Aquasi-three-dimensional multigrid Navier–Stokes solver on singleandmultiple-passage domains is presented for solving unsteady  ows around oscillating turbine and compressor blades. The conventional direct store method is used for applying the phase-shifted periodic boundary condition over a single blade passage. A parallel version of the solver using the message passing interface standard is ...

The forced vibration of the 2D NASA flutter compressor cascade is numerically simulated in full scale with parallel computation technique. The compressor cascade consists of 9 blades bounded by 2 wind tunnel side walls. The implicit line Gauss-Seidel iteration with dual time stepping is employed. The turbulence is modeled with the Baldwin-Lomax model. A newly developed high resolution efficient...

Ever increasing demand of higher pressure ratio of aero-engine compressors has always been hindered by two distinct aerodynamic instabilities. The first known as surge is; large one dimensional periodic mass flow fluctuation through the compressor, which involves the entire pumping system including compressor, ducting, plenum and throttle. The second is the rotating stall which can be character...

To investigate the influence law and mechanism of relative circumferential position intake struts on unsteady load vibration first stage rotor, 1.5-stage a heavy-duty gas turbine compressor with was numerically simulated. The analysis flow field rotor blade reveals that has little effect aerodynamic performance but obviously changes level blade. When strut inlet guide vane wakes coincide, they ...

~ blade-element theory for aanid--ow compre8sor8has been deoeloped and applied to the anulysi8 of the. effects of basic deeign variabkwvuch as Mach number, blude loading, and mJocily didn”buiion on compree80r performance. A graphi.cul method tlwt ia u8efulfor approximate design cakulati0n8 i8 pre8ented. Tle relati0n8 among 8e8eralefinci48 useful in compressor design are derived and &cu8sed. The...

In this article, we report the design of a reflective intensity-modulated optical fiber sensor for blade tip-clearance measurement, and the experimental results for the first stage of a compressor of an aircraft engine operating in real conditions. The tests were performed in a ground test cell, where the engine completed four cycles from idling state to takeoff and back to idling state. During...