Guide Vane Seal Lip Cooling Layout for Uniform Thermal Protection
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Solution Overview
Problem
Turbine blades in turbomachines face high thermal stresses due to high temperatures, leading to potential damage, and existing cooling methods may not provide uniform cooling to seal lips, which are critical for sealing and durability.
Innovation Solution
Incorporating cooling ducts that extend through the seal lip of a guide vane, with multiple ducts arranged radially and connected by a circumferential duct, allowing for efficient and uniform cooling of the platform and seal lip, and using a nickel-based super alloy for the platform and attachment parts to enhance thermal resistance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If cooling ducts are extended through the seal lip, then cooling uniformity and thermal stress resistance are improved, but device complexity and manufacturing difficulty increase
Solution Approach 1:
The cooling duct system is segmented into multiple individual cooling ducts distributed throughout the seal lip, rather than using a single centralized cooling path. This segmentation allows cooling fluid to reach different regions of the seal lip independently, improving thermal stress resistance while maintaining manageable complexity through modular duct design
Solution Approach 2:
Cooling ducts are strategically positioned at specific locations within the seal lip where thermal stresses are most critical. The cooling fluid is delivered locally to high-heat zones through these distributed ducts, providing targeted cooling where it is most needed rather than uniform cooling throughout the entire structure
2Reliability
If multiple cooling ducts are arranged radially and connected by circumferential ducts, then cooling efficiency and uniformity are improved, but manufacturing precision requirements increase
Solution Approach 1:
The cooling duct system is divided into radial cooling ducts that extend from the center outward and circumferential connecting ducts that link these radial ducts. This segmented arrangement allows each duct to be relatively simple in shape while collectively achieving uniform radial cooling distribution across the seal lip
Solution Approach 2:
The circumferential connecting ducts serve multiple functions: they connect the radial cooling ducts to form a complete cooling network, distribute cooling fluid uniformly to all radial ducts, and provide structural support for the duct system. This multi-functionality reduces the need for additional specialized components
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 reduces thermal stresses and damage by ensuring uniform cooling of the guide vane, improving sealing and extending the lifespan of the components through efficient heat transfer and material stability.
Implementation Method 1
at least one cooling duct which forms part of a cooling duct system for cooling the platform and the vane blade extends through the seal lip
Implementation Method 2
a plurality of cooling ducts, the exit openings of which are disposed in the free end of the seal lip, extend through the seal lip in at least a substantially radial direction
Data Source
AI summary
A guide vane for a turbomachine, having a blade airfoil and at least one platform, to which the blade airfoil is connected. A cooling channel system is provided for cooling the platform and the blade airfoil. The platform has, on the side thereof facing the airfoil, at least one sealing lip for sealing to a rotating system of the turbomachine. At least one cooling channel extends through the sealing lip, which cooling channel forms part of the cooling channel system.