Turbine Temperature Estimation via Thermodynamic Surface Maps
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Solution Overview
Problem
Existing measurement systems for gas turbine engines struggle to accurately measure turbine temperature and other engine parameters at high temperatures, leading to inaccuracies in engine control and safety.
Innovation Solution
The method involves generating three-dimensional thermodynamic surface maps based on a thermodynamic engine model, capturing measurable engine parameters during flight, and using these maps to estimate unmeasured temperature values, which are then used to control the gas turbine engine.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If temperature measurements are made downstream of the turbine in a lower temperature environment, then measurement device reliability is improved, but measurement precision deteriorates because the downstream values do not reflect actual turbine temperature
Solution Approach 1:
The patent introduces thermodynamic surface maps as an intermediary between the measurable downstream parameters and the actual turbine temperature. These maps serve as a translation mechanism that correlates downstream measurements (temperature, pressure, shaft speed) to upstream turbine conditions through pre-computed thermodynamic relationships, resolving the contradiction by enabling indirect but accurate measurement.
Solution Approach 2:
The patent creates a virtual copy of the turbine inlet temperature through thermodynamic surface maps. Instead of directly measuring the actual turbine temperature, the system computes a correlated value based on downstream measurements and thermodynamic models, effectively creating an accurate representation of the unmeasurable parameter.
2Measurement precision
If direct measurement of actual turbine temperature is attempted, then measurement precision is improved, but device complexity and reliability worsen due to the extreme high temperature environment exceeding maximum operating temperature for measurement devices
Solution Approach 1:
The patent uses thermodynamic surface maps as an intermediary to bridge the gap between measurable downstream parameters and the unmeasurable upstream turbine temperature. This approach avoids direct exposure of measurement devices to extreme temperatures while maintaining measurement accuracy through computational correlation.
Solution Approach 2:
The patent replaces direct mechanical/physical temperature measurement in the high-temperature turbine environment with a computational thermodynamic model. Instead of using temperature sensors in the hot zone, the system uses a thermodynamic engine model that calculates turbine temperature from downstream measurements, substituting physical measurement with computational analysis.
3Reliability
If thermodynamic surface maps and computational models are used to estimate turbine temperature, then reliability is improved by avoiding direct measurement in high temperature environments, but device complexity increases due to the need for multiple surface maps and computational processing
Solution Approach 1:
The patent performs preliminary computation of thermodynamic surface maps during the design and testing phase. These pre-computed maps capture the complex thermodynamic relationships and are stored for rapid lookup during operation. This preliminary action transfers computational complexity from the operational phase to the design phase, reducing real-time processing requirements.
Solution Approach 2:
The patent transforms the complex thermodynamic relationships into a three-dimensional surface map structure with specific dimensions (e.g., shaft speed, downstream temperature, downstream pressure). This dimensional organization enables efficient data retrieval and reduces computational complexity during operation by converting a complex multi-variable problem into a structured lookup operation.
Data Source
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AI summary
A method includes: receiving a plurality of measurable engine parameters captured using aerial vehicle sensors; reading an estimated parameter value from each of a plurality of thermodynamic surface maps, wherein the plurality of thermodynamic surface maps have a first dimension comprising a first thermodynamic engine parameter, a second dimension comprising a second thermodynamic engine parameter, and a third dimension comprising a third thermodynamic engine parameter whose value is related to the first thermodynamic engine parameter and the second thermodynamic engine parameter, wherein the estimated parameter values are read from the third thermodynamic engine parameter from each of a plurality of thermodynamic surface maps based on selected values for a first thermodynamic engine parameter and a second thermodynamic engine parameter; estimating an unmeasured temperature value based on the estimated parameter values read from the plurality of thermodynamic surface maps; and controlling the turbine engine based on the estimated unmeasured temperature value.