掺混孔结构对燃烧室性能影响研究  被引量:2

Research on Effect of Dilution Holes Structures on Combustor Performance

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作  者:刘凯 王峻宁 曾文 孙丽艳 LIU Kai;WANG Jun-ning;ZENG Wen;SUN Li-yan(School of Aero engine,Shenyang Aerospace University,Shenyang,China,Post Code:110136;Department of Gas Turbine Product Manufacturing,Shenyang Liming Aero Engine Co.,Ltd.of AECC,Shenyang,China,Post Code:110005)

机构地区:[1]沈阳航空航天大学航空发动机学院,辽宁沈阳110136 [2]中航发沈阳黎明航空发动机有限责任公司燃气轮机产品制造部,辽宁沈阳110005

出  处:《热能动力工程》2022年第7期64-69,92,共7页Journal of Engineering for Thermal Energy and Power

基  金:国家自然科学基金(51376133);航空科学基金(2015ZB54003)。

摘  要:针对燃气轮机NO_(x)排放较高的问题,试验研究了某型燃气轮机火焰筒掺混孔前移后,点火、熄火、污染物排放及出口温度场等燃烧性能。研究结果表明:将火焰筒掺混孔前移20 mm至第2道冷却气膜后,贫油点火油气比由0.02335~0.03302增加到0.02446~0.03633;熄火油气比由0.00518~0.00688增加到0.00590~0.00717;污染物排放中CO_(x)由969.54增加到1090.45 mg/m^(3)UHC(未燃碳氢)由116.93增加到145.91 mg/m^(3)NO由163.85降低到87.0 mg/m^(3)出口温度分布系数由0.2255增加到0.2449。通过调整掺混孔孔径比,温度分布系数降低至0.2292,接近原型水平,可以实现较低NO_(x)排放。Aiming at the problem of high NO_(x) emission of gas turbine,the combustion performance of ignition,blowout,pollution emission and outlet temperature field of a certain type of gas turbine flame tube with dilution holes moving forward was studied experimentally.The research results show that the lean ignition fuel-air ratio increases slightly from the range of 0.02335 to 0.03302 to the range of 0.02446 to 0.03633 when the dilution holes is moved forward 20 mm to the second cooling film;the blowout fuel-air ratio increases slightly from the range of 0.00518 to 0.00688 to the range of 0.00590 to 0.00717;In pollutant emissions,NO_(x) concentration increases from 969.54 to 1090.45 mg/m^(3);unburned hydrocarbon(UHC)increases from 116.93 to 145.91 mg/m^(3);NO_(x) decreases from 163.85 to 87.0 mg/m^(3);outlet temperature distribution coefficient increases from 0.2255 to 0.2449.By adjusting the dilution hole diameter ratio,the temperature distribution coefficient is reduced to 0.2292 which is close to the prototype,so as to achieve lower NO_(x) emission.

关 键 词:燃气轮机 燃烧室 掺混孔 燃烧特性 试验 

分 类 号:V231.2[航空宇航科学与技术—航空宇航推进理论与工程]

 

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