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| Activity title | Engine Integration Improvements due to advanced Engine Concepts | Activity Reference | AVT-ET-246 | Panel | AVT | Security Classification | NATO UNCLASSIFIED | Status | Active | Activity type | ET | Start date | 2024-01-01T00:00:00Z | End date | 2024-12-31T00:00:00Z | Keywords | engine integration, engineinlet airflow matching, fighter aircraft, supercruise capability, supersonic intake aerodynamic, thermal and power management, variable cycle engine | Background | Engines for military supersonic applications are strongly integrated into the aircraft platform for reasons of signature. This integration causes significant interactions between engine and aircraft like aerodynamic flows in the engine inlet and the flow around the inlet. These interactions have significant impact on the overall performance and must be considered in the design of such a platform.
New engine technologies like variable cycle engine (VCE) can significantly influence the integration of the propulsion system into a fighter aircraft, providing advantages not only in terms of performance but also in terms of the overall design, integration, and synergy with the aircraft's systems.
| Objectives | The objective of this research activity is to identify and estimate:
• potential engine integration opportunities offered by new engine technologies
• review of the results of similar, topic-related activities
• best practice of advanced engine concepts integration
• possible ways (methods) to investigate these integration potentials
• synergies and contribution possibilities between the research partners
To achieve the objectives this activity includes workshops to discuss topics of new engine capabilities and engine integration technologies.
This ET will determine if a follow-up activity is warranted and if applicable the ET will prepare it.
| Topics | • Aircraft engine integration for fighter application (up to Mach 2.0)
• Variable cycle engine preliminary design
• Engine airflow control and its impact on intake aerodynamics (drag, flow separation, reduced radar cross section)
• Aircraft thermal and power management
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