High Bypass Turbofan Component Development. Phase II. Fan Detail Design.

Abstract : The objective of this program is to develop an advanced, small, high bypass turbofan component applicable to an advanced, fuel-efficient engine for a new Air Force primary trainer aircraft. The program consists of two phases. Phase I consisted of the preliminary design and life cycle cost analysis of candidate engines. This report documents Phase II which was the detail design of the selected fan configuration. Primary design point of the fan is 1.8 pressure ratio at 55.9 lbm/sec flow. At a lower speed, the fan will produce 1.65 pressure ratio at a flow compatible with the GMA500 advanced technology core engine. The resultant engine satisfies all requirements of the contract. The fan stage meets all requirements of Mil-E-5007D, including bird ingestion and predicted noise levels are below FAR Part 36 requirements. (Author)