This paper presents a framework for multi-objective and multidisciplinary design optimization using highfidelity analysis tools. In this framework the aerodynamic performance is evaluated based on a Navier–Stokes equation solver, and the structure dynamics is computed using commercially available finite element software. We employ a genetic algorithm as a robust design optimization tool to faci...

Control and Modeling for stall and surge phenomenon in axial flow compressors have received great importance in recent times. In power generation plant and aerospace propulsion compression system are prone to the aerodynamic instabilities of stall and surge. In aero engine compressors higher pressure ratio has always been a growing stipulates which has over involved by diverse rotating stall an...

Unsteady numerical simulation of single passage was carried out on NASA Rotor 35 to study the influence radial inclined angle self-circulation casing treatment (SCT) performance and stability a transonic compressor at 100% design speed. The angles were set 0°(D0), °(D30) 60°(D60), respectively. calculated result indicates an increase in stall margin improvement (SMI) efficiency (DEI) as increas...

To reduce the negative impacts of stall and surge on compressor performance, a novel combined casing treatment (CCT) structure with axial skewed slots injection groove is proposed in this paper. The aerodynamic as well mechanisms loss generation, transonic NASA Rotor 67 are investigated numerically. simulation results indicate that, compared individual method, CCT works effectively regard to op...

Highly three–dimensional and complex flow structures are closely related to the aerodynamic losses occurring in transonic axial–flow compressor. The large eddy simulation (LES) approach was adopted study performance of NASA rotor 37 for cases at design, near stall (NS), choke (NC) rate. internal vortex topology analyzed by Q–criterion method, omega (Ω) identification Liutex method. It observed ...

In this paper it is attempted to investigate the behavior of an inviscid flow in the meridional plane of an axial flow compressor. For this purpose the 3-D unsteady Euler equations in cylindrical coordinate are averaged in tangential direction. Therefore, the equations are reduced to a 2-D system. By averaging the tangential component of momentum equation, a blade force will result. Axial and r...

Back-to-back testing has been done using NASA fan rotor 67 in the Glenn Research Center W8 Axial Compressor Test Facility. The rotor was baseline tested with a normal industrial RMS surface finish of 0.5-0.6 μm (20-24 microinches) at 60, 80 and 100% of design speed. At design speed the tip relative Mach number was 1.38. The blades were then removed from the facility and ultrapolished to a surfa...