Split Axial-Centrifugal Compressor Speed Optimization
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Gas turbine engines with multiple compressor stages driven at single or different rotational speeds face efficiency limitations, complexity, and stability issues due to non-optimal operation of individual stages, leading to increased costs and reduced performance.
Innovation Solution
A gas turbine engine design incorporating an axial compression stage and a centrifugal compression stage, with a transmission system using planetary gear sets to transmit rotational power from the turbine, allowing the axial stage to rotate at a speed offset from the turbine speed and the centrifugal stage to maintain common rotation, facilitating a smooth transition of air and optimizing operational efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If multiple compressor stages are driven at a single rotational speed by the turbine, then the device complexity is reduced, but the operating efficiency is limited because each stage cannot operate at its individual optimal speed
Solution Approach 1:
The compressor is divided into multiple independently controllable stages, each capable of operating at its own optimal rotational speed. The first compressor stage and second compressor stage are separated with independent drive mechanisms, allowing each stage to be optimized for its specific compression requirements rather than being constrained by a single common speed.
Solution Approach 2:
The compressor drive system is made dynamic by introducing variable speed capabilities through separate drive mechanisms for each compressor stage. This allows the rotational speed of each stage to be independently adjusted and optimized based on operating conditions, transitioning from a static single-speed system to a dynamic multi-speed system.
2Productivity
If multiple turbine units are used to drive each compressor stage at different rotational speeds, then the operating efficiency is improved, but the cost and device complexity increase
Solution Approach 1:
Multiple turbine units are merged into a single turbine that drives a common rotor, which in turn drives multiple compressor stages through a shared rotation. This consolidation reduces the number of separate turbine units while maintaining the ability to operate compressor stages at different speeds through the coupling mechanism and control system.
Solution Approach 2:
A single turbine unit is designed to perform multiple functions by driving a common rotor that connects to multiple compressor stages. This universal drive mechanism allows one turbine to replace what would traditionally require multiple separate turbine units, reducing complexity while maintaining efficiency.
3Device complexity
If one of the rotational speeds is dependent upon the rotational speed of the output shaft of the gas turbine engine, then the device complexity is reduced, but stability problems occur that may necessitate additional features increasing cost
Solution Approach 1:
A feedback control system is implemented that continuously monitors the rotational speeds of compressor stages and the output shaft, and automatically adjusts drive parameters to maintain stable operation. This feedback mechanism detects instability conditions and makes real-time corrections without requiring additional mechanical complexity or stability-enhancing features.
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 design enhances the operational efficiency and stability of the compressor by allowing individual stages to operate closer to their optimal speeds, reducing pressure loss and complexity, while maintaining cost-effectiveness.
Implementation Method 1
The transmission may include a first planetary gear set arranged forward of the axial compression stage about the engine axis
Data Source
AI summary
A gas turbine engine including a compressor, a turbine, and a transmission is disclosed. The turbine is coupled to the compressor to drive rotation of multiple stages of the compressor. The transmission is configured to transmit rotational power from the turbine to at least one stage of the compressor to drive rotation of the at least one stage of the compressor.