Abstract
Using the idea of inlet distortion parallel compressor theory dividing the compressor into some sub compressors, the partial casing treatment compressor was divided into casing treatment sub compressor and solid wall sub compressor. Then the outlet parameter of the partial casing treatment compressor was got according to the laws of momentum conservation and energy conservation, and the assumption of partial casing treatment performance prediction model was acquired based on the experimental conclusions of linear relationship between the mass flow of stall margin point and the casing treatment circumferential angle. Comparisons of the prediction results and the experimental results reveal that the curves of prediction characteristics and experimental characteristics are consistent in overall trend. Under supersonic condition at 98% design rotating speed, the peak efficiency prediction error is smaller than 0.5%, and the comprehensive margin prediction error is under 0.6%.
| Original language | English |
|---|---|
| Pages (from-to) | 1207-1215 |
| Number of pages | 9 |
| Journal | Hangkong Dongli Xuebao/Journal of Aerospace Power |
| Volume | 32 |
| Issue number | 5 |
| DOIs | |
| State | Published - 1 May 2017 |
UN SDGs
This output contributes to the following UN Sustainable Development Goals (SDGs)
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SDG 7 Affordable and Clean Energy
Keywords
- Casing treatment
- Expansion of stall margin
- Modeling
- Parallel compressor
- Performance prediction
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