Gas Turbine Engine Parameter Synthesis Using Model Correction
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Solution Overview
Problem
Existing methods for synthesizing engine parameters in gas turbine engines lack accuracy and precision, particularly when using onboard models that are less accurate than aero-thermal models.
Innovation Solution
A method and system that determine a synthesized engine parameter by obtaining an initial model parameter from an onboard model and applying a correction factor derived from the difference between the onboard model and an aero-thermal model, using engine parameters and operating conditions, to improve accuracy and precision.
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. This correction factor, derived from the differences between onboard model outputs and aero-thermal model outputs under various operating conditions, allows the system to maintain the operational simplicity of onboard models while achieving the measurement precision of complex aero-thermal models.
2Measurement precision
If a correction factor based on multiple parameters (altitude, temperature, pressure ratios) is applied, then the measurement precision of synthesized parameters is improved, but the device complexity increases
Solution Approach 1:
The patent applies preliminary action by pre-calculating correction factors for various combinations of operating conditions (altitude, temperature, pressure ratios) and storing them in correction tables. During actual operation, the system simply looks up the appropriate correction factor from these pre-computed tables based on current operating conditions, rather than performing complex real-time calculations. This approach achieves high measurement precision while maintaining relatively simple device complexity.
Data Source
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AI summary
In a method for determining a synthesized engine parameter of a gas turbine engine (100) an initial model parameter (305) is obtained from an onboard model (220) associated with the gas turbine engine (100). A correction factor for the onboard model (220) is determined by modifying a difference between the onboard model (220) and an aero-thermal model (210) of the gas turbine engine (100) using first and second engine parameters (302) and first and second operating conditions (304), wherein the first and second engine parameters (302) are independent from one another over an operating envelope of the gas turbine engine (100). The initial model parameter (305) is scaled by applying the correction factor thereto to obtain a corrected model parameter (330). The corrected model parameter (330) is output as the synthesized engine parameter.