Heat pumps with rotary compressors operating in low temperature ambient will face heavy performance degradation. A novel vapor injection structure on the blade for the rotary compressor has been proposed in this paper to overcome the back-flowing drawback of the traditional cylinder injection structure and enlarge the injection area. Based on a verified numerical model, the performance of a rot...

The derivation of a compressor characteristic, and the experimental validation of a dynamic model for a variable speed centrifugal compressor using this characteristic, are presented. The dynamic compressor model of Fink et al. is used, and a variable speed compressor characteristic is derived by the use of energy transfer and loss analysis. It is demonstrated that taking into account the losse...

Manufacturing of aero-engine components has been improvised over the years, commensurate with technological developments in the aeronautics sector. Compressor blade plays a vital role in an aircraft engine and flaws in its production can have adverse impacts on the performance of an aero engine. Despite technological advancements, many defects arise in these single crystal blades, which are man...

In This paper, a parametric study of compressor performances was performed by streamline curvature method (SLC). Effects of three input parameters in design process, e.g., number of blades, distribution of blade thickness, and blade sweep angels, on the main objective parameters in aerodynamic design, e.g., velocity distribution, efficiency and pressure ratio, has been investigated in the param...

April 10-15, 2016 Abstract A whole-annulus unsteady numerical simulation is carried out to investigate the mechanism of the rotating stall in a 1.5-stage low-speed axial-compressor. By comparing the experimental and numerical results, the numerical results are validated. The numerical simulation captures the most features of the rotating stall of the 1.5-stage compressor observed from the exper...

The objective of the Stanford ASC project is to develop a framework able to perform multi-disciplinary, integrated simulations on massively parallel platforms. 4 This paper focuses on the turbomachinery computation and, in particular, on the physics of interaction of different turbomachinery components in the engine. Typical flow features such as tip and horse-shoe vortices as well as blade wak...

In axial flow compressor, blade surface roughness is affected by many failure modes such as fouling, erosion, corrosion and foreign object damage. But with development of filter performance, particles with diameter larger than 2 μm cannot enter into compressor, so fouling is the most important influence factor which results in the variation of surface roughness. This study respectively discusse...

A novel parametric control method for the compressor blade, full-blade surface method, is proposed in this paper. Compared with traditional has good smoothness and construction convenience while maintaining low-dimensional characteristics, compared semi-blade a larger degree of geometric deformation freedom can account changes both suction pressure surface. only four more parameters each so it ...

This article explores the simulation of stall phenomena in axial compressor blade rows. The approach is based on the numerical solution of the compressible, two-dimensional Navier-Stokes equations. The results of both unforced and forced low-speed rotor stall are presented. In unforced cases, substantial ow separation is observed before the maximum pressure rise operating point is reached. Thes...

A stage-by-stage wet-compression theory and algorithm have been developed for overspray and interstage fogging in the compressor. This theory and algorithm are used to calculate the performance of an 8-stage compressor under both dry and wet compressions. A 2D compressor airfoil geometry and stage setting at the mean radius are employed. Six different cases with and without overspray have been ...