Aerodynamics of inter-spool duct under the influence of an upstream transonic compressor stage

Kumar, Lakshya; Alone, Dilipkumar Bhanudasji; Pradeep, A. M.

doi:10.1016/j.ast.2023.108282

Cited by 3 publications

(1 citation statement)

References 10 publications

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“…The present investigation is aligned in a similar direction to investigate the transonic flow features such as shock structure, tip leakage flow, and shock boundary layer interaction in an axial flow rotor. This transonic rotor is part of a research compressor stage at the Propulsion Division, CSIR-NAL [16][17] . The technical details are given in Table 1.…”

Section: Introductionmentioning

confidence: 99%

Investigation of Transonic Flow Features in an Axial Flow Compressor Rotor

Kumar,

Alone,

Pradeep

et al. 2024

Def. Sc. J.

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Numerical investigation of an axial flow rotor is carried out for its performance characterization and aerodynamic behavior during the design and off-design operating conditions. The study focuses on capturing the transonic flow features from the choke point (CP) to the near stall (NS) point in the rotor. This includes the analysis of passage shock structure, its movement in the blade passage with varying back-pressure, shock boundary layer interaction, tip leakage flow structure, and resulting losses. The study is carried out from 60 % to 100 % of the design speed using steady and unsteady RANS simulations. Three turbulence models, namely; SST, k-ε, and Reynolds stress models, are employed. The SST model predicted the closest approximation to the experimental data. The rotor aerodynamic performance is predicted in terms of total pressure ratio, efficiency, and flow contours. Unsteady analysis revealed that the primary and secondary tip leakage vortices, combined with the suction side tip corner separation, are the major instabilities near the stall region.

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Section: Introductionmentioning

confidence: 99%

Investigation of Transonic Flow Features in an Axial Flow Compressor Rotor

Kumar,

Alone,

Pradeep

et al. 2024

Def. Sc. J.

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Evolution of unsteady secondary flow structures near the onset of stall in a tip-critical transonic axial flow compressor stage

Kumar,

Alone,

Pradeep

2023

Physics of Fluids

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The aerodynamic stability of an axial compressor stage depends on the rotor and stator. However, due to the specific design requirements, the evolving flow field and the resulting secondary flow structures are different in both components. This study investigates the evolution of dominant secondary flow structures occurring in the rotor and stator of a tip-critical transonic compressor stage at the near-stall condition using unsteady numerical analysis and validates performance characteristics with the experimental data. The investigation reveals that the presence of rotor tip shock creates a large difference in the pressure gradient across the pressure surface and the suction surface, intensifying tip leakage flow and shock-induced boundary layer separation. The higher incidence angle near the hub leading edge creates a local separation and reattachment zone. The radial pressure gradient causes the low momentum flow from this local separation zone to migrate radially upward. This migrated flow interacts with the tip leakage flow and separated blade boundary layer, eventually creating a colossal recirculation zone and subsequent rotor blockage of around 46%. The increasing streamwise adverse pressure gradient pushes the tip shock upstream, and at the onset of the stall, the flow directly separates from the rotor leading edge avoiding the shock formation. The stator flow field is dominated by the asymmetric hub corner separation induced by the streamwise adverse pressure gradient and the tip corner separation caused by the vortex structures convected downstream from the rotor tip region leading to stator blockage of around 48%. Along with the blade passing frequency, four other dominating frequencies (0.06×BPF, 0.12×BPF, 0.44×BPF, and 0.84×BPF) related to the aerodynamic instabilities are observed at the inception of stall.

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A study of the effect of curvature and pressure gradient on aerodynamics performance and turbulence structure of S-shaped compressor transition duct

Sharma¹,

Baloni

2023

Australian Journal of Mechanical Engineering

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Aerodynamics of inter-spool duct under the influence of an upstream transonic compressor stage

Cited by 3 publications

References 10 publications

Investigation of Transonic Flow Features in an Axial Flow Compressor Rotor

Investigation of Transonic Flow Features in an Axial Flow Compressor Rotor

Evolution of unsteady secondary flow structures near the onset of stall in a tip-critical transonic axial flow compressor stage

A study of the effect of curvature and pressure gradient on aerodynamics performance and turbulence structure of S-shaped compressor transition duct

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