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Inlet Total-Pressure-Distortion Considerations for Gas-Turbine Engines
- Aerospace Standard
Published May 28, 2013 by SAE International in United States
Downloadable datasets availableAnnotation ability available
This document addresses many of the significant issues associated with effects of inlet total-pressure distortion on turbine-engine performance and stability. It provides a review of the development of techniques used to assess engine stability margins in the presence of inlet total-pressure distortion. Specific performance and stability issues that are covered by this document include total-pressure recovery and turbulence effects and steady and dynamic inlet total-pressure distortion.
The intent of this document is to provide a basic understanding of the effects of inlet total-pressure distortion on the performance of gas turbine engines, particularly in military applications.
|Aerospace Standard||Inlet Total-Pressure-Distortion Considerations for Gas-Turbine Engines|
|Aerospace Standard||The Measurement of Engine Thrust in an Altitude Test Facility|
|Technical Paper||New Generation Engines - The Military Outlook for Adaptive Propulsion Systems|
Data Sets - Support Documents
|TABLE 1||ALTERNATIVE STABILITY MARGIN DEFINITIONS|
|TABLE 2||DIFFERENT STABILITY MARGIN DEFINITIONS RESULT IN DIFFERENT DISTORTION ACCOUNTING|
|TABLE 3||EFFECT OF STABILITY LIMIT LINE EXTRAPOLATION ON STABILITY ACCOUNTING|
|TABLE 4||METHODOLOGY SCREENS AND COEFFICIENT DETERMINATION|
|TABLE 5||STABILITY ASSESSMENT FACTORS|
|TABLE 6||FAN STABILITY-PRESSURE-RATIO LOSS COEFFICIENTS|
|TABLE 7||FAN STABILITY MARGIN ASSESSMENT|
|TABLE 8||TYPICAL STABILITY MARGIN ASSESSMENT|
|TABLE 9||CLASSICAL CIRCUMFERENTIAL SCREENS|
|TABLE 10||RADIAL AND MIXED SCREENS|
|TABLE 11||OPERATIONAL CONDITIONS|
|TABLE 12||TURBOFAN THRUST LOSS SYNTHESIS|
|TABLE 13||INLET AND AIRCRAFT COMPONENT TESTS|
|TABLE 14||ENGINE COMPONENT AND ENGINE TESTS|
|TABLE 15||PROPULSION SYSTEM TESTS|
|TABLE 16||FLIGHT TEST CONDITIONS|
|TABLE 17||ARP1420 GUIDELINES FOR LOCATION OF THE AIP|
|TABLE 18||DATA SCALING GUIDELINES: STROUHAL NUMBER CONSTANT (SAME REYNOLDS NUMBER AND MACH NUMBER)|
S-16 Turbine Engine Inlet Flow Distortion Committee
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