Calculating Annulus Area in a Compressor

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SUMMARY

The annulus area in a gas turbine engine compressor refers specifically to the flow area between the rotor and the compressor casing, formed by two concentric circles. This area is crucial for understanding compressor performance, particularly in relation to the NACA 65-series rotor performance metrics, which include variables such as annulus-area ratio, solidity, blade angle, and Reynolds number. The foundational research on this topic is documented in NACA TN 4130 by George C. Ashby, Jr., John R. Erwin, and Wallace M. Schulze, published in October 1957.

PREREQUISITES
  • Understanding of gas turbine engine components
  • Familiarity with fluid dynamics principles
  • Knowledge of compressor performance metrics
  • Basic grasp of NACA series rotor characteristics
NEXT STEPS
  • Research NACA 65-series compressor rotor performance analysis
  • Study the impact of annulus-area ratio on compressor efficiency
  • Explore the effects of solidity and blade angle on gas turbine performance
  • Learn about Reynolds number implications in fluid flow within compressors
USEFUL FOR

Aerospace engineers, mechanical engineers, and students studying gas turbine technology will benefit from this discussion, particularly those focused on compressor design and performance optimization.

sid_galt
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What is annulus area in a compressor?
 
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It's not a general term as far as I know, but it can be the area between cylinder and the piston.
 
Sorry for being not clear. I was talking about the annulus area of a compressor in a gas turbine engine, not a reciprocating one.
 
It's the flow area in the compressor. It's an annulus because it is formed by two concentric circles i.e. the rotor and the compressor case.
 
Thanks for the help
 

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