Investigation of the compressible flow through the tip-section turbine blade cascade with supersonic inlet

Luxa, Martin; Příhoda, Jaromír; Šimurda, David; Straka, Petr; Synáč, Jaroslav

doi:10.1007/s11630-016-0844-0

Cited by 12 publications

(11 citation statements)

References 8 publications

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“…The relevant isentropic outlet Mach number in the traversing plane is M2is = 1.97 and the isentropic outlet Reynolds number Re2is = 1.9810 6 . Numerical results were compared with results of optical and pressure measurements, see Luxa et al [13,14].…”

Section: Resultsmentioning

confidence: 99%

Effect of inlet turbulence on compressible flow through the tip-section turbine blade cascade with supersonic inlet

Straka¹,

Příhoda

Fenderl

et al. 2018

MATEC Web Conf.

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Abstract. The contribution deals with the numerical simulation of 2D compressible flow though the tip-section turbine blade cascade with the supersonic inlet boundary conditions. The simulation was carried out by the in-house numerical code using the explicit algebraic Reynolds stress model completed by the bypass transition model with the algebraic equation for the intermittency coefficient. The -Re model implemented in the commercial code Fluent was used for the comparison. Predictions carried out for the nominal conditions were focused on the effect of inlet free-stream turbulence on the flow structure in the blade cascade under supersonic inlet conditions. Numerical results were compared with experimental data.

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Section: Resultsmentioning

confidence: 99%

Effect of inlet turbulence on compressible flow through the tip-section turbine blade cascade with supersonic inlet

Straka¹,

Příhoda

Fenderl

et al. 2018

MATEC Web Conf.

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“…The inner branch of the inlet shock wave on the right image does not collide with the adjacent blade at all, however it can still affect the area of near wake. The shift of the shock wave shape does not have any measurable influence on the time averaged flow field parameters [2]. The effect of this phenomenon must be investigated quantitatively to assess the induced stress in the blade.…”

Section: Unstarted Supersonic Flowmentioning

confidence: 99%

Regarding Certain Aerodynamic Sources of Non-Stationary Force Loads on Turbine Profiles

Radnic¹,

Luxa²,

Šimurda³

2018

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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.

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“…Insufficient or negative gradient of static pressure along the suction side in the point just upstream of the interaction is typical for studied geometries of these tip profiles. According to the CFD simulations that were carried out by Straka and Příhoda [4], the boundary layer transition takes place commonly upstream the point of interaction (see Fig. 11).…”

Section: Interaction With the Boundary Layer On The Suction Sidementioning

confidence: 99%

Shock Wave Boundary Layer Interaction in Profile Cascades Representing Rotor Bladings of the Last Stage of Large Output Steam Turbines

Luxa¹,

Šimurda²,

Příhoda³

et al. 2016

Proceedings of the VII European Congress on Computational Methods in Applied Sciences and Engineering (ECCOMAS Congress 2016)

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This paper is mainly focused on selected interaction phenomena occurring in the root, middle and tip section of the last stage rotor blading consisting of titanium blades Doosan Skoda 1375mm (54") and steel blades Doosan Skoda 1220mm (48"). Measurements and CFD simulations of the flow in selected sections along the blading radius show different types of interaction. Typically for the parts of the blade closer to the hub, only interaction of internal branch of exit shock wave with the suction side boundary layer takes place. At the blade tip where the flow is supersonic at both inlet and outlet, interaction of internal branch of inlet shock wave with the pressure side boundary layer occurs. The "reflected", additional shock wave arising from this interaction affect the flow field close to the suction side of the adjacent profile. The structure of interaction often depends on the flow conditions (nominal conditions and off-design conditions of flow, incl. different inlet flow angles).

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Investigation of the compressible flow through the tip-section turbine blade cascade with supersonic inlet

Cited by 12 publications

References 8 publications

Effect of inlet turbulence on compressible flow through the tip-section turbine blade cascade with supersonic inlet

Effect of inlet turbulence on compressible flow through the tip-section turbine blade cascade with supersonic inlet

Regarding Certain Aerodynamic Sources of Non-Stationary Force Loads on Turbine Profiles

Shock Wave Boundary Layer Interaction in Profile Cascades Representing Rotor Bladings of the Last Stage of Large Output Steam Turbines

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