CN104764610A - System for testing influence of testing gas contamination on performance of supersonic speed combustion chamber - Google Patents
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- 238000012360 testing method Methods 0.000 title claims abstract description 115
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 64
- 238000011109 contamination Methods 0.000 title 1
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 claims abstract description 64
- 239000007789 gas Substances 0.000 claims abstract description 43
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 42
- 229910002092 carbon dioxide Inorganic materials 0.000 claims abstract description 32
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 31
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 29
- 239000001569 carbon dioxide Substances 0.000 claims abstract description 29
- 239000001301 oxygen Substances 0.000 claims abstract description 29
- 230000001105 regulatory effect Effects 0.000 claims description 26
- 239000000446 fuel Substances 0.000 claims description 21
- 238000011056 performance test Methods 0.000 claims description 7
- 239000002828 fuel tank Substances 0.000 claims description 5
- 238000002347 injection Methods 0.000 claims description 5
- 239000007924 injection Substances 0.000 claims description 5
- 239000007788 liquid Substances 0.000 claims description 4
- 239000003344 environmental pollutant Substances 0.000 claims description 3
- 231100000719 pollutant Toxicity 0.000 claims description 3
- 239000003570 air Substances 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 8
- 238000000034 method Methods 0.000 abstract description 7
- 239000012530 fluid Substances 0.000 abstract description 2
- 239000000203 mixture Substances 0.000 abstract description 2
- 238000010438 heat treatment Methods 0.000 description 11
- 230000000052 comparative effect Effects 0.000 description 6
- 238000004134 energy conservation Methods 0.000 description 2
- 229910052739 hydrogen Inorganic materials 0.000 description 2
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- -1 T t Chemical compound 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009833 condensation Methods 0.000 description 1
- 230000005494 condensation Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005485 electric heating Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000005429 filling process Methods 0.000 description 1
- 238000005338 heat storage Methods 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 230000001172 regenerating effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
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Abstract
本发明公开了一种试验气体污染对超音速燃烧室性能影响的试验系统，通过在混合器中添加由电阻加热器输供的高焓纯净空气与水添加系统喷入的水蒸气、二氧化碳添加系统喷入的二氧化碳及氧气添加系统喷入的氧气充分混合；通过喷管进入到燃烧室试验模型中，实现纯净空气和污染气体的对比试验，可有效地“分离”出试验工质组分组成差异、来流参数差别对超音速燃烧室工作过程及性能的影响。在同一试验车次中，可先进行纯净空气试验，再进行相应的污染气体试验；试验系统在提高试验效率的同时，也节省了试验成本。污染气体添加系统的工作性能可很好的满足模拟Ma4飞行状态下的燃烧室进口污染气体参数。
The invention discloses a test system for testing the influence of gas pollution on the performance of a supersonic combustion chamber. The high-enthalpy pure air supplied by a resistance heater and the water vapor and carbon dioxide added by a water adding system are added to a mixer. The injected carbon dioxide and the oxygen injected by the oxygen addition system are fully mixed; they enter the combustion chamber test model through the nozzle to realize the comparison test between pure air and polluted gas, which can effectively "separate" the difference in the composition of the test working fluid , The effect of the difference of incoming flow parameters on the working process and performance of the supersonic combustor. In the same test trip, the pure air test can be carried out first, and then the corresponding polluted gas test can be carried out; while the test system improves the test efficiency, it also saves the test cost. The working performance of the polluting gas addition system can well meet the parameters of the polluting gas at the inlet of the combustor under the simulated flight state of Ma4.
Description
技术领域technical field
本发明涉及航空发动机试验技术领域，具体地说，涉及一种试验气体污染对超音速燃烧室性能影响的试验系统。The invention relates to the technical field of aero-engine testing, in particular to a testing system for testing the influence of gas pollution on the performance of a supersonic combustion chamber.
背景技术Background technique
在超音速燃烧室技术研究过程中，地面试验具有关键性和基础性的作用。地面试验要求模拟真实飞行环境所需的高焓气体状态,超音速燃烧室地面试验数据外推应用到真实飞行条件的不确定性主要来自两方面，即来流条件的差别和试验模型的差别。前者除与流场品质问题相关外，主要是来流参数和试验空气组分的差别，即涉及到试验空气“污染效应”问题；后者主要是试验模型尺度、结构与飞行试验模型的差别，即涉及到试验模型“尺度效应”与结构影响问题。与常规气动力试验、气动热结构试验相比，在超音速燃烧室性能试验中，“污染效应”问题更为突出，由于其重要性和复杂性，一直受到了科研人员的广泛关注和持续研究。In the process of supersonic combustor technology research, ground tests play a key and fundamental role. The ground test is required to simulate the high-enthalpy gas state required for the real flight environment. The uncertainty of extrapolating the ground test data of the supersonic combustor to the real flight condition mainly comes from two aspects, namely the difference of the incoming flow condition and the difference of the test model. In addition to the quality of the flow field, the former is mainly related to the difference between the incoming flow parameters and the test air components, that is, the "pollution effect" of the test air; the latter is mainly the difference between the scale and structure of the test model and the flight test model. That is to say, it involves the "scale effect" and structural influence of the test model. Compared with conventional aerodynamic tests and aerodynamic thermal structure tests, the problem of "pollution effect" is more prominent in supersonic combustion chamber performance tests. Due to its importance and complexity, it has been widely concerned and continuously studied by researchers. .
现有公开的技术文献中，如日本RJTF设备“Comparison of Scramjet EnginePerformance in Mach 6Vitiated and Storage-Heated Air[J].Journal ofPropulsion and Power,Vol.13(5),September-October,1997.”；美国维吉尼亚大学开展的对比试验“Test Gas Vitiation Effects in a Dual-ModeScramjet Combustor[J].Journal of Propulsion and Power,Vol.23(3),July-August 2007.”均可视为严格对比试验，即采用纯净空气，蓄热式加热或电阻加热，和污染空气来流在匹配重要参数的前提下进行对比试验，可有效地分离出试验空气中的净“污染效应”。In the existing published technical literature, such as the Japanese RJTF equipment "Comparison of Scramjet Engine Performance in Mach 6Vitiated and Storage-Heated Air [J]. Journal of Propulsion and Power, Vol.13 (5), September-October, 1997."; The comparative test "Test Gas Vitiation Effects in a Dual-ModeScramjet Combustor[J]. Journal of Propulsion and Power, Vol.23(3), July-August 2007." conducted by the University of Virginia can be regarded as a strict comparative test , that is, using pure air, regenerative heating or resistance heating, and polluted air inflow to conduct comparative tests under the premise of matching important parameters, can effectively separate the net "pollution effect" in the test air.
上个世纪90年代，日本宇航院研究人员在冲压发动机试验设备上进行了模拟马赫数6.0状态下氢燃料超燃冲压发动机的整机自由射流对比试验,“Comparison of Scramjet Engine Performance in Mach 6Vitiated andStorage-Heated Air[J].Journal of Propulsion and Power,Vol.13(5),September-October,1997.”。RJTF设备在模拟马赫数6.0状态时可选择蓄热加热和燃烧加热中任一种。这种污染对比试验系统需要同时具备燃烧加热设备和纯净空气加热设备，使得试验的成本较高。Virginia大学研究人员利用电阻加热设备,针对氢燃料超声速燃烧室开展了纯净空气来流和H2O/CO2污染空气来流下直连式对比试验研究,“Test Gas Vitiation Effects in a Dual-ModeScramjet Combustor[J].Journal of Propulsion and Power,Vol.23(3),July-August 2007.”。利用其现有电阻加热器可产生最高1300K左右的高焓纯净空气来流，同时通过在电阻加热器进口空气来流中添加H2O、CO2污染组分并补入O2来模拟燃烧加热污染空气；因此具备在同一设备、模型上开展模拟飞行马赫数5.0状态下直连式燃烧室对比试验能力。污染试验气体中氧摩尔分数为21％，并匹配两种来流的燃烧室进口总温。相关文献中提到了维吉尼亚大学所使用的污染气体添加措施，但并未公开相关的技术资料，并且维吉尼亚大学所使用的污染气体添加措施中,污染组分中O2和CO2是在主流空气加热之前加入进去，会造成加热器氧化、老化加快，降低加热器的使用寿命，增加试验成本。In the 1990s, researchers at the Japanese Academy of Aeronautics and Astronautics conducted a free-jet comparative test of a hydrogen-fueled scramjet engine at a ramjet test facility simulating a Mach number of 6.0, "Comparison of Scramjet Engine Performance in Mach 6Vitiated and Storage- Heated Air [J]. Journal of Propulsion and Power, Vol.13(5), September-October, 1997.". RJTF equipment can choose either heat storage heating or combustion heating when simulating the Mach number 6.0 state. This kind of pollution comparison test system needs to have combustion heating equipment and pure air heating equipment at the same time, which makes the cost of the test higher. Researchers at the University of Virginia used resistance heating equipment to carry out direct-connected comparative experiments on hydrogen fuel supersonic combustors with pure air coming in and H 2 O/CO 2 polluted air flowing down, "Test Gas Vitiation Effects in a Dual-Mode Scramjet Combustor [J]. Journal of Propulsion and Power, Vol.23(3), July-August 2007.". Using its existing resistance heater, it can generate a high-enthalpy pure air flow at a maximum of about 1300K. At the same time, it can simulate combustion heating by adding H 2 O, CO 2 pollution components and adding O 2 to the resistance heater inlet air flow. Pollution of the air; therefore, it has the ability to carry out direct-connected combustor comparison tests under the simulated flight Mach number 5.0 state on the same equipment and model. The oxygen mole fraction in the polluted test gas is 21%, and matches the total temperature of the combustion chamber inlet of the two incoming streams. Relevant literature mentioned the pollution gas addition measures used by the University of Virginia, but did not disclose relevant technical information, and in the pollution gas addition measures used by the University of Virginia, O 2 and CO in the pollution components 2. Adding it before the mainstream air is heated will cause the heater to oxidize, accelerate aging, reduce the service life of the heater, and increase the test cost.
发明内容Contents of the invention
为了避免现有技术存在的不足，本发明提出一种试验气体污染对超音速燃烧室性能影响的试验系统；在纯净空气试验系统的基础上，通过在混合器内添加水蒸气和二氧化碳污染组分，使得试验系统具有在同一设备上开展模拟飞行马赫数4.0状态下燃烧室污染对比试验能力。In order to avoid the deficiencies in the prior art, the present invention proposes a test system for the influence of test gas pollution on the performance of supersonic combustion chambers; on the basis of the pure air test system, by adding water vapor and carbon dioxide pollution components in the mixer , so that the test system has the ability to carry out the combustion chamber pollution comparison test under the simulated flight Mach number 4.0 state on the same equipment.
本发明解决其技术问题所采用的技术方案是:包括纯净空气试验系统、污染气体添加系统、燃料供应系统、混合器、喷管、燃烧室试验模型，纯净空气试验系统包括空气气源、主路空气流量调节阀、电阻加热器，空气气源通过主路空气流量调节阀与电阻加热器连接，混合器位于电阻加热器与喷管之间，喷管与燃烧室试验模型连接；污染气体添加系统包括水添加系统、二氧化碳添加系统、氧气添加系统，水添加系统中的水活塞缸与水加热器连接，二氧化碳添加系统中的二氧化碳气源与流量调节阀及附件连接，水添加系统与二氧化碳添加系统通过管路和混合器连接，氧气添加系统中的氧气气源通过流量调节阀及附件与混合器连接；燃料供应系统中的燃料罐通过流量调节阀与燃烧室试验模型连接；试验步骤如下:The technical scheme that the present invention solves its technical problem is: comprise pure air test system, polluted gas adding system, fuel supply system, mixer, nozzle, combustion chamber test model, pure air test system comprises air source, main road Air flow regulating valve, resistance heater, the air source is connected to the resistance heater through the main air flow regulating valve, the mixer is located between the resistance heater and the nozzle, and the nozzle is connected to the combustion chamber test model; polluted gas addition system Including water addition system, carbon dioxide addition system, oxygen addition system, the water piston cylinder in the water addition system is connected to the water heater, the carbon dioxide gas source in the carbon dioxide addition system is connected to the flow regulating valve and accessories, the water addition system and the carbon dioxide addition system The oxygen source in the oxygen addition system is connected with the mixer through a flow regulating valve and accessories; the fuel tank in the fuel supply system is connected with the combustion chamber test model through a flow regulating valve; the test steps are as follows:
(1)调节主路空气流量调节阀和电阻加热器功率，将空气加热至800～1000K，在燃烧室试验模型中的流场稳定后，开启燃料供给系统，进行纯净空气来流的超音速燃烧室性能试验；(1) Adjust the main air flow regulating valve and the power of the resistance heater, heat the air to 800-1000K, and after the flow field in the combustion chamber test model is stable, turn on the fuel supply system to perform supersonic combustion with pure air flow Chamber performance test;
(2)完成纯净空气试验后，调节主路空气流量调节阀及电阻加热器功率，当电阻加热器出口空气达到所需状态后，开启污染气体添加系统，高温空气、二氧化碳、水蒸气、氧气在混合器内按一定比例混合均匀，混合器出口气体的氧气摩尔分数为21％；其中,水加热器内液态水被加热至400～750℃的水蒸气，喷入混合器；在燃烧室试验模型中的流场稳定后，开启燃料供应系统，按预定的时序控制向燃烧室试验模型喷射、燃烧，进行污染气体来流的超音速燃烧室性能试验；(2) After completing the pure air test, adjust the main air flow regulating valve and the power of the resistance heater. When the air at the outlet of the resistance heater reaches the required state, turn on the polluting gas addition system. High-temperature air, carbon dioxide, water vapor, and oxygen are The mixer is mixed evenly in a certain proportion, and the oxygen mole fraction of the gas at the outlet of the mixer is 21%; among them, the liquid water in the water heater is heated to 400-750°C steam, which is sprayed into the mixer; the model is tested in the combustion chamber After the flow field in the chamber is stabilized, the fuel supply system is turned on, and the injection and combustion are controlled to the combustion chamber test model according to the predetermined time sequence, and the performance test of the supersonic combustion chamber with the inflow of polluted gas is carried out;
(3)根据采集到的超音速燃烧室试验数据，分析污染组分水及二氧化碳对超音速燃烧室性能的影响。(3) According to the collected test data of the supersonic combustion chamber, the influence of the pollutant components water and carbon dioxide on the performance of the supersonic combustion chamber is analyzed.
有益效果Beneficial effect
本发明提出的一种试验气体污染对超音速燃烧室性能影响的试验系统，通过在混合器中添加经由电阻加热器输供的高焓纯净空气与水添加系统喷入的水蒸气、二氧化碳添加系统喷入的二氧化碳及氧气添加系统喷入的氧气充分混合，通过喷管进入到燃烧室试验模型中；燃料供应系统按预定的时序控制向燃烧室试验模型喷射、燃烧，实现纯净空气和污染气体的对比试验，可有效地“分离”出试验工质组分组成差异、来流参数差别对超音速燃烧室工作过程及性能的影响。在同一试验车次中，可先进行纯净空气试验，再进行相应的污染气体试验，既提高了试验效率，同时也节省了试验成本。污染气体添加系统的工作性能可很好的满足模拟Ma4飞行状态下的燃烧室进口污染空气参数。The present invention proposes a test system for testing the influence of gas pollution on the performance of a supersonic combustion chamber, by adding high-enthalpy pure air supplied through a resistance heater and water vapor injected by a water addition system and a carbon dioxide addition system into the mixer The injected carbon dioxide and the oxygen injected by the oxygen addition system are fully mixed, and enter the combustion chamber test model through the nozzle; the fuel supply system controls the injection and combustion of the combustion chamber test model according to the predetermined time sequence, so as to realize the separation of pure air and polluted gas. The comparative test can effectively "separate" the influence of the difference in the composition of the test working fluid and the difference in the incoming flow parameters on the working process and performance of the supersonic combustor. In the same test trip, the pure air test can be carried out first, and then the corresponding polluted gas test can be carried out, which not only improves the test efficiency, but also saves the test cost. The working performance of the polluting gas adding system can well satisfy the polluted air parameters at the inlet of the combustor under the simulated flight state of Ma4.
附图说明Description of drawings
下面结合附图和实施方式对本发明一种试验气体污染对超音速燃烧室性能影响的试验系统作进一步的详细说明。A test system for testing the influence of gas pollution on the performance of a supersonic combustion chamber of the present invention will be further described in detail below in conjunction with the drawings and embodiments.
图1为试验气体污染对超音速燃烧室性能影响的试验系统示意图。Figure 1 is a schematic diagram of the test system for testing the effect of gas pollution on the performance of a supersonic combustor.
图中:In the picture:
1.空气气源 2.主路空气流量调节阀 3.电阻加热器 4.混合器 5.喷管6.燃烧室试验模型 7.氧气气源 8.燃料罐 9.水加热器 10.水活塞缸11.二氧化碳气源 12.氧气添加系统 13.燃料供应系统 14.二氧化碳添加系统15.水添加系统1. Air source 2. Main air flow regulating valve 3. Resistance heater 4. Mixer 5. Nozzle 6. Combustion chamber test model 7. Oxygen source 8. Fuel tank 9. Water heater 10. Water piston Cylinder 11. Carbon dioxide gas source 12. Oxygen addition system 13. Fuel supply system 14. Carbon dioxide addition system 15. Water addition system
具体实施方式Detailed ways
本实施例是一种试验气体污染对超音速燃烧室性能影响的试验系统。This embodiment is a test system for testing the influence of gas pollution on the performance of a supersonic combustion chamber.
以马赫数4，总温为880K，纯净空气与污染气体的对比试验为例。表1为超音速燃烧室进口各组分的摩尔分数。Take Mach number 4, the total temperature is 880K, the comparison test of pure air and polluted gas as an example. Table 1 shows the mole fraction of each component at the inlet of the supersonic combustor.
表1超音速燃烧室进口状态参数Table 1 State parameters of supersonic combustion chamber inlet
试验气体污染对超音速燃烧室性能影响的试验系统由纯净空气试验系统、污染气体添加系统、燃料供应系统、混合器、喷管、燃烧室试验模型组成；纯净空气试验系统包括空气气源1、主路空气流量调节阀2、电阻加热器3；空气气源1通过主路空气流量调节阀2喷入电阻加热器3加热，并依次通过混合器4、喷管5，进入燃烧室试验模型6。燃料供应系统13中的燃料罐8通过流量调节阀与燃烧室试验模型6连接；燃料供应系统13按预定的时序控制向燃烧室试验模型6喷射、燃烧，进行纯净空气来流的超音速燃烧室性能试验。The test system for testing the influence of gas pollution on the performance of supersonic combustion chambers consists of a pure air test system, a polluted gas addition system, a fuel supply system, a mixer, a nozzle, and a combustion chamber test model; the pure air test system includes air source 1, Main road air flow regulating valve 2, resistance heater 3; air source 1 is sprayed into resistance heater 3 through main road air flow regulating valve 2 for heating, and then passes through mixer 4 and nozzle 5 in turn, and enters combustion chamber test model 6 . The fuel tank 8 in the fuel supply system 13 is connected to the combustion chamber test model 6 through a flow regulating valve; the fuel supply system 13 controls injection and combustion to the combustion chamber test model 6 according to a predetermined sequence, and performs a supersonic combustion chamber in which pure air flows. performance test.
污染气体添加系统包括水添加系统15、二氧化碳添加系统14、氧气添加系统12，水添加系统15中的水活塞缸10内的液态水通过活塞压入水加热器9内，在水加热器9内液态水被加热至400～750℃的水蒸气，喷入混合器4；二氧化碳添加系统14由二氧化碳气源11、流量调节阀及附件组成，二氧化碳通过流量调节阀喷入混合器4；氧气添加系统12由氧气气源7、流量调节阀及附件组成，氧气通过流量调节阀喷入混合器4，混合器4安装在电阻加热器3与喷管5之间，混合器4出口气体的氧气摩尔分数为21％；混合器4通过经由电阻加热器3的高焓纯净空气与水添加系统15喷入的水蒸气、二氧化碳添加系统14喷入的二氧化碳、氧气添加系统12喷入的氧气充分混合，通过喷管5进入到燃烧室试验模型6中。燃料供应系统13中的燃料罐8通过流量调节阀与燃烧室试验模型6连接；燃料供应系统13按预定的时序控制向燃烧室试验模型6喷射、燃烧，进行污染气体来流的超音速燃烧室性能试验。以马赫数4，纯净空气与煤油加热器污染空气的对比试验为例简要说明工作过程:The polluting gas addition system includes a water addition system 15, a carbon dioxide addition system 14, and an oxygen addition system 12. The liquid water in the water piston cylinder 10 in the water addition system 15 is pressed into the water heater 9 by the piston, and the liquid water in the water heater 9 The water is heated to 400-750°C steam and sprayed into the mixer 4; the carbon dioxide adding system 14 is composed of a carbon dioxide gas source 11, a flow regulating valve and accessories, and carbon dioxide is sprayed into the mixer 4 through the flow regulating valve; the oxygen adding system 12 It consists of an oxygen source 7, a flow regulating valve and accessories. Oxygen is sprayed into the mixer 4 through the flow regulating valve. The mixer 4 is installed between the resistance heater 3 and the nozzle 5. The oxygen mole fraction of the outlet gas of the mixer 4 is 21%; the mixer 4 fully mixes the high-enthalpy pure air through the resistance heater 3 with the water vapor injected by the water addition system 15, the carbon dioxide injected by the carbon dioxide addition system 14, and the oxygen injected by the oxygen addition system 12. The tube 5 enters the combustion chamber test model 6 . The fuel tank 8 in the fuel supply system 13 is connected to the combustion chamber test model 6 through a flow regulating valve; the fuel supply system 13 controls injection and combustion to the combustion chamber test model 6 according to a predetermined sequence, and the supersonic combustion chamber in which polluted gas flows performance test. Taking Mach number 4, the comparison test between pure air and kerosene heater polluted air as an example, briefly explain the working process:
第一步.试验状态的确定；纯净空气试验时，根据试验状态要求设定电阻加热器3的预定加热温度值至880K，调整主路空气流量调节阀2，使得燃烧室进口达到需要的流量，并通过燃料供应系统13调节好燃料供应路压力；污染气体的超音速燃烧室试验，关键在于产生满足预期要求的H2O/CO2污染气体。采用在电阻加热器出口高焓纯净空气中定量添加H2O、CO2组分并补氧的方式来模拟燃烧加热污染空气。根据污染试验空气中氧含量、混合前后质量和能量守恒，得到:Step 1. Determination of the test state; during the pure air test, set the predetermined heating temperature value of the resistance heater 3 to 880K according to the test state requirements, and adjust the main air flow regulating valve 2 so that the inlet of the combustion chamber reaches the required flow rate. The pressure of the fuel supply path is adjusted through the fuel supply system 13; the key to the supersonic combustion chamber test of the polluted gas is to generate the H 2 O/CO 2 polluted gas that meets the expected requirements. The method of quantitatively adding H 2 O and CO 2 components to the high-enthalpy pure air at the outlet of the resistance heater and supplementing oxygen was used to simulate combustion to heat the polluted air. According to the oxygen content in the pollution test air, the mass and energy conservation before and after mixing, it is obtained:
式中，XH2O为3.00％，XCO2为3.00％，W、X和h分别表示质量流量、分子量、摩尔分数和比焓，下标O2、air、H2O、CO2和vit分别对应氧气、电阻加热纯净空气、水组分、二氧化碳组分和污染空气的参数，下标t表示总参数。根据式(5)中能量守恒关系，为了产生满足预定要求的污染试验空气总温Tt,vit，可在Tt,air、Tt,H2O、Tt,CO2三者中选其一作为调节量。考虑到操作方便和控制的精度要求，试验中选择调节电阻加热器出口纯净空气总温Tt,air来实现对污染空气总温Tt,vit的控制。二氧化碳以气态形式混入主流，其温度需保证在加注过程中不出现凝结；补入的氧气较少，为室温混入。根据上述方程式解出各污染组分添加的参数，调节各添加系统的参数使其满足污染试验的条件即可开始试验。In the formula, X H2O is 3.00%, X CO2 is 3.00%, W, X, and h represent mass flow, molecular weight, mole fraction, and specific enthalpy, respectively, and the subscripts O2, air, H2O, CO2, and vit correspond to parameters of oxygen, resistance-heated pure air, water components, carbon dioxide components, and polluted air, respectively. , the subscript t represents the total parameter. According to the energy conservation relationship in formula (5), in order to produce the total air temperature T t,vit of the pollution test that meets the predetermined requirements, one of T t,air , T t,H2O , T t,CO2 can be selected as the adjustment value . Considering the convenience of operation and the precision requirements of control, in the test, the total temperature T t,air of pure air at the outlet of the resistance heater is selected to control the total temperature T t,vit of polluted air. Carbon dioxide is mixed into the mainstream in gaseous form, and its temperature needs to ensure that no condensation occurs during the filling process; less oxygen is added, and it is mixed at room temperature. According to the above equations, the parameters of the addition of each pollution component are solved, and the parameters of each addition system are adjusted to meet the conditions of the pollution test to start the test.
第二步.在升温阶段，缓慢打开电阻加热器上游主路空气流量调节阀2，通过阀门开度完成进口空气流量的调节与控制，当空气流量达到电阻加热器3安全启动所需的最低流量时，接通电阻加热器3电源，空气流经电阻加热器3内电热元件得到升温。Step 2. In the heating stage, slowly open the air flow regulating valve 2 of the upstream main circuit of the resistance heater, and complete the adjustment and control of the inlet air flow through the opening of the valve. When the air flow reaches the minimum flow required for the safe start of the resistance heater 3 , turn on the resistance heater 3 power supply, and the air flows through the electric heating element in the resistance heater 3 to heat up.
第三步.纯净空气试验阶段，当电阻加热器3出口温度和流量达到试验要求并恒定后，气流经过主路的设备喷管5后以预定的压力、温度、Ma数和流量流入超音速燃烧室试验模型6，在建立稳定的燃烧室进口流场后，启动燃料供应控制系统13，按照预定的时序向燃烧室喷射、燃烧。Step 3. In the pure air test stage, when the outlet temperature and flow rate of the resistance heater 3 meet the test requirements and become constant, the air flow passes through the equipment nozzle 5 of the main road and flows into the supersonic combustion at a predetermined pressure, temperature, Ma number and flow rate. In the chamber test model 6, after establishing a stable flow field at the inlet of the combustion chamber, the fuel supply control system 13 is activated to inject and burn into the combustion chamber according to a predetermined sequence.
第四步.污染气体试验阶段，调节电阻加热器3出口温度及流量至污染试验要求段并恒定后，在混合器4内喷入污染组分，在建立稳定的燃烧室进口流场后，启动燃料供应系统13，按照预定的时序向燃烧室喷射、燃烧。Step 4. During the polluting gas test stage, adjust the outlet temperature and flow rate of the resistance heater 3 to the required section of the pollution test and keep constant, then spray the polluting components into the mixer 4, and start the process after a stable flow field at the inlet of the combustion chamber is established. The fuel supply system 13 injects and burns into the combustion chamber according to a predetermined timing.
第五步.试验结束阶段，当燃烧结束后，关闭电阻加热器3，并保持一定流量直至电阻加热器3冷却到规定温度后，依次关闭主路空气流量调节阀2、燃料供应系统13、氧气添加系统12、二氧化碳添加系统14、水添加系统15，试验结束。Step 5. At the end of the test, when the combustion is over, turn off the resistance heater 3 and maintain a certain flow until the resistance heater 3 cools down to the specified temperature, then turn off the main road air flow regulating valve 2, the fuel supply system 13, the oxygen Adding system 12, carbon dioxide adding system 14, water adding system 15, the test ends.
第六步.根据采集到的超音速燃烧室试验数据，分析污染组分水及二氧化碳对超音速燃烧室性能的影响。Step 6. According to the collected test data of the supersonic combustion chamber, analyze the influence of the pollutant components water and carbon dioxide on the performance of the supersonic combustion chamber.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105067266A (en) * | 2015-07-29 | 2015-11-18 | 华中科技大学 | Multifunctional combustion chamber experimental system for gas turbine |
| CN108800190A (en) * | 2018-06-25 | 2018-11-13 | 西北工业大学 | A kind of test(ing) medium mixing arrangement |
| CN109932182A (en) * | 2019-03-05 | 2019-06-25 | 北京航空航天大学 | Carbon dioxide high enthalpy inflow generator |
| CN112343733A (en) * | 2020-10-30 | 2021-02-09 | 西安航天动力试验技术研究所 | High-temperature air generation system, precooling combined engine ground test device and method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4201650C2 (en) * | 1992-01-22 | 1994-08-11 | Mahler Dienstleistung | Device for the thermal combustion of exhaust gases contaminated with oxidizable pollutants |
| JPH1030821A (en) * | 1996-07-17 | 1998-02-03 | Ishikawajima Harima Heavy Ind Co Ltd | Gas turbine combustor |
| US20040216535A1 (en) * | 2002-10-15 | 2004-11-04 | Joseph Brostmeyer | High temperature and pressure testing facility |
| CN103597333A (en) * | 2011-03-29 | 2014-02-19 | 佛罗里达涡轮技术股份有限公司 | Apparatus and process for testing an industrial gas turbine engine and components thereof |
| CN103954643A (en) * | 2014-05-06 | 2014-07-30 | 中国航天空气动力技术研究院 | Testing method for simulating high-temperature water-containing air current in combustion chamber |
-
2015
- 2015-03-30 CN CN201510144048.4A patent/CN104764610A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4201650C2 (en) * | 1992-01-22 | 1994-08-11 | Mahler Dienstleistung | Device for the thermal combustion of exhaust gases contaminated with oxidizable pollutants |
| JPH1030821A (en) * | 1996-07-17 | 1998-02-03 | Ishikawajima Harima Heavy Ind Co Ltd | Gas turbine combustor |
| US20040216535A1 (en) * | 2002-10-15 | 2004-11-04 | Joseph Brostmeyer | High temperature and pressure testing facility |
| CN103597333A (en) * | 2011-03-29 | 2014-02-19 | 佛罗里达涡轮技术股份有限公司 | Apparatus and process for testing an industrial gas turbine engine and components thereof |
| CN103954643A (en) * | 2014-05-06 | 2014-07-30 | 中国航天空气动力技术研究院 | Testing method for simulating high-temperature water-containing air current in combustion chamber |
Non-Patent Citations (2)
| Title |
|---|
| 宋文艳等: "纯净空气来流下的超声速燃烧实验装置及其初步实验结果", 《实验流体力学》 * |
| 陈亮等: "H2O/CO2污染对煤油燃料双模态超声速燃烧室影响研究", 《推进技术》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105067266A (en) * | 2015-07-29 | 2015-11-18 | 华中科技大学 | Multifunctional combustion chamber experimental system for gas turbine |
| CN105067266B (en) * | 2015-07-29 | 2017-11-14 | 华中科技大学 | A kind of Multifunctional combustion chamber experimental system suitable for gas turbine |
| CN108800190A (en) * | 2018-06-25 | 2018-11-13 | 西北工业大学 | A kind of test(ing) medium mixing arrangement |
| CN108800190B (en) * | 2018-06-25 | 2020-07-03 | 西北工业大学 | Test medium mixing device |
| CN109932182A (en) * | 2019-03-05 | 2019-06-25 | 北京航空航天大学 | Carbon dioxide high enthalpy inflow generator |
| CN112343733A (en) * | 2020-10-30 | 2021-02-09 | 西安航天动力试验技术研究所 | High-temperature air generation system, precooling combined engine ground test device and method |
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