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Research Papers: Energy Systems Analysis

A Lumped Thermodynamic Model of Gas Turbine Blade Cooling: Prediction of First-Stage Blades Temperature and Cooling Flow Rates

[+] Author and Article Information
Roberta Masci

Department of Mechanical and
Aerospace Engineering,
Sapienza University of Rome,
Rome 00184, Italy
e-mail: roberta.masci@uniroma1.it

Enrico Sciubba

Department of Mechanical and
Aerospace Engineering,
Sapienza University of Rome,
Rome 00184, Italy
e-mail: enrico.sciubba@uniroma1.it

1Corresponding author.

Contributed by the Advanced Energy Systems Division of ASME for publication in the JOURNAL OF ENERGY RESOURCES TECHNOLOGY. Manuscript received January 30, 2017; final manuscript received October 18, 2017; published online November 28, 2017. Assoc. Editor: Tatiana Morosuk.

J. Energy Resour. Technol 140(2), 020901 (Nov 28, 2017) (11 pages) Paper No: JERT-17-1045; doi: 10.1115/1.4038462 History: Received January 30, 2017; Revised October 18, 2017

Turbine inlet temperatures (TIT) of 1500–2000 K have become a sort of standard for most modern advanced applications. First-stage blades are obviously the most exposed components to such hot gases, and thus they need proper cooling. In the preliminary design of the blades and their cooling system, designers must rely on simple models that can be further refined at a later stage, in order to have an approximate but valuable set of guidelines and to reach a feasible first-order configuration. In this paper, a simple lumped thermodynamic model of blade cooling is proposed. It is based on mass/energy balances and heat transfer correlations, and it predicts a one-dimensional temperature profile on the blade external surface along the chord for a given gas temperature profile, as well as the required cooling air flow rates to prevent blade material from creep. The greatest advantage of the model is that it can be easily adapted to any operating condition, process parameter, and blade geometry, which makes it well suited to the last technological trends, namely, the investigation of new cooling methods and alternative coolants instead of air. Therefore, the proposed model is expected to be a useful tool in the field of innovative gas turbine cycle analysis, replacing more computationally intensive and very time-consuming models.

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References

El-Masri, M. A. , 1986, “ On Thermodynamics of Gas Turbine Cycles—Part 2: A Model for Expansion in Cooled Turbines,” ASME J. Eng. Gas Turbines Power, 108(1), pp. 151–159. [CrossRef]
Bolland, O. , and Stadaas, J. F. , 1995, “ Comparative Evaluation of Combined Cycle and Gas Turbine Systems With Water Injection, Steam Injection, and Recuperation,” ASME J. Eng. Gas Turbines Power, 117(1), pp. 138–145. [CrossRef]
De Paepe, M. , and Dick, E. , 2000, “ Cycle Improvements to Steam Injected Gas Turbines,” Int. J. Energy Res., 24(12), pp. 1081–1107. [CrossRef]
Han, J. C. , Park, J. S. , and Lei, C. K. , 1985, “ Heat Transfer Enhancement in Channels With Turbulence Promoters,” ASME J. Eng. Gas Turbines Power, 107(3), pp. 628–635. [CrossRef]
Han, J. C. , and Wright, L. M. , 2006, “ Enhanced Internal Cooling of Turbine Blades and Vanes,” The Gas Turbine Handbook, U.S. Department of Energy, Office of Fossil Energy, National Energy Technology Laboratory (NETL), Pittsburgh, PA, pp. 321–354.
Horlock, J. H. , Watson, D. T. , and Jones, T. V. , 2001, “ Limitations on Gas Turbine Performance Imposed by Large Turbine Cooling Flows,” ASME J. Eng. Gas Turbine Power, 123(3), pp. 487–494. [CrossRef]
Jonsson, M. , Bolland, O. , Bücher, D. , and Rost, M. , 2005, “ Gas Turbine Cooling Model for Evaluation of Novel Cycles,” 18th International Conference ECOS, Trondheim, Norway, June 20–22, pp. 641–650. https://www.noexperiencenecessarybook.com/dNBWV/gas-turbine-cooling-model-for-evaluation-of-novel-cycles.html
Jordal, K. , Bolland, O. , and Klang, A. , 2004, “ Aspects of Cooled Gas Turbine Modeling for the Semi-Closed O2/CO2 Cycle With CO2 Capture,” ASME J. Eng. Gas Turbines Power, 126(3), pp. 507–515. [CrossRef]
Forghan, F. , Askari, O. , Narusawa, U. , and Metghalchi, H. , 2017, “ Cooling of Turbine Blades With Expanded Exit Holes: Computational Analyses of Leading Edge and Pressure-Side of a Turbine Blade,” ASME J. Energy Resour. Technol., 139(4), p. 042004. [CrossRef]
Forghan, F. , Askari, O. , Narusawa, U. , and Metghalchi, H. , 2016, “ Cooling of Turbine Blade Surface With Expanded Exit Holes: Computational Suction-Side Analysis,” ASME J. Energy Resour. Technol., 138(5), p. 051602. [CrossRef]
Han, J.-C. , 2013, “ Fundamental Gas Turbine Heat Transfer,” ASME J. Therm. Sci. Eng. Appl., 5(2), p. 021007. [CrossRef]
Han, J. C. , Dutta, S. , and Ekkad, S. V. , 2000, Gas Turbine Heat Transfer and Cooling Technology, Taylor & Francis, New York, p. 646.
Han, J. C. , and Ekkad, S. V. , 2001, “ Recent Developments in Turbine Blade Film Cooling,” Int. J. Rotating Mach., 7(1), pp. 21–40. [CrossRef]
Sciubba, E. , 2015, “ Air-Cooled Gas Turbine Cycles—Part 1: An Analytical Method for the Preliminary Assessment of Blade Cooling Flow Rates,” Energy, 83, pp. 104–114.
Sciubba, E. , 2014, “ An Analytical Method for the Preliminary Assessment of Blade Cooling Flow Rates in Gas Turbine Blades,” 27th International Conference ECOS, Turku, Finland, June 15–19, pp. 130–146. https://sapienza.pure.elsevier.com/en/publications/an-analytical-method-for-the-preliminary-assessment-of-blade-cool
Cerri, G. , 2008, “ Preliminary Turbine Cooling Requirement,” Università degli studi Roma Tre, European Commission, Brussels, Belgium, Report, No. FP7-ENERGY-2008-TREN-1. https://ec.europa.eu/research/participants/portal/desktop/en/opportunities/fp7/calls/fp7-energy-2008-tren-1.html
Caron, P. , and Khan, T. , 1999, “ Evolution of Ni-Based Superalloys for Single Crystal Gas Turbine Blade Applications,” Aerosp. Sci. Technol., 3(8), pp. 513–523. [CrossRef]

Figures

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Fig. 1

Schematic view of a modern gas turbine vane (a) and blade (b) with common cooling techniques [5]

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Fig. 2

The elemental control volume [14,15]

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Fig. 3

Schematic view of the enhance systems effectiveness [16]

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Fig. 4

Nozzle guide vane and rotor blade midspan section

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Fig. 5

Contours of static temperature in the stator and rotor channels and representation of the channel midstreamlines (marked lines) on which temperature values are extrapolated

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Fig. 6

Gas temperature profiles along stator (a) and rotor (b) channel midstreamline

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Fig. 7

External convective heat transfer coefficient trend along the NGV (a) and blade (b) chord

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Fig. 8

Nozzle guide vane (a) and blade (b) external surface temperature profiles

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Fig. 9

Internal paths representing NGV (a) and blade (b) chord

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Fig. 10

Nozzle guide vane (a) and blade (b) internal surface temperature profiles

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Fig. 11

Larson–Miller stress-rupture curves for third generation single crystal Ni-based superalloy CMSX-10 [17]

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Fig. 12

Coolant paths in NGV (a) and rotor blade (b) cooling cylinders

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Fig. 13

Internal temperature profiles along NGV (a) and rotor blade (b) chord for each value of i (0.06–0.09)

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Fig. 14

Standard deviation values for each i in the NGV (a) and rotor blade (b)

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Fig. 15

Film temperature profiles for each i (0.05–0.1) in the NGV (a) and rotor blade (b)

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Fig. 16

Nozzle guide vane (a) and rotor blade (b) external surface temperature profiles for each i (0.05–0.1)

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