The working process of oil-injected scroll compressor is analysed in this paper. The thermodynamic and dynamic models arc developed for the oil-injected scroll compressor. The property parameters can be calculated under the influences of the leakage and the friction. The results of computer simulation are coincident with the experiment's. so it is useful to predict the compressor performance. I...

Selection of each major type of Reciprocating, Rotary, Centrifugal and axial Compressor is briefly reviewed. It ls explained how the nondimensional scales of Specific Speed and Speclfic Diameter can be used to select any of the above configuration of Compression machinery at its optimum efficiency range. The paper presents the approach of Engineers Constructors in selecting compressors in petro...

One of the possible origins of High Cycle Fatigue in a compressor blade is the rotating stall under the influence of (rotating) inlet pressure or temperature distortion leading to a varying angle of attack on the compressor blades. This paper will be oriented towards the propagation of total pressure and total temperature nonuniformities in axial flow fans and compressors and their subsequent e...

This paper reviews the design of a combination variable I fixed-step port unloader system for moderate capacity refrigeration screw compressors. The general specification of an unloader system to meet application requirements and specific issues of port and flowpath design are discussed. The paper demonstrates use of a comprehensive compressor simulation and a commercial pipe flow analysis prog...

This paper describes an investigation of the aerodynamic performance a Hyperloop pod equipped with axial compressor using CFD simulation. The is expected to reduce drag if operational speed exceeds Kantrowitz Limit (KL). To evaluate effectiveness compressor, two types have been designed: those and without compressor. A validation study was undertaken for supersonic flow around cylindrical body ...

Abstract The aerodynamic performance and pressure ratio of modern aircraft engine compressor are degrading due to unsteady flow distorted loads complex phenomena in the blade tip. This paper attempts improve axial transonic stage under conditions by incorporating combination groove casing, tip injection technique with surface roughness effects. is performed for Mach number ranging between 0.8 1...