TIAN Xue-qing, HUANG Wei-guang. Numerical Study of the Relationship between Pressure Exponent n and Combustor Exit Temperature[J]. Journal of Aerospace Power, 2005, 20(1): 111-115.
Citation:
TIAN Xue-qing, HUANG Wei-guang. Numerical Study of the Relationship between Pressure Exponent n and Combustor Exit Temperature[J]. Journal of Aerospace Power, 2005, 20(1): 111-115.
TIAN Xue-qing, HUANG Wei-guang. Numerical Study of the Relationship between Pressure Exponent n and Combustor Exit Temperature[J]. Journal of Aerospace Power, 2005, 20(1): 111-115.
Citation:
TIAN Xue-qing, HUANG Wei-guang. Numerical Study of the Relationship between Pressure Exponent n and Combustor Exit Temperature[J]. Journal of Aerospace Power, 2005, 20(1): 111-115.
By numerical simulation of two different gas turbine combustors,the selection of pressure exponent n in combustion efficiency simulation test was investigated.It is suggested that for hydrocarbon fuel,the pressure exponent n may be selected in the range of 1.6～2.0,when the combustion process is reaction-controlled. When the combustion process is diffusion-controlled,the range of 1.0～1.4 is suggested.The result is useful for the model test of gas turbine combustors.
DownLoad: