Usually, the first stage of a compressor of a gas turbine works in the region of transonic flow, so that the designer has to take into account a lot of flow details like shocks, boundary layer separation and their interaction, when a new machine is defined. Beside other problems the choice of the blade geometry and profile family is one important consideration. For the design of the blades anal...

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...

This article presents a methodology dedicated to the vibration analysis of turbomachine blades accounting for both geometric nonlinearities and nonlinear blade-tip/casing contacts in numerically efficient way through use reduced order models. Contact is handled with Lagrange multipliers equation motion integrated forward time using an explicit central difference integration scheme. Nonlinear in...

Atmospheric air is a commonly used working fluid in turbomachinery. The typically contains certain amount of suspended solid particles, as well water the form vapor or droplets. In current paper, we focus on numerical modeling humid transonic flow this paper demonstrate rarely considered, but presented herein important influence humidity, pollution and liquid content performance first stage gas...

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...

The paper presents the results of one stages creating a model assessing and forecasting operating characteristics transonic compressor due to erosive wear. A numerical stage is constructed verified substantiate its applicability in calculating various degrees blade article contains review basic approaches for turbulence simulation, their application area features connected with 3D-flow simulati...

In order to prolong the service life of multistage axial compressors, it is increasingly important study influence blade surface roughness on compressor performance. this paper, a five-stage real aero-engine was selected as research object, and an equivalent gravel model used based measured data. Furthermore, impact performance at design rotational speed studied by full three-dimensional numeri...

The seal cavity leakage flow has a considerable impact on the performance of aeroengine, especially multistage compressor. Thus, quasi-three-dimensional simulation program named CAM is developed basing circumferentially averaged throughflow method. enables rapid diagnosis for degradation compressor caused by labyrinth wear. coupling field between and main at root shrouded stator high-loading th...

The demands to apply transonic centrifugal compressor have increased in the advanced gas turbine engines. Various techniques are used increase aerodynamic performance of compressor. effects inclined leading edges diffuser vanes a on flow-field unsteadiness and noise generation investigated by solving compressible, three-dimensional, transient Navier–Stokes equations. Diffuser with various incli...