Segregated Turbine Vane Cooling Passages for Heat Transfer
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Solution Overview
Problem
Gas turbine engines face inefficiencies due to increased airflow required for cooling, which can reduce overall engine performance and thermal, transfer, and propulsive efficiencies.
Innovation Solution
The design incorporates a turbine vane with a partitioned internal structure featuring film cooling holes, impingement cooling, and flow disrupting features to manage airflow and pressure differentials, optimizing heat transfer and reducing the need for excessive cooling airflow.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If airflow is increased for cooling purposes, then temperature control within turbine vanes is improved, but overall engine operating efficiency deteriorates
Solution Approach 1:
The internal passage is segmented into a first passage and a second passage using a partition. The first passage delivers cooling air to the inner surface via impingement cooling, while the second passage delivers cooling air to the outer surface via film cooling holes. This segmentation allows optimized cooling for each surface separately, improving temperature control while minimizing total airflow requirements.
Solution Approach 2:
Different cooling methods are applied to different locations: impingement cooling is used for the inner surface where high heat flux occurs, and film cooling is used for the outer surface. Flow disrupting features are strategically placed in the second passage to enhance film cooling effectiveness. This localized approach optimizes cooling efficiency at each location, reducing the overall airflow needed while maintaining effective temperature control.
2Temperature
If cooling airflow is increased to maintain temperatures, then temperature control is improved, but thermal efficiency deteriorates
Solution Approach 1:
The cooling system is divided into two separate passages with dedicated functions. The first passage handles impingement cooling of the inner surface, and the second passage handles film cooling of the outer surface. This segmentation allows each passage to be optimized for its specific cooling task, maximizing thermal efficiency while maintaining effective temperature control with minimal airflow.
Solution Approach 2:
The partition creates different pressure parameters between the first and second passages. By controlling pressure differentials across the partition, the system optimizes airflow distribution to achieve effective cooling with reduced total airflow, thereby improving thermal efficiency.
3Temperature
If cooling airflow is increased to maintain temperatures, then temperature control is improved, but propulsive efficiency deteriorates
Solution Approach 1:
The partitioned passage structure segments cooling functions into two dedicated channels, allowing each to be optimized for minimal airflow requirements. This reduces the overall cooling airflow bleed from the engine core, preserving more energy for propulsive purposes and improving propulsive efficiency.
4Use of energy by moving object
If partitioned passages are implemented with flow disrupting features, then heat transfer optimization is improved, but device complexity increases
Solution Approach 1:
The partition divides the internal passage into two simpler, dedicated channels rather than one complex channel. Each passage has a specific function and can be designed independently, which simplifies the overall design process and manufacturing while achieving superior heat transfer optimization through targeted cooling strategies.
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 approach maintains temperature control within turbine vanes while minimizing airflow bleed, enhancing engine efficiency and compactness by optimizing heat transfer and pressure management.
Implementation Method 1
a first passage extending between the baffle and the internal surface and delivering cooling air onto the inner surface of the outer wall
Implementation Method 2
a plurality of film cooling holes communicating air from the first passage to an outer surface of the outer wall
Implementation Method 3
the second passage includes flow disrupting features
Data Source
Figure 1
Figure 2~3
Figure 4~5
AI summary
An airfoil for a gas turbine engine includes a cavity (84) including an internal surface (92) of an outer wall (90). A baffle (88) is disposed within the cavity (84) and spaced apart from the internal surface (92). A partition (94) is disposed between the baffle (88) and the internal surface (92) to divide a space between the baffle (88) and the internal surface (92) into at least a first passage (110) and a second passage (112).