Turbomachine Thrust Margin Measurement Bias Correction
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Solution Overview
Problem
The measurement of thrust margin in turbomachines is influenced by varying test conditions, equipment, and suppliers, leading to dispersion and uncertainty in thrust measurements across different test benches.
Innovation Solution
A method and device that calculate a linear or affine function to model the temporal evolution of thrust margin, correcting for biases introduced by bench components and suppliers, ensuring the thrust margin is independent of test conditions and reducing dispersion by subtracting biases from measurements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If thrust measurements are taken on different test benches with different equipment, then measurement versatility is improved, but measurement precision deteriorates due to dispersion from varying test conditions
Solution Approach 1:
The patent applies parameter changes by introducing correction parameters (biases) that represent the influence of different test bench components. These parameters are calculated based on reference measurements and then applied to correct thrust measurements, transforming the measurement data to account for variations in test conditions while maintaining measurement versatility across different benches
Solution Approach 2:
The patent implements feedback through an iterative correction process. Bias parameters are calculated from reference measurements, applied to correct thrust measurements, and the correction results are used to update bias estimates. This closed-loop feedback mechanism progressively reduces measurement dispersion while allowing measurements across multiple test benches
2Measurement precision
If calibration is performed over very long periods to achieve high accuracy, then measurement precision is improved, but productivity deteriorates due to extended calibration time
Solution Approach 1:
The patent applies preliminary action by pre-calculating bias parameters for each test bench component using reference measurements. These pre-computed correction parameters are then stored and applied to subsequent thrust measurements without requiring repeated long-duration calibration procedures, significantly reducing calibration time while maintaining accuracy
Solution Approach 2:
The patent transforms the calibration approach by changing from time-intensive iterative calibration to parameter-based correction. By representing calibration information as compact bias parameters that can be quickly computed and applied, the system achieves high measurement accuracy without requiring prolonged calibration periods
Data Source
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AI summary
The invention relates to a method for measuring the thrust margin of a turbomachine (TUR), in which data is acquired including the thrust margin (y, yi), which is determined as a function of a specified thrust (PSP) and a measured thrust (PST). The measured thrust (PST) is determined on a measuring bench (BM), which comprises bench equipment (k) and on which the turbomachine (TUR) is located. The method is characterized in that a time evolution of the thrust margin (y, yi) is modeled by at least one linear or affine function (Φ, ϕj(ti)), which is calculated for at least a determined time interval (INT1) of the thrust margin (y, yi). At least one bias (bk) of the bench equipment (k) is calculated with respect to the at least one linear or affine function (Φ, ϕj(ti)) having been calculated. The thrust margin (y, yi) is then corrected by subtracting at least one bias. (bk) of the equipment (k) of the bench in at least one determined time interval (INT1).