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)

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1979
Accession Number
ADA082821

Entities

People

  • D. C. Chapman

Organizations

  • General Motors

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Aircrafts
  • Aspect Ratio
  • Boundary Layer
  • Cost Analysis
  • Dynamic Response
  • Failure Mode And Effect Analysis
  • Fan Blades
  • Flight Speeds
  • Frequency
  • Governments
  • High Bypass Turbofans
  • Leading Edges
  • Mach Number
  • Turbines
  • Turbofan Engines
  • Two Dimensional

Readers

  • Aerodynamics.
  • Aerospace Engineering
  • Software Engineering