Research Papers: Gas Turbines: Aircraft Engine

Aircraft Propulsion System Flight Test—Analysis and Evaluation Challenges and Integrated Solutions

[+] Author and Article Information
Donald J. Malloy

US Air Force/AEDC Test Division,
Analysis Branch,
Arnold AFB, TN 37389

Grant T. Patterson

Aerospace Testing Alliance,
Arnold AFB, TN 37389

David S. Kidman

US Air Force/773rd Test Squadron,
Propulsion Integration Branch,
Edwards AFB, CA 93524

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the Journal of Engineering for Gas Turbines and Power. Manuscript received October 22, 2012; final manuscript received November 9, 2012; published online May 20, 2013. Editor: David Wisler.

J. Eng. Gas Turbines Power 135(6), 061201 (May 20, 2013) (9 pages) Paper No: GTP-12-1417; doi: 10.1115/1.4023610 History: Received October 22, 2012; Revised November 09, 2012

The paper describes the challenges and solution methodologies associated with the flight test and evaluation of the propulsion system for a twin-engine military legacy aircraft. Recent flight-test programs evaluated the effects of temperature distortion and biased engine inlet total temperature measurement (TT2) on engine scheduling and compressor stability margin. The challenges are associated with the limited instrumentation and the repeatability of the flight-test points. During the test program it was necessary to employ techniques to extend the usefulness of the data beyond that provided by the acquired and reduced data sets to address the challenges associated with flight-test analysis. The challenges were addressed using mathematical models, engine cycle decks, uninstalled ground-test data, computational fluid dynamics, or some combination of these. Several specific challenges and solutions are described in detail in the paper.

Copyright © 2013 by ASME
Your Session has timed out. Please sign back in to continue.



Grahic Jump Location
Fig. 1

Test configurations (not to scale)

Grahic Jump Location
Fig. 2

Compressor operating point algorithm

Grahic Jump Location
Fig. 3

Compressor stability margin loss definitions

Grahic Jump Location
Fig. 4

Simulated 40-probe data and interpolated temperature contour

Grahic Jump Location
Fig. 5

Empirical correlations for loss in stability pressure ratio for the example engine

Grahic Jump Location
Fig. 6

Flight variation adjustment for temperature differences

Grahic Jump Location
Fig. 7

Thermal stabilization example

Grahic Jump Location
Fig. 8

Predicted heat-transfer effects on T2 duct flow

Grahic Jump Location
Fig. 10

Fuselage thermal boundary layer

Grahic Jump Location
Fig. 11

Scoop and T2 attachment tube performance

Grahic Jump Location
Fig. 12

Snorkel/TT2 duct flow field and recovery

Grahic Jump Location
Fig. 13

CFD evaluation of proposed snorkel location




Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In