Aeronautics and Astronautics Part 11 potx

O 2 /CH 4 Kinetic Mechanisms for Aerospace Applications at Low Pressure and Temperature, Validity Ranges and Comparison 389 M echanisms Reactants Temperature 32species 177reactions 17species 58reactions 6species 2reactions 4species 1reactio n 5species 2reactions 1000 41.13% 95.32% 17.53% 59.31% 1100 19.85% 94.66% 46.47% 72.87% 1200 0.43% 94.81% 56.65% 78.11% 1300 -14.90% 93.34% 58.80% 79.40% 1400 -14.93% -8009.45% 93.83% 60.05% 79.90% 1500 -28.68% -4812.84% 95.28% 53.09% 76.55% 1600 -19.76% -2839.52% 93.35% 50.81% 75.56% 1700 -19.61% -1958.82% 93.17% 45.39% 73.53% 1800 -20.25% -1444.89% 90.21% 40.29% 70.15% 1900 -19.92% -1127.09% 88.09% 38.25% 69.28% 2000 -20.28% -913.99% 85.87% 37.83% 69.37% Table A10. P=3atm, Φ=1.9: t id % differences between reduced and reference mechanisms M echanisms Reactants Temperature 32species 177reactions 17species 58reactions 6species 2reactions 4species 1reactio n 5species 2reactions 1000 23.60% -3020.00% 1100 -0.43% -652.14% 1200 -13.69% -225.82% 1300 -20.00% -87.65% 1400 -17.47% -39.45% 1500 -13.16% -7838.60% -32.02% 1600 -9.90% -3919.80% -49.50% 1700 -8.67% -2115.80% -71.10% 1800 -9.24% -1236.63% -87.46% 1900 -10.89% -746.53% -89.60% 2000 -13.64% -452.60% -75.32% Table A11. P=5atm, Φ=0.3: t id % differences between reduced and reference mechanisms M echanisms Reactants Temperature 32species 177reactions 17species 58reactions 6species 2reactions 4species 1reactio n 5species 2reactions 1000 23.13% -80.60% 1100 0.73% -9.85% 1200 -15.98% 20.53% 1300 -19.12% 40.20% 1400 -20.15% 55.47% 1500 -16.86% -7664.71% 62.31% 1600 -16.04% -4098.11% 61.60% 1700 -10.71% -2360.32% 57.14% 1800 -9.54% -1518.32% 50.00% 1900 -10.88% -1063.27% 41.63% 2000 -9.07% -780.18% 34.15% Table A12. P=5atm, Φ=0.5: t id % differences between reduced and reference mechanisms Aeronautics and Astronautics 390 M echanisms Reactants Temperature 32species 177reactions 17species 58reactions 6species 2reactions 4species 1reactio n 5species 2reactions 1000 26.80% 60.13% 1100 0.31% 63.35% 1200 -10.16% 72.91% 1300 -16.94% 73.97% 1400 -30.08% 79.95% 1500 -20.00% -7198.25% 85.79% 1600 -17.54% -4022.81% 80.70% 1700 -13.42% -2357.47% 79.21% 1800 -12.88% -1574.24% 75.49% 1900 -12.41% -1127.59% 71.24% 2000 -9.79% -836.64% 67.28% Table A13. P=5atm, Φ=0.7: t id % differences between reduced and reference mechanisms M echanisms Reactants Temperature 32species 177reactions 17species 58reactions 6species 2reactions 4species 1reactio n 5species 2reactions 1000 29.65% 82.33% 1100 8.29% 83.12% 1200 -10.51% 86.89% 1300 -18.38% 84.60% 1400 -16.25% 86.00% 1500 -20.89% -6703.80% 87.85% 1600 -17.89% -3859.35% 87.97% 1700 -15.68% -2332.43% 87.19% 1800 -14.34% -1576.47% 85.00% 1900 -14.38% -1153.42% 82.19% 2000 -15.90% -892.88% 79.12% Table A14. P=5atm, Φ=0.9: t id % differences between reduced and reference mechanisms M echanisms Reactants Temperature 32species 177reactions 17species 58reactions 6species 2reactions 4species 1reactio n 5species 2reactions 1000 29.07% 86.34% 1100 8.12% 86.52% 1200 -3.87% 86.66% 1300 -20.92% 87.16% 37.23% 1400 -21.61% 88.27% 44.63% 1500 -21.45% -6486.10% 89.73% 39.58% 1600 -16.03% -3678.63% 90.31% 1700 -16.29% -2299.30% 89.47% 33.45% 1800 -16.00% -1580.00% 87.60% 30.55% 1900 -15.65% -1158.50% 85.24% 30.61% 2000 -14.63% -884.90% 82.93% Table A15. P=5atm, Φ=1.0: t id % differences between reduced and reference mechanisms O 2 /CH 4 Kinetic Mechanisms for Aerospace Applications at Low Pressure and Temperature, Validity Ranges and Comparison 391 M echanisms Reactants Temperature 32species 177reactions 17species 58reactions 6species 2reactions 4species 1reactio n 5species 2reactions 1000 32.97% 93.46% -53.85% 27.47% 1100 9.95% 89.85% 5.22% 52.74% 1200 -9.80% 88.92% 30.29% 68.92% 1300 -16.94% 91.33% 38.21% 69.83% 1400 -21.03% 95.11% 43.59% 73.95% 1500 -23.10% -6332.75% 90.99% 38.30% 69.88% 1600 -21.97% -3695.45% 91.21% 34.70% 69.09% 1700 -10.48% -2288.32% 91.07% 31.10% 65.46% 1800 -16.79% -1571.43% 89.57% 28.21% 63.93% 1900 4.03% -1155.03% 87.65% 27.52% 64.23% 2000 -17.87% -915.38% 85.09% 26.86% 62.72% Table A16. P=5atm, Φ=1.1: t id % differences between reduced and reference mechanisms M echanisms Reactants Temperature 32species 177reactions 17species 58reactions 6species 2reactions 4species 1reactio n 5species 2reactions 1000 34.65% 93.37% -51.49% 25.25% 1100 11.14% 92.95% 4.55% 51.82% 1200 -8.04% 92.58% 27.95% 63.84% 1300 -18.60% 92.50% 37.80% 69.21% 1400 -28.43% 92.53% 40.29% 69.71% 1500 -14.56% -5964.69% 93.34% 37.47% 69.27% 1600 8.45% -3505.63% 93.66% 33.03% 67.46% 1700 -17.65% -2220.26% 93.28% 31.05% 63.89% 1800 -17.99% -1553.98% 92.18% 22.49% 61.59% 1900 -17.88% -1164.90% 90.40% 20.53% 60.40% 2000 -16.97% -905.73% 89.12% 21.22% 62.04% Table A17. P=5atm, Φ=1.3: t id % differences between reduced and reference mechanisms M echanisms Reactants Temperature 32species 177reactions 17species 58reactions 6species 2reactions 4species 1reactio n 5species 2reactions 1000 33.33% 95.12% -55.40% 24.41% 1100 10.81% 95.49% 4.24% 53.18% 1200 -6.56% 97.86% 30.66% 65.98% 1300 -19.32% 94.18% 36.93% 68.18% 1400 -25.89% 97.54% 38.21% 71.96% 1500 -25.58% -5731.20% 94.42% 35.29% 68.29% 1600 -39.69% -3884.73% 96.45% 20.61% 61.37% 1700 -23.43% -2227.45% 94.56% 23.92% 61.48% 1800 -19.80% -1537.58% 93.83% 18.46% 59.40% 1900 -19.48% -1166.23% 92.47% 14.94% 58.12% 2000 -18.59% -920.52% 91.61% 14.37% 58.15% Table A18. P=5atm, Φ=1.5: t id % differences between reduced and reference mechanisms Aeronautics and Astronautics 392 M echanisms Reactants Temperature 32species 177reactions 17species 58reactions 6species 2reactions 4species 1reactio n 5species 2reactions 1000 34.76% 96.42% -50.64% 90.60% 1100 12.30% 96.11% 4.30% 52.93% 1200 0.00% 95.83% 30.83% 68.33% 1300 -17.59% 95.54% 36.75% 68.77% 1400 -23.77% 95.48% 41.48% 74.02% 1500 -24.41% -5397.63% 95.64% 46.45% 68.25% 1600 -21.25% -3218.75% 95.80% 29.38% 66.06% 1700 -21.65% -2110.53% 95.58% 22.71% 60.90% 1800 -21.10% -1510.39% 95.00% 13.96% 57.47% 1900 -20.13% -1151.57% 93.91% 10.06% 55.66% 2000 -19.73% -911.09% 93.28% 9.09% 55.21% Table A19. P=5atm, Φ=1.7: t id % differences between reduced and reference mechanisms M echanisms Reactants Temperature 32species 177reactions 17species 58reactions 6species 2reactions 4species 1reactio n 5species 2reactions 1000 34.68% 98.90% -53.63% 26.61% 1100 13.08% 97.77% 5.16% 53.22% 1200 -0.71% 98.01% 28.37% 64.18% 1300 -17.91% 96.99% 35.32% 68.66% 1400 -25.78% -9821.88% 97.76% 37.27% 69.06% 1500 -30.23% -5365.12% 96.98% 32.56% 66.28% 1600 -24.70% -3146.99% 97.99% 26.51% 63.73% 1700 -25.44% -2105.88% 96.16% 18.09% 58.82% 1800 -22.64% -1484.91% 95.75% 10.06% 55.66% 1900 -22.09% -1139.26% 95.11% 4.91% 53.68% 2000 -21.18% -913.10% 94.26% 2.95% 53.06% Table A20. P=5atm, Φ=1.9: t id % differences between reduced and reference mechanisms Fig. A1. Φ=0.3, P=3atm, temperature O 2 /CH 4 Kinetic Mechanisms for Aerospace Applications at Low Pressure and Temperature, Validity Ranges and Comparison 393 Fig. A2. Φ=0.5, P=3atm, temperature Fig. A3. Φ=0.7, P=3atm, temperature Fig. A4. Φ=0.9, P=3atm, temperature Aeronautics and Astronautics 394 Fig. A5. Φ=1, P=3atm, temperature Fig. A6. Φ=1.1, P=3atm, temperature Fig. A7. Φ=1.3, P=3atm, temperature O 2 /CH 4 Kinetic Mechanisms for Aerospace Applications at Low Pressure and Temperature, Validity Ranges and Comparison 395 Fig. A8. Φ=1.5, P=3atm, temperature Fig. A9. Φ=1.7, P=3atm, temperature Fig. A10. Φ=1.9, P=3atm, temperature Aeronautics and Astronautics 396 Fig. A11. Φ=0.3, P=5atm, temperature Fig. A12. Φ=0.5, P=5atm, temperature Fig. A13. Φ=0.7, P=5atm, temperature O 2 /CH 4 Kinetic Mechanisms for Aerospace Applications at Low Pressure and Temperature, Validity Ranges and Comparison 397 Fig. A14. Φ=0.9, P=5atm, temperature Fig. A15. Φ=1, P=5atm, temperature Fig. A16. Φ=1.1, P=5atm, temperature Aeronautics and Astronautics 398 Fig. A17. Φ=1.3, P=5atm, temperature Fig. A18. Φ=1.5, P=5atm, temperature Fig. A19. Φ=1.7, P=5atm, temperature [...]... Temp., (°C) 112 0 118 0 Quenching Temp., (°C) 114 0 for 1 h 115 0 for 1 h cooled for 15 min in molten salt at 583 °C 116 0 for 1 h 116 5 for 1 h 115 0 for 1 h 116 0 for 1 h cooled for 15 min in oil bath at 120 °C 115 0 for 1 h cooled for 15 min in molten salt at 583 °C 116 0 for 1 h Table 2.1 Heat treatment regime of FGH95 superalloy Double aging treatment 870 °C×1h + 650 °C×24h 405 Creep Behaviors and Influence... fully heat treated (a) 112 0 °C, (b) 115 0 °C, (c) 118 0 °C Creep Behaviors and Influence Factors of FGH95 Nickel-Base Superalloy 409 Moreover, fine white particles were discontinuously precipitated along the boundaries as marked with the long arrow in Fig 3.4(a) and (b), and the fine secondary  phase and white particles were dispersedly distributed in the alloy as shown in Fig 3.4(a) and (b) With the HIP... different temperatures, and cooled in molten salt (a) After solution treated at 115 0 °C, the fine  phase distributed dispersedly in the grains, and the coarse  particles precipitated along the boundaries, (b) after solution treated at 116 0 °C, straight-like boundaries marked by black arrow, and the fine particles distributed dispersedly within the grains 414 Aeronautics and Astronautics 5 Influence... isostatic pressed (HIP) for 4 h under the applied stress of 120 MPa at 112 0 °C, 115 0 °C and 118 0 °C, respectively The heat treatment and long term aged treatment regimes of the alloy are listed, respectively, in the Table 2.1 and Table 2.2 The cooled rates of the specimen in the oil bath and molten salt are measured to be about 205 °C/min and 110 °C/min, respectively The error ranges of the used heating furnace...  phase were defined as previous powder particles After 112 0 °C hot isostatic pressing molded, the alloy consisted of  and  phases, thereinto, the coarser  phase distributed around the powder particles was defined as the previous particle boundaries (PPB) Therefore, the configuration of sphere-like previous particle was clearly appeared, and the power particle size was about 15~25 μm, as shown... disappeared, and the white particles with size about 0.2 μm were precipitated within the grains and along the boundaries as marked by the arrows in Fig 4.3(a) The magnified morphology of the alloy was shown in Fig 4.3(b), indicating that the coarser  particles and depleted zone of the fine 411 Creep Behaviors and Influence Factors of FGH95 Nickel-Base Superalloy  phase had disappeared, and the secondary... temperatures and cooled in oil bath (a) After solution treated at 115 0 °C, the fine  phase distributed dispersedly within the grains, and the depleted zone of -phase as marked by shorter arrow (b) after solution treated at 116 0 °C, the fine  phase and carbide particles distributed dispersedly within the grains, respectively After solution treated at 115 0 °C, then cooled in molten salt and twice... HIP alloy after fully heat treated (a) 112 0 °C, (b) 115 0 °C, (c) 118 0 °C The magnified morphology of the different temperature HIP alloy after fully heat treated was shown Fig 3.4 After the 112 0 °C and 115 0 °C HIP alloys were fully heat treated, a few of coarse  phase was precipitated along the boundary regions as marked with short arrow in Fig 3.4(a) and (b) And the coarse  phase appeared in the... it is indicated that the elements Nb, Ti and C are richer in the white particles which were located within the grain and boundary regions as shown in Fig 4.3 and Fig 4.4, respectively After the alloy was solution treated at 116 0 °C, the fine -particles with the size of about 0.1 m were dispersedly precipitated within the grains as shown in Fig 4.5(a), the particles can effectively hinder the dislocation... smaller space between the fine -particle was measured to be about 0.03 m, the bigger space between the fine -particles is measured to be about 0.12 m as marked by letters L1 and L2 in Fig 4.5(a), respectively It was indicated by TEM/EDS analysis that the elements Nb, Ti and C richer in the carbide particle which was located in the boundary as shown in Fig 4.5(b), and the particle was identified as (Nb, . Double aging treatment 112 0 114 0 for 1 h 115 0 for 1 h 116 0 for 1 h 116 5 for 1 h cooled for 15 min in molten salt at 583 °C 870 °C×1h + 650 °C×24h 118 0 115 0 for 1 h 116 0 for 1 h cooled for. stress of 120 MPa at 112 0 °C, 115 0 °C and 118 0 °C, respectively. The heat treatment and long term aged treatment regimes of the alloy are listed, respectively, in the Table 2.1 and Table 2.2. The. salt or in oil bath, and the microstructure and creep properties of the alloy are related to the chosen heat treatment regimes (Klepser C. A., 1995 ). Aeronautics and Astronautics 404 The