Experimental Investigations on Three-Dimensional Blading Optimization for Low-Speed Model Testing

Zhang, Chenkai; Hu, Jun; Wang, Zhiqiang; Li, Jun

doi:10.1115/1.4033940

Cited by 8 publications

(10 citation statements)

References 11 publications

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“…The test probes and holes of the A-A and L-L plane were always mounted to monitor the performance of the compressor and the other planes are optional which depended on the test requirement. The descriptions of the total pressure pneumatic probes and boundary layer taps could be found in the previous works of our lab [15][16][17][18]. The performance of the compressor was obtained from the inlet A-A plane and outlet L-L plane, and the pressure rise and efficiency characteristic maps were shown in Figure 3.…”

Section: Introductionmentioning

confidence: 99%

“…The detailed tests were conducted by four-hole pneumatic probes, which were driven by the displacement controllers, in the fixed reference frame. More descriptions about the four-hole pneumatic probes and tests for a detailed flow field between two adjacent rows could be found in [15][16][17][18]. As Figure 4 shows, there are nine test slots distributed on the casing that are used to install the displacement controllers for detailed tests of every rotor-stator interface plane, corresponding to the positions of the planes from "B-B" to "K-K" in Figure 2.…”

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Non-Axisymmetric Shroud Profiled Endwall Optimization of an Embedded Stator and Experimental Investigation

Wang

Jiang

et al. 2020

Energies

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Turbomachinery has been widely used in the energy systems as an energy conversion device, such as gas turbine and aero-engine. The losses in the turbomachinery, especially in the multi-stage conditions, restrict the energy conversion efficiency and corresponding fuel economy. Previous studies show that non-axisymmetric endwall could be used to decrease the losses in compressors, but the real effects in the rig tests are usually inconsistent with the numerical simulation. In this paper, a shroud profiled endwall optimization method with the strategy of local loss as the objective function is proposed, aiming at reducing the tip loss of an embedded stator under the operating point. The traditional total loss coefficient and four local loss functions are studied to investigate how the objective functions influence the optimization results. Three optimized endwall geometries are tested in the embedded test platform. It showed that the strategy of loss coefficient above 90% span as the objective function was best at decreasing the stator loss in the tip region as well as the whole span. Under this strategy, the loss above 90% span was suppressed by 48.17% and the loss of the whole span decreased 9.27%, which proved the PEW optimization design method with the strategy of local loss as the objective function is potential.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Non-Axisymmetric Shroud Profiled Endwall Optimization of an Embedded Stator and Experimental Investigation

Wang

Jiang

et al. 2020

Energies

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“…Besides, Boos and Lange also carried out a high loaded blading investigation on this large-scale, low-speed compressor [10,11]. Zhang to reached performance optimization of a low-speed axial rotor by three-dimensional (3D) optimization with numerical computation, and then the experiments were carried out for validation of the numerical results [12,13]. Zhang summarized four procedures with which to achieve the whole process of compressor scaling and performance were validated by numerical computation.…”

Section: Introductionmentioning

confidence: 99%

Research on the Application of Partial Similarity for a 1-1/2 Axial Compressor

2020

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In this paper, a method based on the partial similarity principle is presented to improve the aerodynamic design with low cost and high accuracy for a 1-1/2 axial compressor. By means of this method, during the process of a similar design, the machine Mach number and flowrate coefficient are maintained. The flow similarity between the prototype and its large-scaled alternative was observed, according to a detailed analysis of flow fields of rotor and stator. As well, the relative discrepancies of isentropic efficiency and pressure ratio between two models are 1.25% and 0.4% at design point, respectively. Besides, their performance curves agreed very well in the whole operating range. Moreover, it was also found that the flow similarity between the two models can be maintained under unsteady working conditions. Thereafter, in order to investigate the impact of stability optimization method on the similarity principle, casing treatment with single circumferential groove was applied to these two models. The flow similarity was still maintained and the flowrate near the stall was reduced about 1.1% with negligible deterioration of the overall performance.

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“…For high-pressure compressor blades, low speed testing models were redesigned and implemented by Zhang et al [19], Zhang et al [20]. Their designed LSMT was used to optimize the 3D blade for LSMT [21]. Giovannini et al [22] scaled the three-dimensional lowpressure turbine blades for the low-speed testing.…”

Section: Introductionmentioning

confidence: 99%

On Scaling Method to Investigate High-Speed Over-Tip-Leakage Flow at Low-Speed Condition

Jiang

Zhang

et al. 2018

Journal of Engineering for Gas Turbines and Power

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Modern high-pressure turbine blades operate at high-speed conditions. The over-tip-leakage (OTL) flow can be high-subsonic or even transonic. From the consideration of problem simplification and cost reduction, the OTL flow has been studied extensively in low-speed experiments. It has been assumed a redesigned low-speed blade profile with a matched blade loading should be sufficient to scale the high-speed OTL flow down to the low-speed condition. In this paper, the validity of this conventional scaling approach is computationally examined. The computational fluid dynamics (CFD) methodology was first validated by experimental data conducted in both high- and low-speed conditions. Detailed analyses on the OTL flows at high- and low-speed conditions indicate that, only matching the loading distribution with a redesigned blade cannot ensure the match of the aerodynamic performance at the low-speed condition with that at the high-speed condition. Specifically, the discrepancy in the peak tip leakage mass flux can be as high as 22%, and the total pressure loss at the low-speed condition is 6% higher than the high-speed case. An improved scaling method is proposed hereof. As an additional dimension variable, the tip clearance can also be “scaled” down from the high-speed to low-speed case to match the cross-tip pressure gradient between pressure and suction surfaces. The similarity in terms of the overall aerodynamic loss and local leakage flow distribution can be improved by adjusting the tip clearance, either uniformly or locally.

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Experimental Investigations on Three-Dimensional Blading Optimization for Low-Speed Model Testing

Cited by 8 publications

References 11 publications

Non-Axisymmetric Shroud Profiled Endwall Optimization of an Embedded Stator and Experimental Investigation

Non-Axisymmetric Shroud Profiled Endwall Optimization of an Embedded Stator and Experimental Investigation

Research on the Application of Partial Similarity for a 1-1/2 Axial Compressor

On Scaling Method to Investigate High-Speed Over-Tip-Leakage Flow at Low-Speed Condition

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