一种微型燃气轮机核心机工程设计及分析

DESIGN AND PRELIMINARY PERFORMANCE ANALYSIS OF AN MICROTURBINE CORE ENGINE

高效微型燃气轮机发电机组可用于航空、航天等领域,还可用于分布式发电、军用车辆辅助动力装置、车用混合动力装置等,因此研究这种动力装置有很重要的实用意义。介绍了一种微型燃气轮机核心机设计过程。这种微型燃气轮机由单级离心压气机、折流环形燃烧室、单级轴流涡轮组成。离心压气机采用进口带导叶、出口带有叶扩压器形式。转子轴采用1-0-1支撑方案。为了解决均匀燃烧问题,采用了甩油盘的供油方式。给出了主要设计参数,对设计的微型燃气轮机进行了初步的性能分析。

High-efficiency micro-turbine electrical-power generation' may be used in aeronautical and astronautical field. Meanwhile, it may also be used in the distributed generation market and as the auxiliary power unit of armored vehicles. This paper outlines the design process about a microturbine core engine. The core engine consists of single-stage centrifugal compressor, single-stage axial flow turbine, annular radial-axial combustor. Inlet guide vanes and discharge vaned diffuser are designed in the compressor. The single shaft rest on the bearings arranged 1-0-1 scheme. Sling system is used in order to improve the atomization quality and realize uniformity combustion. The major performance parameters and preliminary performance analysis of the core engine are also illustrated in the paper.