Geared Turbomachine Fan and Compressor Synchronization
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Solution Overview
Problem
Recent turbomachine engine architectures face challenges in maximizing performance due to the differing rotational directions and speeds of the fan and compressor rotors.
Innovation Solution
A high-bypass ratio geared turbomachine design where the rotor of the low-pressure compressor rotates together with the fan rotor at the same speed and direction, utilizing a geared architecture to achieve this synchronization.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If the fan and low-pressure compressor rotors rotate separately in opposite directions at different speeds, then the turbomachine can achieve higher performance through optimized airflow control, but the mechanical complexity and synchronization difficulty increase
Solution Approach 1:
The patent combines the fan rotor and low-pressure compressor rotor into a single integrated rotor assembly that rotates together in the same direction at the same speed, eliminating the need for separate drive shafts and complex synchronization mechanisms while maintaining optimized airflow control for high bypass ratio performance
2Productivity
If the fan and low-pressure compressor rotors rotate in opposite directions at different speeds, then airflow optimization is improved, but the bearing system complexity and maintenance requirements increase
Solution Approach 1:
By merging the fan and low-pressure compressor rotors into a single rotating assembly, the patent reduces the bearing system from multiple separate bearings supporting independently rotating shafts to a single bearing system supporting one common rotor, thereby simplifying manufacturing and maintenance
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 design enhances turbomachine performance by allowing for a higher fan bypass ratio and overall compression ratio, leading to improved efficiency and thrust generation.
Implementation Method 1
a geared architecture connecting the fan section and the turbine section
Implementation Method 2
the shaft that rotates the fan rotor and the compressor rotor rotates at a second speed different than the first speed
Implementation Method 3
a shaft that is rotatably supported by a plurality of tapered bearings
Implementation Method 4
at least one thrust bearing may rotatably support the turbine shaft
Data Source
AI summary
An exemplary gas turbine engine includes a fan section including a fan rotor and at least one fan blade. A fan pressure ratio across the at least one fan blade is less than 1.45, noninclusive of the pressure across any fan exit guide vane system. The engine further includes a low-pressure compressor having a low-pressure compressor rotor that rotates together with the fan rotor at a common speed in operation, and a geared architecture that drives the low-pressure compressor rotor and the fan rotor. The geared architecture has a gear reduction ratio of greater than 2.5. The engine further includes a high-pressure compressor having a pressure ratio greater than 20, a low-pressure turbine having a pressure ratio greater than 5, and a bypass ratio greater than 10.