Gas Turbine Engine Parameter Synthesis With Model Correction
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Solution Overview
Problem
Existing methods for synthesizing engine parameters in gas turbine engines, such as the onboard model, lack accuracy and precision compared to more complex aero-thermal models, necessitating a method to improve the accuracy of synthesized parameters.
Innovation Solution
A method and system that determine a correction factor by modifying the difference between the onboard model and the aero-thermal model using independent engine parameters and operating conditions, which is then applied to scale the initial model parameter to produce a corrected, more accurate synthesized engine parameter.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If an onboard model is used to synthesize engine parameters, then the system complexity is reduced and ease of operation is improved, but the measurement precision and reliability of the synthesized parameters deteriorate
Solution Approach 1:
The patent introduces a correction factor as an intermediary element that mediates between the simple onboard model and the accurate reference values from aero-thermal models or sensor measurements. This correction factor is determined by comparing onboard model outputs with reference values and using the difference to adjust future onboard model predictions, thereby improving measurement precision while maintaining the ease of operation of the onboard model
Solution Approach 2:
The patent implements a feedback mechanism where the difference between onboard model synthesized parameters and reference parameters (from aero-thermal models or sensors) is calculated and used to determine a correction factor. This correction factor is then applied to subsequent onboard model predictions, creating a closed-loop system that continuously improves accuracy while maintaining operational simplicity
2Device complexity
If an onboard model is used to synthesize engine parameters, then the device complexity is reduced, but the reliability of the synthesized parameters deteriorates
Solution Approach 1:
The correction factor serves as an intermediary that bridges the gap between the simple onboard model and reliable reference data. By applying this correction factor to onboard model outputs, the system maintains low device complexity while significantly improving the reliability of synthesized parameters through data from more accurate aero-thermal models or sensors
Solution Approach 2:
The feedback loop continuously refines the correction factor by comparing onboard model predictions with reliable reference measurements. This iterative process improves parameter reliability over time without increasing device complexity, as the correction factor is determined through computational processing of existing data rather than additional hardware
3Measurement precision
If a correction factor is determined by modifying the difference between onboard model and aero-thermal model using multiple independent engine parameters, then the measurement precision of synthesized parameters is improved, but the device complexity increases
Solution Approach 1:
The patent changes parameters by introducing multiple independent engine parameters (such as mass flow rate, power output, ambient temperature, and pressure ratio) to characterize the operating envelope. These parameter changes enable more precise correction factor determination across different operating conditions, improving measurement precision while managing device complexity through systematic parameter selection
Data Source
AI summary
The present disclosure provides methods and systems for determining a synthesized engine parameter of a gas turbine engine. An initial model parameter is obtained from an onboard model associated with the gas turbine engine. A correction factor for the onboard model is determined by modifying a difference between the onboard model and an aero-thermal model of the gas turbine engine using first and second engine parameters and first and second operating conditions, wherein the first and second engine parameters are independent from one another over an operating envelope of the gas turbine engine. The initial model parameter is scaled by applying the correction factor thereto to obtain a corrected model parameter. The corrected model parameter is output as the synthesized engine parameter.