throat diameter can increase the gas pressure and flow rate to increase the gas output power. By adjusting the throat diameter to vary within the range of ±5 to 30%, the gas output power can be adjusted within the range of ±5 to 10%; 2) By adjusting the inner diameter of the annular member, the clearance between the turbine blade tips can be adjusted, thereby adjusting the working efficiency of the turbine to achieve the adjustment of the converted output power. In this way, the output power of the turbine pump can be adjusted within the range of ±5 to 10%; 3) By adjusting the inner diameter of the throttle ring, the exhaust back pressure of the turbine can be adjusted, thereby achieving the adjustment of the conversion efficiency of the gas expansion work and the adjustment of the output power of the energy system. In this way, the output power of the energy system can be adjusted by more than ±10%. In actual use, the above one, or two, or three methods can be combined to achieve the purpose of adjusting the energy system power in a larger range. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is a schematic diagram of the principle of a gas hydraulic servo energy system solution.

[0030] Figure 2 It is a schematic diagram of the installation structure of the turbine intake nozzle in a gas hydraulic servo energy system.

[0031] Figure 3 It is an external structure diagram of a gas turbine pump.

[0032] Figure 4 It is a schematic diagram of the structure of the turbine cavity of the turbine pump in a gas hydraulic servo energy system.

[0033] Figure 5It is a partial schematic diagram of the turbine chamber and exhaust structure of a turbine pump in a gas-hydraulic servo energy system. Specific embodiments

[0034] The present application will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0035] Figure 1 It is a schematic structural diagram of a gas-hydraulic servo system provided by an embodiment of the present application. As Figure 1 shown, the gas-hydraulic servo system applicable to the embodiment of the present application includes a gas source 1, a turbine pump 2, and an oil source assembly 3. The gas source 1 mainly generates high-temperature and high-pressure gas and drives the turbine pump 2 to rotate at high speed through a gas conduit. The turbine pump 2 is installed in the oil source assembly 3, and the oil source assembly 3 may include a housing 9, a booster assembly 8, a check valve 4, a relief valve 5, an inlet connector 7, and an outlet connector 6. The turbine pump 2 sucks hydraulic oil from the oil source assembly 3 and outputs it after boosting. The gas after doing work is released through the turbine gas exhaust passage of the turbine pump 2.

[0036] Combined with Figure 1 and Figure 2 , the gas source 1 can be connected to the supersonic nozzle 15 on the housing 10 of the turbine pump 2 through a gas conduit. The gas drives the turbine 11 of the turbine pump 2 to rotate at high speed after expanding and accelerating through the nozzle 15. In some embodiments, the nozzle 15 may be a component assembled on the housing 10 of the turbine pump 2. That is to say, the nozzle 15 can be disassembled from the housing 10 of the turbine pump 2.

[0037] The housing 10 has a first cavity and a second cavity, and the second cavity is located between the first cavity and the turbine 11. The first cavity is used to install the nozzle 15, and the inner diameter of the first cavity can match the outer diameter of the nozzle 15. The second cavity communicates with the inner cavity of the nozzle 15. The opening size of the nozzle 15 facing the turbine 11 can match the inner diameter size of the second cavity. To ensure mechanical stability, the wall thickness ratio of the first cavity to the second cavity can be 0.4 to 0.6. For different application scenarios, according to the adjusted power requirements, nozzles with different throat diameters are assembled on the housing 10 of the turbine pump 2, so as to realize the adjustment of the throat diameter of the nozzle 15. For different gas-hydraulic servo systems, nozzles 15 with appropriate opening sizes and outer diameter sizes can be selected according to the inner diameter of the second cavity and the inner diameter of the first cavity of the housing 10, which is convenient for application on various gas-hydraulic servo systems.

[0038] Since the mass flow rate of the gas generated by the gas generator is positively correlated with the combustion chamber pressure, a larger throat diameter can reduce the combustion chamber pressure, thereby reducing the gas mass flow rate, and ultimately resulting in a reduction in the gas output power. Conversely, a smaller throat diameter can increase the gas pressure and flow rate to increase the gas output power. The adjustment center value of the throat diameter can be 3 - 6 mm. Adjusting the throat diameter within the range of ±5 - 30% based on the adjustment center value of the throat diameter can cause the combustion chamber pressure to vary within the range of ±5 - 30%, and ultimately achieve an adjustment of the gas output power within the range of ±5 - 10%.

[0039] Combined with Figures 2 to 4 , the nozzle 15 on the housing 10 of the turbopump 2 can deliver gas to the turbine 11 in the turbine cover 12. In some other embodiments, an annular groove can be provided on the side of the turbine cover 12 facing the housing 10, and the space formed by the annular groove can be used to accommodate the turbine 11 and the annular member 13. That is to say, by providing the annular groove, the annular member 13 can be sleeved inside the turbine cover 12. The annular member 13 abuts against the inner wall of the annular groove and surrounds the outer periphery of the turbine 11. The axis of the annular member 13 can be aligned with the axis of the turbine 11. When replacing the annular member 13, the housing 10 and the turbine cover 12 can be disassembled to take out the annular member 13 to be replaced, and then the new annular member 13 can be arranged in the annular groove on the side of the turbine cover 12 facing the housing 10.

[0040] The clearance between the diameter of the annular member 13 and the turbine 11 can be the turbine tip clearance Δh, as Figure 5 shown. In actual use, the inner diameter size of the annular member 13 can be adjusted according to the adjustment power requirement. When the inner diameter decreases, the turbine tip clearance Δh decreases, the secondary flow at the turbine top decreases, and the turbine aerodynamic efficiency increases. Thus, when the power at the gas source input end is constant, the hydraulic power output by the turbine can be increased. Conversely, when the inner diameter of the annular member 13 increases, the hydraulic power output by the turbine decreases. By adjusting the inner diameter size of the annular member 13, the size of the turbine tip clearance of the turbine 11 can be adjusted, thereby realizing the adjustment of the turbine working efficiency to achieve the adjustment of the converted output power. In a possible case, the annular member 13 may not be provided inside the turbine cover 12, so that the clearance between the inner wall of the annular groove on the turbine cover 12 and the diameter of the turbine 11 can constitute the maximum value of the turbine tip clearance Δh.

[0041] The adjustment center value of the turbine tip clearance Δh can be 0.4 - 1 mm. Through experimental statistics, adjusting the turbine tip clearance Δh within the range of ±5 - 40% according to the adjustment center value of the turbine tip clearance Δh can adjust the output power of the turbopump 2 within the range of ±5 - 10%.

[0042] As Figure 5As shown, the exhausted gas after doing work can be discharged through the turbine cover 12. In some other embodiments, a throttle ring 14 can be installed at the tail of the gas exhaust passage of the turbine cover 12, and the inner diameter of the throttle ring 14 can be smaller than the outlet diameter of the turbine cover 12. In actual use, the size of the inner diameter of the throttle ring 14 can be adjusted according to the adjusted power requirement. When the inner diameter of the throttle ring 14 increases, the exhaust back pressure in the turbine cavity decreases, and the isentropic expansion power of the gas increases, so that the output power of the turbine increases. On the contrary, when the inner diameter of the throttle ring 14 decreases, the exhaust back pressure in the turbine cavity increases, and the isentropic expansion power of the gas decreases, so that the output power of the turbine decreases. Thus, by adjusting the size of the inner diameter of the throttle ring 14, the adjustment of the exhaust back pressure of the turbine 11 can be realized, so as to achieve the adjustment of the conversion efficiency of the gas expansion work and the adjustment of the output power of the energy system.

[0043] The adjustment center value of the inner diameter of the throttle ring 14 can be 35 - 50 mm. Through experimental statistics, according to the adjustment center value of the inner diameter of the throttle ring 14, adjusting the inner diameter of the throttle ring 14 within the range of ±10 - 30% can achieve an adjustment of more than ±10% of the output power of the energy system.

[0044] Although the present invention is disclosed above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, the protection scope of the present invention should be subject to the scope defined by the claims of the present invention.

Claims

1. A gas hydraulic servo system, comprising a gas source (1), a turbo pump (2) and an oil source assembly (3), wherein the gas source (1) is used to supply gas to the turbo pump (2) to drive the turbo pump (2) to suck oil from the oil source assembly (3), characterized in that, The gas hydraulic servo system satisfies at least one of the following: The turbopump (2) is provided with a nozzle (15), and the nozzle (15) is used for expanding and accelerating the conveyed gas at the front end of the turbine (11) of the turbopump (2). The nozzle (15) is detachable from the turbopump (2), so as to adjust the gas acceleration degree and gas flow rate by adjusting the throat diameter of the nozzle (15); The turbopump (2) is provided with an annular member (13), and the annular member (13) surrounds the outer periphery of the turbine (11) of the turbopump (2). The annular member (13) is detachable from the turbopump (2), so as to adjust the gas flow rate between the annular member (13) and the turbine (11) by adjusting the gap between the annular member (13) and the turbine (11); A throttle ring (14) is arranged at the gas outlet end of the turbopump (2). The throttle ring (14) is detachable from the turbopump (2), so as to adjust the exhaust back pressure of the turbopump (2) by adjusting the inner diameter of the throttle ring (14).

2. The gas hydraulic servo system according to claim 1, characterized in that, The adjustment center value of the throat diameter is 3-6 mm, and the throat diameter varies within the range of ±5-30% of the adjustment center value.

3. The gas hydraulic servo system according to claim 1 or 2, characterized in that, The turbopump (2) includes a housing (10), and the housing (10) includes a first cavity and a second cavity. The second cavity is located on the side of the first cavity close to the turbine (11). The first cavity is used to accommodate the nozzle (15), and the inner cavity of the nozzle (15) communicates with the second cavity.

4. The gas hydraulic servo system according to claim 3, characterized in that, The housing (10) satisfies at least one of the following: The wall thickness ratio of the first cavity to the second cavity is 0.4-0.6; The inner diameter size of the second cavity matches the opening size of the nozzle (15) facing the turbine (11).

5. The gas hydraulic servo system according to claim 1, characterized in that, The gap between the annular member (13) and the turbine (11) is the turbine tip clearance Δh. The adjustment center value of the turbine tip clearance Δh is 0.4-1 mm, and the turbine tip clearance Δh varies within the range of ±5-40% of the adjustment center value.

6. The gas hydraulic servo system according to claim 5, characterized in that, The turbopump (2) includes a housing (10) and a turbine cover (12) assembled with each other. The housing (10) has a gas passage leading to the turbine (11), and the turbine cover (12) is used to accommodate the turbine (11); wherein, An annular groove is arranged on one side of the turbine cover (12) facing the housing (10). The annular groove corresponds to the position of the turbine (11), and the annular member (13) abuts against the inner wall of the annular groove.

7. The gas hydraulic servo system according to claim 1, characterized in that, The adjustment center value of the inner diameter of the throttle ring (14) is 35-50 mm, and the inner diameter varies within the range of ±10-30% of the adjustment center value.

8. The gas hydraulic servo system according to claim 1, characterized in that, The turbopump (2) includes a turbine cover (12), and the turbine cover (12) is used to accommodate the turbine (11). The turbine cover (12) also has a gas exhaust passage, and the gas from the turbine (11) is discharged through the gas exhaust passage. The throttle ring (14) is arranged at the outlet of the gas exhaust passage.

9. A design method of a gas hydraulic servo system, characterized in that, The method is applied to a gas hydraulic servo system as described in any one of claims 1 to 8; the method includes: According to the adjustment amount of the output power of the energy system, replace or adjust at least one of the following: the nozzle (15), the annular member (13), and the throttle ring (14).

10. The method according to claim 9, characterized in that, The method includes: satisfying at least one of the following when the adjustment amount increases: The throat diameter of the replaced or adjusted nozzle (15) is smaller than the throat diameter of the nozzle (15) before replacement; The inner diameter of the replaced or adjusted annular member (13) is smaller than the inner diameter of the annular member (13) before replacement; The inner diameter of the replaced or adjusted throttle ring (14) is larger than the inner diameter of the throttle ring (14) before replacement.

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