| 大涵道比涡扇发动机涡轮过渡段的数值研究 |
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| 引用本文： | 毛凯.大涵道比涡扇发动机涡轮过渡段的数值研究[J].科学技术与工程,2012,12(6):1308-1313. |
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| 作者姓名： | 毛凯 |
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| 作者单位： | 西北工业大学动力与能源学院,西安,710072 |
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| 摘 要： | 采用CFD数值模拟方法对大涵道比涡扇发动机高压涡轮与低压涡轮之间的过渡流道进行了气动性能计算。通过与实验数据的对比，验证了CFD计算模型预测涡轮过渡段气动性能的可靠性以及计算精度。分析了径向偏移较大的涡轮过渡段流动特点和损失机理，为进一步提高过渡段气动性能提供研究方向。高性能大涵道比发动机中，涡轮过渡流道流动机理复杂，设计难度大，其可供挖掘潜力较大。
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| 关 键 词： | 大涵道比涡扇发动机 涡轮过渡流道 数值模拟 损失 |
| 收稿时间： | 2011/11/28 0:00:00 |
| 修稿时间： | 12/6/2011 4:16:24 PM |
Numerical research for intermediate turbine duct of high bypass turbo-fan engine |
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| maokai.Numerical research for intermediate turbine duct of high bypass turbo-fan engine[J].Science Technology and Engineering,2012,12(6):1308-1313. |
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| Authors: | maokai |
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| Institution: | (School of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,P.R.China) |
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| Abstract: | The aerodynamic performance calculation of high-pressure turbine and low-pressure turbine intermediate duct was numerically simulated. With experimental data, the dependability and accuracy of CFD calculation model for predicting the performance of turbine intermediate duct had been verified. The flow characteristics and the loss mechanism had been analyzed in turbine intermediate duct with large radial offset, in order to provide research direction for improving the aerodynamic performance of ITD further. the improving design of intermediate duct is meaningful to the high bypass turbofan engine |
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| Keywords: | high bypass turbo-fan engine intermediate turbine duct numerical simulation loss |
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