涡轮叶片气膜冷却实验研究
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摘要
应航空发动机设计的要求，在大尺寸低速叶栅传热风洞中分别对发动机涡轮导向叶片和动叶表面的气膜冷却特性进行了研究，具体研究在不同气膜孔出流时，在不同主流雷诺数和吹风比情况下叶片表面局部换热系数的分布规律。实验中导叶叶片有15排气膜孔，动叶叶片有8排气膜孔，孔型都是圆柱孔。
对导叶和动叶，都是先研究了在150000，200000，250000，300000，350000，400000雷诺数下，没有气膜冷却时的表面换热系数分布，然后研究了气膜孔全打开和只打开单排孔时的表面换热系数分布曲线，重点研究来流雷诺数，吹风比和不同孔位出流对换热系数分布的影响规律。实验结果表明，不同孔位出流的换热由于孔排下游表面来流速度及叶片表面曲率的不同而有不同的规律，而主流雷诺数对叶片表面特别是压力面和前缘区域的换热系数比的影响较小，吹风比对换热系数影响较大(特别是导叶)，并且随气膜孔位置和来流雷诺数的变化而情况复杂。
研究了一种用用最小二乘法来拟和单排孔下游换热系数分布曲线的拟合公式，并得到了与实验数据符合良好的结果。
Film cooling of the surface of a gas turbine blade was studied in a large-scale low-speed opening wind tunnel according to actual Requirement of the design of aero-engine. The surface of a gas turbine blade was cooled by cylindrical holes in the experiment,with the hole number of fifteen in stator and eight in rotor.
Above all, the surface of the gas turbine blade including stator and rotor heat transfer coeficience with no film cooling hole was studied with the main stream Reynolds number of 150000,200000 50000,300000,350000,400000. Then, the heat transfer coefficience when all cooling holes opened and only one cooling hole opened was studied partly. And it's studied how the mainstream Reynolds number, blowing ratio and the position of holes affect the heat transfer coefficience of the surface of blade. Results show that the influence of mainstream Reynolds numbers on heat transfer coefficience is little and the heat transfer coefficience raise with the increase of Reynolds numbers. The influence of the position of holes on heat transfer coefficience is complex and correlate with the mainstream speed and the balde surface curvature. And the influence of blowing ratio on heat transfer coefficience is more great (especially to stator) ,and show a complex relation to mainstream Reynolds number and the position of holes.
A simulation fomular was studied to accord the heat transfer experimental data.
对导叶和动叶，都是先研究了在150000，200000，250000，300000，350000，400000雷诺数下，没有气膜冷却时的表面换热系数分布，然后研究了气膜孔全打开和只打开单排孔时的表面换热系数分布曲线，重点研究来流雷诺数，吹风比和不同孔位出流对换热系数分布的影响规律。实验结果表明，不同孔位出流的换热由于孔排下游表面来流速度及叶片表面曲率的不同而有不同的规律，而主流雷诺数对叶片表面特别是压力面和前缘区域的换热系数比的影响较小，吹风比对换热系数影响较大(特别是导叶)，并且随气膜孔位置和来流雷诺数的变化而情况复杂。
研究了一种用用最小二乘法来拟和单排孔下游换热系数分布曲线的拟合公式，并得到了与实验数据符合良好的结果。
Film cooling of the surface of a gas turbine blade was studied in a large-scale low-speed opening wind tunnel according to actual Requirement of the design of aero-engine. The surface of a gas turbine blade was cooled by cylindrical holes in the experiment,with the hole number of fifteen in stator and eight in rotor.
Above all, the surface of the gas turbine blade including stator and rotor heat transfer coeficience with no film cooling hole was studied with the main stream Reynolds number of 150000,200000 50000,300000,350000,400000. Then, the heat transfer coefficience when all cooling holes opened and only one cooling hole opened was studied partly. And it's studied how the mainstream Reynolds number, blowing ratio and the position of holes affect the heat transfer coefficience of the surface of blade. Results show that the influence of mainstream Reynolds numbers on heat transfer coefficience is little and the heat transfer coefficience raise with the increase of Reynolds numbers. The influence of the position of holes on heat transfer coefficience is complex and correlate with the mainstream speed and the balde surface curvature. And the influence of blowing ratio on heat transfer coefficience is more great (especially to stator) ,and show a complex relation to mainstream Reynolds number and the position of holes.
A simulation fomular was studied to accord the heat transfer experimental data.
引文
1. Wieghardt K. 1946, "Hot-Air Discharge for De-icing", AAF Translation,Report No.FTS-919-Re,pp. 1-44.
2. Goldstein,R.J.,et al, 1969, "Film Cooling Following Injection Through Inclined Circular Tubes," NASA Rep. CR-73612.
3. Eriksen,V.L., 1971, "Filming Cooling Effectiveness and Heat Transfer With Injection Through Holes," NASA Rep.CR-72991.
4. Mayle, R. E., and Camarata, F.J., 1975, "Mutihole Cooling Film Effectiveness and Heat Transfer," ASME journal of heat transfer,Vol.97,PP.534-538
5. Petersen, D.R., Eckert, E.R.G., and Goldstein, R.J., 1977 "Filming Cooling With Large Density Differences Between the mainstream and Secondary Fluid Measured by Heat-Mass Transfer Analogy," ASME journal of Heat Transfer,Vol.99,pp,620-627.
6. Foster, N.W., and Lampard, D., 1980, "The Flow Film Cooling Effectiveness Following Injection Through a Row of Holes," ASME journal of Engineering for power, Vol. 102,pp.584-588.
7. Forth,C.J.P., and Jones, T.V., 1985 "The effect of Density Ratio on the Film Cooling of a Flat Plate," AGARD-CP-390,Paper No. 10.
8. Forth,C.J.P., and Jones, T.V., 1986 "Scaling Parameters in Film Cooling," Proc. 8th International Heat Transfer Conference,Vol.3,pp. 1271-1276.
9. Sinha, A.K., Bogard, D.G., and Crawford, M.E., 1991 "Film-Cooling Effectiveness Downstreams of a Single Row of Holes With Variable Density Ratio," ASME Journal of Turbomachinery, Vol. 113,pp.441-449.
10. Goldstein, R.J., 1971, "Film Cooling", Advances in Heat Transfer, Vol.7, pp.321-379, Academic Press, New York and London.
11. Foster, N.W., and Lampard, D., 1975, "Effects of Density. and Velocity Ratio on Discrete Hole Film Cooling," AIAA J, Vol. 13, pp. 1112-1114.
12. Andrews, G.E., Asere, A.A., Gupta, M.L., Mkpadi, M.C., 1985, "Full Coverage Discrete Hole Film Cooling: The Influence of Hole Size," ASME Pager No.85-GT-47.
13. Taylor, A.M.K.P., and WhiteLaw, J.H., 1978, "Effectiveness of Leading-Edge Cooling Arrangements," 6th Int. Heat Transfer Conf., Toronto.
14. U.Drost,and A.Bolcs 1999,"Investigation of Detailed Film Colling Effectiveness and Heat transfer Distibutions on a Gas turbine Airfoil",Journal of Turbomachinery, april 1999,vol121/233-242.
15. Crawford, M.E., Kays, W.M., and Moffat, R.J., 1980, "Full-Coverage Film Cooling-Part Ⅰ: Comparison of Heat Transfer Data for Three Injection Angles," ASME Journal of Engineering for power, Vol. 102, pp, 1000-1005.
16. Kim, H. K., Moffat, R.J., and Keys, W. M., 1979,"Heat Transfer to a Full-Coverage,Film-Cooled Surface With Compound-Angle(30°×45°)Hole Injection," NASA Rep.CR-3103.
17. Ammari, H.D., Hay, N., and Lampard, D., 1989, "Simulation of Cooling Film Density Ratios in a Mass Transfer Tecnique," ASME Paper No.89-GT-200.
18. Bazdidi-Tehrani, F., Andrews, G.E., 1994, "Full-Coverage Discrete Hole Film Cooling: Investigation of the Effect of Variable Density Ratio," ASME Journal of
Cooling: Investigation of the Effect of Variable Density Ratio," ASME Journal of engineering for Gas Turbines and Power, Vol, 116, pp.587-596.
19. Ammari, H.D., Hay, N., and Lampard, D., 1990, "The Effect of Density Ratio on Heat Transfer Coefficient From a Film-Cooled Flat Plate," ASME Journal of Turbomachinery, Vol. 112, pp.444-450.
20. H. Du, J. C. Han and S. V. Ekkad, 1998, "Effect of University Wake on Detailed Heat Transfer Coefficienct and Film Effectiveness Distributions for a Gas Turbine Blade", ASME Journal of Turbomachinery, Vol. 120,pp.808-816.
21. Kadotani, K., and Goldstein, R.J., 1978, "Effect of Mainstream Variable on Jets Issuing from a Row of Inclined Round Holes," ASME Paper No.78-GT-138.
22. Brown, A., and Saluja, C.L., 1979, "Film Cooling from Three Rows of Holes on Adiabatic, Constant Heat Flux and Isothermal Surface in the Presence of Variable Velocity Cradients and Turbulent Intensity," ASME Paper No.79-GT-24.
23. Simonich, J.C., and Bradshaw, P., 1978, "Effect of Free-Stream Turbulence on Heat Transfer Through a Turbulent Boundary Layer," ASME Journal of Heat Transfer, Vol. 100, pp.671-677.
24. Hancock, P.E., and Bradshaw, P., 1983, "the Effect of Free-Stream Turbulence on Turbulent Boundary Layer," ASME Journal of Fluids Engineering, Vol.105, pp.284-289.
25. Blair, M.F., 1983, "Influence of Free-Stream Turbulence on Turbulent Boundary Layer Heat Transfer Mean Profile Development, Part Ⅰ—Experimental Data," ASME Journal of Heat Transfer, Vol. 105, pp,33-40.
26. Blair, M.F., 1983, "Influence of Free-Stream Turbulence on Turbulent Boundary Layer Heat Transfer Mean Profile Development, Part Ⅱ—Analysis of Results," ASME Journal of Heat Transfer, Vol. 105, pp.41-47.
27. Bonnice, M.A., and l'Ecuyer, 1983, "Stagnation Region Gas Film Cooling—Effect of Dimensinless Coolent Temperature," NASA Rep. CR-168197.
28. O'Brien, J.E., and VanFossen, G.J., 1985, "The Influence of Jet-Grid Turbulence on Heat Transfer from the Stagnation Region of a Cylinder in Crossflow," ASME Paper No.85-HT-58.
29. Mick, W.J., and Mayle, R.E., 1988, "Stagnation Film Cooling and Heat Transfer, Including its Effect With the Hole Pattern," ASME Journal of Turbomachinery, Vol. 110, pp.66-72.
30. MacMullin, R., Elrod, W., river, R., 1988, "Free-Stream Turbulence From a Circular Wall Jet on a Flat Plate Heat Transfer and Boundary Layer Flow," ASME Paper No.88-GT-183.
31. Mehendale, A.B., Han, J.C., 1992, "Influence of High Mainstream Turbulence on Leading Edge Film Cooling Heat Transfer," ASME Journal of Turbomachinery, Vol.114, pp.707-715.
32. Kruse, H., 1985, "Effect of Hole Geometry, Wall Curvature and Pressure Gradient on Film Cooling Downstream of a Single Row," AGARD-CP-390, Paper No.8.
33. Ammari, H.D., Hay, N., Lampard, D., 1991, "Effect of Acceleration on the Heat Transfer Coefficient on a Film-Cooled Surface," ASME Journal of Turbomachinery, Vol. 113, pp. 442-449.
34. Hay, N., Lampard, D., and Saluja, C.L., 1984, "Effects of the Condition of the Approach Boundary layer and of Mainstream Pressure Gradients on the Heat
Transfer Coefficient on Film-Cooled Surface," ASME Journal of Engineering for Power, Vol. 107, pp. 99-104.
35．恽起麟，1996，《风洞实验数据的误差与修正》，国防工业出版社
36．吴永生、方可人，1981年，《热工测量及仪表》，水利电力出版社
37．杨世铭、陶文铨，1999年《传热学》第三版，高等教育出版社。
38．封建湖、车刚明，2001，《数值分析原理》
39．张子慧，1994年，《热工测量与自动控制》，西北工业大学出版社
40．周雪琴、安锦文，1995年，《计算机测控系统》，西北工业大学出版社。
41. Han, J. C., 1994, "Unsteady Wake Effect on Film Effectiveness and Heat Transfer Coefficient From a Turbine Blade With One Row of Air and C02 Film Injection," ASME Journal of Heat Transfer, Vol. 116, 921-928.
42．葛绍岩、刘登赢、许靖中、李静，1985年，《气膜冷却》，北京：科学出版社。
43．朱惠人、许都纯，气膜孔形状对空排下游换热的影响，航空动力学报．2001．016(004)．-360-364
2. Goldstein,R.J.,et al, 1969, "Film Cooling Following Injection Through Inclined Circular Tubes," NASA Rep. CR-73612.
3. Eriksen,V.L., 1971, "Filming Cooling Effectiveness and Heat Transfer With Injection Through Holes," NASA Rep.CR-72991.
4. Mayle, R. E., and Camarata, F.J., 1975, "Mutihole Cooling Film Effectiveness and Heat Transfer," ASME journal of heat transfer,Vol.97,PP.534-538
5. Petersen, D.R., Eckert, E.R.G., and Goldstein, R.J., 1977 "Filming Cooling With Large Density Differences Between the mainstream and Secondary Fluid Measured by Heat-Mass Transfer Analogy," ASME journal of Heat Transfer,Vol.99,pp,620-627.
6. Foster, N.W., and Lampard, D., 1980, "The Flow Film Cooling Effectiveness Following Injection Through a Row of Holes," ASME journal of Engineering for power, Vol. 102,pp.584-588.
7. Forth,C.J.P., and Jones, T.V., 1985 "The effect of Density Ratio on the Film Cooling of a Flat Plate," AGARD-CP-390,Paper No. 10.
8. Forth,C.J.P., and Jones, T.V., 1986 "Scaling Parameters in Film Cooling," Proc. 8th International Heat Transfer Conference,Vol.3,pp. 1271-1276.
9. Sinha, A.K., Bogard, D.G., and Crawford, M.E., 1991 "Film-Cooling Effectiveness Downstreams of a Single Row of Holes With Variable Density Ratio," ASME Journal of Turbomachinery, Vol. 113,pp.441-449.
10. Goldstein, R.J., 1971, "Film Cooling", Advances in Heat Transfer, Vol.7, pp.321-379, Academic Press, New York and London.
11. Foster, N.W., and Lampard, D., 1975, "Effects of Density. and Velocity Ratio on Discrete Hole Film Cooling," AIAA J, Vol. 13, pp. 1112-1114.
12. Andrews, G.E., Asere, A.A., Gupta, M.L., Mkpadi, M.C., 1985, "Full Coverage Discrete Hole Film Cooling: The Influence of Hole Size," ASME Pager No.85-GT-47.
13. Taylor, A.M.K.P., and WhiteLaw, J.H., 1978, "Effectiveness of Leading-Edge Cooling Arrangements," 6th Int. Heat Transfer Conf., Toronto.
14. U.Drost,and A.Bolcs 1999,"Investigation of Detailed Film Colling Effectiveness and Heat transfer Distibutions on a Gas turbine Airfoil",Journal of Turbomachinery, april 1999,vol121/233-242.
15. Crawford, M.E., Kays, W.M., and Moffat, R.J., 1980, "Full-Coverage Film Cooling-Part Ⅰ: Comparison of Heat Transfer Data for Three Injection Angles," ASME Journal of Engineering for power, Vol. 102, pp, 1000-1005.
16. Kim, H. K., Moffat, R.J., and Keys, W. M., 1979,"Heat Transfer to a Full-Coverage,Film-Cooled Surface With Compound-Angle(30°×45°)Hole Injection," NASA Rep.CR-3103.
17. Ammari, H.D., Hay, N., and Lampard, D., 1989, "Simulation of Cooling Film Density Ratios in a Mass Transfer Tecnique," ASME Paper No.89-GT-200.
18. Bazdidi-Tehrani, F., Andrews, G.E., 1994, "Full-Coverage Discrete Hole Film Cooling: Investigation of the Effect of Variable Density Ratio," ASME Journal of
Cooling: Investigation of the Effect of Variable Density Ratio," ASME Journal of engineering for Gas Turbines and Power, Vol, 116, pp.587-596.
19. Ammari, H.D., Hay, N., and Lampard, D., 1990, "The Effect of Density Ratio on Heat Transfer Coefficient From a Film-Cooled Flat Plate," ASME Journal of Turbomachinery, Vol. 112, pp.444-450.
20. H. Du, J. C. Han and S. V. Ekkad, 1998, "Effect of University Wake on Detailed Heat Transfer Coefficienct and Film Effectiveness Distributions for a Gas Turbine Blade", ASME Journal of Turbomachinery, Vol. 120,pp.808-816.
21. Kadotani, K., and Goldstein, R.J., 1978, "Effect of Mainstream Variable on Jets Issuing from a Row of Inclined Round Holes," ASME Paper No.78-GT-138.
22. Brown, A., and Saluja, C.L., 1979, "Film Cooling from Three Rows of Holes on Adiabatic, Constant Heat Flux and Isothermal Surface in the Presence of Variable Velocity Cradients and Turbulent Intensity," ASME Paper No.79-GT-24.
23. Simonich, J.C., and Bradshaw, P., 1978, "Effect of Free-Stream Turbulence on Heat Transfer Through a Turbulent Boundary Layer," ASME Journal of Heat Transfer, Vol. 100, pp.671-677.
24. Hancock, P.E., and Bradshaw, P., 1983, "the Effect of Free-Stream Turbulence on Turbulent Boundary Layer," ASME Journal of Fluids Engineering, Vol.105, pp.284-289.
25. Blair, M.F., 1983, "Influence of Free-Stream Turbulence on Turbulent Boundary Layer Heat Transfer Mean Profile Development, Part Ⅰ—Experimental Data," ASME Journal of Heat Transfer, Vol. 105, pp,33-40.
26. Blair, M.F., 1983, "Influence of Free-Stream Turbulence on Turbulent Boundary Layer Heat Transfer Mean Profile Development, Part Ⅱ—Analysis of Results," ASME Journal of Heat Transfer, Vol. 105, pp.41-47.
27. Bonnice, M.A., and l'Ecuyer, 1983, "Stagnation Region Gas Film Cooling—Effect of Dimensinless Coolent Temperature," NASA Rep. CR-168197.
28. O'Brien, J.E., and VanFossen, G.J., 1985, "The Influence of Jet-Grid Turbulence on Heat Transfer from the Stagnation Region of a Cylinder in Crossflow," ASME Paper No.85-HT-58.
29. Mick, W.J., and Mayle, R.E., 1988, "Stagnation Film Cooling and Heat Transfer, Including its Effect With the Hole Pattern," ASME Journal of Turbomachinery, Vol. 110, pp.66-72.
30. MacMullin, R., Elrod, W., river, R., 1988, "Free-Stream Turbulence From a Circular Wall Jet on a Flat Plate Heat Transfer and Boundary Layer Flow," ASME Paper No.88-GT-183.
31. Mehendale, A.B., Han, J.C., 1992, "Influence of High Mainstream Turbulence on Leading Edge Film Cooling Heat Transfer," ASME Journal of Turbomachinery, Vol.114, pp.707-715.
32. Kruse, H., 1985, "Effect of Hole Geometry, Wall Curvature and Pressure Gradient on Film Cooling Downstream of a Single Row," AGARD-CP-390, Paper No.8.
33. Ammari, H.D., Hay, N., Lampard, D., 1991, "Effect of Acceleration on the Heat Transfer Coefficient on a Film-Cooled Surface," ASME Journal of Turbomachinery, Vol. 113, pp. 442-449.
34. Hay, N., Lampard, D., and Saluja, C.L., 1984, "Effects of the Condition of the Approach Boundary layer and of Mainstream Pressure Gradients on the Heat
Transfer Coefficient on Film-Cooled Surface," ASME Journal of Engineering for Power, Vol. 107, pp. 99-104.
35．恽起麟，1996，《风洞实验数据的误差与修正》，国防工业出版社
36．吴永生、方可人，1981年，《热工测量及仪表》，水利电力出版社
37．杨世铭、陶文铨，1999年《传热学》第三版，高等教育出版社。
38．封建湖、车刚明，2001，《数值分析原理》
39．张子慧，1994年，《热工测量与自动控制》，西北工业大学出版社
40．周雪琴、安锦文，1995年，《计算机测控系统》，西北工业大学出版社。
41. Han, J. C., 1994, "Unsteady Wake Effect on Film Effectiveness and Heat Transfer Coefficient From a Turbine Blade With One Row of Air and C02 Film Injection," ASME Journal of Heat Transfer, Vol. 116, 921-928.
42．葛绍岩、刘登赢、许靖中、李静，1985年，《气膜冷却》，北京：科学出版社。
43．朱惠人、许都纯，气膜孔形状对空排下游换热的影响，航空动力学报．2001．016(004)．-360-364
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