| Effects of Various Geometric Features on the Performance of a 7:1 Pressure Ratio Deeply Scalloped and Split Radial Turbine in a Gas Turbine Engine |
| |
| 作者姓名： | GAO Chuang HUANG Weiguang |
| |
| 作者单位： | Shanghai Advanced Research Institute,Chinese Academy of Sciences,Shanghai 201210,China;University of Chinese Academy of Sciences,Beijing 100049,China |
| |
| 基金项目： | This work was supported by the Key Programs of Chinese Academy of Sciences under Project No.ZDRW-CN-2017-2;Innovation Academy of Light-duty Gas Turbine with Project No.CXYJJ19-ZD-01;Changde Institute for Integrated Energy Technology with Project No.El6429ICO 1. |
| |
| 摘 要： | A 2 MW gas turbine engine has been developed for the distributed power market.This engine features a 7:1 pressure ratio radial inflow turbine.In this paper,influences of various geometry features are investigated including turbine tip and backface clearances.In addition to the clearances,the effects of the inducer deep scallop and exducer rounded trailing edge are investigated.Finally,geometric features associated with a split rotor(separate inducer and exducer)are studied.These geometry features are investigated numerically using CFD.Part of the numerical results is also compared to experimental data acquired during engine test to validate the CFD results.
|
| 关 键 词： | radial turbine high pressure ratio SCALLOP LEAKAGE CLEARANCE |
Effects of Various Geometric Features on the Performance of a 7∶1 Pressure Ratio Deeply Scalloped and Split Radial Turbine in a Gas Turbine Engine |
| |
| GAO Chuang,HUANG Weiguang.Effects of Various Geometric Features on the Performance of a 7:1 Pressure Ratio Deeply Scalloped and Split Radial Turbine in a Gas Turbine Engine[J].Journal of Thermal Science,2022,31(1):25-34. |
| |
| Authors: | GAO Chuang HUANG Weiguang |
| |
| Abstract: | A 2 MW gas turbine engine has been developed for the distributed power market.This engine features a 7:1 pressure ratio radial inflow turbine.In this paper,influences of various geometry features are investigated including turbine tip and backface clearances.In addition to the clearances,the effects of the inducer deep scallop and exducer rounded trailing edge are investigated.Finally,geometric features associated with a split rotor(separate inducer and exducer) are studied.These geometry features are investigated numerically using CFD.Part of the numerical results is also compared to experimental data acquired during engine test to validate the CFD results.Results indicated that for this specific turbine,the influences of the exducer radial tip clearance,inducer axial tip clearance,and even scalloped blade backface clearance all have negligible influences on performance.In all cases,1％ increase in clearance only attributes to approximately a 0.1％ lower efficiency.This finding is very different from former published papers with low pressure ratio turbines,indicating different flow physics apply for a turbine with a relatively high-pressure ratio. |
| |
| Keywords: | radial turbine high pressure ratio scallop leakage clearance |
| 本文献已被 维普 万方数据 等数据库收录！ |
