The Combined Effects of Surface Roughness with Upstream Wakes on the Boundary Layer Development of an Ultra-High-Lift LPT Blade
-
Sun Shuang
,
Lei Zhijun
Abstract
The combined effects of upstream wakes and surface roughness on boundary layer development have been investigated experimentally to improve the performance of ultra-high-lift low-pressure turbine (LPT) blades. The measurement was performed on a linear cascade with an ultra-high-lift LP turbine profile named IET-LPTA with a Zweifel loading coefficient of about 1.4. The wakes were simulated by the moving cylindrical bars upstream of the cascade. The surface roughness was achieved using sandpaper strips which were placed into the slot incised on the blades surfaces. Three types of slots combined with three types of roughness heights formed a large measurement matrix. The roughness with a height of 8.82 μm (1.05×10−4 chord length) covering 5.2 % suction surface reduced the profile loss in the whole tested Reynolds number range. The details of the boundary layer were measured with a boundary hot-wire probe. It was found that both the wake-induced transition and the nature transition between wakes were hastened due to the K-H instability expanded by the roughness of the S3-R3 surface. The nature transition process was more sensitive to surface roughness than the wake-induced transition.
Funding statement: Funding: This work was sponsored by the Natural Science Fund of China (51206163, 51306176), Tianjin Municipal Natural Science Foundation (Youth Program 14JCQNJC06800) and Chinese Universities Scientific Fund (3122015C006, ZXH2012H004).
Nomenclature
- AVR
axial velocity ratio
- C
true Chord
- Cx
axial chord
- Cp
pressure coefficient
- FSTI
free stream turbulence intensity
- H12
shape factor
- fr
reduced frequency
- K-H
Kelvin-Helmholtz
- Pt
total pressure
- Ps
static pressure
- Ra
centerline average roughness (designated also as CLA)
- Re
Reynolds number
- s
streamwise location
- SFC
specific fuel consumption
- SSL
suction surface length
- u
local velocity
- ux
axial velocity
- ubar
bar velocity at midspan
- u′
velocity disturbance
- T-S
Tollmien-Schichting
- Y
profile loss
kinematic viscosity
- θ
momentum thickness
- t*
time/periodicity
- Ф
flow coefficient
- Subscripts
- in
inlet
- out
Outlet
References
1. Hodson HP, Howell RJ. The role of transition in high-lift low-pressure turbines for aero-engines. Prog Aerosp Sci 2005;41:419–54.10.1016/j.paerosci.2005.08.001Suche in Google Scholar
2. Bons JP, Pluim J, Gompertz K, Bloxham M, Clark JP. The application of flow control to an aft-loaded low pressure turbine cascade with unsteady wakes. ASME J Turbomach 2011;134:031009–031009–11.10.1115/GT2008-50864Suche in Google Scholar
3. Curtis EM, Hodson HP, Banieghbal MR, Howell RJ, Harvey NW. Development of blade profiles for low-pressure turbine applications. ASME J Turbomach 1997;119:531–8.10.1115/96-GT-358Suche in Google Scholar
4. Hourmouziadis J. Aerodynamic design of low pressure turbines, AGARD Lecture Series “Blading Design for Axial Turbomachines”, No.167, 1989Suche in Google Scholar
5. Mahallati A, Sjolander SA. Aerodynamics of a low-pressure turbine airfoil at low Reynolds numbers—Part II: Blade-Wake interaction. ASME J Turbomach 2012;135:011011–011011–10.10.1115/1.4006320Suche in Google Scholar
6. Zhang XF, Vera M, Hodson HP, Harvey N. Separation and transition control on an aft-loaded ultra-high-lift LP turbine blade at low Reynolds numbers: low-speed investigation. ASME J Turbomach 2005;128:517–27.10.1115/GT2005-68892Suche in Google Scholar
7. Volino RJ. Separation control on low-pressure turbine airfoils using synthetic vortex generator jets, ASME J. Turbomach 2003;125:765–77.10.1115/1.1626686Suche in Google Scholar
8. Volino RJ, Kartuzova O, Ibrahim MB. Separation control on a very high lift low pressure turbine airfoil using pulsed vortex generator jets. ASME J. Turbomach 2011;133:041021–041021–13.10.1115/GT2010-23567Suche in Google Scholar
9. Mack M, Niehui R, Boundary layer control on a low pressure turbine blade by means of pulsed blowing, Proceedings of ASME TURBO EXPO 2012, June 11–15, Copenhagen, Denmark, GT2012-69029, 2012Suche in Google Scholar
10. Huang J, Corke TC, Thomas FO. Plasma actuators for separation control of low pressure turbine blades. AIAA J 2006;44:51–7.10.2514/6.2003-1027Suche in Google Scholar
11. Lake JP, King PI, Rivir RB. Reduction of separation losses on a turbine blade with low Reynolds number, AIAA Paper No. 99-0242, 1999.10.2514/6.1999-242Suche in Google Scholar
12. Lake JP, King PI, Rivir RB. Low Reynolds number loss reduction on turbine blades with dimples and v-grooves, AIAA Paper No. 00-0738, 2000.10.2514/6.2000-738Suche in Google Scholar
13. Vera M, Zhang XF, Hodson H, Harvey N. Separation and transition control on an aft-loaded ultra-high-lift LP turbine blade at low Reynolds numbers: high-speed validation. ASME J Turbomach 2006;129:340–7.10.1115/GT2005-68893Suche in Google Scholar
14. Martinstetter M, Niehuis R. Passive boundary layer control on a highly loaded low pressure turbine cascade, Proceedings of ASME TURBO EXPO 2010, June 14–18, Glasgow, UK., GT2010-22739, 2010.10.1115/GT2010-22739Suche in Google Scholar
15. Boynton JL, Tabibzadeh R, Hudson ST. Investigation of rotor blade roughness effects on turbine performance. ASME J Turbomach 1993;115:614–20.10.1115/92-GT-297Suche in Google Scholar
16. Abuaf N, Bunker RS, Lee CP. Effects of surface roughness on heat transfer and aerodynamic performance of turbine airfoils. ASME J Turbomach 1998;120:522–9.10.1115/97-GT-010Suche in Google Scholar
17. Zhang Q, Goodro M, Ligrani PM, Trindade R, Sreekanth S. Influence of surface roughness on the aerodynamic losses of a turbine vane. ASME J Fluids Eng 2005;128:568–78.10.1115/GT2005-68832Suche in Google Scholar
18. Bons JP. A review of surface roughness effects in gas turbines. ASME J Turbomach 2010;132:021004–021004–16.10.1115/1.3066315Suche in Google Scholar
19. Flack KA, Schultz MP. Review of hydraulic roughness scales in the fully rough regime. ASME J Fluid Eng 2010;132:pp.041203–041203–10.10.1115/1.4001492Suche in Google Scholar
20. Im JH, Shin JH, Hobson GV, Song SJ, Millsaps KT. Effect of leading edge roughness and reynolds number on compressor profile loss, Proceedings of ASME TURBO EXPO 2013, June 3–7, San Antonio, Texas, USA, GT2013-95487, 2013.10.1115/GT2013-95487Suche in Google Scholar
21. Ramesh ON, Hodson HP, Harvey NW. Separation control in ultra high lift airfoils by unsteadiness and surface roughness, 15th International Symposium on Airbreathing Engines, September, Bangalore, India, 2001.Suche in Google Scholar
22. Roberts SK, Yaras MI. Effects of surface-roughness geometry on separation-bubble transition. ASME J Turbomach 2006;128:349–56.10.1115/GT2005-68664Suche in Google Scholar
23. Lorenz M, Schulz A, Bauer HJ. Experimental study of surface roughness effects on a turbine airfoil in a linear cascade—Part II: aerodynamic losses. ASME J Turbomach 2011;134:041007–041007–10.10.1115/GT2010-23801Suche in Google Scholar
24. Montomoli F, Hodson H, Haselbach F. Effect of roughness and unsteadiness on the performance of a new low pressure turbine blade at low Reynolds numbers. ASME J Turbomach 2010;132:031018–031018–9.10.1115/1.3148475Suche in Google Scholar
25. Montis M, Niehuis R, Fiala A, Aerodynamic measurements on a low pressure turbine cascade with different levels of distributed roughness, Proceedings of ASME TURBO EXPO 2011, June 6–10, Vancouver, British Columbia, Canada, GT2011-45015, 2011.10.1115/GT2011-45015Suche in Google Scholar
26. Zhang XF, Hodson HP. The combined effects of surface trips and unsteady wakes on the boundary layer development of an ultra-high-lift LP turbine blade. ASME J Turbomach 2005;127:479–88.10.1115/GT2004-53081Suche in Google Scholar
27. Wills JAB. The correction of hot-wire readings for proximity to a solid boundary. ASME J Fluid Mech 1962;12:65–92.10.1017/S0022112062000282Suche in Google Scholar
28. Walker GJ. Transitional flow on axial turbomachine blading. AIAA J 1989;27:595–602.10.2514/6.1987-10Suche in Google Scholar
29. Volino RJ. Separated flow transition under simulated low-pressure turbine airfoil conditions –Part 2: turbulence spectra. ASME J Turbomach 2002;124:656–64.10.1115/GT2002-30237Suche in Google Scholar
© 2017 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- Frontmatter
- Influence of Structural Parameters on the Performance of Vortex Valve Variable-Thrust Solid Rocket Motor
- Numerical Studies on the Performance of Scramjet Combustor with Alternating Wedge-Shaped Strut Injector
- Investigation of HP Turbine Blade Failure in a Military Turbofan Engine
- Nozzle Admittance and Damping Analysis Using the LEE Method
- Software Development for EECU Platform of Turbofan Engine
- Numerical Study of the Propulsive Performance of the Hollow Rotating Detonation Engine with a Laval Nozzle
- Analysis of Compressor Surge in a Military Turbojet Engine: A Case Study
- The Combined Effects of Surface Roughness with Upstream Wakes on the Boundary Layer Development of an Ultra-High-Lift LPT Blade
- Numerical Investigation of a Model Scramjet Combustor Using DDES
- Flow Field Measurement in Multi-stage Axial Compressor Stator by Using Multi-hole Pneumatic Probes
- Effect of Air Pressure and Gutter Angle on Flame Stability and DeZubay Number for Methane-Air Combustion
- Control of Subsonic and Sonic Jets with Limiting Tabs
Artikel in diesem Heft
- Frontmatter
- Influence of Structural Parameters on the Performance of Vortex Valve Variable-Thrust Solid Rocket Motor
- Numerical Studies on the Performance of Scramjet Combustor with Alternating Wedge-Shaped Strut Injector
- Investigation of HP Turbine Blade Failure in a Military Turbofan Engine
- Nozzle Admittance and Damping Analysis Using the LEE Method
- Software Development for EECU Platform of Turbofan Engine
- Numerical Study of the Propulsive Performance of the Hollow Rotating Detonation Engine with a Laval Nozzle
- Analysis of Compressor Surge in a Military Turbojet Engine: A Case Study
- The Combined Effects of Surface Roughness with Upstream Wakes on the Boundary Layer Development of an Ultra-High-Lift LPT Blade
- Numerical Investigation of a Model Scramjet Combustor Using DDES
- Flow Field Measurement in Multi-stage Axial Compressor Stator by Using Multi-hole Pneumatic Probes
- Effect of Air Pressure and Gutter Angle on Flame Stability and DeZubay Number for Methane-Air Combustion
- Control of Subsonic and Sonic Jets with Limiting Tabs
