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INLET TOTAL-PRESSURE-DISTORTION CONSIDERATIONS FOR GAS-TURBINE ENGINES
- Aerospace Standard
- AIR1419
- Issued
Downloadable datasets available
Annotation ability available
Sector:
Issuing Committee:
Language:
English
Rationale
Equation 2.12 may be expressed for the full AIP or a tip or hub region at the AIP in the form:
(2.32)
Introducing circumferential and radial distortion parameters, DPC and DPR, for pure patterns
(2.33)
(2.34)
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
(2.35)
which may be written
(2.36)
where
The term B is a specified function of corrected flow and is independent of the pattern. Equation 2.36 may be used to define a screening parameter:
(2.37)
-
For pure circumferential distortion DPR = 0
-
For pure radial distortion DPC = 0, b = 1.0
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Topic
Data Sets - Support Documents
| Title | Description | Download |
|---|---|---|
| TABLE A | SPONSORING ORGANIZATIONS AND PARTICIPATING PERSONNEL SAE AEROSPACE COUNCIL TECHNICAL COMMITTEE S-16 | |
| TABLE B | DISTORTION ASSESSMENT USES DURING THE PROPULSION SYSTEM LIFE CYCLE | |
| TABLE 1.1 | Alternative Surge Margin Definitions | |
| TABLE 1.2 | Different Surge Margin Definitions Result in Different Distortion Accounting | |
| TABLE 1.3 | Effect of Surge Line Extrapolation on Stability Accounting | |
| TABLE 2.1 | Methodology Screens and Coefficient Determination | |
| Unnamed Dataset 7 | ||
| TABLE 3.1 | Stability Assessment Factors | |
| TABLE 3.2 | Fan Surge-Pressure-Ratio Loss Coefficients | |
| TABLE 3.3 | Fan Surge Margin Assessment | |
| TABLE 3.4 | Typical Surge Margin Stability Assessment | |
| TABLE 4.1 | Classical Circumferential Screens | |
| TABLE 4.2 | Radial And Mixed Screens | |
| Unnamed Dataset 14 | ||
| TABLE 4.3 | Operational Conditions | |
| TABLE 4.4 | Turbofan Thrust Loss Synthesis | |
| TABLE 5.1 | Inlet And Aircraft Component Tests | |
| TABLE 5.2 | Engine Component And Engine Tests | |
| TABLE 5.3 | Propulsion System Tests | |
| TABLE 5.4 | Flight Test Conditions | |
| TABLE 6.1 | ARP 1420 Guidelines For Location Of The AIP | |
| TABLE 6.2 | Data Scaling Guidelines. Strouhal Number Constant (Same Reynolds Number And Mach Number) | |
| TABLE 6.3 | Recording Frequencies | |
| TABLE 6.4 | Analog Tape Information | |
| TABLE 6.5 | Digital Tape Information | |
| Unnamed Dataset 26 | ||
| Unnamed Dataset 27 | ||
| TABLE A.1 | Stability Assessment Worksheet |
Issuing Committee
S-16 Turbine Engine Inlet Flow Distortion Committee
Scope: Committee S-16 develops uniform procedures for adoption by industry. These procedures will permit representation of inletdistortion and evaluation of its effect on propulsion systems' stability and performance.
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