Gas Turbine Rotor Blade Wall Thickness Profile
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Solution Overview
Problem
The existing rotor blades in gas turbines face challenges in achieving optimal heat transfer, flow distribution, and mechanical load transfer due to suboptimal wall thickness profiles, which affect their service life and efficiency in high-temperature environments.
Innovation Solution
The proposed rotor blade features a specific wall thickness profile with normalized values for pressure side, suction side, leading edge, and trailing edge thicknesses, ranging between defined limits across the airfoil span, optimizing the internal cavity for improved heat transfer and mechanical load distribution.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a conventional wall thickness profile is used in rotor blades, then manufacturing is simpler, but heat transfer and mechanical load transfer are suboptimal
Solution Approach 1:
The patent applies local quality by defining different normalized wall thickness values for different regions of the airfoil (pressure side, suction side, leading edge, trailing edge) at different span locations (root, mid-span, tip). Each region has optimized thickness ranges that differ from conventional uniform profiles, allowing heat transfer and mechanical load transfer to be optimized locally where needed most while maintaining manufacturability through normalized parameter specifications.
2Strength
If wall thickness is increased to improve mechanical strength, then load transfer improves, but heat transfer efficiency decreases
Solution Approach 1:
The patent resolves this contradiction by changing the wall thickness parameters from conventional uniform values to a specific non-uniform distribution defined by normalized ranges. The pressure side wall thickness ranges from 0.080-0.100 at the tip to 0.194-0.214 at the root, while the suction side ranges from 0.089-0.109 at the tip to 0.202-0.222 at the root. This parameter optimization allows sufficient thickness for mechanical strength while maintaining adequate heat transfer paths.
3Temperature
If wall thickness is decreased to improve heat transfer, then heat transfer efficiency improves, but mechanical strength decreases
Solution Approach 1:
The patent applies local quality by specifying different minimum thickness requirements for different airfoil regions. The leading edge maintains thicker walls (0.108-0.128 at mid-span) to handle bending stresses, while the trailing edge can be thinner (0.900-1.100 normalized) where mechanical loads are lower but heat transfer is critical. This regional differentiation optimizes both heat transfer and mechanical strength simultaneously.
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 optimized wall thickness profile enhances heat transfer, flow distribution, and mechanical load transfer, leading to improved performance and extended service life of the rotor blades in high-temperature environments.
Implementation Method 1
a cooling medium such as compressed air is routed through the internal cooling cavity and/or cooling passages to cool the rotor blade
Implementation Method 2
The thickness of the rotor blade walls is crucial for heat transfer, flow distribution, and mechanical load transfer
Data Source
AI summary
In one aspect of the present disclosure, an airfoil for a rotor blade of a gas turbine includes a normalized pressure side wall portion thickness, a normalized suction side wall portion thickness, a normalized leading edge wall thickness, and a normalized trailing edge wall thickness. The values of theses thicknesses define the pressure side wall portion thickness, the suction side wall portion thickness, the leading edge wall thickness, and the trailing edge wall thickness, which improve heat transfer, flow distribution, and mechanical load transfer.