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Gas Turbine Engine Inlet Flow Distortion Guidelines
- Aerospace Standard
Published April 27, 2017 by SAE International in United States
Downloadable datasets availableAnnotation ability available
The turbine-engine inlet flow distortion methodology addressed in this document applies only to the effects of inlet total-pressure distortion. Practices employed to quantify these effects continue to develop and, therefore, periodic updates are anticipated. The effects of other forms of distortion on flow stability and performance, and of any distortion on aeroelastic stability are not addressed.
The guidelines can be used as necessary to create a development method to minimize the risk of inlet/engine compatibility problems. The degree to which guidelines for descriptor use, assessment techniques, and testing outlined in this document are applied to a specific program should be consistent with the expected severity of the compatibility problem.
This document provides definitions of stability margin and total-pressure distortion descriptors for gas turbine engines. In addition, guidelines for stability assessments, testing, instrumentation, data acquisition, and data processing are addressed. This document contains information that is fundamental to the discipline of inlet-engine compatibility and is expected to remain stable for the foreseeable future.
|Aerospace Standard||Inlet Total-Pressure-Distortion Considerations for Gas-Turbine Engines|
|Aerospace Standard||Turbofan and Turbojet Gas Turbine Engine Test Cell Correlation|
|Aerospace Standard||A Methodology for Assessing Inlet Swirl Distortion|
Data Sets - Support Documents
|[Unnamed Dataset 1]|
|TABLE 1||Data Scaling Guidelines Strouhal Number Constant (Same Reynolds Number and Mach Number)|
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