TECHNICAL PAPERS: Gas Turbines: Aircraft Engine

A Numerical Simulation Capability for Analysis of Aircraft Inlet-Engine Compatibility

[+] Author and Article Information
Alan Hale, Milt Davis, Jim Sirbaugh

Aerospace Testing Alliance (ATA),  Arnold Engineering Development Center, Arnold AFB, TN 37389-9013

J. Eng. Gas Turbines Power 128(3), 473-481 (Mar 01, 2004) (9 pages) doi:10.1115/1.1925649 History: Received October 01, 2003; Revised March 01, 2004

Two primary aircraft propulsion subsystems are the inlet and the engine. Traditionally these subsystems have been designed, analyzed, and tested as isolated systems. The interaction between the subsystems is modeled primarily through evaluating inlet distortion in an inlet test and then simulating this distortion in engine tests via screens or similar devices. Recently, it has been recognized that significant improvements in both performance and operability can be realized when both the inlet and the engine are designed with full knowledge of the other. In this paper, a computational tool called Turbine Engine Analysis Compressor Code is used to evaluate the effect of inlet distortion on a three-stage military fan. This three-stage military fan is further connected to an F-16 inlet and forebody operating at an angle of attack and sideslip to demonstrate the effect of inlet distortion generated by flight maneuvers. The computational approach of simulating an integrated inlet-engine system is expected to provide additional insight over evaluating the components separately.

Copyright © 2006 by American Society of Mechanical Engineers
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Figure 1

CFD flow field and inlet computations of the F-16 inlet and AIP

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Figure 2

TEACC technical approach

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Figure 3

Streamline curvature code geometry and far-field boundary condition

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Figure 4

Steady-state methodology for calculating turbomachinery source terms

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Figure 5

Modifications to SLCC for calculating dynamic source terms over a single blade row

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Figure 6

Grid layout for three-stage fan

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Figure 7

Three-stage military fan performance for clean inlet flow

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Figure 8

Total and static pressure for three-stage fan at 80% corrected speed

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Figure 9

Three-stage military fan at 90% speed with total pressure distortion in one quadrant

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Figure 10

Three-stage military fan at 90% speed with total-temperature distortion in one quadrant

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Figure 11

Fan transient with both pressure and temperature distortion present—collocated and opposing

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Figure 12

Inlet computational setup with and without the three-stage military fan

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Figure 13

Total and static pressure profiles at the AIP with and without the three-stage military fan connected to the inlet

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Figure 14

Simulation of F-16 inlet-fan combination while at high angles of attack and sideslip




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