A scaled up test model simulating a realistic leading edge cooling system of a high pressure gas turbine blade was designed with the aim of performing heat transfer measurements in static and rotating conditions. The test model is composed by a trapezoidal supply channel which feeds three large racetrack holes, generating coolant impingement on the internal concave leading edge surface. Four big fins allow to confine the impingement jets impact zones. Air is then extracted through 4 rows of 6 holes each, two of showerhead (SH) and two of film cooling (FC). The test model is installed on a rotating test rig, which allows to reach jet Reynolds numbers (Rej) up to 40000 and rotation numbers (Roj) up to 0.05. The effect of cross-flow in the supply channel is also considered. The heat transfer coefficient (HTC) distribution on the internal concave surface was evaluated by means of a steady state technique, using wide band thermochromic liquid crystals (TLCs) to measure the wall temperature and an electrically heated Inconel sheet to provide a constant heat flux to the investigated surface. This paper reports experimental results obtained in static conditions for Rej 10000 and 30000 and for two cross-flow cases representative of blade tip and hub sections. The effects of different mass flow extraction between pressure and suction side is also investigated by varying the mass flow rate through FC and SH holes. The effect of the coolant extraction holes geometry on the Nusselt number distribution is analyzed by comparing the experimental results, reported as 2D Nusselt number (Nu) maps, with a previous investigation on an analogous test model with similar impingement geometry. A CFD campaign was also carried out on the present test rig, exploiting a previously validated computational model. Both numerical and experimental results reveal that the effects of differentiated mass flow extraction and extraction area modification are secondary with respect to the effects of Rej and crossflow variation. © 2015 The Authors. Published by Elsevier Ltd.
Heat transfer investigation on an internal cooling system of a gas turbine leading edge model / Andreini, Antonio; Burberi, Emanuele; Cocchi, Lorenzo; Facchini, Bruno; Massini, Daniele; Pievaroli, Marco. - In: ENERGY PROCEDIA. - ISSN 1876-6102. - ELETTRONICO. - 82:(2015), pp. 222-229. (Intervento presentato al convegno 70th Conference of the Italian Thermal Machines Engineering Association, ATI 2015 tenutosi a Italy nel 2015) [10.1016/j.egypro.2015.12.026].
Heat transfer investigation on an internal cooling system of a gas turbine leading edge model
ANDREINI, ANTONIO;BURBERI, EMANUELE;COCCHI, LORENZO;FACCHINI, BRUNO;MASSINI, DANIELE;PIEVAROLI, MARCO
2015
Abstract
A scaled up test model simulating a realistic leading edge cooling system of a high pressure gas turbine blade was designed with the aim of performing heat transfer measurements in static and rotating conditions. The test model is composed by a trapezoidal supply channel which feeds three large racetrack holes, generating coolant impingement on the internal concave leading edge surface. Four big fins allow to confine the impingement jets impact zones. Air is then extracted through 4 rows of 6 holes each, two of showerhead (SH) and two of film cooling (FC). The test model is installed on a rotating test rig, which allows to reach jet Reynolds numbers (Rej) up to 40000 and rotation numbers (Roj) up to 0.05. The effect of cross-flow in the supply channel is also considered. The heat transfer coefficient (HTC) distribution on the internal concave surface was evaluated by means of a steady state technique, using wide band thermochromic liquid crystals (TLCs) to measure the wall temperature and an electrically heated Inconel sheet to provide a constant heat flux to the investigated surface. This paper reports experimental results obtained in static conditions for Rej 10000 and 30000 and for two cross-flow cases representative of blade tip and hub sections. The effects of different mass flow extraction between pressure and suction side is also investigated by varying the mass flow rate through FC and SH holes. The effect of the coolant extraction holes geometry on the Nusselt number distribution is analyzed by comparing the experimental results, reported as 2D Nusselt number (Nu) maps, with a previous investigation on an analogous test model with similar impingement geometry. A CFD campaign was also carried out on the present test rig, exploiting a previously validated computational model. Both numerical and experimental results reveal that the effects of differentiated mass flow extraction and extraction area modification are secondary with respect to the effects of Rej and crossflow variation. © 2015 The Authors. Published by Elsevier Ltd.
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