Aircraft ECS Turbine Weight Flow Control Without Extra Sensors
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Solution Overview
Problem
Existing aircraft environmental control systems require additional weight flow sensors, increasing complexity and weight, which in turn increase fuel consumption and operational costs.
Innovation Solution
The method determines weight flow through a turbine using existing sensors and a Turbine Flow Coefficient Map, eliminating the need for a separate weight flow sensor by calculating weight flow based on turbine inlet pressure, outlet pressure, rotational shaft speed, and nozzle area, and adjusts valve settings to maintain a target range.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If a weight flow sensor is added to directly measure weight flow through the turbine, then measurement precision is improved, but device complexity and weight increase
Solution Approach 1:
The patent introduces intermediate parameters (pressure, temperature, shaft speed) as mediators to indirectly determine weight flow. Instead of directly measuring weight flow with a sensor, the system uses these intermediate measurements combined with turbine characteristics to calculate the weight flow, thereby avoiding the need for a direct weight flow sensor and reducing system complexity
Solution Approach 2:
The patent replaces the mechanical/physical weight flow sensor with a computational approach. By substituting the direct measurement device with a calculation system that uses thermodynamic relationships and turbine performance data, the system achieves the same measurement objective without the additional hardware complexity
2Measurement precision
If a weight flow sensor is added to directly measure weight flow through the turbine, then measurement precision is improved, but weight increases leading to fuel consumption increase
Solution Approach 1:
The patent uses intermediate parameters (pressure, temperature, shaft speed) as mediators to indirectly determine weight flow. This indirect measurement approach eliminates the need for a direct weight flow sensor, reducing aircraft weight and consequently fuel consumption while maintaining measurement capability
Solution Approach 2:
The patent extracts the weight flow measurement capability from a separate physical sensor and integrates it into the existing control system through calculation. By taking out the need for a dedicated weight flow sensor, the system reduces overall weight and associated fuel consumption
3Device complexity
If existing sensors and calculation methods are used to determine weight flow, then device complexity is reduced, but measurement precision may be compromised
Solution Approach 1:
The patent uses multiple intermediate parameters (inlet pressure, outlet pressure, temperature, shaft speed) as mediators to reconstruct weight flow information. By utilizing several intermediate measurements rather than a single direct measurement, the system compensates for individual measurement uncertainties and achieves accurate weight flow determination through calculation
Solution Approach 2:
The patent makes the existing sensors serve multiple functions. The pressure and temperature sensors, originally intended for other control purposes, are also used for weight flow determination. This multi-functionality approach maintains measurement precision while avoiding additional sensors and system complexity
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
This approach reduces system complexity and weight, leading to fuel and cost savings by eliminating the need for additional sensors and enhancing the efficiency of air pressure regulation for cabin comfort and safety.
Implementation Method 1
Air is expanded through a turbine to drive a shaft
Implementation Method 2
Air is compressed in a compressor
Data Source
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AI summary
A method of determining and controlling a weight flow in an environmental control system includes sensing, using a turbine inlet temperature sensor (120), a turbine inlet temperature. A turbine inlet pressure is sensed using a turbine inlet pressure sensor (122). A turbine outlet pressure is sensed using a turbine outlet pressure sensor (124). A rotational shaft speed of a shaft is sensed using a rotational shaft speed sensor (126). The sensed turbine inlet temperature, the sensed turbine inlet pressure, the sensed turbine outlet pressure, and the sensed rotational shaft speed are received by a controller (130). A flow coefficient is determined by the controller using the turbine inlet pressure, the turbine outlet pressure, the shaft speed, and a Turbine Flow Coefficient Map. A weight flow through the turbine is determined by the controller using the flow coefficient, the turbine inlet temperature, a nozzle area, and the turbine inlet pressure.