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Inlet Total-Pressure-Distortion Considerations for Gas-Turbine Engines
- Aerospace Standard
Published July 19, 2011 by SAE International in United States
Downloadable datasets availableAnnotation ability available
AIR1419 “Inlet Total Pressure Distortion Considerations for Gas Turbine Engines” documents engineering information for use as reference material and for guidance. Inlet total-pressure distortion and other forms of flow distortion that can influence inlet/engine compatibility require examination to establish their effect on engine stability and performance. This report centers on inlet-generated total-pressure distortion measured at the Aerodynamic Interface Plane (AIP), not because this is necessarily the sole concern, but because it has been given sufficient attention in the aircraft and engine communities to produce generally accepted engineering practices for dealing with it. The report does not address procedures for dealing with performance destabilizing influences other than those due to total-pressure distortion, or with the effects of any distortion on aeroelastic stability. The propulsion system designer must be careful to assure that, throughout the development process, other forms of inlet flow distortion, which can have just as serious effects on system stability and performance, have been effectively addressed.
The report deals with spatial total-pressure distortion, as defined by an array of high-response total-pressure probes. Time-variant total-pressure distortion, synthesized from statistical data, can provide useful information. However, the consensus of SAE S-16 is that such techniques are not developed sufficiently to permit general guidelines to be formulated.
Concepts which are fundamental to this report are:
Inlet flow quality can be characterized, in a form relevant to engine distortion response, with numerical descriptors derived from an array of high-response total-pressure probes;
Propulsion system stability can be controlled by the aircraft and engine designers;
Engine stability can be demonstrated by tests using equivalent levels of steady state distortion.
The report is organized into seven sections, expanding upon the ideas and recommended practice set forth in ARP1420. The first two sections deal with surge margin, loss of surge pressure ratio, and procedures for correlating the loss of surge pressure ratio with total-pressure distortion. Through use of the terms and procedures discussed earlier, Sections 5 and 6 develop engine stability and performance assessment techniques for handling total-pressure distortion by putting them into context with other destabilizing influences and performance detriments. Section 7 describes various test procedures, equipment, and methods currently available for generating the information needed to apply distortion assessment techniques. Section 8 discusses interface instrumentation, data-acquisition system accuracy, frequency response, record length, recording systems, and the data management procedures necessary to minimize communication errors among participating organizations. Section 9 provides a short overview of “state-of-the-art”, a brief discussion of other forms of distortion at the inlet/engine Aerodynamic Interface Plane, a summary of other considerations involved in assessments of inlet/engine compatibility, and brief summaries of probable future activity in each of these areas.
The distortion descriptor is the vehicle by which engine reaction to inlet distortion is forecast and assessed, from program outset well into field use of the system. ARP1420 defines the distortion descriptor as a non-dimensional, numerical representation of the measured inlet pressure distribution, and provides a means for identifying critical inlet flow distortions and for communicating during propulsion system development. Central issues are the distortion descriptors, methods of correlating them with performance and stability changes and test and information acquisition techniques. Use and accuracy of the descriptors vary, depending upon the stage of the engine development, but their definitions and purpose remain constant - to assess status, forecast stability and identify required engineering activity.
The activities associated with distortion descriptor use can be categorized for convenience in phases (Table 2), recognizing that there is little consensus concerning the definitions of these phases and that no clear lines of demarcation exist between them.
Equation 12 may be expressed for the full AIP or a tip or hub region at the AIP in the form:
Introducing circumferential and radial distortion parameters, DPC and DPR, for pure patterns
The terms KC and KR are empirically established circumferential and radial compressor sensitivities and are independent of the pattern. Then, for a combined distortion pattern
(Eq. 45)which may be written
The term B is a specified function of corrected flow and is independent of the pattern. Equation 46 may be used to define a screening parameter:
For pure circumferential distortion DPR = 0
For pure radial distortion DPC = 0, b = 1.0
|Aerospace Standard||Inlet Total-Pressure-Distortion Considerations for Gas-Turbine Engines|
|Aerospace Standard||A Methodology for Assessing Inlet Swirl Distortion|
Data Sets - Support Documents
|TABLE 1||Sponsoring Organizations and Participating Personnel SAE Aerospace Council Technical Committee S-16|
|TABLE 2||Distortion Assessment Uses During the Propulsion System Life Cycle|
|TABLE 3||Alternative Surge Margin Definitions|
|TABLE 4||Different Surge Margin Definitions Result in Different Distortion Accounting|
|TABLE 5||Effect of Surge Line Extrapolation on Stability Accounting|
|TABLE 6||Methodology Screens and Coefficient Determination|
|Unnamed Dataset 7|
|TABLE 7||Stability Assessment Factors|
|TABLE 8||Fan Surge-Pressure-Ratio Loss Coefficients|
|TABLE 9||Fan Surge Margin Assessment|
|TABLE 10||Typical Surge Margin Stability Assessment|
|TABLE 11||Classical Circumferential Screens|
|TABLE 12||Radial and Mixed Screens|
|Unnamed Dataset 14|
|TABLE 13||Operational Conditions|
|TABLE 14||Turbofan Thrust Loss Synthesis|
|TABLE 15||Inlet and Aircraft Component Tests|
|TABLE 16||Engine Component and Engine Tests|
|TABLE 17||Propulsion System Tests|
|TABLE 18||Flight Test Conditions|
|TABLE 19||ARP1420 Guidelines for Location of the AIP|
|TABLE 20||Data Scaling Guidelines Strouhal Number Constant (Same Reynolds Number and Mach Number)|
|TABLE 21||Recording Frequencies|
|TABLE 22||Analog Tape Information|
|TABLE 23||Digital Tape Information|
|Unnamed Dataset 26|
|Unnamed Dataset 27|
|TABLE A1||Stability Assessment Worksheet|
S-16 Turbine Engine Inlet Flow Distortion Committee
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