Comparison of Alternative Engine Architectures for Next Generation Supersonic Aircraft
The present paper illustrates the design space exploration of a supersonic mixed-flow turbofan engine for civil applications. The aircraft platform selected is a 10-passenger business jet, cruising at Mach 1.6. To overcome noise limitations at take-off, an alternative engine architecture with additi...
Saved in:
| Main Authors: | , , , |
|---|---|
| Format: | Article |
| Language: | English |
| Published: |
MDPI AG
2025-05-01
|
| Series: | Engineering Proceedings |
| Subjects: | |
| Online Access: | https://www.mdpi.com/2673-4591/90/1/115 |
| Tags: |
Add Tag
No Tags, Be the first to tag this record!
|
| Summary: | The present paper illustrates the design space exploration of a supersonic mixed-flow turbofan engine for civil applications. The aircraft platform selected is a 10-passenger business jet, cruising at Mach 1.6. To overcome noise limitations at take-off, an alternative engine architecture with additional exhaust nozzle variability, to overcome the take-off noise limit, is proposed. The fully variable area nozzle configuration allows for an overall 15% weight reduction against a partially variable area nozzle architecture. In terms of overall aircraft mission fuel burn, it shows an 8% mission fuel burn reduction against the partially variable area nozzle architecture, with a final fuel efficiency of 11.4 pax-mile/us gallon. |
|---|---|
| ISSN: | 2673-4591 |