Accounting for Unsteady Interaction in Transonic Stages

Rubechini, Filippo; Marconcini, Michele; Giovannini, Matteo; Bellucci, Juri; Arnone, Andrea

doi:10.1115/1.4028667

Cited by 12 publications

(7 citation statements)

References 33 publications

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“…overestimation of the turbine total-to-static efficiency, especially at lower specific speed. Similar conclusions about the diffusivity of the mixing-plane interface in the presence of transonic flows are also reported in other works in the literature [46]. The accuracy of the flow solver of SU2 is also confirmed by the comparison of the averaged flow kinematic quantities measured and computed at the stator and rotor outlet sections (cf.…”

Section: B Apu Turbinesupporting

confidence: 88%

Multistage Turbomachinery Design Using the Discrete Adjoint Method Within the Open-Source Software SU2

Vitale

Pini

Colonna

2020

Journal of Propulsion and Power

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This paper documents a fully turbulent discrete adjoint method for three-dimensional multistage turbomachinery design. The method is based on a duality preserving algorithm and is implemented in the open-source computational fluid dynamics tool SU2. The SU2 Reynolds-averaged Navier-Stokes solver is first extended to treat threedimensional steady turbomachinery flow using a conservative formulation of the mixing-plane coupled to nonreflective boundary conditions. The numerical features of the flow solver are automatically inherited by the discrete adjoint solver, ensuring the same convergence rate of the primal solver. The flow solver is then validated against experimental data available for three turbine configurations, namely, a one-and-half axial turbine stage, a transonic radial turbine coupled to a downstream diffuser, and a supersonic mini-organic Rankine cycle radial turbine operating with a fluid made by a heavy molecule. Finally the adjoint-based optimization framework is applied to the concurrent shape optimization of three rows of the axial turbine, demonstrating the advantages deriving from adopting multirow automated design methods in the context of turbomachinery design.

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Section: B Apu Turbinesupporting

confidence: 88%

Multistage Turbomachinery Design Using the Discrete Adjoint Method Within the Open-Source Software SU2

Vitale

Pini

Colonna

2020

Journal of Propulsion and Power

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“…Other interesting studies on the interaction in transonic turbine are [39][40], where different conditions and geometries are discussed.…”

Section: Stator Shock-rotor Blade Interactionmentioning

confidence: 99%

Stator-Rotor Interaction in Axial Turbine: Flow Physics and Design Perspective

Gaetani¹

2018

Aircraft Technology

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The stator-rotor interaction is an important issue in turbomachinery design when the highest performances are targeted. Different characters mark the interaction process in high-pressure or low-pressure turbines depending both on the blade height and on the Reynolds number. For small blade heights, being the stator secondary flows more important, a more complex interaction is found with respect to the high blades, where the stator blade wake dominates. In low-pressure turbines, the stator wake promotes the transition to turbulent boundary layer, allowing for an efficient application of ultra-high lift blades. First, a detailed discussion of the flow physics is proposed for high-and low-pressure turbines. Some off-design conditions are also commented. Then, a design perspective is given by discussing the effect of the axial gap between the stator and the rotor and by commenting the effects of three-dimensional design on the interaction.

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“…The CFD solver used is the TRAF code ( [16]) in its parallelized version. The numerical setup has been developed in the framework of the collaboration between Ansaldo Energia and the University of Florence.…”

Section: Appendix -Cfd Solvermentioning

confidence: 99%

Rotor tip stall from a designer's perspective

Schneider

Silingardi

Astrua

et al. 2017

European Conference on Turbomachinery Fluid Dynamics and Hermodynamics

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The operating range of a compressor is the most critical aspect to consider when dealing with new designs. Two distinct routes to compressor stall are known in literature: modal-stall that occurs near the peak of the overall characteristic and spike-stall that initiates on the negatively-sloped part of the characteristic curve. Modal type stall can be taken into account from the very beginning during the design process. The basic mechanisms that drive the phenomena are essentially 2D in nature and there are well-established and experimentally validated design criteria available. Unfortunately this statement no longer applies when dealing with spike-type stall. This short length-scale instability is related to a threedimensional breakdown of the flow that appears at rotor tip. Since when firstly observed, much effort has been expended trying to understand the flow features underlying this abrupt stall. Nevertheless, a well-established and validated design criterion is still missing. This paper deals with the topic from a designer's perspective. A discussion which tries to highlight the design variables affecting the spike-stall is presented in the first part of the paper. Then CFD results on core stages of an heavy-duty axial compressor are discussed. The aim is to derive useful considerations for the designer work and discuss which design actions are more effective to successfully complete a spike-stall safe design.

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Accounting for Unsteady Interaction in Transonic Stages

Cited by 12 publications

References 33 publications

Multistage Turbomachinery Design Using the Discrete Adjoint Method Within the Open-Source Software SU2

Multistage Turbomachinery Design Using the Discrete Adjoint Method Within the Open-Source Software SU2

Stator-Rotor Interaction in Axial Turbine: Flow Physics and Design Perspective

Rotor tip stall from a designer's perspective

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