REGARDING CERTAIN AERODYNAMIC SOURCES OF NON-STATIONARY FORCE LOADS ON TURBINE PROFILES

The paper deals with selected phenomena present in a blade cascade flow field. The presented research was performed on prismatic blade cascades composed mostly of the tip and root sections of the last stage rotor blade of a large output steam turbine. The unstarted supersonic flow on the cascade inlet, the separation of the flow and the swirl line behind the trailing edge have been identified as the possible sources of the unsteady force effects

Shock wave configuration in a transonic flow through a mid-section of a last stage turbine blade cascade equipped with a part-span connector

This paper deals with the study of a flow field and namely the configuration of shock waves in a blade cascade equipped with a part-span connector called tie-boss. The cascade consists of prismatic blades formed from the mid-section of a very long last-stage blade of a steam turbine. The study is based on numerical simulations of the flow through a cascade that was previously tested in a wind tunnel. Commercial software Ansys CFX was used for the simulations and Ansys ICEM for the mesh generation. The computational domain contains non-homogenous mesh interfaces. The simulations showed that the presence of the tie-boss has a profound effect on the configuration of the shock waves. The blade exit shock waves are disturbed and new lateral shock waves are introduced into the flow

REGARDING CERTAIN AERODYNAMIC SOURCES OF NON-STATIONARY FORCE LOADS ON TURBINE PROFILES

The paper deals with selected phenomena present in a blade cascade flow field. The presented research was performed on prismatic blade cascades composed mostly of the tip and root sections of the last stage rotor blade of a large output steam turbine. The unstarted supersonic flow on the cascade inlet, the separation of the flow and the swirl line behind the trailing edge have been identified as the possible sources of the unsteady force effects

Shock wave configuration in a transonic flow through a mid-section of a last stage turbine blade cascade equipped with a part-span connector

This paper deals with the study of a flow field and namely the configuration of shock waves in a blade cascade equipped with a part-span connector called tie-boss. The cascade consists of prismatic blades formed from the mid-section of a very long last-stage blade of a steam turbine. The study is based on numerical simulations of the flow through a cascade that was previously tested in a wind tunnel. Commercial software Ansys CFX was used for the simulations and Ansys ICEM for the mesh generation. The computational domain contains non-homogenous mesh interfaces. The simulations showed that the presence of the tie-boss has a profound effect on the configuration of the shock waves. The blade exit shock waves are disturbed and new lateral shock waves are introduced into the flow

Topical Problems of Fluid Mechanics 2022

Proceedings consist of papers presented during the conference Topical Problems of Fluid Mechanics 2022. \

Numerická simulace aerodynamické interakce křídla a trupu

In order to investigate and understand extent of the wing-body interaction effects taking place during operation of a particular self-launching sailplane, commercial code Fluent 6.3 was used for numerical simulation of flow past a simplified model of TST-10a. Several methods were used to identify vortex structures originating due to interference effects in this part of the aircraft. 3D effects and distortions of pressure and velocity distributions taking place in the junction of the body and the fuselage were observed

Pneumatic measurements on cascade TR-P-3

The research report deals with results and analysis of pneumatic measurements on the root section of rotor blade 54" (1375mm) in the case of 52 blades in the rotor row

Topical Problems of Fluid Mechanics 2020

Proceedings consist of contributions dealing with both research on various problems in fluid mechanics and mathematical or experimental methods utilizable for solution of such problems

Measurement on Valve II - Appendix

Report contains results and evaluation of pneumatic measurements conducted on the overloading valve system

Experimental Data on High-Speed Flow Past the Root Blade Cascade

The paper deals with experimental results of high-speed aerodynamic research on a blade cascade. The blade cascade represents root section of the last stage rotor blades of large output steam turbine. Basic aerodynamic characteristics of the blade cascade are presented together with photographs of flow fields in the range of transonic flow regimes. Results are analysed and discussed to provide a new knowledge on design and operation of the last rotor at the region of the blade root