ARTICLE:

• FLOW DISTRIBUTION INSIDE COOLED NON-ROTATING GAS TURBINE BLADE WITH FILM COOLING HOLES  download article

S. L. Borse
Indian Institute of Technology, Bombay, India

Dr. A. W. Date
Department Mechanical Engineering, Indian Institute of Technology, Bombay, Mumbai-400076, India

ABSTRACT

A typical internally cooled gas turbine blade consists of three passages viz, leading edge passage, middle serpentine passage and trailing edge passage. Accurate estimation of the heat transfer coefficient in each passage is required to determine turbine blade temperature distribution. One of the factors on which heat transfer coefficient depends is the mass flow through the given passage. Experimental study is carried out on simplified cold stationary model of a turbine blade. This work focuses attention on the effect of provision of film cooling holes on the flow distribution in internal coolant passages. Results are compared for supply of air mass flow as constant rate to the test section for, a) No film cooling holes, b) Film cooling holes in leading edge passage, c) Film cooling holes in leading and serpentine passages and d) Film cooling holes in all passages. Results indicate that provision of film cooling holes drastically reduces supply pressure requirement. Provision of film cooling holes also nearly equalises flows in the three passages.

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