High Inlet Relative Mach Number Centrifugal Compressor Impeller Design

Volume 6: Turbo Expo 2007, Parts A and B ◽

10.1115/gt2007-27864 ◽

2007 ◽

Cited By ~ 3

Author(s):

James M. Sorokes ◽

Jason A. Kopko

Keyword(s):

Mach Number ◽

Test Data ◽

Centrifugal Compressor ◽

High Mach Number ◽

Performance Map ◽

Compressor Impeller ◽

The Subject ◽

Mach Numbers ◽

High Mach

This document presents an overview of impeller inlet relative Mach number, how the parameter is calculated, and its importance as an indicator of impeller performance. Comments are also offered regarding the comparison of inlet relative Mach numbers obtained from different compressor vendors. A sample impeller is used to illustrate the various methods used to calculate the inlet relative Mach number. Test data for that impeller is also offered to indicate the performance map achievable with high Mach number designs. Please note that this document is not intended to be an all-inclusive treatment of the subject; rather, it summarizes the OEM’s methodologies and perspective.

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Comparisons of a three-dimensional, full Navier Stokes computer model with high Mach number conbustor test data

10.2514/6.1990-5217 ◽

1990 ◽

Cited By ~ 2

Author(s):

WILLIAM WATKINS

Keyword(s):

Mach Number ◽

Test Data ◽

Computer Model ◽

Three Dimensional ◽

Navier Stokes ◽

High Mach Number ◽

High Mach

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Design Consideration of a Centrifugal Compressor Impeller With High Mach Number and High Swirl Angle at Exit

Volume 5: Energy Systems Analysis, Thermodynamics and Sustainability; NanoEngineering for Energy; Engineering to Address Climate Change, Parts A and B ◽

10.1115/imece2010-40930 ◽

2010 ◽

Author(s):

Kangsoo Im

Keyword(s):

Mach Number ◽

Centrifugal Compressor ◽

Swirl Flow ◽

Stable Operation ◽

Compression Process ◽

Vaned Diffuser ◽

Flow Angle ◽

Compressor Impeller ◽

High Mach ◽

Exit Mach Number

A centrifugal compressor impeller with high exit Mach number (M = 0.8–1.1) & high outlet flow angle (ALPHA 2 = 78–85 degrees) was designed. The objective of this work is to create a real condition for the better understanding of the behavior of the fluid flow in transonic and high swirl flow vaned diffusers. Particular attention was given to the flows located at the rotor–stator interface. The unsteady interaction between impeller and diffuser plays an important role in the compression process, especially in high loaded impellers. Actually, the vaned diffuser has to tolerate the distorted upstream flow due to the jet-wake structure coming from the impeller. Following the impeller design, numerical investigations were conducted for the transonic centrifugal compressor impeller composed of backswept unshrouded blades. The characteristic plots of the impeller resulting from the simulations show a good stable operation.

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