Research Papers: Gas Turbines: Microturbines and Small Turbomachinery

Continuous Closed-Loop Transonic Linear Cascade for Aerothermal Performance Studies in Microturbomachinery

[+] Author and Article Information
Eli Yakirevich

Turbomachinery and Heat Transfer Laboratory,
Aerospace Engineering Department,
Technion—Israel Institute of Technology,
Technion City,
Haifa 3200003, Israel
e-mail: eliyakir@campus.technion.ac.il

Ron Miezner

Turbomachinery and Heat Transfer Laboratory,
Aerospace Engineering Department,
Technion—Israel Institute of Technology,
Technion City,
Haifa 3200003, Israel
e-mail: ronmi@technion.ac.il

Boris Leizeronok

Turbomachinery and Heat Transfer Laboratory,
Aerospace Engineering Department,
Technion—Israel Institute of Technology,
Technion City,
Haifa 3200003, Israel
e-mail: borisl@technion.ac.il

Beni Cukurel

Turbomachinery and Heat Transfer Laboratory,
Aerospace Engineering Department,
Technion—Israel Institute of Technology,
Technion City,
Haifa 3200003, Israel
e-mail: beni@cukurel.org

Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 3, 2017; final manuscript received July 4, 2017; published online September 19, 2017. Editor: David Wisler.

J. Eng. Gas Turbines Power 140(1), 012301 (Sep 19, 2017) (9 pages) Paper No: GTP-17-1265; doi: 10.1115/1.4037611 History: Received July 03, 2017; Revised July 04, 2017

The present work summarizes the design process of a new continuous closed-loop hot transonic linear cascade. The facility features fully modular design which is intended to serve as a test bench for axial microturbomachinery components in independently varying Mach and Reynolds numbers ranges of 0–1.3 and 2 × 104–6 × 105, respectively. Moreover, for preserving heat transfer characteristics of the hot gas section, the gas to solid temperature ratio (up to 2) is retained. This operational environment has not been sufficiently addressed in prior art, although it is critical for the future development of ultra-efficient high power or thrust devices. In order to alleviate the dimension specific challenges associated with microturbomachinery, the facility is designed in a highly versatile manner and can easily accommodate different geometric configurations (pitch, ±20 deg stagger angle, and ±20 deg incidence angle), absence of any alterations to the test section. Owing to the quick swap design, the vane geometry can be easily replaced without manufacturing or re-assembly of other components. Flow periodicity is achieved by the inlet boundary layer suction and independently adjustable tailboard mechanisms. Enabling test-aided design capability for microgas turbine manufacturers, aerothermal performance of various advanced geometries can be assessed in engine relevant environments.

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Jouini, D. , Sjolander, S. , and Moustapha, S. , 2000, “ Aerodynamic Performance of a Transonic Turbine Cascade at Off-Design Conditions,” ASME Paper No. 2000-GT-0482.
Vogel, G. , 2002, “ Experimental Study on a Heavy Film Cooled Nozzle Guide Vane With Contoured Platforms,” Ph.D. thesis, Ecole Polytechnique Federale de Lausanne (EPFL), Lausanne, Switzerland. https://infoscience.epfl.ch/record/103717
Schreiber, H.-A. , Steinert, W. , and Küsters, B. , 2000, “ Effects of Reynolds Number and Free-Stream Turbulence on Boundary Layer Transition in a Compressor Cascade,” ASME Paper No. 2000-GT-0263.
Detemple-Laake, E. , 1991, “ Detailed Measurements of the Flow Field in a Transonic Turbine Cascade,” ASME Paper No. 91-GT-029.
Giel, P. W. , Boyle, R. J. , and Bunker, R. S. , 2003, “ Measurements and Predictions of Heat Transfer on Rotor Blades in a Transonic Turbine Cascade,” ASME Paper No. GT2003-38839.
Liu, C. , Zhu, H. R. , Fu, Z. Y. , and Xu, R. H. , 2015, “ The Effects of Inlet Reynolds Number, Exit Mach Number and Incidence Angle on Leading Edge Film Cooling Effectiveness of a Turbine Blade in a Linear Transonic Cascade,” ASME Paper No. GT2015-42888.
Woodason, R. , Asghar, A. , and Allan, W. , 2009, “ Assessment of the Flow Quality of a Transonic Turbine Cascade,” ASME Paper No. GT2009-60164.
Mack, M. , Niehuis, R. , Fiala, A. , and Guendogdu, Y. , 2013, “ Boundary Layer Control on a Low Pressure Turbine Blade by Means of Pulsed Blowing,” ASME J. Turbomach., 135(5), p. 051023. [CrossRef]
Mihelish, M. , and Ames, F. , 2013, “ The Development of a Closed Loop High Speed Cascade Wind Tunnel for Aerodynamic and Heat Transfer Testing at Moderate to Low Reynolds Numbers,” ASME Paper No. GT2013-95048.
Povey, T. , Oldfield, M. , and Haselbach, F. , 2008, “ Transonic Turbine Vane Tests in a New Miniature Cascade Facility,” Proc. Inst. Mech. Eng., Part A, 222(5), pp. 529–539. [CrossRef]
Carullo, J. , Nasir, S. , Cress, R. D. , Ng, W. F. , Thole, K. A. , Zhang, L. J. , and Moon, H. K. , 2011, “ The Effects of Freestream Turbulence, Turbulence Length Scale, and Exit Reynolds Number on Turbine Blade Heat Transfer in a Transonic Cascade,” ASME J. Turbomach., 133(1), p. 011030. [CrossRef]
Paniagua, G. , Sieverding, C. , and Arts, T. , 2013, “ Review of the Von Karman Institute Compression Tube Facility for Turbine Research,” ASME Paper No. GT2013-95984.
Dixon, S. L. , and Hall, C. , 2013, Fluid Mechanics and Thermodynamics of Turbomachinery, Butterworth-Heinemann, Oxford, UK.
Hirsch, C. , 1993, “ Advanced Methods for Cascade Testing,” Specialised Printing Services Limited, Loughton, UK, No. AGARD-AG-328.
White, F. M. , and Corfield, I. , 2006, Viscous Fluid Flow, Vol. 3, McGraw-Hill, New York.
Kenneth, E. , and Nichols, P. , 2012, “ How to Select Turbomachinery for Your Application,” Barber-Nichols Inc., Arvada, CO, pp. 5–6. http://www.barber-nichols.com/sites/default/files/wysiwyg/images/how_to_select_turbomachinery_for_your_application.pdf
Brassard, D. , and Ferchichi, M. , 2005, “ Transformation of a Polynomial for a Contraction Wall Profile,” ASME J. Fluids Eng., 127(1), pp. 183–185. [CrossRef]
Bell, J. H. , and Mehta, R. D. , 1988, “ Contraction Design for Small Low-Speed Wind Tunnels,” Stanford University, Stanford, CA, Technical Report No. NASA-CR-182747. https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19880012661.pdf
Al-Nassri, S. , and Unny, T. , 1981, “ Developing Laminar Flow in the Inlet Length of a Smooth Pipe,” Appl. Sci. Res., 36(5–6), pp. 313–332. [CrossRef]
So, R. M. , and Mellor, G. L. , 1973, “ Experiment on Convex Curvature Effects in Turbulent Boundary Layers,” J. Fluid Mech., 60(1), pp. 43–62. [CrossRef]
Rae, W. H. , and Pope, A. , 1984, Low-Speed Wind Tunnel Testing, Wiley, Hoboken, NJ.
Mehta, R. D. , and Bradshaw, P. , 1979, “ Design Rules for Small Low Speed Wind Tunnels,” Aeronaut. J., 83(827), pp. 443–453. https://www.cambridge.org/core/journals/aeronautical-journal/article/design-rules-for-small-low-speed-wind-tunnels/600999B496885D7383AB1B04CFF9F4C0
Fournier, R. L. , 2011, Basic Transport Phenomena in Biomedical Engineering, CRC Press, Boca Raton, FL.
Loehrke, R. , and Nagib, H. , 1976, “ Control of Free-Stream Turbulence by Means of Honeycombs: A Balance Between Suppression and Generation,” ASME J. Fluids Eng., 98(3), pp. 342–351. [CrossRef]
Bernstein, D. , 1953, “ An Investigation of Pressure-Drop Coefficients for Orifice Plates and Honeycomb Grids,” MSc thesis, Georgia Institute of Technology, Atlanta, GA. http://hdl.handle.net/1853/13065
Scheiman, J. , 1981, “ Considerations for the Installation of Honeycomb and Screens to Reduce Wind-Tunnel Turbulence,” NASA Langley Research Center, Hampton, VA, Report No. NASA-TM-81868. https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19810020599.pdf
Aufderheide, T. , Bode, C. , Friedrichs, J. , and Kozulovic, D. , 2014, “ The Generation of Higher Levels of Turbulence in a Low-Speed Cascade Wind Tunnel by Pressurized Tubes,” VI European Conference on Computational Fluid Dynamics (ECFD), Barcelona, Spain, July 20–25. http://congress.cimne.com/iacm-eccomas2014/admin/files/fileabstract/a2331.pdf
Han, J.-C. , Dutta, S. , and Ekkad, S. , 2012, Gas Turbine Heat Transfer and Cooling Technology, CRC Press, Boca Raton, FL.
Hylton, L. , Mihelc, M. S. , Turner, E. R. , Nealy, D. A. , and York, R. E. , 1983, “ Analytical and Experimental Evaluation of the Heat Transfer Distribution Over the Surfaces of Turbine Vanes,” Detroit Diesel Allison, Indianapolis, IN, Report No. NASA-CR-168015. https://ntrs.nasa.gov/search.jsp?R=19830020105
Hilditch, M. A. , Smith, G. C. , and Singh, U. K. , 1998, “ Unsteady Flow in a Single Stage Turbine,” ASME Paper No. 98-GT-531.
Goethert, B. H. , 1961, “ Transonic Wind Tunnel Testing,” DTIC Document, Dover Publications, Mineola, NY.
Paniagua, G. , Cuadrado, D. , Saavedra, J. , Andreoli, V. , Meyer, T. , Meyer, S. , and Lawrence, D. , 2016, “ Design of the Purdue Experimental Turbine Aerothermal Laboratory for Optical and Surface Aero-Thermal Measurements,” ASME Paper No. GT2016-58101.
Chue, S. , 1975, “ Pressure Probes for Fluid Measurement,” Prog. Aerosp. Sci., 16(2), pp. 147–223. [CrossRef]
Shiau, C.-C. , Chen, A. F. , Han, J. C. , Azad, S. , and Lee, C. P. , 2015, “ Full-Scale Turbine Vane End-Wall Film-Cooling Effectiveness Distribution Using PSP Technique,” ASME Paper No. GT2015-42206.
Bogard, D. , and Thole, K. , 2006, “ Gas Turbine Film Cooling,” J. Propul. Power, 22(2), pp. 249–270. [CrossRef]
Flegel, A. B. , Welch, G. E. , Giel, P. W. , Ames, F. E. , and Long, J. A. , 2015, “ Complementary Aerodynamic Performance Datasets for Variable Speed Power Turbine Blade Section From Two Independent Transonic Turbine Cascades,” International Symposium on Air Breathing Engines (ISABE), Phoenix, AZ, Oct. 25–30, Paper No. ISABE 2015-20163. https://ntrs.nasa.gov/search.jsp?R=20150022187


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Fig. 1

Closed-loop TTLC facility layout

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Fig. 2

Technion transonic linear cascade test section layout and reference frame

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Fig. 3

Flow lines across the inlet XY (top) and XZ (bottom) cross sections

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Fig. 4

Turbulence grid design (mm)

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Fig. 5

Main frame assembly

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Fig. 6

Disks rotation mechanism set to ± 20 deg

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Fig. 7

Frontboards sealing and support mechanisms

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Fig. 8

Frontboard XY flow simulation: mesh and results for straight frontboards (left) and bellmouth shaped frontboards (right)

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Fig. 9

Frontboard three-dimensional flow simulation: mesh and results for bellmouth shaped frontboards

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Fig. 10

Test section window frame

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Fig. 11

Vane mounting and friction bearings setup

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Fig. 12

Stagger control mechanism set to ±20 deg

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Fig. 13

Tailboards design features

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Fig. 14

Tailboards angle control mechanism

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Fig. 15

Mach (top) and total pressure (bottom) distribution in the streamlines

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Fig. 16

Outlet configuration for compressor and turbine stators

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Fig. 17

Static probes arrangement

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Fig. 18

Cascade assembly in basic operation

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Fig. 19

Technion transonic linear cascade open-loop operational envelope

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Fig. 20

Closed-loop operational envelope manipulation



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