Experimental Study of Effects of Bowed Blade on the Flow Field in a Cantilevered Stator Passage

Luo, Junhui; Hu, Jun; Wang, Zhiqiang; Tu, Baofeng

doi:10.1115/gt2014-25766

Cited by 5 publications

(4 citation statements)

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“…Many studies [10][11][12][13][14] have shown that curved blades which have been matched reasonably well have good results in restraining the flow separation. At present the amount of researches concerning the transition phenomenon in curved compressor cascades is small.…”

Section: Introductionmentioning

confidence: 97%

Investigation of Positively Curved Blade in Compressor Cascade Based on Transition Model

Chen

Lan

Zhou

et al. 2016

International Journal of Turbo &Amp; Jet-Engines

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Experiment and numerical simulation of flow transition in a compressor cascade with positively curved blade is carried out in a low speed. In the experimental investigation, the outlet aerodynamic parameters are measured using a five-hole aerodynamic probe, and an ink-trace flow visualization is applied to the cascade surface. The effects of transition flow on the boundary layer development, three-dimensional flow separation and aerodynamic performance are studied. The feasibility of a commercial computational fluid dynamic code is validated and the numerical results show a good agreement with experimental data. The blade-positive curving intensifies the radial force from the endwalls to the mid-span near the suction surface, which leads to the smaller scope of the intermittent region, the lesser extents of turbulence intensity and the shorter radial height of the separation bubble near the endwalls, but has little influence on the flow near the mid-span. The large passage vortex is divided into two smaller shedding vortexes under the impact of the radial pressure gradient due to the positively curved blade. The new concentrated shedding vortex results in an increase in the turbulence intensity and secondary flow loss of the corresponding region.

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Section: Introductionmentioning

confidence: 97%

Investigation of Positively Curved Blade in Compressor Cascade Based on Transition Model

Chen

Lan

Zhou

et al. 2016

International Journal of Turbo &Amp; Jet-Engines

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“…In addition, non-uniform clearance is also used to control the loss. 12 Other effective methods to control the loss caused by the hub leakage flow are to adopt bowed [13][14][15][16][17] and forward end-sweep 18,19 cantilevered stator design to improve the flow field near the hub. In this paper, the cantilevered stator adopts positive bowed and fore-sweep three-dimensional design of the fore-loaded blade near the hub region to control the loss.…”

Section: Introductionmentioning

confidence: 99%

Hub clearance effect in the design space of the cantilevered stator embedded in a 4-stage low-speed research compressor

Teng

et al. 2021

Advances in Mechanical Engineering

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This paper focuses on the effect of hub clearance in the design space of the highly loaded cantilevered stator. The embedded 1.5 stages of a low-speed research compressor (LSRC) were conducted with Unsteady Reynolds Average Navier-Stokes (URANS) numerical investigation, and the cantilevered stator adopts positive bowed and fore-sweep three-dimensional design. The research details that with the hub clearance increasing from 1.1% to 4.5% span, the loss coefficient and the total leakage momentum of the cantilevered stator correspond to the change of the blade loading near the hub. When designing the inlet metal angle of the rotor downstream the cantilevered stator, emphasis should be given to considering the inter-stage matching below 15% span. The mixing of leakage flow in 1.1% span clearance and 2.5% span clearance is basically completed in the S3 passage, but the mixing of leakage flow in 3.5% span clearance and 4.5% span clearance is still relatively strong downstream of S3. When calculating the relative entropy variation based on Denton’s mixing model, attention should be paid to the relationship between the leakage flow velocity affected by the hub gap and the mainstream velocity, as well as whether the mixing has been completed in the blade passage.

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“…George et al 25 applied the end-bend on stators and they found that the hub loading of the blade was improved with the smaller secondary flow. Luo et al 26 conducted an experimental investigation on the 2-stage compressor with bowed cantilevered stators and the leakage vortex, corner stall and passage cross flow were eliminated obviously.…”

Section: Introductionmentioning

confidence: 99%

The effect of end wall boundary layer on matching and corresponding flow control technique for multistage axial compressor

Zheng

Liu

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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The development pattern of the end wall boundary layer (BL) in whole conditions and its effect on the matching of multistage compressor have been studied in detail in this paper. Moreover, one method of end wall zone blade modification is carried out, using computational fluid dynamics, to improve the stage matching by re-camber. It is found that the pitch-averaged thickness of end wall BL gradually increases along streamline direction and the BL is highly skewed in the pitchwise direction. In addition, the value of BL thickness, mainly depends on the stage pressure rise coefficient [Formula: see text]. For a fixed rotating speed, the axial BL displacement thickness is changed dramatically from choked condition to near surge operating point. However, this thickness shows insensitive to the change of rotating speeds. On the other hand, BL degrades the pressure-rise characteristics of stages with low efficiency, and it results in mismatching of the compressor stage. Furthermore, the deviation angle of the blades is strongly affected by the end wall BL. Finally, two rows of stators are re-cambered on the leading edge to improve the matching near the hub region where it is influenced by end wall BL. The results show that the total pressure loss coefficient of the stators is reduced by 0.6 points and 1.73 points each. Moreover, the overall isentropic efficiency of multistage compressor is enhanced by 0.39 points without compromising pressure-rise capability and surge margin.

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Experimental Study of Effects of Bowed Blade on the Flow Field in a Cantilevered Stator Passage

Cited by 5 publications

References 0 publications

Investigation of Positively Curved Blade in Compressor Cascade Based on Transition Model

Investigation of Positively Curved Blade in Compressor Cascade Based on Transition Model

Hub clearance effect in the design space of the cantilevered stator embedded in a 4-stage low-speed research compressor

The effect of end wall boundary layer on matching and corresponding flow control technique for multistage axial compressor

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