CN113202632B - High-pressure hydrogen supply system suitable for hypersonic aircraft engine - Google Patents
High-pressure hydrogen supply system suitable for hypersonic aircraft engine Download PDFInfo
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- CN113202632B CN113202632B CN202110690787.9A CN202110690787A CN113202632B CN 113202632 B CN113202632 B CN 113202632B CN 202110690787 A CN202110690787 A CN 202110690787A CN 113202632 B CN113202632 B CN 113202632B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/232—Fuel valves; Draining valves or systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
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- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention discloses a high-pressure hydrogen supply system suitable for a hypersonic aircraft engine, which comprises a high-pressure hydrogen cylinder, a main supply unit, a power system supply unit and a lubricating system supply unit, wherein the main supply unit is connected with the main supply unit; the input end of the main supply unit is communicated with the high-pressure hydrogen cylinder, and the output end of the main supply unit is respectively communicated with the power system supply unit and the lubricating system supply unit; the main supply unit comprises a main pipeline, and a high-pressure hydrogen charging and discharging valve, an electric explosion valve, a nitrogen charging valve and a hydrogen reducing valve which are sequentially arranged on the main pipeline along the flow direction of hydrogen; the power system supply unit comprises a first pipeline, a hydrogen splitter and two branch pipelines; the lubricating system supply unit comprises a second pipeline, a lubricating oil storage tank, a lubricating oil pipeline, a lubricating oil filling and discharging valve, a lubricating oil electromagnetic valve and a lubricating oil pore plate; the invention realizes that hydrogen is supplied to the hypersonic aerocraft as fuel, and high-pressure hydrogen is used as power to extrude lubricating oil to supply an engine, thereby improving the compactness and reliability of the system.
Description
Technical Field
The invention relates to the technical field of engine fuel supply, in particular to a high-pressure hydrogen supply system suitable for a hypersonic aircraft engine.
Background
In the selection of the hypersonic aircraft propellant, hydrogen as the propellant has high specific impulse but has great difficulty in supply control, and a supply system of the hydrogen is the key of the success or failure of the hypersonic aircraft.
As one of the key systems of the engine of a hypersonic aircraft, this supply system should have the following functions: firstly, hydrogen is supplied to the engine according to the flow and pressure requirements of the working medium required by the engine; and secondly, lubricating oil is supplied to a cooling channel of the turbine shaft system, so that the reliable and stable operation of the rotor system is ensured.
The existing hypersonic aircraft engine uses normal-temperature or low-temperature liquid fuel, so the existing normal-temperature or low-temperature liquid fuel supply system cannot be applied to the hypersonic aircraft using high-pressure hydrogen as fuel.
Meanwhile, the high-pressure hydrogen supply system adopted in the current market is mostly applied to industrial hydrogen production and hydrogen energy vehicles. Since the industrial hydrogen production system is a large ground-based device, its scale and quality are not suitable for hypersonic aircrafts. The flow of a hydrogen supply system in the hydrogen energy automobile is only several grams per second, and the hydrogen flow required by the hypersonic aircraft is in kilogram magnitude, so that the high-pressure hydrogen supply system adopted in the current market cannot be suitable for the hypersonic aircraft engine.
Disclosure of Invention
The invention aims to provide a high-pressure hydrogen supply system suitable for an engine of a hypersonic aircraft aiming at the problem that the existing high-pressure hydrogen supply system cannot meet the requirement of the hypersonic aircraft on high-pressure hydrogen supply.
The specific technical scheme of the invention is as follows:
the high-pressure hydrogen supply system suitable for the hypersonic aircraft engine comprises a high-pressure hydrogen cylinder, a main supply unit, a power system supply unit and a lubricating system supply unit;
the input end of the main supply unit is communicated with the high-pressure hydrogen cylinder, and the output end of the main supply unit is respectively communicated with the power system supply unit and the lubricating system supply unit;
the main supply unit comprises a main pipeline, and a high-pressure hydrogen charging and discharging valve, an electric explosion valve, a nitrogen charging valve and a hydrogen reducing valve which are sequentially arranged on the main pipeline along the flow direction of hydrogen;
the power system supply unit comprises a first pipeline, a hydrogen splitter and at least two branch pipelines; the input end of the first pipeline is communicated with the output end of the main pipeline, the output end of the first pipeline is communicated with the input end of a hydrogen splitter, and the hydrogen splitter is provided with a plurality of output ends and is respectively communicated with at least two branch pipelines;
each branch pipeline is provided with a hydrogen hole plate, one branch pipeline is provided with a hydrogen solenoid valve, the high-speed opening and closing of the hydrogen solenoid valve are controlled through rectangular pulse signals, and the adjustment of the hydrogen flow is realized by counting the opening and closing time proportion of the valve;
the lubricating system supply unit comprises a second pipeline, a lubricating oil storage tank, a lubricating oil pipeline, a lubricating oil filling and discharging valve, a lubricating oil electromagnetic valve and a lubricating oil pore plate;
the input end of the second pipeline is communicated with the output end of the main pipeline, the output end of the second pipeline is connected with the input end of the lubricating oil storage tank, and the output end of the lubricating oil storage tank is connected with the lubricating oil pipeline;
and a lubricating oil filling and discharging valve, a lubricating oil electromagnetic valve and a lubricating oil pore plate are sequentially arranged on the lubricating oil pipeline along the flow direction of the lubricating oil.
Further, the high-pressure hydrogen charging and discharging valve is of a four-interface one-way valve structure and comprises a first interface connected with ground hydrogen filling equipment, a second interface connected with a high-pressure hydrogen cylinder, a third interface connected with a remote control end and a fourth interface connected with a hydrogen gas discharging and air entraining device;
the high-pressure hydrogen cylinder is inflated through the first interface and the second interface, and remote deflation of the high-pressure hydrogen cylinder is realized through the third interface and the fourth interface.
Further, a piston is arranged in the lubricating oil storage tank, and the piston separates the lubricating oil storage tank into a hydrogen chamber and a lubricating oil chamber. When the device works, hydrogen enters the hydrogen chamber through the second pipeline to push the piston, so that lubricating oil in the lubricating oil chamber is pressed to be injected into an external lubricating oil system through the lubricating oil pipeline.
Further, the hydrogen gas porous plate is a gas sound velocity pore plate.
Furthermore, a filter is arranged on the main pipeline and between the electric explosion valve and the nitrogen gas charging valve.
Further, the pressure of hydrogen stored in the high-pressure hydrogen cylinder is more than or equal to 70 MPa; the pressure capacity of the high-pressure hydrogen charging and discharging valve is more than or equal to 75 MPa; the inlet pressure of the hydrogen pressure reducing valve is less than or equal to 70MPa, and the outlet pressure is 6 +/-0.5 MPa; the working pressure of the hydrogen safety valve is 7 +/-0.3 MPa; the normal working pressure difference of the hydrogen electromagnetic valve 9 is more than or equal to 6MPa, and the switching frequency is more than or equal to 30 Hz; the working pressure of the lubricating oil storage tank is more than or equal to 6.5 MPa; the normal working pressure difference of the lubricating oil electromagnetic valve is more than or equal to 5MPa, and the response time is less than or equal to 30 ms.
Further, if the hydrogen flow rate regulation precision of the power system supply unit is constant, the regulation precision is 10% to 25%;
case a: when the required hydrogen flow regulation range is less than or equal to Q, a branch pipeline is selected to be provided with a hydrogen electromagnetic valve, and the hydrogen flow regulation is realized by controlling the on-off time proportion of the switch of the hydrogen electromagnetic valve; wherein the value range of Q is as follows: 30g/s to 45 g/s;
case B: when the required hydrogen flow regulation range is larger than Q, the hydrogen solenoid valves with different response frequencies are respectively installed on the N branch pipelines, N is larger than or equal to 2, the opening and closing time proportion of the switches of the N hydrogen solenoid valves is respectively controlled, the solenoid valve with the small response frequency is responsible for roughly regulating the flow, the solenoid valve with the large response frequency is used for performing supplementary correction on the roughly regulated flow, and the hydrogen flow regulation is realized by utilizing the coupling action of the hydrogen solenoid valves with different response frequencies.
Further, the number of hydrogen solenoid valves in the above case B should be determined according to the following principle:
N＝0.0013*Q2-0.0333 × Q +0.8, and N rounded upwards;
the specification of the hydrogen electromagnetic valve is selected according to the following principle; the flow of each path of hydrogen electromagnetic valve meets an equal ratio series with the ratio of 2, and the response frequency of each path of hydrogen electromagnetic valve is determined by the volume flow of the gas flowing through each path of hydrogen electromagnetic valve.
The invention has the following advantages:
1. the supply system of the invention realizes that hydrogen is supplied to the hypersonic aircraft as fuel, and high-pressure hydrogen is used as power to extrude lubricating oil to supply an engine, so that compared with the traditional supply system scheme, one set of high-pressure gas extrusion system is reduced, and the compactness and reliability of the system are improved.
2. The system realizes the stable control of the hydrogen flow supplied by the external power system through the at least two branch pipelines, the multi-path pore plate and the hydrogen solenoid valve which are arranged on the branch pipelines, and realizes the purpose of flow regulation.
Drawings
FIG. 1 is a schematic structural view of the present invention;
the reference numbers are as follows:
the system comprises a 1-high-pressure hydrogen cylinder, a 2-main supply unit, a 3-power system supply unit, a 4-lubricating system supply unit, a 5-main pipeline, a 6-high-pressure hydrogen charging and discharging valve, a 7-electric explosion valve, an 8-filter, a 9-nitrogen charging valve, a 10-hydrogen pressure reducing valve, a 11-first pipeline, a 12-hydrogen flow divider, a 13-branch pipeline, a 14-hydrogen air hole plate, a 15-hydrogen electromagnetic valve, a 16-second pipeline, a 17-lubricating oil storage tank, an 18-lubricating oil pipeline, a 19-lubricating oil charging and discharging valve, a 20-lubricating oil electromagnetic valve, a 21-lubricating oil hole plate, a 22-piston, a 23-hydrogen chamber and a 24-lubricating oil chamber.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In the selection of the hypersonic aircraft propellant, hydrogen as the propellant has high specific impulse but has great difficulty in supply control, and a supply system of the hydrogen is the key of the success or failure of the hypersonic aircraft. The existing engine supply system of the hypersonic aircraft is suitable for normal-temperature or low-temperature liquid fuel and cannot be suitable for the hypersonic aircraft taking high-pressure hydrogen as fuel. The invention develops research and innovation under the requirement, and provides a high-pressure hydrogen supply system suitable for a hypersonic aircraft engine.
Example 1
As shown in fig. 1, the supply system includes a high-pressure hydrogen cylinder 1, a main supply unit 2, a power system supply unit 3, and a lubrication system supply unit 4; the high-pressure hydrogen is in a supercritical state, the pressure and the temperature of the hydrogen used at present exceed the critical pressure of hydrogen of 1.297MPa and the critical temperature of 33.3K, so the hydrogen is in the supercritical state, and the physical parameters of the supercritical state, such as hydrogen viscosity, density and the like, are between a gas state and a liquid state.
The input end of the main supply unit 2 is communicated with the high-pressure hydrogen cylinder 1, and the output end of the main supply unit 2 is respectively communicated with the power system supply unit 3 and the lubricating system supply unit 4;
the main supply unit 2 comprises a main pipeline 5, and a high-pressure hydrogen charging and discharging valve 6, an electric explosion valve 7, a filter 8, a nitrogen charging valve 9 and a hydrogen reducing valve 10 which are sequentially arranged on the main pipeline 5 along the hydrogen flow direction;
the functions of the respective parts in the main supply unit 2 are as follows:
the high-pressure hydrogen charging and discharging valve 6 is used for controlling the charging of high-pressure hydrogen into the high-pressure hydrogen cylinder 1 and also used for discharging the high-pressure hydrogen cylinder 1;
the electric explosion valve 7 is used for sealing the high-pressure hydrogen in the high-pressure hydrogen cylinder, and the opening time is not more than 200ms
The filter 8 is used for filtering impurities in the pipeline;
the nitrogen gas charging valve 9 is used for vacuumizing each hydrogen pipeline (the main pipeline 5, the first pipeline 11, the second pipeline 16 and the branch pipelines 13) before filling hydrogen gas into the high-pressure hydrogen cylinder 1 and then filling nitrogen gas to protect the system;
the hydrogen pressure reducing valve 10 is used for reducing the pressure of hydrogen, so that the pressure of the hydrogen at the outlet of the pressure reducing valve is stable, the effect of controlling the hydrogen flow by a downstream hydrogen pore plate is achieved, the constant extrusion air source pressure of the lubricating oil storage tank is provided, and the lubricating oil flow is stable.
The power system supply unit 3 includes a first conduit 11, a hydrogen splitter 12, and at least two branch conduits 13; the input end of the first pipeline 11 is communicated with the output end of the main pipeline 5, the output end of the first pipeline 11 is communicated with the input end of the hydrogen splitter 12, and the hydrogen splitter 12 is provided with at least two output ends and is respectively communicated with at least two branch pipelines 13;
each branch pipeline 13 is provided with a hydrogen orifice plate 14, because the adjustment range of the required hydrogen flow is less than or equal to 35g/s and the adjustment precision is 20% in this embodiment, only one branch pipeline is provided with a hydrogen solenoid valve 15 in this embodiment, wherein the branch pipeline provided with the hydrogen solenoid valve 15 can control the high-speed opening and closing of the hydrogen solenoid valve through a rectangular pulse signal, the adjustment of the hydrogen flow in the branch pipeline is realized by counting the opening and closing time proportion of the valve, and the rest branch pipelines 13 not provided with the hydrogen solenoid valve 15 can flexibly select appropriate hydrogen orifice plates to enable the branch pipelines 13 to provide constant hydrogen flow for the power system.
The lubricating system supply unit 4 comprises a second pipeline 16, a lubricating oil storage tank 17, a lubricating oil pipeline 18, a lubricating oil filling and discharging valve 19, a lubricating oil electromagnetic valve 20 and a lubricating oil pore plate 21;
the input end of the second pipeline 16 is communicated with the output end of the main pipeline 5, the output end of the second pipeline 16 is connected with the input end of the lubricating oil storage tank 17, and the output end of the lubricating oil storage tank 17 is connected with the lubricating oil pipeline 18; a lubricating oil filling and discharging valve 19, a lubricating oil electromagnetic valve 20 and a lubricating oil pore plate 21 are sequentially arranged on the lubricating oil pipeline 18 along the flow direction of the lubricating oil;
in which a piston is provided in the oil reservoir 17, and the piston 22 separates the oil reservoir 17 into a hydrogen chamber 23 and an oil chamber 24. In operation, hydrogen enters the hydrogen chamber 23 through the second conduit 16 to push the piston, thereby forcing the oil in the oil chamber 24 to be injected into the external oil system through the oil conduit 18.
The oil charge/discharge valve 19 is used to charge or discharge oil into the oil reservoir 17.
The lube solenoid valve 20 is used to control the opening or closing of the lube line.
The oil orifice 21 is used to control the flow of oil in the oil conduit 18.
Based on the above description of the structure of the supply system, the working process of the supply system will now be described:
1. firstly, the nitrogen gas charging valve is used for vacuumizing each hydrogen pipeline (the main pipeline, the first pipeline, the second pipeline and the branch pipelines) before the high-pressure hydrogen cylinder is charged with hydrogen gas and then filling nitrogen gas to protect the system;
2. the high-pressure hydrogen cylinder carries out hydrogen filling through the high-pressure hydrogen charging and discharging valve;
3. the circular telegram of electricity explosion valve is opened, and high-pressure hydrogen begins to divide into 2 ways at the output hydrogen of trunk line behind hydrogen filter, the hydrogen relief pressure valve again after the trunk line process electricity explosion valve:
the 1 path of hydrogen is distributed to two branch pipelines through a first pipeline and a hydrogen splitter, wherein the hydrogen of one branch pipeline enters an external power system after flowing through a hydrogen electromagnetic valve and a hydrogen pore plate, and the hydrogen of the other branch pipelines enters the external power system after passing through a hydrogen pore plate 2;
the description is as follows: the hydrogen flow in the branch pipeline provided with the hydrogen electromagnetic valve can be adjusted in real time, and the specific adjusting process is as follows: the principle of the method is that when the control valve signal is rectangular, the valve is in an open state, when the control valve signal is a zero-position signal, the valve is in a closed state, and different hydrogen flows can be obtained by integrating unit hydrogen flows by adjusting the rectangular and zero-position occurrence time ratios, so that the accurate control of the hydrogen flows is realized.
The 1-path hydrogen is used as high-pressure gas to extrude a hydrogen chamber of the lubricating oil storage tank through the second pipeline and then pushes the piston to enable the lubricating oil in the lubricating oil chamber to enter an external lubricating system through the lubricating oil electromagnetic valve and the lubricating oil pore plate.
Example 2
Referring to fig. 1, the structure and operation principle of the present embodiment are basically the same as those of embodiment 1, except that: in this embodiment, the adjustment range of the hydrogen flow rate is greater than 35g/s, and the adjustment precision is 20%, so in this embodiment, at least N (N is greater than or equal to 2) branch pipelines are required to be provided with hydrogen solenoid valves 15 with different response frequencies, and the adjustment is performed by respectively controlling the opening and closing time ratios of the N hydrogen solenoid valves, where the solenoid valve with a small response frequency is responsible for roughly adjusting the flow rate, the solenoid valve with a large response frequency performs supplementary correction on the roughly adjusted flow rate, and the hydrogen flow rate is adjusted by using the coupling effect of the hydrogen solenoid valves with different response frequencies.
Here, it is to be emphasized that:
the number of the hydrogen solenoid valves is determined according to the following principle:
N＝0.0013*Q2-0.0333 × Q +0.8, and N rounded upwards;
the specification of the hydrogen electromagnetic valve is selected according to the following principle; the flow of each path of hydrogen electromagnetic valve meets an equal ratio series with the ratio of 2, and the response frequency of each path of hydrogen electromagnetic valve is determined by the volume flow of the gas flowing through each path of hydrogen electromagnetic valve; for example: if N equals 3, the flow ratio of the 3-way electromagnetic valve is 1:2: 4.
Example 3
The structure and the working principle of the embodiment are basically the same as those of the embodiment 1, and the difference is that: the high-pressure hydrogen charging and discharging valve 2 is of a four-interface one-way valve structure and comprises a first interface connected with ground hydrogen filling equipment, a second interface connected with a high-pressure hydrogen cylinder, a third interface connected with a remote control end and a fourth interface connected with a hydrogen gas discharging and air entraining device;
during the use, open first, the inflation process of second interface realization hydrogen, can realize the long-range gassing process of hydrogen through third, fourth interface.
In the two embodiments, the basic parameter indexes of the parts are the same, and the specific parameter indexes are as follows:
A. the pressure of hydrogen stored in the high-pressure hydrogen cylinder 1 is not less than 70 MPa;
B. the pressure capacity of the high-pressure hydrogen charging and discharging valve 2 is not lower than 75 MPa;
C. the inlet pressure of the hydrogen pressure reducing valve 6 is not more than 70MPa, and the outlet pressure is 6 +/-0.5 MPa;
D. the working pressure of the hydrogen safety valve 7 is 7 +/-0.3 MPa;
E. the normal working pressure difference of the hydrogen electromagnetic valve 9 is not lower than 6MPa, and the switching frequency is not lower than 30 Hz;
F. the working pressure of the lubricating oil storage tank 12 is not less than 6.5 MPa;
G. the normal working pressure difference of the lubricating oil electromagnetic valve 14 is not lower than 5MPa, and the response time is not more than 30 ms;
in short, the supply system disclosed by the invention solves the problems that hydrogen has high specific impulse as a propellant but is difficult to supply and control, and the existing engine supply system of the hypersonic aircraft is only suitable for normal-temperature or low-temperature liquid fuel and cannot be suitable for the hypersonic aircraft taking high-pressure hydrogen as fuel.
When the hydrogen is supplied to the hypersonic aircraft, the engine is supplied by extruding the lubricating oil by using the high-pressure hydrogen, compared with the traditional supply system scheme, a set of high-pressure gas extrusion system is reduced, the compactness and the reliability of the system are improved, and the requirement of the hypersonic aircraft on the high-pressure hydrogen and lubricating oil combined supply system is met.
The invention has not been described in detail in part of the common general knowledge of those skilled in the art.
Claims (8)
1. A high-pressure hydrogen supply system suitable for hypersonic aircraft engines, characterized in that:
comprises a high-pressure hydrogen cylinder, a main supply unit, a power system supply unit and a lubricating system supply unit;
the input end of the main supply unit is communicated with the high-pressure hydrogen cylinder, and the output end of the main supply unit is respectively communicated with the power system supply unit and the lubricating system supply unit;
the main supply unit comprises a main pipeline, and a high-pressure hydrogen charging and discharging valve, an electric explosion valve, a nitrogen charging valve and a hydrogen reducing valve which are sequentially arranged on the main pipeline along the flow direction of hydrogen;
the power system supply unit comprises a first pipeline, a hydrogen splitter and two branch pipelines; the input end of the first pipeline is communicated with the output end of the main pipeline, the output end of the first pipeline is communicated with the input end of a hydrogen splitter, and the hydrogen splitter is provided with a plurality of output ends and is respectively communicated with at least two branch pipelines;
wherein, each branch pipeline is provided with a hydrogen hole plate, and at least one branch pipeline is provided with a hydrogen solenoid valve;
the lubricating system supply unit comprises a second pipeline, a lubricating oil storage tank, a lubricating oil pipeline, a lubricating oil filling and discharging valve, a lubricating oil electromagnetic valve and a lubricating oil pore plate;
the input end of the second pipeline is communicated with the output end of the main pipeline, the output end of the second pipeline is connected with the input end of the lubricating oil storage tank, and the output end of the lubricating oil storage tank is connected with the lubricating oil pipeline;
and a lubricating oil filling and discharging valve, a lubricating oil electromagnetic valve and a lubricating oil pore plate are sequentially arranged on the lubricating oil pipeline along the flow direction of the lubricating oil.
2. The high pressure hydrogen supply system for hypersonic aircraft engines as claimed in claim 1, wherein: the high-pressure hydrogen charging and discharging valve is of a four-interface one-way valve structure and comprises a first interface connected with ground hydrogen filling equipment, a second interface connected with a high-pressure hydrogen cylinder, a third interface connected with a remote control end and a fourth interface connected with a hydrogen gas discharging and air entraining device;
the high-pressure hydrogen cylinder is inflated through the first interface and the second interface, and remote deflation of the high-pressure hydrogen cylinder is realized through the third interface and the fourth interface.
3. The high pressure hydrogen supply system for hypersonic aircraft engines as claimed in claim 1, wherein: a piston is arranged in the lubricating oil storage tank, and the piston separates the lubricating oil storage tank into a hydrogen chamber and a lubricating oil chamber.
4. A high-pressure hydrogen supply system suitable for hypersonic aircraft engines, according to claim 1 or 2 or 3, characterized in that: the pressure of hydrogen stored in the high-pressure hydrogen cylinder is more than or equal to 70 MPa; the pressure capacity of the high-pressure hydrogen charging and discharging valve is more than or equal to 75 MPa; the inlet pressure of the hydrogen pressure reducing valve is less than or equal to 70MPa, and the outlet pressure is 6 +/-0.5 MPa; the working pressure of the hydrogen safety valve is 7 +/-0.3 MPa; the normal working pressure difference of the hydrogen electromagnetic valve is more than or equal to 6MPa, and the switching frequency is more than or equal to 30 Hz; the working pressure of the lubricating oil storage tank is more than or equal to 6.5 MPa; the normal working pressure difference of the lubricating oil electromagnetic valve is more than or equal to 5MPa, and the response time is less than or equal to 30 ms.
5. The high pressure hydrogen supply system for hypersonic aircraft engines as claimed in claim 4, wherein: the hydrogen porous plate is a gas sound velocity pore plate.
6. The high pressure hydrogen supply system for hypersonic aircraft engines as claimed in claim 5, wherein: and a filter is arranged on the main pipeline and between the electric explosion valve and the nitrogen gas charging valve.
7. The high pressure hydrogen supply system for hypersonic aircraft engines as claimed in claim 1, wherein: when the hydrogen flow regulation precision of the power system supply unit is constant, the regulation precision is 10 to 25 percent;
case a: when the required hydrogen flow regulation range is less than or equal to Q, a branch pipeline is selected to be provided with a hydrogen electromagnetic valve, and the hydrogen flow regulation is realized by controlling the on-off time proportion of the switch of the hydrogen electromagnetic valve; wherein the value range of Q is as follows: 30g/s to 45 g/s;
case B: when the required hydrogen flow regulating range is larger than Q, the hydrogen solenoid valves with different response frequencies are respectively installed on the N branch pipelines, N is larger than or equal to 2, and the on-off time proportion of the switches of the N hydrogen solenoid valves is respectively controlled to regulate; the solenoid valve with small response frequency is responsible for roughly adjusting the flow, the solenoid valve with large response frequency performs supplementary correction on the roughly adjusted flow, and the hydrogen flow is adjusted by using the coupling effect of the hydrogen solenoid valves with different response frequencies.
8. The high pressure hydrogen supply system for hypersonic aircraft engines as claimed in claim 7, wherein:
the number of hydrogen solenoid valves in the case B is determined according to the following principle:
N＝0.0013*Q2-0.0333 × Q +0.8, and N rounded upwards;
the specification of the hydrogen electromagnetic valve is selected according to the following principle; the flow of each path of hydrogen electromagnetic valve meets an equal ratio series with the ratio of 2, and the response frequency of each path of hydrogen electromagnetic valve is determined by the volume flow of the gas flowing through each path of hydrogen electromagnetic valve.
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| US3690102A (en) * | 1970-10-29 | 1972-09-12 | Anthony A Du Pont | Ejector ram jet engine |
| US5133183A (en) * | 1991-03-01 | 1992-07-28 | The United States Of America As Represented By The Secretary Of The Army | Gel/solid bipropellant propulsion system with energy management capability |
| KR0130714B1 (en) * | 1995-07-25 | 1998-04-09 | 전성원 | Fuel supply apparatus of gasoline engine |
| JP2009041418A (en) * | 2007-08-08 | 2009-02-26 | Japan Aerospace Exploration Agency | Air-breathing engine for space transport and method of improving its accelerating performance |
| CN103541832A (en) * | 2013-09-30 | 2014-01-29 | 中国人民解放军国防科学技术大学 | Engine fuel supplying system |
| CN103696883B (en) * | 2013-12-18 | 2016-01-20 | 中国航天科技集团公司第六研究院第十一研究所 | A kind of RBCC motor pump pressure based on hydrogen peroxide and the integrated oil-fired system of extruding |
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2021
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