Technological Research On Propulsion by HYdrogen

Project Information

TROPHY

Grant agreement ID: 101140638

DOI

10.3030/101140638

Project terminated on 8 November 2024

EC signature date 12 December 2023

Start date 1 January 2024

End date 31 December 2026

Funded under

• Climate, Energy and Mobility

Total cost

€ 29 012 882,57

EU contribution

€ 20 599 024,07

Coordinated by

SAFRAN AIRCRAFT ENGINES
France

Periodic Reporting for period 1 - TROPHY (Technological Research On Propulsion by HYdrogen)

Reporting period: 2024-01-01 to 2024-12-31

Summary of the context and overall objectives of the project

The TROPHY project, which stands for Technological Research On Propulsion by HYdrogen, aimed at supporting the Clean Aviation HYDEA funded project (HYdrogen DEmonstrator for Aviation), which proposes a technology maturation plan to develop an H2C (Hydrogen Combustion) propulsion system compatible with an Entry Into Service of a zero CO2 low-emission aircraft in 2035. TROPHY supported design activities related to the development of an H2 engine fuel system as well as the investigation of integration aspects between engine and aircraft. Decision was made by the consortium to close TROPHY grant agreement as it turned out that key objectives as initially envisaged were no longer relevant.

Work performed from the beginning of the project to the end of the period covered by the report and main results achieved so far

WP1 – H2 Engine Fuel System design & make
The H2 Engine fuel system system and component design activities supported the concept phase and culminated with the Final Concept Review for a Flight Test configuration. As a consequence of the change in the new Hydrogen Combustion (H2C) demonstrator strategy, the project scope got reconfigured for ground testing only and tailored to the wet rig configuration. Top project objectives and requirements were updated, constraints on equipment got relaxed (no longer flight safety), opportunities were identified for a SEFS architecture simplification, physical installation got revised, and a functional alternative to capsules was specified.

WP2 - Waste Heat Recovery (WHR) System equipment design & make
From the WHR concept selection coming from HYDEA,
- Aerothermal conceptual design review was passed, including test enabling hardware. Coupon tests objectives were set, coupons were defined (CAD & drawings).
- Mechanical conceptual design review was completed
With regards to the hardware delivery related activities, RFI were sent and the received responses got evaluated.

WP3 - Propulsion System preparation for Flight Test Demonstrator (FTD)
Activities related to the FTD propulsion system structural architecture design covered the definition and verification of thermal management & ventilation system architecture and integration into the nacelle and stub. Simulation of Fire Risk Hydrogen leak in propulsion perimeter were performed. Extensive and main work was performed on the capsule design: consolidation of the capsule architecture, system installation analysis, identification of a baseline design including manufacturing strategy, delivery of the FEM elements (capsule, stub).
With regards to the FTD systems maturation and flight clearance initiation, the fire prevention systems architecture, testing strategy and documentation were defined. Large part of the activities covered the overall End-to-End Fuel and Propulsion System (EFPS) definition, the related specification document for modelling activities was defined.

Progress beyond the state of the art and expected potential impact (including the socio-economic impact and the wider societal implications of the project so far)

Despite the project got terminated well ahead of the planned end date, TROPHY played a key role looking at the overall Hydrogen Combustion (H2C) demonstrator strategy as it helped mitigate the schedule risk on the HYDEA project (in supporting design activities related to the concept phase or evaluating the necessary reconfiguration for ground testing only). Capitalisation activities were also performed on the requirements of a Flight Test configuration (flight safety aspects, design constraints such as system installation, encapsulation concept). Important knowledge was gained that will feed future product architecture definition.