Turbine Disk Rim Protrusions for Cooling Fluid Turbulence
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Solution Overview
Problem
Gas turbine engines face challenges in efficiently managing heat transfer and protecting components from high-temperature gases, leading to potential damage and reduced efficiency.
Innovation Solution
The implementation of protrusions on the radially outer rim surfaces of the disk, which turbulate the cooling fluid flow, enhancing heat transfer and maintaining the disk at a stable temperature, includes elongated ridges, chevron-shaped protrusions, and varying geometric patterns to optimize fluid mixing and turbulence.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling fluid flow is used to protect the disk from high temperatures, then the disk temperature is controlled, but the heat transfer efficiency is insufficient
Solution Approach 1:
The invention changes the physical parameters of the cooling fluid flow by introducing protrusions that modify flow velocity, turbulence intensity, and flow distribution. These parameter changes enhance the convective heat transfer coefficient, improving heat transfer efficiency while maintaining disk temperature control
Solution Approach 2:
The protrusions induce mechanical turbulence and chaotic flow patterns in the cooling fluid, creating eddies and mixing that enhance thermal convection. This mechanical disturbance of the flow field increases heat transfer efficiency without requiring additional energy input
2Loss of energy
If protrusions are added to the disk rim surfaces, then heat transfer efficiency is enhanced, but the device complexity increases
Solution Approach 1:
The disk rim surface is segmented into multiple protrusion elements distributed around the periphery. Each protrusion acts as an independent flow modification element, collectively enhancing heat transfer while maintaining a modular structure that can be manufactured using standard techniques
Solution Approach 2:
The protrusions feature curved or rounded geometries rather than sharp edges, which promotes smoother flow transitions and reduces turbulence generation from abrupt geometric changes. This curvature optimization enhances heat transfer while maintaining manufacturing simplicity
3Productivity
If protrusions with specific geometric ratios are used, then fluid mixing and turbulence are optimized, but manufacturing precision requirements increase
Solution Approach 1:
The invention establishes specific parameter ranges for protrusion geometry (height ratios between 0.05-0.2 times the rim thickness, pitch spacing between 0.5-2 times the protrusion height) that optimize fluid mixing while being tolerant of normal manufacturing variations. These parameter ranges provide a design space that balances performance with manufacturability
Solution Approach 2:
The protrusions are designed with specific local geometric characteristics (height, pitch, channel dimensions) that create optimized flow patterns in the cooling fluid passages. These localized geometric features enhance mixing efficiency while the overall pattern repeats around the disk, allowing standardization and reduced manufacturing 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 solution effectively facilitates thermal transfer, protecting the disk from high temperatures and improving engine efficiency by ensuring optimal mixing and heat dissipation through the use of protrusions with controlled height, pitch spacing, and channel height ratios.
Implementation Method 1
The radially outer rim surfaces (64) each include a plurality of protrusions (70) that extend into the passage (68). The protrusions (70) function to turbulate, or mix, the flow of the cooling fluid as it travels through the passage (68).
Implementation Method 2
A plurality of seals (66) are arranged between the turbine blades (58) and the periphery (62) of the disk (60). A cooling fluid may be provided into a passage (68) that is bounded on a radially outer side by the seal (66) and on a radially inner side by the radially outer rim surfaces (64) of the disk (60).
Data Source
Figure 1
Figure 2
Figure 3~7
AI summary
A gas turbine engine includes a turbine section that has a disk rotatable about an axis. The disk has circumferentially-spaced blade mounting features and radially outer rim surfaces extending circumferentially between the blade mounting features. Turbine blades are mounted circumferentially around the disk in the blade mounting features. Seals are arranged radially outwards of the disk adjacent the radially outer rim surfaces such that there are respective passages between the seals and the radially outer rim surfaces. The radially outer rim surfaces include radially-extending protrusions that extend into the respective passages.