Closure to “Discussion of ‘A Study of Performance Improvement for High Specific Speed Centrifugal Compressors by Using Diffusers With Half Guide Vanes’” (1987, ASME J. Fluids Eng., 109, p. 366)

1987 ◽  
Vol 109 (4) ◽  
pp. 367-367
Author(s):  
Y. Yoshinaga ◽  
T. Kaneki ◽  
H. Kobayashi ◽  
M. Hoshino
Keyword(s):  
Performance Improvement ◽  
Centrifugal Compressors ◽  
Guide Vanes ◽  
Specific Speed

A Study of Performance Improvement for High Specific Speed Centrifugal Compressors by Using Diffusers With Half Guide Vanes

1987 ◽  
Vol 109 (4) ◽  
pp. 359-366 ◽  
Author(s):  
Y. Yoshinaga ◽  
T. Kaneki ◽  
H. Kobayashi ◽  
M. Hoshino
Keyword(s):  
Performance Improvement ◽  
Side Wall ◽  
Axial Direction ◽  
Pressure Recovery ◽  
Guide Vanes ◽  
Small Height ◽  
Optimum Height ◽  
New Type ◽  
Specific Speed ◽  
Width Measurements

The experimental results from eighteen different centrifugal compressor stages showed that the pressure recovery of vaneless diffusers for high specific speed compressors was extremely low compared with the value expected by an ideal two-dimensional analysis. Consequently a new type of diffuser with half guide vanes on the shroud side wall was proposed. The pressure recovery of this diffuser at distorted inlet flow was considerably improved by the half guide vanes. The optimum height of the vanes was a little less than one half of the diffuser width. Measurements of the velocity distribution in the diffusers using Pitot tubes and a laser-two-focus velocimeter, clearly showed that the small height guide vanes gave a uniform flow in the axial direction and improved the pressure recovery of the diffuser.

Influence of the Different Design Parameters to the Centrifugal Compressor Tip Clearance Loss

2011 ◽  
Author(s):  
Teemu Turunen-Saaresti ◽  
Ahti Jaatinen
Keyword(s):  
Centrifugal Compressor ◽  
Tip Clearance ◽  
Design Parameters ◽  
Clear Correlation ◽  
Compressor Stage ◽  
Centrifugal Compressors ◽  
Blade Number ◽  
Overall Performance ◽  
Specific Speed

In this paper the effect of the tip clearance was studied with six different centrifugal compressors and data available in literature. The changes in the overall performance of the compressor stage were examined. The aim was to study the influence of the different design parameters to the tip clearance loss. It was evident by the previous studies that the sensitivity of the centrifugal compressor to the tip clearance loss varies with different designs. However, for the designer it is important to know the effect of the tip clearance loss in order to initially evaluate the quality of different designs. Analysis of the data demonstrated that no clear correlation between the sensitivity of the tip clearance loss and the specific speed, the diffusion ratio, the blade number and the ratio of blade heights exists.

scholarly journals Flow through Guide Vanes of Low Specific Speed Mixed Flow Pumps.

1993 ◽  
Vol 59 (568) ◽  
pp. 3831-3837
Author(s):  
Toshiaki Kanemoto ◽  
Hirotaka Akamatsu ◽  
Shigenori Matsunaga ◽  
Hiroshi Tsukamoto
Keyword(s):  
Mixed Flow ◽  
Guide Vanes ◽  
Flow Through ◽  
Low Specific Speed ◽  
Specific Speed

scholarly journals The Efficiencies of Single-Stage Centrifugal Compressors for Aircraft Applications

1991 ◽  
Author(s):  
C. Rodgers
Keyword(s):  
Mach Number ◽  
State Of The Art ◽  
Single Stage ◽  
Critical Parameters ◽  
Design Parameters ◽  
Centrifugal Compressors ◽  
Design Work ◽  
Engine Design ◽  
Specific Speed ◽  
System Power

The thrust of most recent advances in single– and two–stage centrifugal compressor technology by the aerospace community has been motivated by interest in increasing airbreathing propulsion system power density, and improving specific fuel consumption with higher stage pressure ratios. Advances in the last decade have made it appropriate to review the major design parameters influencing the efficiency levels of single–stage centrifugal compressors for aircraft applications. A simple efficiency correlation was derived for advanced single–stage centrifugal compressors. It was based upon four critical parameters: • Inlet Specific Speed • Impeller Tip Diameter • Inducer Tip Relative Mach Number • Exit Discharge Mach Number The correlation was shown to predict attainable state–of–the–art efficiencies within a band width of ± 2 % points. This was considered acceptable for preliminary compressor and engine design work.

scholarly journals A 1D mean line model for centrifugal compressors with variable inlet guide vanes

2019 ◽  
Vol 1 (1) ◽  
Author(s):  
Brett Dewar ◽  
Mike Creamer ◽  
Mariana Dotcheva ◽  
Jovana Radulovic ◽  
James M. Buick
Keyword(s):  
Centrifugal Compressors ◽  
Line Model ◽  
Guide Vanes ◽  
Inlet Guide Vanes
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