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SAE AIR5867 2017 Edition, November 1, 2017
Assessment of the Inlet/Engine Total Temperature Distortion Problem
Description / Abstract:
This report revises ARD50015 document to the AIR format. This report, as was the original, is intended to complement ARP1420C and AIR1419C documents issued by the SAE S-16 Committee on spatial total-pressure distortion.
These previous documents addressed only total-pressure distortion and excluded total temperature distortion. The subject of inlet total temperature distortion is addressed in this report with some background and identification of the problem area. The status of past efforts is reviewed, and an attempt is made to define where we are today. Deficiencies, voids, and limitations in knowledge and test techniques for total temperature distortion are identified.
Purpose
Suggested approaches to fill these voids and a proposed total temperature distortion methodology are presented. Successful techniques, employed to date, are reviewed and recommendations for future research work are indicated.
Field of Application
Intake/engine aerodynamic compatibility continues to be a major interface operability consideration affecting the design and development of aircraft propulsion systems. Engine performance degradation, including power loss due to engine blowout and/or compressor instability, has been attributed to engine inlet total temperature distortion (time-variant spatial total temperature distortion and/or total temperature ramp at the Aerodynamic Interface Plane (AlP)). Reported inlet distortion sources include ingestion of gases from armament firings, ingestion of steam from catapult launch systems, ingestion of engine exhaust gases from thrust reverser systems, and ingestion of engine exhaust gases during helicopter and V/STOL aircraft operations.
System operability problems generally have been solved by avoiding or minimizing AlP total temperature variations by system configuration changes and/or operating procedure changes (reduced system operability) to remove the source of high-temperature gases from the capture region of the aircraft inlet system, or by engine accommodations to withstand the distortion. Total temperature distortion avoidance techniques are not practical for all systems. In order to properly account for and accommodate total temperature distortion, guidelines for understanding turbine engine response to and accounting for total temperature distortion are required.
A significant database that can be used as a start for the future formulation of recommended industry guidelines is reported. An inlet total temperature distortion problem assessment and status review, based on available data, are summarized in this report with suggestions for the development of practical guidelines.
These previous documents addressed only total-pressure distortion and excluded total temperature distortion. The subject of inlet total temperature distortion is addressed in this report with some background and identification of the problem area. The status of past efforts is reviewed, and an attempt is made to define where we are today. Deficiencies, voids, and limitations in knowledge and test techniques for total temperature distortion are identified.
Purpose
Suggested approaches to fill these voids and a proposed total temperature distortion methodology are presented. Successful techniques, employed to date, are reviewed and recommendations for future research work are indicated.
Field of Application
Intake/engine aerodynamic compatibility continues to be a major interface operability consideration affecting the design and development of aircraft propulsion systems. Engine performance degradation, including power loss due to engine blowout and/or compressor instability, has been attributed to engine inlet total temperature distortion (time-variant spatial total temperature distortion and/or total temperature ramp at the Aerodynamic Interface Plane (AlP)). Reported inlet distortion sources include ingestion of gases from armament firings, ingestion of steam from catapult launch systems, ingestion of engine exhaust gases from thrust reverser systems, and ingestion of engine exhaust gases during helicopter and V/STOL aircraft operations.
System operability problems generally have been solved by avoiding or minimizing AlP total temperature variations by system configuration changes and/or operating procedure changes (reduced system operability) to remove the source of high-temperature gases from the capture region of the aircraft inlet system, or by engine accommodations to withstand the distortion. Total temperature distortion avoidance techniques are not practical for all systems. In order to properly account for and accommodate total temperature distortion, guidelines for understanding turbine engine response to and accounting for total temperature distortion are required.
A significant database that can be used as a start for the future formulation of recommended industry guidelines is reported. An inlet total temperature distortion problem assessment and status review, based on available data, are summarized in this report with suggestions for the development of practical guidelines.
SAE AIR5867 2017 Edition, November 1, 2017
Assessment of the Inlet/Engine Total Temperature Distortion Problem