Design and Test of a Small, High Pressure Ratio Radial Turbine
Design and Test of a Small, High Pressure Ratio Radial Turbine
复制标题
DOI：
10.1115/1.2836651
复制
发表时间：
1994-06
影响因子：
1.7
通讯作者：
Anthony C. Jones
中科院分区：
文献类型：
--
作者：
Anthony C. Jones
本文介绍了转子叶尖直径为4.58英寸的向心涡轮机的气动设计和台架试验。单级涡轮机设计用于Sundstrand动力系统（SPS）T-100多用途小型动力装置（MPSPU）。T-100是一种小型、单轴、简单循环燃气涡轮机发动机，用于机载、车载和地面辅助动力应用。发动机的额定功率输出为50马力，在最小修改的情况下可以增长到100马力。发动机的燃油消耗率目标要求很高，因此涡轮机的效率目标要求在膨胀比为5.7：1、流量为0.73 lb/s时达到87%的静态总效率（指排气扩压器出口）。详细的设计方法，以及涡轮驱动装置的测试结果。结果包括整个级的测绘和转子出口调查。
This paper describes the aerodynamic design and rig test of a radial inflow turbine having a rotor tip diameter of 4.58 inches. The single-stage turbine was designed for use in the Sundstrand Power Systems (SPS) T-100 Multipurpose Small Power Unit (MPSPU). The T-100 is a small, single-shaft, simple-cycle gas turbine engine intended for airborne, vehicular, and ground-based auxiliary power application. Nominal power output of the engine is 50 hp, with growth capability to 100 hp with minimal modification. Aggressive specific fuel consumption goals for the engine led to a demanding turbine efficiency target of 87 percent total to static, referred to exhaust diffuser exit, at an expansion ratio of 5.7:1 and a flow rate of 0.73 Ib/s. Details of the design approach are given, together with test results from the turbodrive rig. The results include overall stage mapping and rotor exit surveys.