Abstract
Thermal radiation is the most dominant type of heat transfer inside the combustion chamber, which can directly affect the temperature distributions at the combustor walls. This paper provides a comprehensive analysis of the effects of two radiation models on the flame and liner-walls temperatures. A combustion chamber used in the Rolls-Royce-RB-183 turbofan engine was examined in this study by integrating a solid combustor model with the numerical fluid domain. The results indicated that the implementation of radiation models shrinks the flame peak-temperature and altered temperature distribution across the liner. The Discrete Ordinates Method (DOM) estimated a 10% higher temperature at the front part of the liner compared to the non-radiation model and 15% less than the P-1 radiation method. After the dilution zone, the DOM and P-1 models estimated respectively 15% and 25% reduction in the liner temperature compared to the non-radiation combustor. The radiation models have also down predicted the flame temperature by 200 K and more than 200 K for DOM and P-1 case respectively. The results also showed that the emissivity value had minimal effects on the combustor temperature distribution. The DOM considered being more accurate to estimate the combustor wall and flow temperatures compared to the P-1 radiation method.
Highlights
The combustion chamber is one of the primary components of gas turbine engines, the combustor design, performance, and durability are very important parameters which affect the overall gas turbine operation and efficiency [1]
This paper provides a comprehensive assessment of P-1 and Discrete Ordinates Method (DOM) radiation models on combustion liner coupled with conjugate heat transfer by integrating both solid and fluid in the computational domain
P-1 and DOM radiation models were assessed numerically to highlight their influences on the combustion chamber temperature distribution and the heat transfer process towards the combustor liner
Summary
The combustion chamber is one of the primary components of gas turbine engines, the combustor design, performance, and durability are very important parameters which affect the overall gas turbine operation and efficiency [1]. Temperature distri bution inside the combustion chamber is an important parameter, which affects the combustor and turbine’s durabilities. Thermal radiation is the dominant and the most difficult heat transfer mode to simulate inside the combustion chambers [2]. In some appli cations, the thermal radiation is responsible for 96% of heat transfer inside the combustion chamber and the combustor walls and hot gases absorb and reflect part of the combustion energy [3,4]. The DOM model is simple to implement, it requires a long time to converge for optical thick media [6]. The DOM and P-1 models have been examined under atmospheric conditions, simple geometries and considering
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