Abstract
A life cycle cost (LCC) methodology is presented which can be effectively applied during advanced development of turbine engines and engine components. The APSICOST (Aircraft Propulsion Subsystem Integrated Cost of Ownership with System Tradeoffs) methodology is sensitive to engine design and performance parameters, reflects the impact of engine design decisions on total system LCC, and is economical and timely to apply. The application of the APSICOST methodology to an aircraft/engine baseline design study for an undergraduate pilot training mission is described. This system baseline is then used to evaluate the LCC reduction potential of five alternate engine component development concepts: centrifugal compressor rotor, axial compressor rotor, LP turbine rotor, LP turbine assembly, and low aspect ratio fan. It was found that engines in the bypass ratio range 1.0 to 1.65 offer the lowest LCC in a fixed-mission, high-performance trainer/light strike fighter application. The LCC savings can be as much as $1.5 billion for a 700 aircraft fleet vs. the choice of a high bypass ratio engine. The low aspect ratio fan concept was selected as the best of the five candidate concepts, with an estimated potential system LCC savings of $93.48 million. A joint airframe/propulsion/government effort is recommended to standardize methods for reflecting aircraft system LCC impacts in advanced turbine engine development.
Published Version
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