Survivability of «wing-engine&lraquo; system at engine burn-through

Subject: Experimental determination of thermal state of titanium alloy samples under high-velocity high-temperature jet impact. Obtaining data to validate numerical tools for engine nacelle survivability prediction in case of wing-engine burn-through in collaboration with CNRS-LCSR (ICARE at present).

• 1. Design, organization of pieces manufacturing, and assembling of test facility.
• 2. Test series at various air heater regimes with data acquisition.
• 3. Temperature measurements on the back side of a titanium plate using thermocouples and infrared camera to validate a heat transfer model based on the inverse method.
• 4. Post-processing of experimental data.

Scheme of facility

View of a titanium plate during and after a test run: front and back sides

IR-image of the plate back side during the test. Temperature of jet 1930 K

Project was done in frame of contract with Airbus, France,2005 with participation of CNRS specialist (France).

MThis work was performed under contract with Airbus France in 2005. Main results are reported in the paper «Experimental studies of underexpanded hot jets: free jet velocity field and jet impact on a flat plate», 2ND EUROPEAN CONFERENCE FOR AEROSPACE SCIENCES (EUCASS), Brussels, Belgium, 1-6 Jule, 2007.