0
Research Papers: Gas Turbines: Aircraft Engine

Development of a Flexible Turbine Cooling Prediction Tool for Preliminary Design of Gas Turbines

[+] Author and Article Information
Feijia Yin

Faculty of Aerospace Engineering,
Delft University of Technology,
Kluyverweg 1,
Delft 2629 HS, The Netherlands
e-mail: F.yin@tudelft.nl

Floris S. Tiemstra

Faculty of Aerospace Engineering,
Delft University of Technology,
Kluyverweg 1,
Delft 2629HS, The Netherlands
e-mail: Floris.tiemstra@gmail.com

Arvind G. Rao

Faculty of Aerospace Engineering,
Delft University of Technology,
Kluyverweg 1,
Delft 2629 HS, The Netherlands
e-mail: A.gangolirao@tudelft.nl

1Corresponding author.

Contributed by the Aircraft Engine Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received February 2, 2018; final manuscript received February 18, 2018; published online May 29, 2018. Editor: David Wisler.

J. Eng. Gas Turbines Power 140(9), 091201 (May 29, 2018) (12 pages) Paper No: GTP-18-1043; doi: 10.1115/1.4039732 History: Received February 02, 2018; Revised February 18, 2018

As the overall pressure ratio (OPR) and turbine inlet temperature (TIT) of modern gas turbines are constantly being increased in the pursuit of increasing efficiency and specific power, the effect of bleed cooling air on the engine performance is increasingly becoming important. During the thermodynamic cycle analysis and optimization phase, the cooling bleed air requirement is either neglected or is modeled by simplified correlations, which can lead to erroneous results. In this current research, a physics-based turbine cooling prediction model, based on semi-empirical correlations for heat transfer and pressure drop, is developed and verified with turbine cooling data available in the open literature. Based on the validated model, a parametric analysis is performed to understand the variation of turbine cooling requirement with variation in TIT and OPR of future advanced engine cycles. It is found that the existing method of calculating turbine cooling air mass flow with simplified correlation underpredicts the amount of turbine cooling air for higher OPR and TIT, thus overpredicting the estimated engine efficiency.

FIGURES IN THIS ARTICLE
<>
Copyright © 2018 by ASME
Your Session has timed out. Please sign back in to continue.

References

Yin, F. , 2016, “ Modeling and Characteristics of a Novel Multi-Fuel Hybrid Engine for Future Aircraft,” Doctoral thesis, Delft University of Technology, Delft, The Netherlands.
Baldauf, S. A. , Scheurlen, M. , Schulz, A. , and Wittig, S. , 2002, “ Correlation of Film Cooling Effectiveness From Thermographic Measurements at Engine Like Conditions,” ASME Paper No. GT2002-30180.
Han, J. C. , and Zhang, Y. M. , 1992, “ High Performance Heat Transfer Ducts With Parallel Broken and V-Shaped Broken Ribs,” Int. J. Heat Mass Transfer, 35(2), pp. 513–523. [CrossRef]
Lau, S. C. , McMillin, R. D. , and Han, J. C. , 1991, “ Heat Transfer Characteristics of Turbulent Flow in a Square Channel With Angled Discrete Ribs,” ASME J. Turbomach., 113(3), pp. 367–374. [CrossRef]
Lau, S. C. , McMillin, R. D. , and Han, J. C. , 1991, “ Turbulent Heat Transfer and Friction in a Square Channel With Discrete Rib Turbulators,” ASME J. Turbomach., 113(3), pp. 360–366. [CrossRef]
Lau, S. C. , Kukreja, R. T. , and McMillin, R. D. , 1991, “ Effects of V-Shaped Rib Arrays on Turbulent Heat Transfer and Friction of Fully Developed Flow in a Square Channel,” Int. J. Heat Mass Transfer, 34(7), pp. 1605–1616. [CrossRef]
Han, J. C. , Ou, S. , Park, J. S. , and Lei, C. K. , 1989, “ Augmented Heat Transfer in Rectangular Channels of Narrow Aspect Ratios With Rib Turbulators,” Int. J. Heat Mass Transfer, 32(9), pp. 1619–1630. [CrossRef]
Han, J. C. , and Park, J. S. , 1988, “ Developing Heat Transfer in Rectangular Channels With Rib Turbulators,” Int. J. Heat Mass Transfer, 31(1), pp. 183–195. [CrossRef]
Metzger, D. , Shepard, W. , and Haley, S. , 1986, “ Row Resolved Heat Transfer Variations in Pin-Fin Arrays Including Effects of Non-Uniform Arrays and Flow Convergence,” ASME Paper No. 86-GT-132.
Metzger, D. , Fan, Z. , and Shepard, W. , 1982, “ Pressure Loss and Heat Transfer Through Multiple Rows of Short Pin Fins,” Seventh International Conference, Munich, Germany, Sept. 6–10.
VanFossen, G. J. , 1982, “ Heat-Transfer Coefficients for Staggered Arrays of Short Pin Fins,” ASME J. Eng. Power, 104(2), pp. 268–274. [CrossRef]
Arora, S. C. , and Abdel Messeh, W. , 1983, “ Heat Transfer Experiments in High Aspect Ratio Rectangular Channel With Epoxied Short Pin Fins,” ASME Paper No. 83-GT-57.
Florschuetz, L. , Truman, C. , and Metzger, D. , 1981, “ Streamwise Flow and Heat Transfer Distributions for Jet Array Impingement With Crossflow,” ASME J. Heat Transfer, 103(2), pp. 337–342. [CrossRef]
Chupp, R. E. , Helms, H. E. , and McFadden, P. W. , 1969, “ Evaluation of Internal Heat-Transfer Coefficients for Impingement-Cooled Turbine Airfoils,” J. Aircr., 6(3), pp. 203–208. [CrossRef]
Levy, Y. , Rao, A. G. , Erenburg, V. , Sherbaum, V. , Gaissinski, I. , and Krapp, V. , 2012, “ Pressure Losses for Jet Array Impingement With Crossflow,” ASME Paper No. GT2012-68386.
Idel′chik, I. E. , and Steinberg, M. O. , 1996, Handbook of Hydraulic Resistance, Begell House, New York.
Tiemstra, F. , 2014, “ Design of a Semi-Empirical Tool for the Evaluation of Turbine Cooling Requirements in a Preliminary Design Stage,” Master's thesis, Delft University of Technology, Delft, The Netherlands. http://resolver.tudelft.nl/uuid:225cfccd-2fc3-4a4d-a8a8-c24bd24bae44
Halila, E. E. , Lenahan, D. T. , and Thomas, T. T. , 1982, “ Energy Efficient Engine High Pressure Turbine Test Hardware Detailed Design Report,” National Aeronautics and Space Administration, Cleveland, OH, Technical Report No. NASA CR-167955. https://ntrs.nasa.gov/search.jsp?R=19850002687
Stearns, E. M. , 1982, “ Energy Efficient Engine Core Design and Performance Report,” National Aeronautics and Space Administration, Cincinnati, OH, Technical Report No. NASA-CR-168069. https://ntrs.nasa.gov/search.jsp?R=19900019243
Visser, W. P. , and Broomhead, M. J. , 2000, “ GSP, a Generic Object-Oriented Gas Turbine Simulation Environment,” ASME Paper No. 2000-GT-0002.
Saravanamuttoo, H. I. H. , Rogers, G. F. C. , Cohen, H. , and Straznicky, P. V. , 2008, Gas Turbine Theory, 6th ed, Pearson Education Ltd., Harlow, UK.
Hartsel, J. , 1972, “ Prediction of Effects of Mass-Transfer Cooling on the Blade-Row Efficiency of Turbine Airfoils,” Tenth Aerospace Sciences Meeting, San Diego, CA, pp. 1–7.
Kurzke, J. , 2002, “ Performance Modeling Methodology: Efficiency Definitions for Cooled Single and Multistage Turbines,” ASME Paper No. GT2002-30497.
Young, J. , and Horlock, J. , 2006, “ Defining the Efficiency of a Cooled Turbine,” ASME J. Turbomach., 128(4), pp. 658–667. [CrossRef]
Jonsson, M. , Bolland, O. , Bücker, D. , and Rost, M. , 2005, “ Gas Turbine Cooling Model for Evaluation of Novel Cycles,” International ECOS Conference, Trondheim, Norway, June 20–22, pp. 641–650. https://www.researchgate.net/publication/237502557_Gas_turbine_cooling_model_for_evaluation_of_novel_cycles
MathWorks, 2015, “ MATLAB Support Documentation—Optimization Toolbox Function,” The MathWorks Inc., Natick, MA, accessed Apr. 4, 2018, http://nl.mathworks.com/help/optim/ug/fmincon.html

Figures

Grahic Jump Location
Fig. 1

Comparison of TIT and metal operating temperature [1]

Grahic Jump Location
Fig. 2

Flowchart of the turbine cooling model

Grahic Jump Location
Fig. 3

Schematic of an advanced aero engine cooled HPT blade

Grahic Jump Location
Fig. 4

Schematic of a channel with ribs

Grahic Jump Location
Fig. 5

Flowchart of the turbine cooling

Grahic Jump Location
Fig. 6

Schematic of jet impingement

Grahic Jump Location
Fig. 7

Schematic of an advanced geared turbofan engine

Grahic Jump Location
Fig. 8

The layout of a turbofan engine modeled using GSP

Grahic Jump Location
Fig. 9

Variation in turbine cooling fraction versus temperature difference between hot gas and coolant for different coolant pressures. The cooling requirement is predicted by the in-house turbine cooling tool. AMOT = 1450 K.

Grahic Jump Location
Fig. 10

Variation in turbine cooling fraction versus temperature difference between hot gas and coolant for different coolant pressures. The cooling requirement is predicted by the empirical turbine cooling correlation (Eq. (64)). AMOT = 1450K.

Grahic Jump Location
Fig. 11

Variation in turbine cooling fraction versus the AMOT for different TIT. The in-house cooling prediction tool used.

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In