RESEARCH PAPERS: Gas Turbines: Combustion and Fuels

The Development of a Computer Code for the Estimation of Combustor Exhaust Temperature Using Simple Gas Analysis Measurements

[+] Author and Article Information
R. J. Bideau

Combustion Technology Center, Aero and Industrial Technology Ltd., P. O. Box 46, Burnley BB11 4BX, Lancashire, United Kingdom

J. Eng. Gas Turbines Power 121(1), 80-88 (Jan 01, 1999) (9 pages) doi:10.1115/1.2816317 History: Received April 01, 1998; Online November 19, 2007


Advances in gas turbine technology have led to levels of turbine inlet temperature that preclude the use of thermocouple and simple gas analysis techniques for gas temperature determination. Simple gas analysis schemes rely on the measurement of a very limited range of species in the gas sample: typically, CO2 , CO, and hydrocarbons (UHC). A method of estimating the other important species is required. Simple gas analysis schemes that rely only on elemental mass balance equations to determine the concentration of species are inadequate where high temperature results in significant dissociation. A method has been developed to enable temperature determination at levels that render simple schemes inaccurate. The procedure is based on the measurement of CO2 , CO, UHC, and oxides of nitrogen in the exhaust gas. Other species concentrations are calculated using an assumption of partial thermodynamic equilibrium. This allows the calculation of many important combustion parameters. The method has been implemented as a computer code, with an object orientated design approach using the C++ language. The paper details the theory behind the approach and its implementation. The expected errors for practical applications are discussed and quantified. The method is illustrated by an exhaust temperature pattern factor investigation of an annular combustor. Temperatures determined by thermocouples are compared with those calculated from gas samples.

Copyright © 1999 by The American Society of Mechanical Engineers
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