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Jet engine cutaway showing the centrifugal compressor and other parts

Centrifugal flow compressors, sometimes referred to as radial compressors, are a special class of radial-flow work-absorbing turbomachinery that include pumps, fans, blowers and compressors.[1]

The earliest forms of these dynamic-turbo machines[2] were pumps, fans and blowers. What differentiates these early turbo machines from compressors is that the working fluid can be considered incompressible, thus permitting accurate analysis through Bernoulli's equation. In contrast, modern centrifugal compressors are higher in speed and analysis must deal with compressible flow.

For purposes of definition, centrifugal compressors often have density increases greater than 5 percent. Also, they often experience relative fluid velocities above Mach 0.3 when the working fluid is air or nitrogen. In contrast, fans or blowers are often considered to have density increases of less than 5 percent and peak relative fluid velocities below Mach 0.3-0.5

In an idealized sense, the dynamic compressor achieves a pressure rise by adding kinetic-energy/velocity to a continuous flow of fluid through the rotor or impeller. This kinetic energy is then converted to an increase in static pressure by slowing the flow through a diffuser.



Centrifugal compressors are used throughout industry because they have fewer rubbing parts, are relatively energy efficient, and give higher airflow than a similarly sized reciprocating compressor (i.e. positive-displacement). Their primary drawback is that they cannot achieve the high compression ratio of reciprocating compressors without multiple stages. Centrifugal fan/blowers are more suited to continuous-duty applications such as ventilation fans, air movers, cooling units, and other uses that require high volume with little or no pressure increase. In contrast, multi-stage reciprocating compressors often achieve discharge pressures of 8,000 to 10,000 psi (55 to 69 MPa). One example of an application of centrifugal compressors is their use in re-injecting natural gas back into oil fields to increase oil production.

Centrifugal compressors are often used in small gas turbine engines like APUs (auxiliary power units) and smaller aircraft gas turbines. A significant reason for this is that with current technology, the equivalent flow axial compressor will be less efficient due primarily to a combination of rotor and variable stator tip-clearance losses. There are few single stage centrifugal compressors capable of pressure-ratios over 10:1, due to stress considerations which severely limit the compressor's safety, durability and life expectancy.

Additionally for aircraft gas-turbines; centrifugal flow compressors offer the advantages of simplicity of manufacture and relatively low cost. This is due to requiring fewer stages to achieve the same pressure rise. The fundamental reason for this stems from a centrifugal compressor's large change in radius (relative to a multi-stage axial compressor); it is the change in radius that allows the centrifugal compressor to generate large increases in fluid energy over a short axial distance.


A partial list of centrifugal compressor applications include:

Operating limits

Many centrifugal compressors have one or more of the following operating limits:

  • Minimum Operating Speed - the minimum speed for acceptable operation, below this value the compressor may be controlled to stop or go into an "Idle" condition.
  • Maximum Allowable Speed - the maximum operating speed for the compressor. Beyond this value stresses may rise above prescribed limits and rotor vibrations may increase rapidly. At speeds above this level the equipment will likely become very dangerous and be controlled to lower speeds.
  • Stonewall or Choke - occurs under one of 2 conditions. Typically for high speed equipment, as flow increases the velocity of the gas/fluid can approach the gas/fluid's sonic speed somewhere within the compressor stage. This location may occur at the impeller inlet "throat" or at the vaned diffuser inlet "throat". In most cases, it is generally not detrimental to the compressor. For low speed equipment, as flows increase, losses increase such that the pressure ratio drops to 1:1.
  • Surge - is the point at which the compressor cannot add enough energy to overcome the system resistance.[3] This causes a rapid flow reversal (i.e. surge). As a result, high vibration, temperature increases, and rapid changes in axial thrust can occur. These occurrences can damage the rotor seals, rotor bearings, the compressor driver and cycle operation. Most turbo machines are designed to easily withstand occasional surging. However, if the turbo machine is forced to surge repeatedly for a long period of time or if the turbo machine is poorly designed, repeated surges can result in a catastrophic failure. Of particular interest, is that while turbo machines may be very durable, the cycles/processes that they are used within can be far less robust.

See also


  1. ^ Dixon S.L. (1978). Fluid Mechanics, Thermodynamics of Turbomachinery (Third Edition ed.). Pergamon Press. ISBN 0-08-022722-8.  
  2. ^ Aungier, Ronald H. (2000). Centrifugal Compressors A Strategy for Aerodynamic design and Analysis. ASME Press. ISBN 0-7918-0093-8.  
  3. ^ Pampreen, Ronald C. (1993). Compressor Surge and Stall. Concepts ETI. ISBN 0-933283-05-9.  

Further reading

  • Lakshminarayana, B. Fluid Dynamics and Heat Transfer of Turbomachinery. Wiley-Interscience. ISBN 0-471-85546-4.  
  • Wilson, D.G. and Korakianitis, T. (1998). The Design of High-Efficiency Turbomachinery and Gas Turbines (2nd Edition ed.). Prentice Hall. ISBN 0-13-312000-7.  
  • Cumpsty, N.A. (2004). Compressor Aerodynamics. Krieger Publishing. ISBN 1-57524-247-8.  
  • Whitfield, A. and Baines, N.C. (1990). Design of Radial Turbomachines. Longman Scientific & Technical. ISBN 0-470-21667-0.  
  • Saravanamuttoo, H.I.H., Rogers, G.F.C. and Cohen, H. (2001). Gas Turbine Theory (5th Edition ed.). Prentice Hall. ISBN 0-13-015847-X.  
  • Japikse, David and Baines, N.C. (1994). Introduction to Turbomachinery. Oxford University Press. ISBN 0-933283-06-7.  
  • Japikse, David (1996). Centrifugal Compressor Design and Performance. Concepts ETI. ISBN 0-933283-03-2.  
  • Japikse, David and Baines, N.C. (1998). Diffuser Design Technology. Concepts ETI. ISBN 0-933283-08-3.  
  • Wennerstrom, Arthur J. (2000). Design of Highly Loaded Axial-Flow Fans and Compressors. Concepts ETI. ISBN 0-933283-11-3.  
  • Japiske, D., Marschner, W.D., and Furst, R.B. (1997). Centrifugal Pump Design and Performance. Concepts ETI. ISBN 0-933283-09-1.  
  • Editor:David Japikse (1986). Advanced Experimental Techniques in Turbomachinery (1st Edition ed.). Concepts ETI. ISBN 0-933283-01-6.  
  • Shepard, Dennis G. (1956). Principles of Turbomachinery. Mcmillan. LCCN 56002849.  
  • Baines, Nicholas C. (2005). Fundamentals of Turbocharging. Concepts ETI. ISBN 0-933283-14-8.  

External links



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