Variable Pitch Fan and Compressor for Gas Turbine Optimization
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Solution Overview
Problem
Gas turbine engines face challenges in optimizing performance characteristics such as fuel consumption, thrust, inlet temperature, noise, and emissions across varying operating conditions and flight phases due to limitations in existing fixed geometry designs.
Innovation Solution
A gas turbine engine with a variable pitch fan and compressor geometry, controlled by a system that adjusts fan blades and compressor vanes to specific angles within preset limits, optimizing performance characteristics based on current operating conditions and flight phases.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If fixed geometry designs are used, then device complexity is reduced, but adaptability to different operating conditions deteriorates
Solution Approach 1:
The patent applies variable pitch mechanisms to both fan blades and compressor vanes, allowing their geometry to dynamically adjust according to operating conditions. The fan blade pitch can be varied independently from the compressor vane pitch, enabling the system to adapt to different flight phases and operating scenarios while maintaining manageable complexity through systematic control architecture.
2Productivity
If variable pitch fan and compressor geometry are implemented, then performance optimization across different operating conditions is improved, but device complexity increases
Solution Approach 1:
Variable pitch mechanisms are implemented on both fan blades and compressor vanes, enabling dynamic geometry adjustment to optimize performance across different operating conditions including various flight phases, altitudes, and throttle settings.
Solution Approach 2:
The pitch angles of fan blades and compressor vanes are varied as controllable parameters to optimize engine performance. The control system adjusts these geometric parameters based on operating conditions to maximize fuel efficiency, thrust, and reduce emissions across the operating envelope.
Solution Approach 3:
The variable pitch fan and compressor system serves multiple functions: optimizing fuel consumption during cruise, maximizing thrust during takeoff and climb, reducing noise during approach and landing, and controlling emissions across all operating phases, making it a multi-functional performance optimization system.
3Productivity
If geometry is adjusted to optimize performance characteristics, then fuel efficiency and thrust are improved, but operational safety limits may be approached
Solution Approach 1:
The control system continuously monitors operating parameters and adjusts fan blade pitch and compressor vane pitch in real-time while maintaining adherence to preset operational limits such as surge margins, temperature constraints, and structural load limits, ensuring both performance optimization and operational safety.
Solution Approach 2:
The system varies geometric parameters within bounded ranges defined by safety limits. The control algorithm selects optimal pitch angles from feasible ranges that balance performance optimization with adherence to operational constraints including surge limits, temperature limits, and mechanical load limits.
Data Source
AI summary
A gas turbine engine includes a fan and an engine core that includes a compressor, a combustor, and a turbine. The fan and the compressor include variable pitch geometry. The gas turbine engine further includes a control system configured to adjust the variable pitch geometry of the fan and the compressor to optimize a performance characteristic of the gas turbine engine.