Accession Number:

ADA089067

Title:

High Bypass Turbofan Component Development. Amendment I. Small Fan Redesign.

Descriptive Note:

Final rept. Jun-Oct 79,

Corporate Author:

GENERAL ELECTRIC CO LYNN MA AIRCRAFT ENGINE GROUP

Personal Author(s):

• Mauch,H.
• Oldakowski,T.
• Sehra,A.
• Weldon,D.

Report Date:

1980-02-01

Pagination or Media Count:

34.0

Abstract:

The aerodynamic and mechanical redesign of a small, high through-flow, single stage fan rotor to increase its design-point airflow rate was completed. Since the original design exhibited excellent aeromechanical characteristics, the redesign was confined to changes in the blade meanline angle parameters such as maximum thickness-to-chord ratio, thickness distribution, aspect ratio, and solidity being unchanged from the original design. Procurement of the redesign fan rotor has been completed on schedule, thus fulfilling the requirements of this contract. Author

Descriptors:

• *FANS
• *ROTOR BLADES
• *AXIAL FLOW TURBINE ROTORS
• *HIGH BYPASS TURBOFANS
• AERODYNAMIC CONFIGURATIONS
• STRESS ANALYSIS
• ENGINE COMPONENTS
• EXPERIMENTAL DESIGN
• AERODYNAMIC CHARACTERISTICS

Subject Categories:

• Fluid Mechanics
• Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE