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Research Papers

Sensitivity Analysis on Turbine Blade Temperature Distribution Using Conjugate Heat Transfer Simulation

[+] Author and Article Information
Mohammad Alizadeh

e-mail: em.alizadeh@gmail.com

Ali Izadi

e-mail: aliizadi.ut@gmail.com
School of Mechanical Engineering,
College of Engineering,
University of Tehran,
Tehran, Iran

Alireza Fathi

K.N.T. University,
Tehran, Iran
e-mail: alireza.fathy@gmail.com

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the Journal of Turbomachinery. Manuscript received May 8, 2012; final manuscript received March 17, 2013; published online September 20, 2013. Assoc. Editor: Karen A. Thole.

J. Turbomach 136(1), 011001 (Sep 20, 2013) (13 pages) Paper No: TURBO-12-1045; doi: 10.1115/1.4024637 History: Received May 08, 2012; Revised March 17, 2013

Heat transfer parameters are the most critical variables affecting turbine blade life. Therefore, accurately predicting heat transfer parameters is essential. In this study, for precise prediction of the blade temperature distribution, a conjugate heat transfer procedure is used. This procedure involves three different physical aspects: flow and heat transfer in external domain and internal cooling passages and conduction within metal blade. For the external flow simulation and conduction within metal, three-dimensional solvers are used. However, three-dimensional modeling of blade cooling passages is time-consuming because of complex cooling passage geometries. Therefore, in the current work, a one-dimensional network method is used for the simulation of cooling passages. For validation of the numerical procedure, simulation results are compared with the available experimental data for a C3X vane. Results show good agreement against experimental data. The present paper investigates uncertainties of some parameters that affect turbine blade heat transfer, namely, (1) turbine inlet temperature and pressure, (2) upstream stator coolant mass flow rate and temperature, (3) rotor shroud heat transfer coefficient and fluid temperature over shroud, (4) rotor coolant inlet pressure and temperature (as a result of secondary air system), (5) blade metal thermal conductivity, and (6) blade coating thickness and thermal conductivity. Results show that turbine inlet temperature, pressure drop and temperature rise in the secondary air system (SAS) and coating parameters have significant effect on the blade temperature.

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Figures

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Fig. 1

Conjugate heat transfer algorithm

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Fig. 2

Solution algorithm of the 1D network method

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Fig. 3

C3X geometry and the 1D elements of ten coolant channels

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Fig. 4

View of numerical mesh on plane of constant spanwise coordinates

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Fig. 5

Predicted and measured pressure distribution on the midspan plane

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Fig. 6

Nondimensional temperature distribution on the midspan plane

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Fig. 7

Temperature contours of the vane on (a) pressure side (b) suction side

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Fig. 8

CAD model of simulated blade and its internal cooling passages

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Fig. 9

Schematic view of the rotor blade cooling passages network

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Fig. 10

Boundary connections between 1D code and 3D model

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Fig. 11

Blade temperature distribution for the reference case

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Fig. 12

Flow field and metal temperature distribution at 70% span

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Fig. 13

The diagram of different regions of blade. (a) Defined regions for averaging, (b) shroud surface on which HTC and bulk temperature is applied (light gray).

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Fig. 14

Computational domain and locations of boundary conditions

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Fig. 15

The effects of turbine inlet temperature on the blade temperature

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Fig. 16

The effects of turbine inlet pressure on the blade temperature

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Fig. 17

Blade temperature distribution versus vane coolant mass flow rate

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Fig. 18

Blade temperature distribution versus its upstream vane coolant temperature

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Fig. 19

The flow from outer casing

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Fig. 20

Blade temperature variation versus shroud heat transfer coefficient

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Fig. 21

Blade temperature variation versus coolant temperature over shroud

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Fig. 22

Blade temperature variation versus pressure drop at the coolant inlet

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Fig. 23

Blade temperature variation versus coolant inlet temperature

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Fig. 24

Blade temperature variation versus blade metal thermal conductivity

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Fig. 25

Blade temperature variation versus coating thickness

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Fig. 26

Blade temperature variation versus coating thermal conductivity

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