Turbine Vane Rear Insert Cooling Scheme
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Solution Overview
Problem
Gas turbine engine turbine airfoils face reduced service life and increased maintenance costs due to high thermal and mechanical loads from elevated gas flow temperatures, necessitating efficient cooling schemes that can be fine-tuned with minimal design and manufacturing changes.
Innovation Solution
An internally air-cooled turbine vane design featuring a pressure side, suction side, and hollow sections with an insert that directs pressurized cooling air through channels between the pressure and suction side chambers, utilizing a pressure differential to enhance cooling efficiency and reduce temperature gradients.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If elevated combustion temperatures are used to increase thermodynamic efficiency and power output, then efficiency and performance are improved, but thermal and mechanical loads on turbine airfoils increase, reducing service life and reliability
Solution Approach 1:
The turbine airfoil is divided into multiple functional zones with separate cooling channels for the leading edge, platform, and trailing edge. This segmentation allows each region to be cooled independently according to its specific thermal requirements, enabling the airfoil to withstand higher combustion temperatures while maintaining reliability
Solution Approach 2:
Different cooling strategies are applied to different regions of the airfoil based on local thermal conditions. The leading edge receives impingement cooling with high heat flux, while the platform and trailing edge use film cooling and internal convection channels. This localized approach optimizes cooling efficiency where needed most, allowing higher overall operating temperatures
2Reliability
If complex cooling schemes are implemented to reduce thermal loads on turbine airfoils, then service life and reliability are improved, but device complexity and manufacturing difficulty increase
Solution Approach 1:
Multiple cooling functions are merged into a single integrated insert component that fits within the turbine airfoil. The insert combines impingement cooling holes, internal convection channels, and film cooling outlets in one piece, simplifying manufacturing compared to separate components while maintaining comprehensive cooling coverage for improved reliability
Solution Approach 2:
The cooling system uses the turbine's own operating conditions to drive cooling airflow. The pressure differential between the leading edge and trailing edge, created by the turbine's rotation and pressure gradient, automatically drives cooling air through the channels without requiring external pumps or complex control systems
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 effectively cools turbine airfoils by directing cooling air through channels between the pressure and suction side chambers, reducing temperature gradients and extending the service life of airfoils while minimizing changes to existing design and manufacturing processes.
Implementation Method 1
utilizing a pressure differential to enhance cooling efficiency and reduce temperature gradients
Implementation Method 2
an internally air cooled turbine airfoil for a gas turbine engine having air flow channels between the interior walls of the airfoil and an insert
Data Source
AI summary
An internally cooled turbine vane for a gas turbine engine has coolant flow channels between the interior walls of the vane and an insert, where the channels serve to convey a portion of the cooling air flow from a pressure side chamber to a suction side chamber. The turbine vane defines a radially extending passage with a dividing wall defining a front section and a rear section; the rear section having interior walls spaced apart from an insert to define the pressure side chamber and the suction side chamber. The insert may receive cooling air and conveys the cooling air into the pressure side chamber and the suction side chamber. A front surface of the insert or a rear surface of the dividing wall may have a clearance gap and an air flow channel communicating between the pressure side chamber and the suction side chamber.