Gas Turbine Film-Cooling Channel Vortex Induction
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Solution Overview
Problem
Conventional cooling systems for gas turbine engine components, such as convection cooling and film-cooling, are inadequate for efficiently managing high temperatures, leading to a need for improved methods to prevent component damage from combustion products.
Innovation Solution
A gas turbine engine component design featuring a film-cooling channel with a vortex chamber, vectoring, and vortexing segments, along with a metering segment, which induces secondary flow vortices and ensures a uniform coolant flow and boundary layer, enhancing coolant film adherence and insulation on the exterior surface.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If conventional convection cooling and film-cooling systems are used, then cooling function is provided, but coolant flow requirements are high and thermal insulation is insufficient
Solution Approach 1:
The film-cooling channel is segmented into multiple functional sections: vectoring segment for flow direction control, vortexing segment for secondary flow generation, metering segment for flow rate regulation, and diffusor segment for pressure recovery. This segmentation allows each section to optimize a specific aspect of coolant flow, improving overall thermal insulation efficiency while reducing total coolant requirements.
Solution Approach 2:
The vortex chamber acts as an intermediary structure that receives coolant from multiple inlets and generates controlled vortices before distributing the coolant through the film-cooling channel. This intermediary vortex generation mechanism enhances the coolant's ability to adhere to and insulate the component surface, improving thermal protection with reduced flow rates.
2Stability of the object's composition
If simple film-cooling channels are used, then manufacturing is easier, but coolant flow distribution is non-uniform and film adherence is poor
Solution Approach 1:
The film-cooling channel incorporates dynamic flow control features including vectoring segments that redirect flow at specific angles, vortexing segments that generate rotational flow patterns, and a metering segment with adjustable flow resistance. These dynamic elements transform simple linear flow into controlled, uniform distribution patterns that ensure stable coolant delivery across the component surface.
Solution Approach 2:
The channel geometry parameters are specifically optimized: the vectoring segment creates angular flow redirection, the vortexing segment generates rotational velocity components, and the metering segment controls flow rate through its length and cross-sectional area. These parameter changes transform the coolant flow from non-uniform to uniformly distributed, ensuring consistent film adherence.
3Productivity
If high coolant flow rates are used, then cooling capacity increases, but energy efficiency decreases and system complexity increases
Solution Approach 1:
The vortex chamber and vectoring segments utilize the kinetic energy and pressure of the incoming coolant itself to generate the required flow patterns and distribution, without requiring external actuators or complex control systems. The metering segment automatically regulates flow rates based on pressure differential, enabling the system to achieve optimal cooling capacity with minimal energy input and reduced coolant consumption.
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 design effectively reduces coolant flow requirements and improves thermal insulation, allowing for superior temperature tolerance and efficiency in cooling gas turbine engine components.
Implementation Method 1
the vortex chamber is configured and adapted for inducing secondary flow vortices in coolant traversing the film-cooling channel
Implementation Method 2
the metering segment includes a development length with a further discrete length, along which the coolant develops a substantially uniform boundary layer adjacent to the film-cooling channel wall
Implementation Method 3
The film functions as a thermal insulator, separating the component from the hot gas while allowing mechanical communication between combustion products traversing the turbine section and turbine section components
Implementation Method 4
Convection cooling involves flowing coolant through a cooled component such that heat transfers from the component exterior, through the component, and into a coolant stream flowing through the component
Data Source
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AI summary
A gas turbine engine component (100; 200; 300) includes a body (120) with a wall (122) surrounding an interior cavity (124). The wall has opposed interior (126; 226; 326) and exterior surfaces (128; 228). The interior surface has a plurality of coolant inlets (142, 144; 242, 244, 247; 342, 344, 347) and the exterior surface has a coolant outlet (140; 240; 340) defined therein. A coolant conduit (80) extends between the coolant inlets and the coolant outlet and is configured and adapted to induce secondary flow vortices in coolant traversing the coolant conduit and in an adherent coolant film over a portion of the exterior surface of component body.