Sand ingestion test and performance degradation evaluation of turboshaft engine

被引：0

作者：

Liu W. ^{[1
]}

Zhang Y. ^{[1
]}

机构：

[1] Naval Aeronautical University, Aviation Foundation College, Shandong, Yantai

来源：

Hangkong Dongli Xuebao/Journal of Aerospace Power | 2023年 / 38卷 / 01期

关键词：

damage mechanism; evaluation model; sand ingestion test; sand protection; turboshaft engine;

D O I：

10.13224/j.cnki.jasp.20210283

中图分类号：

学科分类号：

摘要：

In order to grasp the effect of sand and dust erosion on the turboshaft engine, the differences and applicability of the sand ingestion test terms at home and abroad were analyzed. The sand ingestion test of a turboshaft engine was implemented and investigated. A rapid test data evaluation model of turboshaft engine was established based on the aero-thermodynamic equations and engine matching constraint. The method was used to evaluate the performance degradation of overall unit and components, which was validated using data from other references. The results indicated that the power and fuel consumption rate degradation presented a quadratic function law. The output power degradation was 10.2% and specific fuel consumption degradation was 3.2% after 10 h of sand ingestion. The chord length of the compressor first stage blade became shorter by 0.7%− 3.4% and the thickness was reduced by 1.0%− 3.0%, which resulted in the compressor flow rate decrease by 4.1%, the efficiency decrease by 3.1% and the pressure ratio decrease by 4.5%. The turbine cooling hole had slight blockage and ablation, the cooling air volume was reduced by 1.5%, and the gas turbine efficiency was reduced by 0.5%. The power turbine efficiency had a slight improvement due to blade smoothness. © 2023 BUAA Press. All rights reserved.

引用

页码：127 / 133

页数：6

共 21 条

[1] HERMAN R，, OWCZARZAK J，, MUSALLAM Y., Early performance assessment of bradley and abrams[R], (1992)
[2] COLUCCI F., Advanced coatings protect helicopter engines from compressor erosion to save lives and money, (2004)
[3] RAPP G C，, ROSENTHAL S H., Problems and solutions for sand environment operation of helicopter gas turbines, (1968)
[4] BOJDO N，, FILIPPONE A., Fabric filter performance for helicopter inlet barrier filters, (2012)
[5] BOJDO N，, FILIPPONE A., Comparative study of helicopter engine particle separators, (2014)
[6] FILIPPONE A，, BOJDO N., Turboshaft engine air particle separation, Progress in Aerospace Sciences, 46, pp. 224-245, (2010)
[7] BOJDO N，, FILIPPONE A., Operational performance parameters of engine inlet barrier filtration systems for rotorcraft, (2011)
[8] RHEE D H, LIM B J, AHN I K., Effect of sand and dust ingestion on small gas turbine engines, The Korean Society of Mechanical Engineers, 38, 8, pp. 791-796, (2012)
[9] MURUGAN D M，, GHOSHAL D A，, WALOCK D M，, Et al., Mi-crostructure based material sand particulate interactions and assessment of coatings for high temperature turbine blades, (2017)
[10] DUNN M G, PADOVA C, MOLLER G E., Performance deterioration of a turbofan and a turbojet engine upon exposure to a dust environment, Gas Turbines Power, 109, 3, pp. 336-343, (1987)

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