This content is not included in your SAE MOBILUS subscription, or you are not logged in.
Inlet Total-Pressure-Distortion Considerations for Gas-Turbine Engines
- Aerospace Standard
Published November 20, 2017 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. The document was revised to incorporate an Introduction containing material inadvertently omitted from revision B.
|Aerospace Standard||Gas Turbine Engine Inlet Flow Distortion Guidelines|
|Aerospace Standard||A Methodology for Assessing Inlet Swirl Distortion|
|Aerospace Standard||Distortion Synthesis/Estimation Techniques|
Data Sets - Support Documents
|Table 1||Distortion assessment uses during the propulsion system life cycle|
|Unnamed Dataset 2|
|Table 2||Alternative stability margin definitions|
|Table 3||Different stability margin definitions result in different distortion accounting|
|Table 4||Effect of stability limit line extrapolation on stability accounting|
|Table 5||Methodology screens and coefficient determination|
|Table 6||Stability assessment factors|
|Table 7||Fan stability-pressure-ratio loss coefficients|
|Table 8||Fan stability margin assessment|
|Table 9||Typical stability margin assessment|
|Table 10||Classical circumferential screens|
|Table 11||Radial and mixed screens|
|Table 12||Operational conditions|
|Table 13||Turbofan thrust loss synthesis|
|Table 14||Inlet and aircraft component tests|
|Table 15||Engine component and engine tests|
|Table 16||Propulsion system tests|
|Table 17||Flight test conditions|
|Table 19||Data scaling guidelines: Strouhal number constant (same Reynolds number and Mach number)|
* Redlines comparisons are available for those standards listed in the Revision History that contain a radio button. A redline comparison of the current version against a revision is accomplished by selecting the radio button next to the standard and then selecting 'compare'. At this time, Redline versions only exist for some AMS standards. SAE will continue to add redline versioning with ongoing updates to SAE MOBILUS.