Account of Film Turbulence for Predicting Film Cooling Effectiveness in Gas Turbine Combustors

[+] Author and Article Information
G. J. Sturgess

Turbine Durability and Combustion, United Technologies Corporation, Pratt & Whitney Aircraft Group, Commercial Products Division, East Hartford, Conn.

J. Eng. Power 102(3), 524-534 (Jul 01, 1980) (11 pages) doi:10.1115/1.3230295 History: Received January 17, 1979; Online September 28, 2009


The paper deals with a small but important part of the overall gas turbine engine combustion system and continues earlier published work on turbulence effects in film cooling to cover the case of film turbulence. Film cooling of the gas turbine combustor liner imposes certain geometric limitations on the coolant injection device. The impact of practical film injection geometry on the cooling is one of increased rates of film decay when compared to the performance from idealized injection geometries at similar injection conditions. It is important to combustor durability and life estimation to be able to predict accurately the performance obtainable from a given practical slot. The coolant film is modeled as three distinct regions, and the effects of injection slot geometry on the development of each region are described in terms of film turbulence intensity and initial circumferential non-uniformity of the injected coolant. The concept of the well-designed slot is introduced and film effectiveness is shown to be dependent on it. Only slots which can be described as well-designed are of interest in practical equipment design. A prediction procedure is provided for well-designed slots which describes growth of the film downstream of the first of the three film regions. Comparisons of predictions with measured data are made for several very different well-designed slots over a relatively wide range of injection conditions, and good agreement is shown.

Copyright © 1980 by ASME
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