Effect of blade sweep on inlet flow in axial compressor cascades

Chang, Hao; Zhu, Fuguo; Jin, Donghai; Gui, Xingmin

doi:10.1016/j.cja.2014.12.023

Cited by 21 publications

(8 citation statements)

References 22 publications

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“…The findings further showed that there are two distinct stages in the stall evolution: the part span stall and the global stall correlated with the axisymmetric and asymmetric disruptions and the paper addressed the causes of these stalls. Chang et al [13] delved the influence of blade sweep in axial compressor cascades on inlet flow, and a sequence of sweeping and straight cascades was designed for this intent. The measurements are carried out with NUMECA International's finite-volume dependent Reynolds-Averaged Navier -Stokes FINE Turbo solver.…”

Section: Literature Reviewmentioning

confidence: 99%

Design of Multi-Stage Axial Flow Compressor and Validation using Numerical Simulations

D.*,

A.G.

2019

IJITEE

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The optimum yield of gas turbine engines has so far been driven on and around the operational efficiency of the compressor and in essence around the efficiency of the compressor blade. The efficacy of a compressor is ascertained substantially by the smoothness of the air flowing through it. In this present work, a multi-stage axial compressor in the Turbojet engine with an application for propulsion is designed based on thermodynamic calculations. The calculations were carried out employing the principles of thermodynamics, and aerodynamics along the mean streamline based on the technique of a velocity triangle in the lack of inlet guide vanes. The coordinates for the blade profile has been calculated on and around the premise of the calibrated blade base profile. The model for the seven-stage axial flow compressors based on thermodynamic calculations was devised and analyzed utilizing computational fluid dynamics methodology. The multiple reference frame approach was used to represent the impact of both rotating and stationary components and the simulation for the first stage was conducted using a periodic approach. For the intent of the verification, a comparison was made between the analytical values and the simulated values and the variation between these values was found to be 16.7%. Validation results demonstrate that the proposed method is valid and can be used for multi-stage axial compressor design and performance evaluation.

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Section: Literature Reviewmentioning

confidence: 99%

Design of Multi-Stage Axial Flow Compressor and Validation using Numerical Simulations

D.*,

A.G.

2019

IJITEE

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“…The results indicate that blade sweep does affect inlet radial equilibrium, such as blade camber angles, solidity. Halder et al [21] researched an unswept blade and a 10 ∘ backward-swept blade, respectively. It was found that the backward-swept blade strongly affects the blade stall margin.…”

Section: Mathematical Problems In Engineeringmentioning

confidence: 99%

Axial‐Swept Influence on Inner Flow Performance of HP Steam Turbine Based on CFD

Feng

Guo

Wei

et al. 2019

Mathematical Problems in Engineering

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Swept blade technology was used to redesign the supercritical steam turbine sets that could improve the inner-efficiency of turbine sets and decrease the consumption of coal the noxious gas such as NOx. The eighth high-pressure stages, including static and rotor cascades, were selected as tested prototypes that were blew in the low-velocity wind tunnel. We used the five-hole ball head needle to measure the aerodynamic parameters distribution along the width and span direction of the high-pressure stage cascades. With the inkblot display technology, the limit flow spectrums were displaced in the blade surface and the endwalls. These tested data could be used to check the simulation results of CFD software. To improve the efficiency of the steam turbine high-pressure (HP) stage, we selected the supercritical steam turbine HP stage cascade blade as the prototype to research into its inner flow performance of the axial-swept blade by the CFD software. Two different redesigned blades, with ±20°, swept angle, and 30% swept height, named axial fore-swept and axial aft-swept, were built up. The stage passages flow field of the prototype blade, and the two redesigned swept blades were simulated using CFD software with stage interface planes between the stages. The CFD simulation results indicated that the leading edge of swept blades influenced the inlet flow field; the pressure in aft-swept blade stage in both endwalls was higher than in the middle and was beneficial to improve the passage flow properties of HP stage. But for the fore-swept HP stage, its pressure distribution was lower in both endwalls than in the middle and not beneficial to passage flow.

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“…[1][2][3][4][5][6][7][8][9][10][11] Compressor cascade is a simplified model of real axial compressor stator blade and has been widely applied to researching the mechanism and control of corner separation, as well as the compressor tip clearance flow structures and effects of threedimensional compressor blades. 12,13 Active flow control methods, such as boundary layer suction, [14][15][16] flow blowing, 17,18 plasma flow control 19,21 etc, have been applied to the control of compressor cascade corner separations over years. Meanwhile, the application of passive flow control methods, such as vortex generator, [22][23][24] endwall contouring 25 etc, as well as combination of passive and active control methods, 26 for corner separation control have been investigated with great efforts.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation on a high subsonic compressor cascade flow

Zhang

et al. 2015

Chinese Journal of Aeronautics

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With the aim of deepening the understanding of high-speed compressor cascade flow, this paper reports an experimental study on NACA-65 K48 compressor cascade with high subsonic inlet flow. With the increase of passage pressurizing ability, endwall boundary layer behavior is deteriorated, and the transition zone is extended from suction surface to the endwall as the adverse pressure gradient increases. Cross flow from endwall to midspan, mixing of corner boundary layer and the main stream, and reversal flow on the suction surface are caused by corner separation vortex structures. Passage vortex is the main corner separation vortex. During its movement downstream, the size grows bigger while the rotating direction changes, forming a limiting circle. With higher incidence, corner separation is further deteriorated, leading to higher flow loss. Meanwhile, corner separation structure, flow mixing characteristics and flow loss distribution vary a lot with the change of incidence. Compared with low aspect-ratio model, corner separation of high aspect-ratio model moves away from the endwall and is more sufficiently developed downstream the cascade. Results obtained present details of high-speed compressor cascade flow, which is rare in the relating research fields and is beneficial to mechanism analysis, aerodynamic optimization and flow control design.

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Effect of blade sweep on inlet flow in axial compressor cascades

Cited by 21 publications

References 22 publications

Design of Multi-Stage Axial Flow Compressor and Validation using Numerical Simulations

Design of Multi-Stage Axial Flow Compressor and Validation using Numerical Simulations

Axial‐Swept Influence on Inner Flow Performance of HP Steam Turbine Based on CFD

Experimental investigation on a high subsonic compressor cascade flow

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