Reduction of pressure loss in suction flow passage of oil flooded screw compressors

The flow passage including supply hole of externally pressurized gas was investigated. The outlet velocity of supply hole, bearing number and supply pressure’s relationship were built. According to supply hole’s speed, supersonic or subsonic model was chosen to calculate bearing clearance’s pressure distribution. Bearing number’s effects on pressure’s distribution was also studied. The calculation result shows that at larger bearing number, supply hole’s speed is harder to be chocked. Both in supersonic and subsonic condition, larger bearing number produces lower pressure loss.

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Investigation on the modifications of the suction flow passage in a scroll refrigeration compressor

Applied Thermal Engineering ◽

10.1016/j.applthermaleng.2020.115031 ◽

2020 ◽

Vol 170 ◽

pp. 115031 ◽

Cited By ~ 1

Author(s):

Shuaihui Sun ◽

Xianwen Wang ◽

Pengcheng Guo ◽

Zhe Song

Keyword(s):

Flow Passage ◽

Suction Flow ◽

Refrigeration Compressor

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Optimizing a Suction Channel to Improve Performance of a Centrifugal Compressor Stage

Volume 7: Turbomachinery, Parts A, B, and C ◽

10.1115/gt2010-23019 ◽

2010 ◽

Cited By ~ 1

Author(s):

Manabu Yagi ◽

Takanori Shibata ◽

Hideo Nishida ◽

Hiromi Kobayashi ◽

Masanori Tanaka ◽

...

Keyword(s):

Pressure Loss ◽

Flow Coefficient ◽

Design Parameters ◽

Compressor Stage ◽

Flow Distortion ◽

Dominant Design ◽

Improvement Effect ◽

Computational Fluid Dynamics Cfd ◽

Suction Flow ◽

Stage Efficiency

Design parameters for a suction channel of process centrifugal compressors were investigated, and an optimizing method to improve efficiency by using the new design parameters was proposed. Both pressure loss and circumferential flow distortion in the suction channel were evaluated by using computational fluid dynamics (CFD). The main dimensions, which had a large influence on pressure loss and circumferential flow distortion, were identified by using design of experiments (DOE). Next, the passage sectional area ratios Ac/Ae, Ae/As, and Ac/As were found to be the dominant design parameters for the pressure loss and circumferential flow distortion, where Ac, Ae and As are passage sectional areas for the casing upstream side, casing entrance and impeller eye, respectively. Then the shape of the suction channel was optimized using Ac/Ae, Ae/As, and Ac/As. Finally, to evaluate the improvement effect of optimizing the values of Ac/Ae, Ae/As, and Ac/As on compressor stage performance, a base suction channel and an optimized type of suction channel were manufactured and tested. The design suction flow coefficient was 0.1 and the peripheral Mach number was 0.78. Test results showed that the optimized suction channel achieved 3.8% higher stage efficiency than the base one while maintaining the overall operating range from surge to choke. The method for optimizing suction channels by using the three described design parameters was concluded to be very effective for improving the stage efficiency.

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C02 Effect of Boundary Flow Passage on Pressure Loss in Regenerator

The Proceedings of the Symposium on Stirlling Cycle ◽

10.1299/jsmessc.2001.5.103 ◽

2001 ◽

Vol 2001.5 (0) ◽

pp. 103-106

Author(s):

Manabu SAWADA ◽

Kazuhiro HAMAGUCHI ◽

Iwao YAMASHITA

Keyword(s):

Pressure Loss ◽

Flow Passage ◽

Boundary Flow

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Review on the aerodynamics of intermediate compressor duct

JOURNAL OF MECHANICAL ENGINEERING AND SCIENCES ◽

10.15282/jmes.14.4.2020.13.0587 ◽

2020 ◽

Vol 14 (4) ◽

pp. 7446-7468

Author(s):

Manish Sharma ◽

Beena D. Baloni

Keyword(s):

High Pressure ◽

Pressure Loss ◽

Flow Analysis ◽

Outer Wall ◽

Optimization Techniques ◽

Optimum Pressure ◽

Research Areas ◽

Static Pressure Distribution ◽

High Pressure Compressor ◽

Pressure Compressor

In a turbofan engine, the air is brought from the low to the high-pressure compressor through an intermediate compressor duct. Weight and design space limitations impel to its design as an S-shaped. Despite it, the intermediate duct has to guide the flow carefully to the high-pressure compressor without disturbances and flow separations hence, flow analysis within the duct has been attractive to the researchers ever since its inception. Consequently, a number of researchers and experimentalists from the aerospace industry could not keep themselves away from this research. Further demand for increasing by-pass ratio will change the shape and weight of the duct that uplift encourages them to continue research in this field. Innumerable studies related to S-shaped duct have proven that its performance depends on many factors like curvature, upstream compressor’s vortices, swirl, insertion of struts, geometrical aspects, Mach number and many more. The application of flow control devices, wall shape optimization techniques, and integrated concepts lead a better system performance and shorten the duct length. This review paper is an endeavor to encapsulate all the above aspects and finally, it can be concluded that the intermediate duct is a key component to keep the overall weight and specific fuel consumption low. The shape and curvature of the duct significantly affect the pressure distortion. The wall static pressure distribution along the inner wall significantly higher than that of the outer wall. Duct pressure loss enhances with the aggressive design of duct, incursion of struts, thick inlet boundary layer and higher swirl at the inlet. Thus, one should focus on research areas for better aerodynamic effects of the above parameters which give duct design with optimum pressure loss and non-uniformity within the duct.

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