Turbofan Thrust Synthesis via Compressor Exit Parameters
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Solution Overview
Problem
Existing techniques for estimating thrust from engines are not sufficiently accurate or efficient, particularly in varying operational conditions, necessitating improved methods for understanding and predicting engine performance.
Innovation Solution
A method and system for synthesizing thrust in turbofan engines using compressor exit pressure and temperature measurements, allowing for the calculation of a synthesized thrust value that aids in understanding current engine operating conditions and performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If existing techniques are used for estimating thrust from engines, then the estimation process is simpler, but the accuracy of thrust estimation is insufficient
Solution Approach 1:
The patent introduces compressor exit pressure and temperature as intermediary parameters to estimate thrust. These intermediaries serve as measurable proxies that correlate with thrust production, allowing accurate thrust estimation without direct measurement. The system uses these intermediary parameters in conjunction with engine operating conditions to calculate thrust, resolving the contradiction between accuracy and complexity.
Solution Approach 2:
The patent replaces complex mechanical thrust measurement systems with a computational approach. Instead of using direct mechanical sensors in the hot section, the system substitutes a calculation-based method that uses readily available engine parameters (compressor exit pressure, temperature, and operating conditions) to derive thrust. This substitution eliminates the need for complex instrumentation while maintaining or improving accuracy.
2Measurement precision
If instrumentation is placed in the hot section to measure thrust directly, then measurement accuracy improves, but engine component life decreases
Solution Approach 1:
The patent extracts the measurement function from the hot section environment and relocates it to the compressor exit, which is in the cold section. By taking out the pressure and temperature sensors from the harsh hot section and placing them in the more benign compressor exit environment, the system maintains measurement accuracy while eliminating the detrimental effects of high temperature and pressure on sensor life and engine components.
Solution Approach 2:
The patent uses compressor exit parameters as intermediaries to indirectly measure thrust without direct contact in the hot section. This intermediary approach allows the system to obtain accurate thrust data while keeping all instrumentation in the cooler compressor section, thereby protecting both the sensors and engine components from thermal damage and extending their operational life.
3Loss of information
If direct thrust measurement is used, then understanding of engine operating conditions is more direct, but the system becomes more complex
Solution Approach 1:
The patent makes the compressor exit pressure and temperature sensors serve multiple functions. These same sensors are used both for engine control and for thrust estimation, eliminating the need for separate dedicated thrust measurement instrumentation. This multi-functionality approach provides comprehensive information about engine operating conditions while keeping the system simple by reusing existing sensors.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The proposed solution enables accurate synthesis of engine thrust, improving predictability and understanding of engine performance, while potentially extending engine component life by reducing the need for instrumentation in the hot section.
Implementation Method 1
a compressor section 14 for pressurizing the air
Implementation Method 2
a combustor 16 in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases
Implementation Method 3
a turbine section 18 for extracting energy from the combustion gases
Data Source
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AI summary
A method and a system for synthesizing thrust from a turbofan engine (100) are provided. The turbofan engine (100) comprising a compressor section (14), a combustor (16), and a turbine section (18) in serial fluid flow communication. The engine is operated and, during the operating of the turbofan engine (100), a pressure of fluid at an exit of the compressor section (14) and a temperature of fluid at a location upstream of the exit of the compressor section (14) are determined. A synthesized value of thrust from the turbofan engine (100) is determined based on a product of at least a first factor and a second factor, the first factor being a function of the pressure and the second factor being a function of the temperature. The synthesized value of thrust from the turbofan engine (100) is output.