平均载荷系数0.5一级的双模式压气机设计研究与验证

Design and verification of a dual-mode compressor with an average load coefficient of 0.5

关键词:  高负荷压气机  双模式  核心驱动风扇  大攻角  低损失导叶

Key words:  High-load compressor  Dual-mode  Core driven fan stage  Large angle of attack  Low loss guide vane

摘要:

为全面提升压气机的研制能力，本文对平均载荷系数0.5一级的带单双外涵两种模式（双模式）核心驱动风扇的四级压气机开展了设计技术研究与验证。针对其平均级载荷系数高、两个模式性能变化大等特点，开展了双模式高负荷压气机设计、低损失大流量范围导叶设计以及低损失大攻角范围可调静子设计等技术研究工作，并在此基础上完成双模式核心驱动风扇与四级压气机的设计，开展0.8~1.0相对转速的三维特性分析，全面研究单双外涵两种模式下各级的匹配情况。试验结果表明：单双外涵两种模式下，压气机流量、压比、效率达到设计指标。单外涵模式1.0相对转速，最高效率0.874，双外涵模式0.924相对转速，最高效率0.87，两种模式下压气机流量调节范围达到31.4%。各级匹配良好，突破了双模式核心驱动风扇与压气机一体化匹配设计和平均载荷系数0.5一级的高负荷压缩部件设计等关键技术，为下一代发动机的核心压缩部件设计奠定了基础。

Abstract:

To comprehensively improve the development capability of compressor， the design and verification of a four-stage compressor with a single and double-bypass mode （dual-mode） core driven fan stage with an average load coefficient of 0.5 was introduced . It is characterized by high average load coefficient and the large variation of performance of the dual-mode. The design technology of high-load compressor with a dual-mode design point， the design technology of guide vane with low loss and large flow rate range， and the design technology of adjustable stator with low loss and large angle of attack range were studied . The design of a high-load four-stage compressor combined with a dual-mode core driven fan stage was accomplished and the 3D simulation of 80%~100% relative rotating speed was conducted to explore the matching of each stage under the two modes of single and double-bypass. The test results show that the compressor flow rate， pressure ratio and efficiency meet the design index under the single and double-bypass modes. The maximum efficiency of the single-bypass mode is 0.874 at 100% relative rotating speed， and that of the double-bypass mode is 0.87 at 92.4% relative rotating speed. Under the two modes， the compressor flow regulation range reaches 31.4%， which is well matched at all stages. It has broken through the key technologies such as the integrated matching design of dual-mode core driven fan stage and compressor and the design of high-load compressor with an average load coefficient of 0.5. It provides data and method support for the development of the next generation aero engines.