Rotor Blade Sweep Effect on the Performance of a Small Axial Supersonic Impulse Turbine

Jeong, Sooin; Choi, Byoung-Ik; Kim, Kui-Soon

doi:10.5139/ijass.2015.16.4.571

Cited by 4 publications

(2 citation statements)

References 13 publications

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“…In 2015, Neshat et al [19] investigated the simultaneous effects of the sweep and lean of the blades in one stage of a transonic compressor on its performance. The numerical results indicated that the backward sweep rotor blade increased the stage efficiency by 0.5% at design conditions, while the stall margin reduces, and the chocking mass flow rate diminished by 1.5%.…”

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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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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“…Pullan and Harvey (2008) and Yoon et al (2014) achieved the same results for axial flow turbines. Jeong et al (2015) numerically showed that backward sweep provided up to 1% efficiency increasing compared with the baseline. However, preliminary results obtained in the previous part of the paper did not show any positive effect of a backward sweep for the axial impulse turbine with axisymmetric nozzles.…”

Section: Introductionmentioning

confidence: 98%

Effects of hub endwall geometry and rotor leading edge shape on performance of supersonic axial impulse turbine. Part II: Method validation and final results.

Sebelev

Smirnov

Боровков

et al. 2019

European Conference on Turbomachinery Fluid Dynamics and Hermodynamics

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The present paper continues the investigation started in Part I. The basic turbine stage remains the same as in Part I (an axial turbine stage with axisymmetric nozzles and mean diameter 103.5 mm). The numerical simulation method used in Part I was corrected by adding analytical correlation for disc friction losses. This approach was validated on the base of the experimental data for a geometrically close turbine. Variation of the radial velocity component at the rotor inlet was proposed as a new modification compared with Part I. The mathematical formulations of the rotor blade sweep and radial velocity component at the rotor inlet were proposed. The new modifications of the baseline were provided to establish the effects of the rotor blade sweep, velocity radial component at the rotor inlet and hub endwall contouring separately. The using of backward swept rotor blades together with the positive cinematic lean provided efficiency increasing up to 2.9% at the design conditions. It was also established that absence of a velocity radial component at the rotor inlet in the model with backward swept blades leads decreasing of the turbine performance. Axisymmetric hub contouring provided up to 1.9% efficiency growth at the part-load operation.

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Effect of Centrifugal Force on Gas Flow in a Supersonic Turbine

Kanda

Nakai

Inagaki

et al. 2022

Journal of Engineering for Gas Turbines and Power

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The flow condition between the rotor blades of a liquid rocket engine supersonic turbine was studied experimentally and numerically. The entrance Mach number was 1.94, and the turning angle of the blades was 120&#176;. A shock wave was created at the leading edge of the blade, and the Mach number in the passage between the blades decreased to around unity. A similar deceleration has been reported in several past studies. It was found that centrifugal force created the shock wave at the leading edge, reducing both the Mach number and total pressure. This phenomenon is characteristic of high-speed blades with large turning angles. The Mach number in the passage was restricted when the mass flow rate was specified under the specified passage configuration. A convergent-divergent configuration of the passage between the blades suppresses the performance degradation of supersonic turbines.

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Rotor Blade Sweep Effect on the Performance of a Small Axial Supersonic Impulse Turbine

Cited by 4 publications

References 13 publications

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

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

Effects of hub endwall geometry and rotor leading edge shape on performance of supersonic axial impulse turbine. Part II: Method validation and final results.

Effect of Centrifugal Force on Gas Flow in a Supersonic Turbine

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