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基本信息

ARP1420B
Gas Turbine Engine Inlet Flow Distortion Guidelines
Gas Turbine Engine Inlet Flow Distortion Guidelines
2011-07-01
有效
【范围】 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.strRefField
【与前一版的变化】

包含缩略语

AIP:Aerodynamic Interface Plane
ARP:Aerospace Recommended Practice
C:Offset term (Equation A9)
C(τ):Covariance of time varying pressures
f:Frequency
KC:Circumferential distortion sensitivity (Equation A9)
KR:Radial distortion sensitivity (Equation A9)
L:Characteristic length (cowl lip to compressor face)
MPR:Multiple-per-revolution element
N:Number of instrumentation rings
P:Total pressure
- P:Time-averaged total pressure
PAV:Ring average total pressure
PAVLOW:Average total pressure of low total-pressure region for a ring (Equations A2 and A5)
PFAV:Face average total pressure (A.1.2)
PR:Pressure ratio of given compression components
PRDS:Stability pressure ratio with distortion
PRO:Operating pressure ratio
PR1:Undistorted stability pressure ratio
P(θ):Total pressure at any angle θ for a given ring
Q:Number of low-pressure regions
R:Radius
RMS:Root mean square
SM:Stability margin
T:Total temperature
ΔPC/P:Circumferential distortion intensity element (Equations A2 and A5, A.1.1)
ΔPR/P:Radial distortion intensity element (Equation A8, A.1.2)
ΔPRMS:Root mean square of time varying total-pressure fluctuations
ΔPRS:Stability pressure ratio loss (Equation A9)
ΔSM:Stability margin loss (Equation A10)
θ:Circumferential location in degrees
θ +:Extent of high-total-pressure region
θ –:Extent of low-total-pressure region
τ:Time increment
φ (f):Power spectral density of time-varying pressure
c:Circumferential
i:
j:
k:
MAX:
MIN:
r:

替代标准

引用文件/被引文件

Orientation of Engine Axis
Gas turbine Engine Steady State Performance Presentation for Digital Computer Programs
Turbine Engine Performance Station Identification and Nomenclature
Gas Turbine Engine Interface Test Data Reduction Computer Programs
Gas Turbine Engine Transient Performance Presentation for Digital Computer Programs
Inlet Total-Pressure-Distortion Considerations for Gas-Turbine Engines

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包含图表

formula 1
Stability Margin Def
formula 2
Probe Orientation -
Digital Data Acquisi
Ring Circumferential
formula 3
Ring Circumferential
formula 4
formula 5
formula 6
formula 7
formula 8
formula 9
formula 10
Radial Distortion Pa
formula 11
formula 12
Data Scaling Guideli

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