Geared Fan and Booster Compressor Speed Split in Gas Turbines
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Solution Overview
Problem
Existing gas turbine engines face inefficiencies due to non-optimized fan and high-pressure/low-pressure turbine speeds, necessitating the use of a gearbox that reduces airflow and increases weight, complexity, and manufacturing costs.
Innovation Solution
A gearbox is coupled between the low-pressure turbine and the fan assembly, allowing the fan assembly to operate at a reduced speed while the booster compressor operates at a higher speed, optimized by a flex connection and bearing assemblies to manage rotational forces and maintain alignment.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If a gearbox is coupled between the low-pressure turbine and the fan assembly to reduce fan speed and improve fan efficiency, then fan efficiency is improved, but the quantity of airflow channeled to the booster compressor is reduced
Solution Approach 1:
The patent segments the drive system into two independent rotational speed domains: the fan assembly operates at a reduced speed through the gearbox while the booster compressor operates at a higher speed directly coupled to the low-pressure turbine. This segmentation allows each component to operate at its optimal speed without compromising the other, resolving the contradiction between fan efficiency and airflow quantity.
2Stress or pressure
If additional stages are added to the booster compressor to achieve proper pressure after using a gearbox, then pressure requirement is met, but the overall weight, design complexity and manufacturing costs increase
Solution Approach 1:
The patent applies dynamic speed control by allowing the booster compressor to rotate at a higher speed directly from the low-pressure turbine, while the fan assembly operates at a reduced speed through the gearbox. This dynamic differentiation eliminates the need for additional compressor stages, maintaining pressure requirements while reducing design complexity and weight.
Data Source
AI summary
A method of assembling a gas turbine assembly includes providing a core gas turbine engine including a high-pressure compressor, a combustor, and a turbine, coupling a. A low-pressure turbine is axially aft from the core gas turbine engine, coupling a fan assembly is axially forward from the core gas turbine engine, and coupling a booster compressor is coupled to the low-pressure turbine such that the booster compressor and the low-pressure turbine rotate at a first rotational speed, and an epicyclic gearbox is coupled to the low-pressure turbine and the fan assembly such that the fan assembly rotates at a second rotational speed.