Accession Number:

ADA090506

Title:

Numerical Analysis of the Flow in the Connecting Passage between the Fan Section and High Pressure Section of a Turbojet Engine.

Descriptive Note:

Final rept.,

Corporate Author:

TEXAS TECH UNIV LUBBOCK DEPT OF MECHANICAL ENGINEERING

Personal Author(s):

• Goldman,Allen

Report Date:

1980-06-01

Pagination or Media Count:

89.0

Abstract:

The flow field in a bifurcated channel was calculated using finite difference techniques which incorporated a body fitted coordinate system. The flow model used was incompressible and could be axisymmetric or two-dimensional and laminar or turbulent flow. The objective was to calculate the flow field for a Reynolds number of 750000. It was found that the results obtained from the axisymmetric formulation were different from the two-dimensional formulation. Since the actual flow geometry is axisymmetric this means that only the axisymmetric formulation should be used in further investigations. The maximum velocity in the channel was 1.7 times the inlet velocity which corresponds to a Mach number of greater than .5. Therefore, the flow is compressible and further investigations should incorporate this fact. Author

Descriptors:

• *CHANNEL FLOW
• *AIRCRAFT ENGINE DUCTS
• COMPUTATIONS
• COMPARISON
• TURBULENT FLOW
• FINITE DIFFERENCE THEORY
• COMPRESSIBLE FLOW
• FLOW FIELDS
• TWO DIMENSIONAL FLOW
• SUBROUTINES
• NAVIER STOKES EQUATIONS
• MACHINE CODING
• REYNOLDS NUMBER
• AXISYMMETRIC FLOW

Subject Categories:

• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE