بررسی تجربی تأثیر یک روزنه نوین جت نخودی بر عملکرد حرارتی جت های تزریق‌شده در یک جریان عرضی

نویسندگان

1 مرکز تحصیلات تکمیلی، دانشکاه هوایی شهید ستاری

2 دانشکده مهندسی هوافضا، دانشگاه علوم و فنون هوایی شهید ستاری

چکیده

در خنک­کاری لایه­ای، هوای خنک­کننده از طریق جت­هایی روی سطح تزریق می­شود تا لایه­ای محافظ در برابر گازهای دما بالا  فراهم شود. عملکرد خنک­کاری لایه­ای تا حد زیادی تحت تأثیر شکل روزنه جت­ها قرار دارد. و لذا بهینه­سازی و اصلاح شکل هندسی روزنه جت برای      دست­یابی به عملکرد خنک­کاری بهتر ضروری است. در این پژوهش، عملکرد خنک­کاری لایه­ای هندسه جدید جت­های استوانه­ای ناقص (نخودی) به­صورت تجربی با استفاده از روش دما نگاری مادون­قرمز بررسی شده است. آزمایش­ها در حالت انتقال حرارت پایا در عدد رینولدز جریان اصلی براساس قطر معادل جت (Rejet) 10,000 روی صفحه تخت انجام شده است. اندازه­گیری­ها در چهار نسبت­ دمش (M=ρjetVjet/ρ∞V∞) مختلف 4/0، 5/0، 7/0 و 8/0 انجام شده­اند. نتایج حاصل نشان می­دهد که هندسه­ پیشنهادی دارای نسبت دمش بهینه 7/0 در زاویه تزریق جت 30 درجه است و در نسبت دمش یکسان، اثربخشی خنک­کاری لایه­ای هندسه جدید بیش­تر است. به­عبارت دیگر، با استفاده از همان مقدار نرخ جریان جرمی تزریق­شده، توزیع یکنواخت­تری از لایه سیال خنک­کننده حاصل می­شود.

کلیدواژه‌ها


عنوان مقاله [English]

Experimental Investigation of the Effect of a Novel Pea Jet Hole on Thermal Behavior of Jets Injected into a Crossflow

نویسندگان [English]

  • younes poladrang 1
  • mahdi ramezani zade 2
1 satari
2 satari
چکیده [English]

In film cooling, coolant air is injected over the surface to provide a protective cool  film against the high temperature gases. Film-cooling performance is largely influenced by the jet hole shape. And thus optimizing the hole shape configuration is necessary to achieve better cooling performance. The present study investigated the cooling effectiveness of the novel incomplete cylindrical jet hole (pea jet hole) experimentally, using an infrared thermography method. Steady state heat transfer experiments were performed at free stream Reynolds number, based on jet hole diameter of 10,000, over a flat plate. Measurements were carried out at four blowing ratios (M=ρjetVjetV) of 0.4, 0.5, 0.7, and 0.8. Out results show that the novel pea jet hole has an optimum blowing ratio of 0.7 and at the same blowing ratio, in comparison to the cylindrical jet hole, the cooling effectiveness of the new geometry is higher. Another words applying the same amount of injected fluid, the coolout fluid is distributed more uniformly over the surface.

کلیدواژه‌ها [English]

  • Film Cooling Effectiveness
  • Novel Jet Hole Geometry
  • Pea Jet Hole
  • Experimental Test
  • Wind Tunnel
Bazdidi-Tehrani, M.J.F. and Mousavi, S.M.
“Investigation of Film Cooling on Model Turbine
Blade Leading Edge Using DES and LES
Approaches”, Modarres Mech. Eng., Vol. 15, No.
8, pp. 260-270, 2015.

2. An, B., Liu, J., Zhou, S., Zhang, X., and Zhang, C.
Film Cooling Investigation of a Slot-Based
Diffusion Hole, ASME Turbo Expo 2016:
Turbomachinery Technical Conference and
Exposition, Vol. 5C, p. V05CT19A005, 2016.

3. Goldstein, R.B.R.J. and Eckert, E.G. “Effects of
Hole Geometry and Denstty on Three-dimensional
Film Cooling, Int. J. Heat Mass Trans., Vol. 17,
No. 5, pp. 595-607, 1974.

4. Andreopoulos, J. and Rodi, W. “Experimental
Investigation of Jets into a Crossflow, J. Fluid
Mech., Vol. 138, No. 1, pp. 93-127, 1984.

5. Gritsch, S., Schulz, M., and Wittig, A. “Adiabatic
Wall Effectiveness Measurements of Film-Cooling
Holes with Expanded Exits”, ASME J.
Turbomach., Vol. 3, No. 120, pp. 549-556, 1998.

6. Saumweber, C., Schulz, A., and Wittig, S.
“FreeStream Turbulence Effects on Film Cooling
with Shaped Holes”, ASME J. Turbomach, Vol.
125, No. 1, pp. 65-73, 2003.

7. Saumweber, C. and Schulz, A. “Effect of Geometry
Variations on the Cooling Performance of Fan-
Shaped Cooling Holes, ASME Turbo Expo., Vol.
134, No.6 , pp. 1-16, 2012.

8. Burd, S.W., Kaszeta, R.W., and Simon, T.W.
“Measurements in Film Cooling Flows: Hole LID
and Turbulence Intensity Effects, ASME J.
Turbomach., Vol. 120, No.4, pp. 791798, 1998.

9. Yuen, C.H.N. and Martinex-Botas, R.F. “Film
Cooling Characteristics of a Single Round Hole at
Various Streamwise Angles in a Crossflow: Part I
Effectiveness, J. Heat Mass Trans., Vol. 46, pp.
221-235, 2003.

10. Bernsdorf, M., Rose, G., and R.S. Abhari,
“Modeling of Film Cooling – Part 1: Experimental
Study of Flow Structure, ASME Turbo Expo.,
Vol. 128, No.1, pp. 141149, 2005.
Bunker, R.S. “A Review of Shaped Hole Turbine
Film- Cooling Technology, J. Heat Trans., Vol.
127, No.4, pp. 441453, 2005.

12. Asghar, F.H. and Hyder, M.J. “Computational
Study of Film Cooling from Single and Two
Staggered Rows of Novel Semi-Circular Cooling
Holes Including Coolant Plenum, Energy Conv.
Manag., Vol. 52, No.1, pp. 329-334, 2011.

13. Dai, P. and Lin, F. “Numerical Study on Film
Cooling Effectiveness from Shaped and Crescent
Holes, Heat Math Transf., Vol. 47, No.2, pp. 147-
154, 2011.

14. Islami, S.B., Tabrizi, S.P.A., Jubran, B.A., and
Esmaeilzadeh, E. “Influence of Trenched Shaped
Holes on Turbine Blade Leading Edge Film
Cooling, Heat Transf. Eng., Vol. 31, No.10, pp.
889-906, 2011.

15. Montomoli, F., Ammaro, A.D., and Uchida, S.
“Numerical and Experimental Investigation of a
New Film Cooling Geometry with High P/D
Ratio, Int. J. Heat Mass Trans., Vol. 66, No. 11,
pp. 366-375, 2013.

16. Yusop, N.M., Ali, A.H., and Abdullah, M.Z.
“Computational Study of a New Scheme for A Fi
lm-Cooling Hole on Convex Surface of Turbine
Blades,” Int. Commun. Heat Mass Trans., Vol. 43,
No. 4, pp. 90-99, 2013.

17. Salimi, M.R., Ramezanizadeh, M., and Taeibi-
Rahni, M., and Farhadi-Azar, R. “Film Cooling
Effectiveness Enhancement Applying another Jet in
the Upstream Neighbor of the Main Jet,Using LES
Approach, J. Appl. Fluid Mech., Vol. 9, No. 1, pp.
33-42, 2016.

18. Baheri Islami, S. and Jubran, B.A. “The Effect of
Turbulence Intensity on Film Cooling of Gas
Turbine Blade from Trenched Shaped Holes, Heat
Math Trans., Vol. 48, No. 5, pp. 831840, 2012.

19. Liu, C., Zhu, H., Zhang, Z., and Xu, D.,
“Experimental Investigation on the Leading Edge
Film Cooling of Cylindrical and Laid-Back Holes
with Different Hole Pitches, Int. J. Heat Mass
Trans., Vol. 55, No.23-24 , pp. 68326845, 2012.

20. York, W. D. and Leylek, J. H. “Leading-Edge
Film-Cooling PhysicsPart III: Diffused Hole
Effectiveness, ASME, Vol. 125, No. 2, pp. 252
259, 2003.

21. Wang, T. and Li, X. “Mist Film Cooling Simulation
at Gas Turbine Operating Conditions, Int. J. Heat
Mass Trans., Vol. 51, pp. 53055317, No. 21-22,
2008.

22. Baheri, S., AlaviTabrizi, S.P., and Jubran, B.A.
“Film Cooling Effectiveness from Trenched
Shaped and Compound Holes, Heat Mass Trans.,
Vol. 44, No. 8, pp. 989-998, 2008.

23. Elnady, T., Hassan, I., Kadem, L., and Lucas, T.
“Cooling Effectiveness of Shaped Film Holes for
Leading Edge, Exp. Therm. Fluid Sci., Vol. 44,
No. 1, pp. 649-661, 2013.

24. Liu, C., Zhu, H., Zhang, X., Xu, D., and Zhang, Z.
“Experimental Investigation on the Leading Edge
Film Cooling of Cylindrical and Laid-Back Holes
with Different Radial Angles , Heat Mass Transf.,
Vol. 71, No. 4, pp. 615625, 2014.

25. Lee, K., Choi, D., and Kim, K., “Optimization of
Ejection Angles of Double-Jet Film-Cooling Holes
Using RBNN Model, Int. J. Therm. Sci., Vol. 73,
No. 11, pp. 69-78, 2013.

26. Moon, Y., Park, S.S., Park, J.S., and Kwak, J.S.
“Effect of Angle Between the Primary and
Auxiliary Holes of an Anti-Vortex Film Cooling
Hole”, Asia-Pacific Int. Symp. Aerosp. Technol.
APISAT2014, Vol. 99, pp. 1492-1496, 2015.

27. Farhadi-Azar, R., Ramezanizadeh, M., Taeibi-
Rahni, M., and Salimi, M. “Compound Triple Jets
Film Cooling Improvements via Velocity and
Density Ratios: Large Eddy Simulation, J. Fluids
Eng., Vol. 133, No. 3, p. 31202, 2011.

28. Ramesh, S., Gomez, D., Ekkad, S.V., and Anne, M.
“Analysis of Film Cooling Performance of
Advanced Tripod Hole Geometries with and
without Manufacturing Features, Int. J. Heat Mass
Trans., Vol. 94, No. 3, pp. 9-19, 2016.

29. Chen, S.P., Chyu, M.K., and Shih, T.I. “Effects of
Upstream Ramp on the Performance of Film
Cooling, Int. J. Therm. Sci., Vol. 50, No. 6, pp.
1085-1094, 2011.

30. Rigby, L.D. and Heidmann, J.D. “Improved Film
Cooling Effectiveness by Placing a Vortex
Generator Downstream of Each Hole ASME
Turbo Expo 2008: Power for Land, Sea, and Air,
Vol. 4, pp. 1161-1174, 2008.

31. An, B.T., Liu, J.J., Zhang, C., and Zhou, S.J. “Film
Cooling of Cylindrical Hole with a Downstream
Short Crescent-Shaped Block, J. Heat Trans., Vol.
135, No. 3, p. 31702, 2013.

32. Ramezanizadeh, M. and Pouladrang, Y.
“Experimental Investigation of Film Cooling
Effectiveness Applying a Novel Integrated
Compound Jets Design for the Jet Holes, Modares
Mech. Eng., Vol. 18, No. 3, pp. 302-310, 2018.

33. Pouladrang, Y. “Experimental Study of the Effects
of Jet Hole Geometry on the Film Cooling
Effectiveness in Gas Turbines, MSc Thesis,
Graduate Center, Shahid Sattari Aeronautical
University of Science & Technology, 2017.

34. Moffat, R.J. “Describing the Uncertainties in
Experimental Results, Exp. Therm. Fluid Sci.,
Vol. 1, No. 1, pp. 3-17, 1988.
35.Dhungel, A., Lu, Y., Phillips, W., Srinath, E., and
James, H. “Film Cooling from a Row of Holes
Supplemented with Antivortex Holes, J.
Turbomach., Vol. 131, No. 2, p. 21007, 2009.

36. Lawson, S.A., and Thole, K.A. “Effects of
Simulated Particle Deposition on Film Cooling,
ASME, Vol. 133, No. 2, p. 21009, 2011.

37. Kunze, M., Preibisch, S., and Landis, K. “A New
Test Rig for Film Cooling Experiments on Turbine
Endwalls, Proc. ASME Turbo Expo., Vol. 4, pp.
989-998, 2008.
Johnson, B., Tian, W., Zhang, K., and Hu, H. “An
Experimental Study of Density Ratio Effects on the
Film Cooling Injection from Discrete Holes by
Using PIV and PSP Techniques, Int. J. Heat Mass
Trans., Vol. 76, No. 9, pp. 337349, 2014.

39. Sinha, A. K., Bogard, D. G., and Crawford, M. E.
“Film-Cooling Effectiveness Downstream of a
Single Row of Holes with Variable Density Ratio,
J. Turbomach., Vol. 113, No. 3, pp. 442449, 1991.

40. Rallabandi, A.P., Grizzle, J., and Han, J. “Effect of
Upstream Step on Flat Plate Film-Cooling
Effectiveness Using PSP, J. ASME Turbomach.,
Vol. 133, No. 4, p. 041024, 2011.