The goal of this project is to report on some computational investigations about the return flow passages. The return flow channel provides the connection and carries the flow between two stages of a multistage centrifugal compressor. Of course, deswirl vanes are indispensable between the inlet and outlet section, because usually the inlet flow angle, which comes from the impeller, is 70◦ − 75◦...

Significance of the Problem Control of blade-tip clearance in the compressor and turbine sections of gas turbine engines can improve efficiency, minimize leakage flow, and shorten engine development time. Tip clearance varies throughout different operating conditions (e.g., start-up, idle, full power, shut-down) because of different radial forces and different thermal expansion coefficients and...

This study investigates the aerodynamic and aeroelastic characteristics of a transonic axial compressor, focusing on blade count reduced rotor behavior. The analysis is based experiments, conducted at Transonic Compressor Darmstadt test rig Technical University compulsory simulations. In order to obtain measurement data for detailed investigation, extensive steady unsteady instrumentation was a...

Abstract Aeronautical compressor fans currently operate with minimal blade-casing clearance. This therefore makes the occurrence of rub events very likely. Under specific circumstances, blade undergoes excessive amplification contact-induced oscillations, called hereafter divergence, which can be critical for structural integrity engine. paper proposes an investigation mechanisms responsible di...

Blade-surface boundary layer and wake computational models for estimation of axial-flow compressor and fan blade-row fluid turning angles and losses " (1978). Retrospective Theses and Dissertations. Paper 6457. INFORMATION TO USERS This material was produced from a microfilm copy of the original document. While the most advanced technological means to photograph and reproduce this document have...