Effect Of Tip Clearance And Rotor-stator Axial Gap On Axial Compressor Performance

The purpose of this work is to add to the existing knowledge in relation to tip clearance and rotor-stator axial hole on the performance of the engine particularly the faster equipment parts that include the enthusiasts or compressors. Different kinds of complex three-dimensional CFD models have been created with transonic compressor degree (for example NASA stage 37). The present study is concerned with the impact of rotor tip clearance on the level of a transonic axial compressor. Due to the rotation of the blades of the rotor while the stator blades are fixed, the float subject on this equipment is very much in relative motion hence unstable. In addition, there is a range of/post technological effects on the device in the form of tips clearances, blade complexity, and differences in axial distance between stator and rotor. It is therefore one of the most difficult exercises that a CFD professional can embark upon – namely, to analyze a complex, highly swirling flow regime within a compressor. The NASA 37 transonic axial compressor degree with a rotor tip clearance of 0. 5mm is studied with computational tools through numerical simulations with the aid of the ANSYS CFX software suite. For the first stage, Rotor–Stator, all the simulations were done. The experimental study and the assessment of the standard performance parameters derived through modelling of tip clearance were seen to align fairly well with each other.