Turbine Platform Cooling Circuit Flow Divider
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Solution Overview
Problem
Gas turbine engines face challenges in effectively cooling components, particularly in the turbine section, where high temperatures necessitate efficient cooling methods to maintain efficiency and longevity.
Innovation Solution
An airfoil assembly with a platform cooling circuit featuring a common feed tube and flow divider that divides cooling air between two branches, supplying air to the airfoil and platform, enhancing cooling efficiency and reducing stagnation and weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a common feed tube supplies cooling air to multiple branches, then the cooling system structure is simplified, but uneven distribution of cooling air may occur
Solution Approach 1:
A flow divider is introduced as an intermediary component between the common feed tube and the cooling branches. This flow divider actively mediates the cooling air distribution, ensuring uniform flow to each branch while maintaining the simplified common feed tube structure. The flow divider acts as a flow control element that balances the cooling air distribution without requiring complex individual control mechanisms for each branch.
2Reliability
If cooling air flow rate is increased, then cooling efficiency is improved, but pressure losses increase
Solution Approach 1:
Curved surfaces are incorporated into the flow divider design to guide the cooling air flow smoothly into the branches. These curved surfaces reduce flow separation and turbulence, minimizing pressure losses while maintaining high cooling efficiency. The curved geometry optimizes the flow path, allowing effective cooling with reduced energy penalties compared to sharp-edged or straight transitions.
3Reliability
If the platform cooling circuit is implemented, then cooling coverage is expanded, but the system weight increases
Solution Approach 1:
The common feed tube serves multiple functions: it supplies cooling air to multiple branches, acts as a flow distribution manifold, and provides structural support for the platform cooling circuit. By making the feed tube multi-functional, the need for separate components is reduced, expanding cooling coverage while minimizing additional weight.
Solution Approach 2:
The flow divider is integrated directly into the platform structure, merging the flow control function with the structural component. This integration eliminates the need for separate flow divider housings or mounting structures, reducing overall system weight while maintaining effective cooling distribution across the platform.
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 solution provides improved cooling efficiency, reduces dust accumulation, and increases the longevity of turbine engine components by effectively distributing cooling air and minimizing pressure losses.
Implementation Method 1
a flow divider confronting the feed tube and dividing fluid from the feed tube between the first and second branches
Implementation Method 2
dividing the supplied cooling air between the at least two cooling branches by directing the cooling air along opposing curved surfaces
Implementation Method 3
Gas turbine engines for aircraft are designed to operate at high temperatures to maximize engine efficiency, so cooling of certain engine components, such as those in the turbine section, can be beneficial
Implementation Method 4
an airfoil cooling circuit passing through the base, platform and into an interior of the airfoil
Data Source
AI summary
An airfoil assembly for a turbine engine can comprise a platform having first and second opposing surfaces, an airfoil extending from the first surface, a base extending from the second surface, and a platform cooling circuit including a feed tube, a first branch, a second branch, and a flow divider.