Development of a Preliminary Design Method for Subsonic Splittered Blades in Highly Loaded Axial-Flow Compressors

Liu, Baojie; Du, Feng; Yu, Xin

doi:10.3390/app7030283

Cited by 9 publications

(8 citation statements)

References 18 publications

(27 reference statements)

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“…Previous studies only treated splitter vanes as the equivalent of blade solidity changes, such as the concepts of equivalent solidity or effective blade number. The former is discussed in splittered axial compressor rotor researches [19][20][21] and the latter is used in centrifugal impeller designs. 5 These two concepts are proved to be equivalent.…”

Section: Research Object and Methodsmentioning

confidence: 99%

A novel approach to determine splitter vane length for an extremely high hub/tip ratio mixed-flow compressor impeller

Xiang

Jiang

Cheng

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part A:

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This paper presents an approach to determine splitter vane length in radial compressor impellers based on a modified 1D performance prediction model, which considers the effects of splitter vane length and blade number on impeller internal losses. The splitter vane length corresponding to optimum blade number is investigated to achieve the maximum efficiency of a mixed-flow compressor impeller with an extremely high hub/tip ratio. An empirical formula for calculating splitter vane length is proposed. CFD results show that blade number and splitter vane length have a complex coupling interaction which makes it inappropriate to be described by equivalent solidity or effective blade number. 1D results and CFD verification indicate that optimum full-length blade number is 42 and corresponding splitter vane length is 20% of full-length blade length at design flow rate. The impeller peak efficiency mainly depends on minimum loss superposition of blade loading, skin friction and tip clearance. With the increase of splitter vane length and blade number, blade loading loss and clearance loss decline while skin friction loss increases.

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Section: Research Object and Methodsmentioning

confidence: 99%

A novel approach to determine splitter vane length for an extremely high hub/tip ratio mixed-flow compressor impeller

Xiang

Jiang

Cheng

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part A:

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show abstract

“…Hence, separation in smaller radial gap sizes happens earlier, and it is bigger than that of higher radial gap size (Figure 20). Liu et al [36] also showed that the compressor performance deterioration is the result of this supersonic acceleration and notable shock waves interaction with boundary layers. Figure 19 represents the effect of the radial gap ratio on the shock wave structure on the basis of absolute Mach number contours superimposed with isoclines at the mid-span of the vane diffuser at Mu = 1.16.…”

Section: Effects Of Radial Gap Ratio On Vaned Diffuser Performancementioning

confidence: 99%

“…Hence, separation in smaller radial gap sizes happens earlier, and it is bigger than that of higher radial gap size (Figure 20). Liu et al [36] also showed that the compressor performance deterioration is the result of this supersonic acceleration and notable shock waves interaction with boundary layers. However, according to Figure 20, as the impeller inlet tip-speed Mach number is less than the unity value (Mu = 0.69), the flow does not accelerate substantially.…”

Section: Effects Of Radial Gap Ratio On Vaned Diffuser Performancementioning

confidence: 99%

Effects of Radial Gap Ratio between Impeller and Vaned Diffuser on Performance of Centrifugal Compressors

Hosseini

Sun

et al. 2017

Applied Sciences

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Abstract:A high-performance centrifugal compressor is needed for numerous industry applications nowadays. The radial gap ratio between the impeller and the diffuser vanes plays an important role in the improvement of the compressor performance. In this paper, the effects of the radial gap ratio on a high-pressure ratio centrifugal compressor are investigated using numerical simulations. The performance and the flow field are compared for six different radial gap ratios and five rotational speeds. The minimal radial gap ratio was 1.04 and the maximal was 1.14. Results showed that reducing the radial gap ratio decreases the choke mass flow rate. For the tip-speed Mach number (impeller inlet) with M u < 1, the pressure recovery and the loss coefficients are not sensitive to the radial gap ratio. However, for M u ≥ 1, the best radial gap ratio is 1.08 for the pressure recovery and the loss coefficients. Furthermore, the impeller pressure ratio and efficiency are reduced by increasing the radial gap ratio. Finally, the compressor efficiency was compared for different radial gap ratios. For M u < 1, the radial gap ratio does not have noticeable effects. In comparison, the radial gap ratio of 1.08 has the best performance for M u ≥ 1.

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“…The studies carried out by Tzuoo et al., 14 Qiu et al., 15 and Liu et al. 16 indicates that the pressure ratio increase and loss reduction are achieved by splittered axial compressors under the highly loaded condition. In addition, splitter blades have been also used by Lavagnoli et al., 17 Yasa et al., 18 Spataro et al., 19 and Clark et al.…”

Section: Introductionmentioning

confidence: 97%

Passive flow control of the corner separation in an annular compressor cascade with a micro-blade

Wang

2018

Proceedings of the Institution of Mechanical Engineers, Part A:

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Corner separation contributes greatly to the loss and the passage blockage in a compressor stage. In order to mitigate the corner separation and improve the aerodynamic performance of compressors, a novel passive flow control method, an off-surface micro-blade installed upstream of the separation onset location, was proposed. A numerical investigation has was performed in an annular compressor cascade to assess the control effectiveness of the micro-blade. The results show that the location of the micro-blade affects the control effect significantly. The application of the well-designed micro-blade enhances the diffusion capacity considerably under the inflow incidence from −2° to +10°, accompanied by a slight loss reduction at some particular incidences. Detailed analysis of the predicted flow field was carried out to understand the underlying mechanism. It indicates that a “jet” forms upstream of the separation onset location with the application of the micro-blade. The formation of the jet reduces the thickness of boundary layer on the suction surface and builds a “jet barrier” near the endwall to hinder the accumulation of the low momentum fluid. The influence of the incidence was also investigated. It is concluded that the incidence increase has both positive and negative influences on the control effect of the micro-blade. As a result, the performance of the micro-blade is sensitive to the variation of inlet incidence.

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Development of a Preliminary Design Method for Subsonic Splittered Blades in Highly Loaded Axial-Flow Compressors

Cited by 9 publications

References 18 publications

A novel approach to determine splitter vane length for an extremely high hub/tip ratio mixed-flow compressor impeller

A novel approach to determine splitter vane length for an extremely high hub/tip ratio mixed-flow compressor impeller

Effects of Radial Gap Ratio between Impeller and Vaned Diffuser on Performance of Centrifugal Compressors

Passive flow control of the corner separation in an annular compressor cascade with a micro-blade

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