Abstract
A calibrated simulation model was created in this research and the accuracy and applicability was verified by experiment. This model was used to match the appropriate turbochargers and explore how the diverse pressure ratio distribution affects the engine performance on the whole operating range considering the efficacy of the intercooler and pressure loss in inlet. Based on the objective of minimizing the energy consumption of turbocharging compressors, series of theories were revealed about how to distribute the pressure ratio between two turbochargers, and a matching method was got to optimize the pressure ratio distribution on a certain two-stage turbocharged aircraft piston engine by virtue of research. Results showed the turbochargers had high efficiency under all working condition and kept 7% away from the dangerous margin via the method. This also provided a foundation for further study on the safety of the two-stage turbocharged aircraft piston engine at service ceiling.
| Translated title of the contribution | Study of compression ratio distribution in two-stage series turbocharged aircraft piston engine |
|---|---|
| Original language | Chinese (Traditional) |
| Pages (from-to) | 769-775 |
| Number of pages | 7 |
| Journal | Hangkong Dongli Xuebao/Journal of Aerospace Power |
| Volume | 33 |
| Issue number | 4 |
| DOIs | |
| State | Published - 1 Apr 2018 |
UN SDGs
This output contributes to the following UN Sustainable Development Goals (SDGs)
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SDG 7 Affordable and Clean Energy
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