Advanced Compressor Loss Correlations, Part II: Experimental Verifications
Reliable efficiency calculation of high-subsonic and transonic compressor stages requires a detailed and accurate prediction of the flow field within these stages. Despite the tremendous progress in turbomachinery computational fluid mechanics, the compressor designer still uses different loss corre...
Saved in:
| Main Author: | |
|---|---|
| Format: | Article |
| Language: | English |
| Published: |
Wiley
1997-01-01
|
| Series: | International Journal of Rotating Machinery |
| Subjects: | |
| Online Access: | http://dx.doi.org/10.1155/S1023621X97000171 |
| Tags: |
Add Tag
No Tags, Be the first to tag this record!
|
| Summary: | Reliable efficiency calculation of high-subsonic and transonic compressor stages requires a
detailed and accurate prediction of the flow field within these stages. Despite the tremendous
progress in turbomachinery computational fluid mechanics, the compressor designer still
uses different loss correlations to estimate the total pressure losses and thus the efficiency of
the compressor stage. The new shock loss model and the modified diffusion factor, developed
in Part I, were implemented into a loss calculation procedure. In this part, correlations
for total pressure loss, profile loss, and secondary loss coefficients are presented, using the
available experimental data. Based on the profile loss coefficients, correlations were also
established for boundary layer momentum thickness. These correlations allow the compressor
designer to accurately estimate the blade losses and therefore the stage efficiency. |
|---|---|
| ISSN: | 1023-621X |