An innovative approach to gas turbine design involves mounting
compressor and turbine blades to an outer rotating shell.
Designated the exoskeletal engine, compression (preferable to
tension for high-temperature ceramic materials, generally) becomes
the dominant blade force. Exoskeletal engine feasibility lies in
the structural and mechanical design (as opposed to cycle or
aerothermodynamic design), so this study focused on the development
and assessment of a structural-mechanical exoskeletal concept using
the Rolls-Royce AE3007 regional airliner all-axial turbofan as a
baseline. The effort was further limited to the definition of an
exoskeletal high-pressure spool concept, where the major structural
and thermal challenges are represented. The mass of the
high-pressure spool was calculated and compared with the mass of
AE3007 engine components. It was found that the exoskeletal engine
rotating components can be significantly lighter than the rotating
components of a conventional engine. However, bearing technology
development is required, since the mass of existing bearing systems
would exceed rotating machinery mass savings. It is recommended
that once bearing technology is sufficiently advanced, a "clean
sheet" preliminary design of an exoskeletal system be accomplished
to better quantify the potential for the exoskeletal concept to
deliver benefits in mass, structural efficiency, and cycle design
flexibility.
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