CN116879349B - Device and method for testing combustion reaction mechanism of liquid propellant - Google Patents
Device and method for testing combustion reaction mechanism of liquid propellant Download PDFInfo
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- CN116879349B CN116879349B CN202310862127.3A CN202310862127A CN116879349B CN 116879349 B CN116879349 B CN 116879349B CN 202310862127 A CN202310862127 A CN 202310862127A CN 116879349 B CN116879349 B CN 116879349B
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 170
- 239000007788 liquid Substances 0.000 title claims abstract description 93
- 239000003380 propellant Substances 0.000 title claims abstract description 87
- 238000012360 testing method Methods 0.000 title claims abstract description 46
- 238000000034 method Methods 0.000 title claims description 9
- 239000007800 oxidant agent Substances 0.000 claims abstract description 88
- 230000001590 oxidative effect Effects 0.000 claims description 67
- 239000000446 fuel Substances 0.000 claims description 64
- 239000007789 gas Substances 0.000 claims description 62
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 40
- 229910052757 nitrogen Inorganic materials 0.000 claims description 18
- 239000003638 chemical reducing agent Substances 0.000 claims description 17
- 239000011521 glass Substances 0.000 claims description 17
- 239000002912 waste gas Substances 0.000 claims description 15
- 230000001105 regulatory effect Effects 0.000 claims description 10
- 238000004891 communication Methods 0.000 claims description 9
- 238000004088 simulation Methods 0.000 claims description 7
- 238000005259 measurement Methods 0.000 claims description 5
- 238000001311 chemical methods and process Methods 0.000 claims description 3
- 238000010998 test method Methods 0.000 claims 1
- 238000006243 chemical reaction Methods 0.000 abstract description 4
- 238000002156 mixing Methods 0.000 abstract description 4
- 238000012795 verification Methods 0.000 abstract description 4
- 238000005516 engineering process Methods 0.000 abstract description 3
- 238000012827 research and development Methods 0.000 abstract description 3
- 238000013461 design Methods 0.000 description 6
- 239000002828 fuel tank Substances 0.000 description 5
- 229910001873 dinitrogen Inorganic materials 0.000 description 4
- WFPZPJSADLPSON-UHFFFAOYSA-N dinitrogen tetraoxide Chemical compound [O-][N+](=O)[N+]([O-])=O WFPZPJSADLPSON-UHFFFAOYSA-N 0.000 description 4
- 238000010304 firing Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 239000000428 dust Substances 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 230000003287 optical effect Effects 0.000 description 2
- 238000010079 rubber tapping Methods 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000007084 catalytic combustion reaction Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000003912 environmental pollution Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000009832 plasma treatment Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N25/00—Investigating or analyzing materials by the use of thermal means
- G01N25/20—Investigating or analyzing materials by the use of thermal means by investigating the development of heat, i.e. calorimetry, e.g. by measuring specific heat, by measuring thermal conductivity
- G01N25/22—Investigating or analyzing materials by the use of thermal means by investigating the development of heat, i.e. calorimetry, e.g. by measuring specific heat, by measuring thermal conductivity on combustion or catalytic oxidation, e.g. of components of gas mixtures
- G01N25/24—Investigating or analyzing materials by the use of thermal means by investigating the development of heat, i.e. calorimetry, e.g. by measuring specific heat, by measuring thermal conductivity on combustion or catalytic oxidation, e.g. of components of gas mixtures using combustion tubes, e.g. for microanalysis
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N25/00—Investigating or analyzing materials by the use of thermal means
- G01N25/20—Investigating or analyzing materials by the use of thermal means by investigating the development of heat, i.e. calorimetry, e.g. by measuring specific heat, by measuring thermal conductivity
- G01N25/22—Investigating or analyzing materials by the use of thermal means by investigating the development of heat, i.e. calorimetry, e.g. by measuring specific heat, by measuring thermal conductivity on combustion or catalytic oxidation, e.g. of components of gas mixtures
- G01N25/26—Investigating or analyzing materials by the use of thermal means by investigating the development of heat, i.e. calorimetry, e.g. by measuring specific heat, by measuring thermal conductivity on combustion or catalytic oxidation, e.g. of components of gas mixtures using combustion with oxygen under pressure, e.g. in bomb calorimeter
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N25/00—Investigating or analyzing materials by the use of thermal means
- G01N25/20—Investigating or analyzing materials by the use of thermal means by investigating the development of heat, i.e. calorimetry, e.g. by measuring specific heat, by measuring thermal conductivity
- G01N25/22—Investigating or analyzing materials by the use of thermal means by investigating the development of heat, i.e. calorimetry, e.g. by measuring specific heat, by measuring thermal conductivity on combustion or catalytic oxidation, e.g. of components of gas mixtures
- G01N25/28—Investigating or analyzing materials by the use of thermal means by investigating the development of heat, i.e. calorimetry, e.g. by measuring specific heat, by measuring thermal conductivity on combustion or catalytic oxidation, e.g. of components of gas mixtures the rise in temperature of the gases resulting from combustion being measured directly
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N31/00—Investigating or analysing non-biological materials by the use of the chemical methods specified in the subgroup; Apparatus specially adapted for such methods
- G01N31/12—Investigating or analysing non-biological materials by the use of the chemical methods specified in the subgroup; Apparatus specially adapted for such methods using combustion
Abstract
The invention belongs to the field of engine research and development, relates to a liquid propellant combustion reaction mechanism testing technology, and particularly discloses a liquid propellant combustion reaction mechanism testing device and a liquid propellant combustion reaction mechanism testing method. The device can realize the combustion reaction mechanism test of the oxidants and the liquid propellants with different mixing ratios under different pressure working conditions, and in the combustion process, the temperature and pressure change conditions in the combustion chamber are respectively tested through the temperature sensor and the pressure sensor, the flame related data in the combustion chamber are collected through the image acquisition device, and the combustion products in the combustion chamber are analyzed through the gas chromatograph, so that various combustion reaction mechanism verification data can be provided, the correctness of the reaction mechanism is comprehensively judged, and the technical blank of comprehensively acquiring the combustion reaction parameters of the liquid propellants at present is filled.
Description
Technical Field
The invention belongs to the field of engine research and development, relates to a liquid propellant combustion reaction mechanism testing technology, and particularly relates to a liquid propellant combustion reaction mechanism testing device and a liquid propellant combustion reaction mechanism testing method.
Background
Liquid propellants are the most widely used propellants of modern liquid rocket engines. The combustion reaction mechanism of the liquid propellant is critical to the design of the engine, and the correct and comprehensive combustion reaction mechanism of the liquid propellant can only enable the design state of the engine to be close to the actual use condition. However, in the aspect of engine design at present, partial liquid propellant combustion parameters cannot be directly obtained, so that the difficulty in design and research and development of the engine is improved. Therefore, it is necessary to propose a test technology specifically aiming at the combustion reaction mechanism of the liquid propellant so as to obtain accurate and comprehensive parameters of the combustion reaction mechanism of the liquid propellant, and accumulate relevant technological bases and experience for the design, development and development of the engine.
Disclosure of Invention
The invention aims to provide a liquid propellant combustion reaction mechanism testing device and a liquid propellant combustion reaction mechanism testing method, which can simulate a liquid propellant combustion reaction mechanism and acquire accurate and comprehensive liquid propellant combustion parameters according to the liquid propellant combustion reaction mechanism, so as to solve the problem that the prior art cannot acquire part of liquid propellant combustion parameters directly, thereby improving the difficulty of engine design and research.
In order to achieve the above object, the present invention provides the following solutions:
the invention provides a liquid propellant combustion reaction mechanism testing device, which comprises:
a combustion chamber in which an ignition device is disposed;
a propellant supply unit connected to the combustion chamber for providing a liquid propellant to the combustion chamber;
an oxidant supply unit connected to the combustion chamber for providing an oxidant to the combustion chamber to provide a combustion environment for the liquid propellant;
the measurement and control unit comprises a control system, a first pressure sensor, a temperature sensor, a gas chromatograph-mass spectrometer and an image acquisition device, wherein the first pressure sensor, the temperature sensor and the gas chromatograph-mass spectrometer are connected with the combustion chamber, and the image acquisition device is used for acquiring flame images generated by combustion reaction in the combustion chamber; the first pressure sensor, the temperature sensor, the gas chromatograph-mass spectrometer and the image acquisition device are all in communication connection with the control system.
Optionally, the system further comprises a combustion chamber exhaust gas treatment unit, wherein the combustion chamber exhaust gas treatment unit is used for collecting and treating exhaust gas generated by combustion in the combustion chamber.
Optionally, the combustion chamber exhaust gas treatment unit comprises an exhaust gas collection device and an exhaust gas treatment device connected to the exhaust gas collection device.
Optionally, the propellant supply unit includes a first nitrogen cylinder, a first fuel exhaust treatment device, a fuel storage tank and a fuel path pneumatic valve which are sequentially connected through a pipeline, the fuel path pneumatic valve is connected with the combustion chamber, and a first manual stop valve is arranged between the first nitrogen cylinder and the first fuel exhaust treatment device, between the first fuel exhaust treatment device and the fuel storage tank, and between the fuel storage tank and the fuel path pneumatic valve; a second pressure sensor is further arranged between the fuel path pneumatic valve and the combustion chamber, and a first automatic pressure regulating pressure reducer and a first pressure relief pneumatic valve are further arranged at the air outlet of the first nitrogen cylinder and the air inlet of the first fuel waste gas treatment device respectively;
the fuel path pneumatic valve, the first automatic pressure regulating pressure reducer, the first pressure relief pneumatic valve and the second pressure sensor are all in communication connection with the control system.
Optionally, the propellant supply unit further comprises a second fuel exhaust gas treatment device, a first exhaust stop valve, a fuel receiving tank, a first transparent glass tube and a first liquid discharge stop valve which are sequentially connected, and the first liquid discharge stop valve is connected between the fuel path pneumatic valve and the fuel storage tank;
the first exhaust stop valve and the first liquid discharge stop valve are both in communication connection with the control system.
Optionally, the oxidant supply unit includes a second nitrogen cylinder, a first oxidant exhaust gas treatment device, an oxidant storage tank and an oxidant path pneumatic valve which are sequentially connected through pipelines, the oxidant path pneumatic valve is connected with the combustion chamber, and second manual stop valves are respectively arranged between the second nitrogen cylinder and the oxidant exhaust gas treatment device, between the oxidant exhaust gas treatment device and the oxidant storage tank, and between the oxidant storage tank and the oxidant path pneumatic valve; a third pressure sensor is further arranged between the oxidant path pneumatic valve and the combustion chamber, and a second automatic pressure regulating pressure reducer and a second pressure relief pneumatic valve are further arranged at the air outlet of the second nitrogen cylinder and the air inlet of the oxidant waste gas treatment device respectively;
the oxidant way pneumatic valve, the second automatic pressure regulating pressure reducer, the second pressure relief pneumatic valve and the third pressure sensor are all in communication connection with the control system.
Optionally, the oxidant supply unit further includes a second oxidant exhaust gas treatment device, a second exhaust stop valve, an oxidant receiving tank, a second transparent glass tube, and a second liquid discharge stop valve that are sequentially connected, where the second liquid discharge stop valve is connected between the oxidant path pneumatic valve and the oxidant storage tank;
and the second exhaust stop valve and the second liquid discharge stop valve are both in communication connection with the control system.
Optionally, the image acquisition device set up in the outside of burning cavity, be provided with on the burning cavity and supply the image acquisition device carries out the transparent glass window of image acquisition.
Optionally, the image acquisition device is a high-speed camera.
The invention also provides a liquid propellant combustion reaction mechanism testing method, which is implemented by adopting the liquid propellant combustion reaction mechanism testing device according to any one of the above steps, and comprises the following steps:
introducing the oxidant and the liquid propellant into the combustion chamber, and igniting the liquid propellant by the ignition device;
measuring the temperature generated by combustion through the temperature sensor, measuring the pressure generated by combustion through the first pressure sensor, recording the flame length of combustion through the image acquisition device, and analyzing the gas product generated by combustion through the gas chromatograph-mass spectrometer; and acquiring data of the temperature sensor, the first pressure sensor, the image acquisition device and the gas chromatograph-mass spectrometer through the control system.
Optionally, the method for testing the combustion reaction mechanism of the liquid propellant further comprises the following steps:
and solving and calculating an Arrhenius equation of the combustion of the liquid propellant by adopting a quantum chemistry method for a gas product generated by the combustion, then adopting the Arrhenius equation in a numerical simulation model to simulate the temperature, the pressure and the flame length generated by the combustion, and then comparing a simulation result with an actual test result to verify the accuracy of a combustion reaction mechanism.
Compared with the prior art, the invention has the following technical effects:
the liquid propellant combustion reaction mechanism testing device provided by the invention has novel and reasonable structure, can realize combustion reaction mechanism testing of oxidants and liquid propellants with different mixing ratios under different pressure working conditions, respectively tests the temperature and pressure change conditions in the combustion chamber through the temperature sensor and the pressure sensor in the combustion process, acquires flame related data in the combustion chamber through the image acquisition device, and analyzes combustion products in the combustion chamber through the gas chromatograph, thereby providing various combustion reaction mechanism verification data so as to comprehensively judge the correctness of the reaction mechanism and fill the technical blank of comprehensively acquiring the combustion reaction parameters of the liquid propellant at present.
The liquid propellant combustion reaction mechanism testing method provided by the invention is simple and convenient to operate, and can acquire various combustion reaction mechanism verification data so as to comprehensively judge the correctness of the reaction mechanism, thereby filling the technical blank of comprehensively acquiring the combustion reaction parameters of the liquid propellant at present.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic diagram of the overall structure of a device for testing the mechanism of combustion reaction of a liquid propellant according to an embodiment of the present invention.
Wherein, the reference numerals are as follows:
100. the liquid propellant combustion reaction mechanism testing device;
1. a combustion chamber; 11. a transparent glass window;
2. a propellant supply unit; 21. a first nitrogen cylinder; 22. a first fuel off-gas treatment device; 23. a fuel tank; 24. a fuel path pneumatic valve; 25. a first manual shut-off valve; 26. a second pressure sensor; 27. a first automatic pressure regulator and reducer; 28. a first pressure relief pneumatic valve; 29. a second fuel off-gas treatment device; 210. a first exhaust shutoff valve; 211. a fuel receiving tank; 212. a first transparent glass tube; 213. a first tapping stop valve; 214. a first flowmeter;
3. an oxidizing agent supply unit; 31. a second nitrogen cylinder; 32. a first oxidant exhaust treatment device; 33. an oxidant reservoir; 34. an oxidant line pneumatic valve; 35. a second manual shut-off valve; 36. a third pressure sensor; 37. a second automatic pressure regulating reducer; 38. the second pressure relief pneumatic valve; 39. a second oxidant exhaust treatment device; 310. a second exhaust shutoff valve; 311. an oxidant receiving tank; 312. a second transparent glass tube; 313. a second tapping stop valve; 314. a second flowmeter;
4. a control system; 5. a first pressure sensor; 6. a temperature sensor; 7. a gas chromatograph-mass spectrometer; 8. an image acquisition device; 9. an exhaust gas collection device; 10. an exhaust gas treatment device.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention aims to provide a liquid propellant combustion reaction mechanism testing device which can simulate a liquid propellant combustion reaction mechanism and acquire accurate and comprehensive liquid propellant combustion parameters according to the liquid propellant combustion reaction mechanism, so as to solve the problem that in the prior art, partial liquid propellant combustion parameters cannot be acquired directly, and therefore the difficulty in designing and developing an engine is improved.
The invention also aims to provide a liquid propellant combustion reaction mechanism testing method implemented by the liquid propellant combustion reaction mechanism testing device.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
Example 1
As shown in fig. 1, the present embodiment provides a liquid propellant combustion reaction mechanism testing device 100, which mainly includes a combustion chamber 1, a propellant supply unit 2, an oxidizer supply unit 3, and a measurement and control unit. Wherein, the combustion chamber 1 is internally provided with an ignition device for igniting the liquid propellant, and the ignition device can be an existing firing ignition device and an existing electric firing ignition device; the propellant supply unit 2 is connected to the combustion chamber 1 for supplying the fuel to be tested to the combustion chamber 1, which may be a single-component liquid propellant, a fuel in a two-component liquid propellant or a fuel in a multi-component liquid propellant; the oxidant supply unit 3 is connected to the combustion chamber 1 and is used for supplying an oxidant to the combustion chamber 1 to provide a combustion environment for fuel, wherein the oxidant can be dinitrogen tetroxide, green dinitrogen tetroxide or nitric acid-27S; the measurement and control unit comprises a control system 4, a first pressure sensor 5, a temperature sensor 6, a gas mass spectrometer 7 and an image acquisition device 8, wherein the first pressure sensor 5, the temperature sensor 6 and the gas mass spectrometer 7 are connected with the combustion chamber 1 to respectively measure the chamber pressure, the temperature and the gas products generated by combustion in the combustion chamber 1 in the combustion process of the liquid propellant, and the image acquisition device 8 is used for acquiring flame images generated by combustion reaction in the combustion chamber 1 to acquire relevant flame parameters such as flame length and the like. The first pressure sensor 5, the temperature sensor 6, the gas chromatograph-mass spectrometer 7 and the image acquisition device 8 are all in communication connection with the control system 4, and the control system 4 receives detection or analysis data of each component to obtain the combustion reaction parameters of the liquid propellant, including parameters such as temperature, pressure and the like. The gas chromatograph 7 is an existing online gas chromatograph, and the specific structure and working principle are not described herein.
In the present embodiment, in view of environmental protection, a combustion chamber exhaust gas treatment unit is also provided, which is mainly used for collecting and treating exhaust gas generated by combustion in the combustion chamber 1. The combustion chamber exhaust gas treatment unit mainly comprises an exhaust gas collecting device 9 and an exhaust gas treatment device 10 connected to the exhaust gas collecting device 9. In actual operation, the exhaust gas collecting device 9 may be a bag-type dust collector or a cartridge-type dust collector, the exhaust gas treatment device 10 may be a catalytic combustion device or a plasma treatment device, and the exhaust gas collecting device 9 and the exhaust gas treatment device 10 both adopt the prior art, and specific structures and working principles are not described herein.
In this embodiment, the propellant supply unit 2 includes a first nitrogen cylinder 21, a first fuel off-gas treatment device 22, a fuel tank 23, and a fuel line pneumatic valve 24 connected in this order by piping, thereby forming a "fuel line", in which the liquid propellant is stored in the fuel tank 23. The fuel path pneumatic valve 24 of the fuel path is connected with the combustion chamber 1, and a first manual stop valve 25 is arranged between the first nitrogen cylinder 21 and the first fuel waste gas treatment device 22, between the first fuel waste gas treatment device 22 and the fuel storage tank 23, and between the fuel storage tank 23 and the fuel path pneumatic valve 24; a second pressure sensor 26 is also arranged between the fuel path pneumatic valve 24 and the combustion chamber 1 and is used for monitoring the air pressure of the fuel path in real time; the air outlet of the first nitrogen cylinder 21 and the air inlet of the first fuel off-gas treatment device 22 are also provided with a first automatic pressure regulator and reducer 27 and a first pressure relief pneumatic valve 28, respectively. The propellant supply unit 2 further includes a second fuel off-gas treatment device 29, a first exhaust shutoff valve 210, a fuel receiving tank 211, a first transparent glass tube 212, and a first drain shutoff valve 213 that are connected in this order, and the first drain shutoff valve 213 is connected between the fuel line pneumatic valve 24 and the fuel reservoir 23. The fuel path pneumatic valve 24, the first automatic pressure-regulating pressure reducer 27, the first pressure-releasing pneumatic valve 28, the second pressure sensor 26, the first exhaust stop valve 210 and the first liquid-discharging stop valve 213 are all in communication connection with the control system 4, and in the test process, the opening and closing and the opening of each valve are controlled by the control system 4.
In this embodiment, the oxidizing agent supply unit 3 includes a second nitrogen gas cylinder 31, a first oxidizing agent exhaust gas treatment device 32, an oxidizing agent reservoir 33, and an oxidizing agent passage air-operated valve 34, which are connected in this order by pipes, so that an "oxidizing agent passage" is formed, and the oxidizing agent reservoir 33 stores therein, that is, the oxidizing agent for combustion of the liquid propellant. An oxidant passage pneumatic valve 34 of the "oxidant passage" is connected to the combustion chamber 1, and a second manual shutoff valve 35 is provided between the second nitrogen gas cylinder 31 and the oxidant exhaust gas treatment device 10, between the oxidant exhaust gas treatment device 10 and the oxidant reservoir tank 33, and between the oxidant reservoir tank 33 and the oxidant passage pneumatic valve 34; a third pressure sensor 36 is also arranged between the oxidant path pneumatic valve 34 and the combustion chamber 1, and is used for monitoring the air pressure of the 'oxidant path' in real time; the air outlet of the second nitrogen cylinder 31 and the air inlet of the oxidizer exhaust gas treatment device 10 are also provided with a second automatic pressure regulator and reducer 37 and a second pressure relief pneumatic valve 38, respectively. The oxidizing agent supply unit 3 further includes a second oxidizing agent exhaust gas treatment device 39, a second exhaust stop valve 310, an oxidizing agent receiving tank 311, a second transparent glass tube 312, and a second drain stop valve 313, which are connected in this order, and the second drain stop valve 313 is connected between the oxidizing agent passage air valve 34 and the oxidizing agent storage tank 33. The oxidant way pneumatic valve 34, the second automatic pressure-regulating pressure reducer 37, the second pressure-releasing pneumatic valve 38, the third pressure sensor 36, the second exhaust stop valve 310 and the second liquid discharge stop valve 313 are all in communication connection with the control system 4, and in the test process, the opening and closing and the opening of the valves are controlled by the control system 4.
In this embodiment, in order to avoid that the combustion environment in the combustion chamber 1 affects the normal use of the image capturing device 8, it is preferable to set the combustion chamber outside the combustion chamber 1, and based on this, a transparent glass window 11 for the image capturing device 8 to capture images is provided on the combustion chamber 1. In order to obtain flame parameters more accurately, the image acquisition device 8 may employ a high-speed camera which is supported around the combustion chamber 1 by a structure such as a bracket.
In this embodiment, the components are preferably connected by stainless steel pipes having an inner diameter of 10 mm.
The testing process and the testing principle of the device 100 for testing the combustion reaction mechanism of a two-component liquid propellant according to the present embodiment will be specifically described below.
Step 1: the fuel tank 23 and the oxidizer tank 33 are filled with 10L of fuel (i.e., a two-component liquid propellant) and 10L of oxidizer, respectively.
Step 2: the liquid propellant combustion reaction mechanism testing apparatus 100 is assembled.
Step 3: the valves of the first nitrogen gas cylinder 21 and the second nitrogen gas cylinder 31 are opened.
Step 4: the first automatic pressure regulator and reducer 27 and the second automatic pressure regulator and reducer 37 were adjusted to increase the pressures of the fuel tank 23 and the oxidizer tank 33 to 0.1MPa.
Step 5: opening the first liquid discharge stop valve 213 and the first exhaust stop valve 210, filling the propellant to the inlet of the fuel path pneumatic valve 24, observing the first transparent glass tube 212, and closing the first liquid discharge stop valve 213 and the first exhaust stop valve 210 when no bubble exists in the first transparent glass tube 212 after filling; and simultaneously performing oxidant filling, namely opening the second liquid discharge stop valve 313 and the second exhaust stop valve 310, performing oxidant filling, filling the oxidant to the inlet of the oxidant path pneumatic valve 34, observing the second transparent glass tube 312, and closing the second liquid discharge stop valve 313 and the second exhaust stop valve 310 when no bubbles exist in the second transparent glass tube 312 after filling is completed.
Step 6: the fuel path pneumatic valve 24 and the oxidant path pneumatic valve 34 are opened simultaneously by the control system 4 and kept open for 5 seconds.
Step 7: the temperature generated by combustion in the combustion chamber 1 is measured by the temperature sensor 6, the pressure generated by combustion in the combustion chamber 1 is measured by the first pressure sensor 5, the length of flame generated by combustion in the combustion chamber 1 is recorded by the high-speed camera through the transparent glass window 11, and the gas products generated by combustion in the combustion chamber 1 are analyzed by the online gas chromatograph-mass spectrometer, wherein all data such as temperature, pressure and the like are collected and processed by the control system 4.
Step 8: according to the gas product data obtained by the combustion of the control system 4, a quantum chemistry method is adopted to solve and calculate an Arrhenius equation (also called as an Arrhenius equation) of the combustion of the bi-component liquid propellant, then the Arrhenius equation (also called as an Arrhenius equation) is adopted in a numerical simulation model to simulate the temperature pressure and the flame length generated by the combustion, and the simulation result is compared with an actual test result to verify the accuracy of a combustion reaction mechanism.
Step 9: the test can be carried out according to the mixing ratio of different fuels and oxidants and different pressure working conditions.
The liquid propellant combustion reaction mechanism testing device 100 and the corresponding testing method provided by the technical scheme are characterized in that the respective flow rates are controlled by adjusting the pressure of the oxidant storage tank and the fuel storage tank, the temperature and pressure change conditions in the combustion chamber can be tested according to different mixing ratios and different pressure working conditions, the flame length data in the combustion chamber are collected through the image collecting device, the combustion products in the combustion chamber are analyzed through the gas chromatograph, and finally the simulation calculation method is combined to verify and judge the combustion reaction mechanism of the liquid propellant. The technical proposal fills the technical blank of comprehensively acquiring the combustion reaction parameters of the liquid propellant at present, and has the following specific beneficial effects:
1. the technical scheme can measure flame length, gas products, temperature and pressure data generated by the combustion of the two-component liquid propellant, can provide various combustion reaction mechanism verification data, and comprehensively judges the correctness of the reaction mechanism;
2. the high-speed camera of the technical scheme can measure optical signals of fuel and oxidant in a fire delay period from meeting to firing of the combustion chamber, flame length and the like, and meets the optical signal measurement requirement of the combustion flame under the conditions of high temperature and high pressure;
3. the device of the technical scheme adopts closed-loop connection, is provided with a corresponding waste gas treatment device, avoids environmental pollution in the whole testing process, realizes closed loop of all material treatment, and can rapidly repeat testing.
It should be noted that it will be apparent to those skilled in the art that the present invention is not limited to the details of the above-described exemplary embodiments, but may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein.
The principles and embodiments of the present invention have been described in detail with reference to specific examples, which are provided to facilitate understanding of the method and core ideas of the present invention; also, it is within the scope of the present invention to be modified by those of ordinary skill in the art in light of the present teachings. In view of the foregoing, this description should not be construed as limiting the invention.
Claims (6)
1. A liquid propellant combustion reaction mechanism testing device, comprising:
a combustion chamber in which an ignition device is disposed;
a propellant supply unit connected to the combustion chamber for providing a liquid propellant to the combustion chamber; the propellant supply unit comprises a first nitrogen cylinder, a first fuel waste gas treatment device, a fuel storage tank and a fuel path pneumatic valve which are sequentially connected through pipelines, wherein the fuel path pneumatic valve is connected with the combustion chamber, and first manual stop valves are arranged between the first nitrogen cylinder and the first fuel waste gas treatment device, between the first fuel waste gas treatment device and the fuel storage tank and between the fuel storage tank and the fuel path pneumatic valve; a second pressure sensor is further arranged between the fuel path pneumatic valve and the combustion chamber, and a first automatic pressure regulating pressure reducer and a first pressure relief pneumatic valve are further arranged at the air outlet of the first nitrogen cylinder and the air inlet of the first fuel waste gas treatment device respectively; the propellant supply unit further comprises a second fuel waste gas treatment device, a first exhaust stop valve, a fuel receiving tank, a first transparent glass tube and a first liquid discharge stop valve which are connected in sequence, wherein the first liquid discharge stop valve is connected between the fuel path pneumatic valve and the fuel storage tank;
an oxidant supply unit connected to the combustion chamber for providing an oxidant to the combustion chamber to provide a combustion environment for the liquid propellant; the oxidant supply unit comprises a second nitrogen cylinder, a first oxidant waste gas treatment device, an oxidant storage tank and an oxidant path pneumatic valve which are sequentially connected through pipelines, wherein the oxidant path pneumatic valve is connected with the combustion chamber, and second manual stop valves are arranged between the second nitrogen cylinder and the oxidant waste gas treatment device, between the oxidant waste gas treatment device and the oxidant storage tank and between the oxidant storage tank and the oxidant path pneumatic valve; a third pressure sensor is further arranged between the oxidant path pneumatic valve and the combustion chamber, and a second automatic pressure regulating pressure reducer and a second pressure relief pneumatic valve are further arranged at the air outlet of the second nitrogen cylinder and the air inlet of the oxidant waste gas treatment device respectively; the oxidant supply unit further comprises a second oxidant waste gas treatment device, a second exhaust stop valve, an oxidant receiving tank, a second transparent glass tube and a second liquid discharge stop valve which are connected in sequence, and the second liquid discharge stop valve is connected between the oxidant path pneumatic valve and the oxidant storage tank;
the measurement and control unit comprises a control system, a first pressure sensor, a temperature sensor, a gas chromatograph-mass spectrometer and an image acquisition device, wherein the first pressure sensor, the temperature sensor and the gas chromatograph-mass spectrometer are connected with the combustion chamber, and the image acquisition device is used for acquiring flame images generated by combustion reaction in the combustion chamber; the system comprises a first pressure sensor, a temperature sensor, an air mass spectrometer, an image acquisition device, a fuel path pneumatic valve, a first automatic pressure regulating pressure reducer, a first pressure relief pneumatic valve, a second pressure sensor, a first exhaust stop valve, a first liquid discharge stop valve, an oxidant path pneumatic valve, a second automatic pressure regulating pressure reducer, a second pressure relief pneumatic valve, a third pressure sensor, a second exhaust stop valve and a second liquid discharge stop valve, wherein the second automatic pressure regulating pressure reducer, the second pressure relief pneumatic valve, the third pressure sensor, the second exhaust stop valve and the second liquid discharge stop valve are all in communication connection with a control system.
2. The liquid propellant combustion reaction mechanism testing apparatus of claim 1, further comprising a combustion chamber exhaust gas treatment unit for collecting and treating exhaust gas generated by combustion in the combustion chamber.
3. The liquid propellant combustion reaction mechanism testing apparatus of claim 2, wherein the combustion chamber exhaust treatment unit comprises an exhaust collection device and an exhaust treatment device coupled to the exhaust collection device.
4. The liquid propellant combustion reaction mechanism testing device according to claim 1, wherein the image acquisition device is arranged outside the combustion chamber, and a transparent glass window for image acquisition by the image acquisition device is arranged on the combustion chamber.
5. A method for testing the combustion reaction mechanism of a liquid propellant, which is implemented by using the device for testing the combustion reaction mechanism of a liquid propellant according to any one of claims 1 to 4, and is characterized by comprising the following steps:
introducing the oxidant and the liquid propellant into the combustion chamber, and igniting the liquid propellant by the ignition device;
measuring the temperature generated by combustion through the temperature sensor, measuring the pressure generated by combustion through the first pressure sensor, recording the flame length of combustion through the image acquisition device, and analyzing the gas product generated by combustion through the gas chromatograph-mass spectrometer; and acquiring data of the temperature sensor, the first pressure sensor, the image acquisition device and the gas chromatograph-mass spectrometer through the control system.
6. The method of testing a liquid propellant combustion reaction mechanism of claim 5, further comprising:
and solving and calculating an Arrhenius equation of the combustion of the liquid propellant by adopting a quantum chemistry method for a gas product generated by the combustion, then adopting the Arrhenius equation in a numerical simulation model to simulate the temperature, the pressure and the flame length generated by the combustion, and then comparing a simulation result with an actual test result to verify the accuracy of a combustion reaction mechanism.
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