CHT Analysis of Trailing Edge Region Cooling In HP Stage Turbine Blade

Kini, Chandrakant R.; Yalamarty, Sai Sharan; Mendonca, Royston Marlon; Sharma, Neha; Shenoy, Bhaskar

doi:10.17485/ijst/2016/v9i6/76607

Cited by 3 publications

(2 citation statements)

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“…The turbulence model is explained in [16][17][18] and summarized in Table 2 without further explanation. Boundary conditions and material properties were specified as derived from Kini, et al [7][8][9][10][11][12][13][14]. The through flow of hot gases had a convective heat transfer coefficient of 2028 W/m2K and a free stream temperature of 1561 K. The inlet of the coolant had a pressure of 1.6 MPa and a temperature of 644 K [19][20].…”

Section: Numerical Model and Boundary Conditionsmentioning

confidence: 99%

“…The numerical and experimental techniques discussed above were used for the present work. Kini, et al [7][8][9][10][11][12][13][14] found that greater thickness of the turbulator geometry improves the cooling effect of the gas turbine blade. A helicoidal shaped duct was analyzed and it was observed that blade cooling was improved in comparison to straight ducted cooling ducts for an HP stage turbine blade.…”

Section: Introductionmentioning

confidence: 99%

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Effect of V-shaped Ribs on Internal Cooling of Gas Turbine Blades

Kamat

Shenoy

Kini

2017

J. Eng. Technol. Sci.

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Abstract. Thermal efficiency and power output of gas turbines increase with increasing turbine rotor inlet tem[1perature. The rotor inlet temperatures in most gas turbines are far higher than the melting point of the blade material. Hence the turbine blades need to be cooled. In this work, simulations were carried out with the leading edge of gas turbine blade being internally cooled by coolant passages with V-shaped ribs at angles of 30°, 45° or 60° and at three aspect ratios (1:1, 1:2 and 2:3). The trailing edge of the blade was cooled by cylindrical and triangular pin-fin perforations in staggered and inline arrangements. Numerical analyses were carried out for each configuration of the cooling passages. The best cooling passages for leading edge and trailing edge were deduced by comparing the results of these analyses. It was found that using V-shaped ribs and fins induces a swirling flow, which in turn increases the velocity gradient and hence produces an improvement in heat transfer. The results show that under real time flow conditions, the application of V-shaped ribs and pin-fin perforations is a very promising technique for improving blade life.

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