Radially Outward Turbine Rotor Arrangement for Gas Engine Weight Reduction
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Solution Overview
Problem
Gas turbine engines with axial series flow arrangement of compressors and turbines face challenges with weight, strength, and efficiency due to the presence of concentric shafts, which reduce the strength of discs and increase weight, leading to potential shaft break issues and inefficiencies.
Innovation Solution
The turbine rotor is positioned radially outward of the compressor rotor, eliminating the need for a shaft and allowing for stronger discs and higher blade speeds, thereby reducing weight and fluid leakage, and increasing efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If concentric shafts are used to join compressors and turbines in axial series flow, then the structural integrity is maintained, but the weight increases and disc strength is reduced
Solution Approach 1:
The patent removes the concentric shafts that traditionally join compressors and turbines in axial series flow arrangements. By extracting these shafts, the design eliminates the weight they contribute and removes the structural constraint they impose on disc strength, allowing for stronger, lighter disc constructions without compromising the mechanical connection between components.
Solution Approach 2:
The patent transitions from an axial series flow arrangement (where components are arranged along the axial dimension with shafts connecting them) to a radial flow arrangement where the turbine is positioned radially outward from the compressor. This dimensional reconfiguration eliminates the need for longitudinal shafts and allows direct mechanical coupling through the disc structure itself, improving both weight and strength characteristics.
2Productivity
If shafts are used to connect turbine and compressor, then mechanical coupling is achieved, but fluid leakage increases and efficiency decreases
Solution Approach 1:
The patent extracts the shafts that create leakage paths between the turbine and compressor sections. By removing these shafts, the design eliminates the seals and clearances required around them, thereby reducing fluid leakage and improving overall engine efficiency.
Solution Approach 2:
By reconfiguring the turbine-compressor arrangement from axial to radial positioning, the patent eliminates the need for shafts that traverse the engine length. This dimensional change removes the associated leakage pathways and allows for more efficient fluid flow paths with fewer leakage points.
3Reliability
If axial series flow arrangement is used, then compact design is achieved, but shaft break issues and reliability problems occur
Solution Approach 1:
The patent removes the shafts that connect the turbine and compressor in the axial series flow arrangement. By extracting these shafts, the design eliminates the reliability issues associated with shaft breakage and reduces the mechanical complexity of the shaft support and alignment systems.
Solution Approach 2:
The patent reconfigures the turbine-compressor arrangement from an axial layout requiring long shafts to a radial layout where components are positioned side-by-side. This dimensional change eliminates the need for long shafts and their associated support structures, thereby improving reliability and reducing mechanical 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 configuration reduces the length and weight of the gas turbine engine, enhances the strength of compressor and turbine blades, and improves efficiency by allowing higher blade speeds and reduced fluid leakage, leading to improved performance and noise characteristics.
Implementation Method 1
turbines for extracting work from the hot combustion products and driving the compressors and a propulsor
Implementation Method 2
compressors that compress fluid flowing through the compressors
Implementation Method 3
a combustor in which fuel is injected into the fluid and the mixture combusted
Data Source
AI summary
A gas turbine engine includes a propulsor, a compressor comprising a compressor rotor, and a turbine comprising a turbine rotor fixedly mechanically coupled to the compressor rotor. The propulsor and the compressor are arranged in axial flow series. The turbine rotor is radially outward of the compressor rotor, and the direction of fluid flow through the turbine is generally opposite the direction of gas flow through the propulsor and the compressor.