Serpentine Cooling Circuit for Multi-Wall Blade Tip
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Gas turbine systems face challenges in effectively cooling the tip area of multi-wall blades, which are exposed to very high heat loads, leading to potential component failure and reduced performance.
Innovation Solution
A serpentine cooling circuit is implemented, extending radially outward to cover central plenums and near wall cooling channels, with an air feed cavity supplying cooling air that flows through the circuit, providing shielding and film cooling to the tip area, thereby managing high heat loads.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If conventional internal cooling channels are used in multi-wall blades, then cooling air can be provided through the blade structure, but the tip area is exposed to very high heat loads that exceed the cooling capability of traditional channels
Solution Approach 1:
The cooling system is divided into multiple independent cooling circuits: near-wall cooling channels for high heat load regions, low cooling effectiveness channels for other areas, and a new serpentine cooling circuit specifically for the tip area. This segmentation allows each circuit to be optimized for its specific thermal environment, with the serpentine circuit providing dedicated cooling protection to the previously under-cooled tip region.
Solution Approach 2:
The serpentine cooling circuit extends in the radial direction outward from the multi-wall blade structure to reach the tip area, adding a new dimensional approach to cooling. This radial extension allows cooling air to be delivered directly to the tip region where it is most needed, rather than relying solely on axial or circumferential channel configurations.
2Productivity
If higher temperature flows are used to increase gas turbine performance, then efficiency and power output improve, but the risk of component failure increases due to excessive heat exposure
Solution Approach 1:
Cooling air is supplied to the serpentine cooling circuit in advance through an air feed cavity positioned to deliver cooled air before it reaches the high heat load tip area. This preliminary cooling action ensures that the blade tip is protected from excessive heat exposure before the hot gas flow arrives, enabling the turbine to operate at higher temperatures without compromising component integrity.
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 serpentine cooling circuit effectively shields low and high cooling effectiveness channels from excessive heat, enhancing the cooling efficiency of the tip area and maintaining performance by providing a cooling film, thus preventing component failure and optimizing gas turbine operation.
Implementation Method 1
Cooling air provided by, for example, a compressor of a gas turbine system may be passed through the internal cooling channels to cool the turbine blades
Implementation Method 2
providing shielding and film cooling to the tip area, thereby managing high heat loads
Data Source
AI summary
A cooling system according to an embodiment includes: a serpentine cooling circuit, the serpentine cooling circuit including a first leg extending in a first direction, a second leg extending in a second direction, and a turn fluidly coupling the first leg and the second leg; and an air feed cavity for supplying cooling air to the serpentine cooling circuit; wherein the first leg of the serpentine cooling circuit extends radially outward from and at least partially covers at least one central plenum of a multi-wall blade, and wherein the second leg of the serpentine cooling circuit extends radially outward from and at least partially covers a first set of near wall cooling channels of the multi-wall blade.