Multi-Directional Turbulators for Gas Turbine Cooling
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing turbulators in gas turbine engines are unidirectional, leading to reduced heat transfer efficiency when cooling airflow direction changes, as their turbulation capabilities are dependent on the airflow direction.
Innovation Solution
The use of multi-directional turbulators with a central axis and equally spaced facets, such as triangular or polygonal shapes, which are symmetrical and arranged to maintain turbulence-inducing capabilities regardless of airflow direction, increasing the surface area and enhancing heat transfer across all airflow directions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If unidirectional turbulators are used in cooling passages, then heat transfer efficiency is improved when cooling airflow flows in a specific direction, but heat transfer efficiency deteriorates when cooling airflow direction changes
Solution Approach 1:
The patent applies asymmetry in reverse by using symmetry to solve an asymmetry problem. Traditional turbulators have asymmetric shapes (like triangles) that work well in one direction but poorly in opposite directions. This patent uses symmetric diamond-shaped turbulators that are equally effective regardless of airflow direction, resolving the directional dependency issue while maintaining heat transfer efficiency.
Solution Approach 2:
The patent changes the geometric parameters of the turbulator from asymmetric triangular shapes to symmetric diamond shapes with specific angle ranges (30-60 degrees for acute angles, 60-150 degrees for obtuse angles). This parameter change enables the turbulator to maintain consistent performance across different airflow directions while still generating sufficient turbulence for effective heat transfer.
2Power
If triangular turbulators are used to increase turbulence, then heat transfer is improved in one direction, but turbulation capability is greatly reduced when airflow direction reverses
Solution Approach 1:
The patent resolves the directional dependency by applying symmetry rather than asymmetry. The diamond-shaped turbulator with its symmetric geometry generates consistent turbulence levels regardless of which direction the airflow approaches from, unlike triangular turbulators that are highly directional in their turbulence generation.
3Temperature
If cooling airflow passages are added to turbine components, then thermal management is improved, but component complexity increases
Solution Approach 1:
The patent combines the cooling passage function with the turbine component structure itself. The cooling passages are integrated into the blade, vane, or airseal bodies rather than being separate components. This merging approach provides effective thermal management while minimizing additional structural complexity.
Solution Approach 2:
The patent applies cooling passages and turbulators at specific locations where thermal management is most needed, such as on the suction and pressure surfaces of blades and vanes, and in the backwall of airseals. This localized approach provides targeted thermal conditioning without requiring complex cooling systems throughout the entire component.
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 ensures consistent and enhanced heat transfer efficiency between cooling airflow and turbine components, maintaining optimal temperature ranges and extending the service life of components like turbine blades, vanes, and outer airseals.
Implementation Method 1
Turbulators are often included in the cooling passages, affixed to one or more walls of the cooling passage to increase turbulence of the cooling airflow flowing through the cooling passage, thereby improving heat transfer characteristics of the cooling passage
Implementation Method 2
increase turbulence of the cooling airflow flowing through the cooling passage, thereby improving heat transfer characteristics
Implementation Method 3
cooling airflow to flow through, and additionally may have openings in an outer surface of the vane for cooling airflow to exit the interior of the vane structure and form a cooling film of air over the outer surface to provide the necessary thermal conditioning
Implementation Method 4
cooling airflow to exit the interior of the vane structure and form a cooling film of air over the outer surface
Data Source
Figure 1
Figure 2
Figure 3
AI summary
A gas turbine engine component (32) includes a body defining a cooling airflow passage (42) thereat configured for directing a cooling airflow (44) therethrough. A plurality of turbulators (46) are positioned at at least one passage wall of the cooling airflow channel. Each turbulator of the plurality of turbulators (46) includes a plurality of facets extending outwardly from a central portion. The gas turbine engine component may be a blade outer airseal. The invention also extends to a gas turbine comprising a combustor and a plurality of said gas turbine engine components in fluid communication with the combustor.