Title

用數值計算方法對出口溫度與壓力指數關係的研究

Translated Titles

Numerical Study of the Relationship between Pressure Exponent n and Combustor Exit Temperature

Authors

田學清(Xue-Qing Tian);黃偉光(Wei-Guang Huang)

Key Words

航空、航天推進系統 ; 出口溫度 ; 壓力指數 ; 數值計算 ; aerospace propulsion system ; exit temperature ; pressure exponent ; numerical calculation

PublicationName

航空動力學報

Volume or Term/Year and Month of Publication

20卷1期(2005 / 02 / 01)

Page #

111 - 115

Content Language

簡體中文

Chinese Abstract

通過對兩種不同類型的燃氣輪機燃燒室的數值計算,研究了不同燃燒類型對燃氣輪機燃燒效率模化試驗中壓力指數選取的影響,結果表明壓力指數除受到燃料、餘氣係數等影響之外,燃燒類型對其也有很大影響。對於以碳氫化合物為燃料,化學動力學控制類型燃燒室模化中n值相對較大,範圍為1.6~2.0。當燃燒過程受擴散火焰控制時,n值相對較小,範圍為1.0~1.4。

English Abstract

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.

Topic Category 工程學 > 交通運輸工程