access icon openaccess Gas–liquid flow field analysis of the compressor vorticity and rotational speed based on NASA Stage 36

The aero-engine to be cleaned online can significantly improve compressor performance and increase maintenance intervals, but the cleaning online cannot achieve the anticipated effects due to the lack of cognisance of the internal multiphase flow field. In order to explore the characteristics of the compressor's internal flow field, a compressor and nozzle's flow channel model was established based on the data of the Rotor36 compressor blades published by NASA. The fluid simulation software was used to analyse the effects of circumferential vortex and axial vortex on the wall surface at different jet parameters and characteristics of the gas–liquid flow field formed by the compressor blades at different rotation speeds. It is concluded that the flow field formed at a jet pressure of 5 atm and a rotational speed of 2880 rpm is more favourable to the removal of fouling.

Inspec keywords: flow simulation; jets; blades; channel flow; compressors; vortices; aerospace engines; two-phase flow; computational fluid dynamics; nozzles

Other keywords: pressure 5.0 atm; nozzle flow channel; NASA Stage 36; jet parameters; compressor vorticity; rotational speed; gas–liquid flow field analysis; fluid simulation software; internal multiphase flow field; axial vortex; circumferential vortex; Rotor36 compressor blades; aeroengine

Subjects: Aerospace industry; Jets in fluid dynamics; Flows in ducts, channels, and conduits; Rotational flow, vortices, buoyancy and other flows involving body forces; Nozzles; Fluid mechanics and aerodynamics (mechanical engineering); Mechanical components; Engines; Applied fluid mechanics; General fluid dynamics theory, simulation and other computational methods; Multiphase flows

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