| In this thesis, preliminary study was conducted in shock tube on temperature measurements by two-line NO-PLIF technique in which regular and Mach reflection of planar shock wave along rigid wall and wedge were selected as the subject investigated. The works are summarized as follows:1、Chapter 1 presents the background, related progress on this topic and the primary coverage of this thesis.2、Chapter 2 introduces the shock tube facility and NO-PLIF system used in this thesis. Modification was done on the shock tube in which the electro-heating diaphragm bursting device was involved to increase the repeatability of shots and decrease the deviation of shock speed. The diaphragm bursting device and the PLIF system were synchronized by the synchronization system. The results imply that the fluctuation of shock speed is small, the shock tube performance shows great repeatability, the deviation of shock speed is less than 1%. The available temperature lies in 300K-1700K by adjusting the pressure ratio between the high pressure section and the low pressure section.3、Temperature measurements by NO-PLIF were carried out under different test conditions in Chapter 3, in which the temperature field generated by planar incident and reflected shock wave, the temperature field generated by the regular and Mach reflection of planar shock wave were taken into account. The results from experiments, theoretical estimation and CFD were compared. The primary works are as follows:1)The temperature distribution of still mixture (98%N2+2%NO) that was at room-temperature was measured by NO-PLIF. The measured temperature is 304±15K and the relative error is less than 5% which implies the practicability of the NO-PLIF system and the reliability of the conversion algorithm of temperature.2)The temperature field in front of and behind of the planar incident shock wave was measured. When the temperature in front of the shock wave is 300K and the pressure ratio between the high pressure section and the low pressure section is 25.5, the temperature behind the shock wave estimated by shock relation is 665K. The measured temperature in front of and behind of the shock wave is 295K ? 20K and 620K ? 50K, respectively. The relative error is less than 10%. When pressure ratio between the high pressure section and the low pressure section is 88.1, the temperature behind of the shock wave estimated by shock relation is 980K. The measured temperature in front of and behind the shock wave is 340K±30K and 1000K±150K, respectively. The relative error is less than 10% and 15%, respectively.3)The temperature field in front of and behind of the planar reflected shock wave was measured and compared with CFD results. When the pressure ratio between the high pressure section and the low pressure section is 25.5, the estimated temperature in front of and behind of the reflected shock wave is 639K and 1065K, respectively. The measured temperature is 630K±50K and 980K±100K, respectively. The relative error is less than 10%. When pressure ratio between the high pressure section and the low pressure section is 88.1, the estimated temperature in front of and behind of the reflected shock wave is 951K and 1653K, respectively. The measured temperature is 950K±70K and 1500K±250K, respectively. The relative error is less than 15%.4)Temperature distribution in regular shock reflection field along wedge with 55°wedge angle was measured at the same pressure ratios mention above, the results are compared with CFD results. When the pressure ratio is 25.5, the temperature in front of and behind of the incident and reflected shock wave obtained by CFD is 300K, 664K and 996K, respectively. The measured temperature is 320K±20K, 630K±40K and 1030±100K,respectively. The relative error is less than 10%. When the pressure ratio is 88.1, the temperature in front of and behind of the incident and reflected shock wave obtained by CFD is 300K, 951K and 1533K, respectively. The measured temperature is 330K±50K, 950K±150K and 1600±200K,respectively. The relative error is less than 15%. Obviously, higher temperature leads to larger relative error.5)Temperature distribution in Mach shock reflection field along wedge with 15°wedge angle was measured at the same pressure ratios mention above, the results are compared with CFD results. When the pressure ratio is 25.5, the temperature in front of and behind of the incident and reflected shock wave and in the reflection zone obtained by CFD is 300K, 666K and 766K, respectively. The measured temperature is 310K±20K, 590K±70K and 870±130K,respectively. The relative error is less than 10%. When the pressure ratio is 88.1, the temperature in front of and behind of the incident and reflected shock wave and in the reflection zone obtained by CFD is 300K, 956K and 1133K, respect- ively. The measured temperature is 320K±40K, 850K±150K and 1150±150K,respectively. The relative error is less than 15%. Obviously, higher temperature leads to larger relative error. 6)The source of experimental error is briefly discussed.4、Chapter four gives the conclusions and proposals for future studies.The innovations in thesis are as follows:1、In this thesis, temperature distribution in planar incident and reflected shock wave, regular reflection and Mach reflection field was measured by NO-PLIF. The results were compared with the results from shock relation and CFD. The main difficulties of NO-PLIF thermometry, error band and the main source of error were preliminarily understood. Thermometry by NO-PLIF on impulse facility is more difficult than that on continuous facility.2、Data manipulation software was introduced and co-operatively developed based on the relationship between fluorescence intensity and temperature. NO-PLIF images can be mathematical calculated by this software. The temperature distribution along line or zone can also be obtained. This would benefit the PLIF thermometry in the popularization in industrial application. |
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