航空发动机

李瑞军,郝旺,谢业平,张付震.变几何涡轮对变循环发动机性能的影响[J].航空发动机,2026,52(1):145-153

变几何涡轮对变循环发动机性能的影响

Impact of Variable Geometry Turbine on Variable Cycle Engine Performance

DOI：10.12482/ISSN.1672-3147.20250223002

英文关键词:variable geometry turbine engine performance single-bypass dual-bypass variable cycle engine

基金项目:国防工业重点研究项目资助

作者	单位
李瑞军	中国航发沈阳发动机研究所,沈阳 110015
郝旺	中国航发沈阳发动机研究所,沈阳 110015
谢业平	中国航发沈阳发动机研究所,沈阳 110015
张付震	中国人民解放军93128部队,北京 100843

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中文摘要:

为深入剖析变几何涡轮对变循环发动机性能的影响，构建了双外涵变循环发动机的整机性能模型，并提出2种变几何涡轮特性建模方法。以双外涵模式亚声速巡航工况作为设计点，详细探究了变几何高压涡轮、低压涡轮单独调节及组合调节时，对变循环发动机在地面起飞、超声速巡航和亚声速巡航状态下性能的影响。结果表明：在单外涵模式下，当低压涡轮喉部面积增大20%时，地面起飞推力和超声速巡航推力分别增大约2%和6%；若高压涡轮喉部面积增大20%，地面起飞推力将小幅减小，降幅约为0.3%，而超声速巡航推力增大约2%；低压涡轮导向器面积的最小值以及高压涡轮导向器面积的最大值均受风扇裕度的限制；在双外涵模式下，相较于常规涡扇发动机，变循环发动机在亚声速巡航状态下的耗油率优势约为8%～9%。其中，变几何低压涡轮是变循环发动机中不可或缺的可调部件，而高压涡轮是否具备可调节性对耗油率的影响相对较小。

英文摘要:

To thoroughly investigate the impact of variable geometry turbines on variable cycle engine performance, an performance model of a dual-bypass variable cycle engine was developed, along with two characteristic modeling approaches for variable geometry turbines. Using the subsonic cruise condition under dual-bypass mode as the design point, the effects of individual and combined adjust? ments of the variable geometry high-pressure turbine and low-pressure turbine on engine performance were examined in ground take-off, supersonic cruise, and subsonic cruise operating states. The results indicate that in single-bypass mode, a 20% increase in the low- pressure turbine throat area raises ground take-off thrust and supersonic cruise thrust by approximately 2% and 6%, respectively. A cor? responding 20% increase in the high-pressure turbine throat area leads to a slight reduction in ground take-off thrust by about 0.3%, while supersonic cruise thrust increases by approximately 2%. Furthermore, the minimum allowable area of the low-pressure turbine guide vanes and the maximum allowable area of the high-pressure turbine guide vanes are both constrained by fan stability margin. In dual-bypass mode, compared to a conventional turbofan engine, the variable cycle engine achieves a fuel consumption rate improvement of approximately 8% - 9% under subsonic cruise conditions. Within this configuration, the variable geometry low-pressure turbine serves an essential adjustable component for the variable cycle engine. In contrast, whether the high-pressure turbine is variable has a relatively minor impact on fuel consumption rate.

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