Turbine Engine Multi-Walled Cooling Structure
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Solution Overview
Problem
Current turbine engine combustors lack an efficient cooling mechanism to manage heat distribution and thermal energy transfer between the shell and heat shield, leading to suboptimal performance and potential thermal issues.
Innovation Solution
A multi-walled structure with tapered cooling cavities and varying cooling element densities between the shell and heat shield, where cooling elements such as pins, nodules, or ribs are integrated to enhance convective thermal energy transfer and air flow, directing air through specific apertures to impinge and effuse, thereby increasing thermal management.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If traditional cooling mechanisms are used in turbine engine combustors, then the structure is simpler, but thermal management efficiency is insufficient
Solution Approach 1:
The cooling cavity is segmented into multiple regions with different cooling element densities. The first region has a first density of cooling elements, while the second region has a second density that differs from the first. This segmentation allows optimized thermal management in different zones without requiring complete redesign of the entire cooling system.
Solution Approach 2:
Different regions of the cooling cavity are assigned different local qualities through varying cooling element densities. The first region and second region have distinct cooling element configurations tailored to their specific thermal requirements, enabling precise local thermal management while maintaining overall system efficiency.
2Use of energy by moving object
If cooling element density is increased uniformly throughout the cooling cavity, then thermal energy transfer improves, but air flow distribution becomes less efficient
Solution Approach 1:
The cooling element density is optimized locally in different regions rather than uniformly throughout. The first region has a first density and the second region has a second density, allowing each zone to have the appropriate cooling intensity for its thermal requirements while maintaining efficient air flow distribution across the entire cavity.
Solution Approach 2:
The density parameter of cooling elements is changed between different regions of the cooling cavity. By varying the density from the first region to the second region, the system optimizes both thermal energy transfer and air flow efficiency through parameter optimization rather than uniform configuration.
3Reliability
If cooling elements are added to enhance convective thermal energy transfer, then cooling efficiency increases, but the manufacturing complexity increases
Solution Approach 1:
The cooling elements are segmented into different groups based on their location and function. The first plurality of cooling elements and second plurality of cooling elements are configured differently, allowing for modular manufacturing approaches that can improve cooling efficiency while managing manufacturing complexity through standardized segments.
Solution Approach 2:
Different local qualities are provided in different regions through selectively placed cooling elements. This allows manufacturing processes to focus on critical cooling zones with higher element density while using simpler configurations in less critical areas, balancing cooling efficiency requirements with manufacturing feasibility.
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 enhances thermal energy transfer and air flow, improving heat management and engine performance by increasing the density of cooling elements in specific regions and directing air flow to optimize cooling efficiency.
Implementation Method 1
enhance convective thermal energy transfer and air flow, directing air through specific apertures to impinge and effuse
Implementation Method 2
fluidly couple impingement apertures defined in the shell with effusion apertures defined in the heat shield
Implementation Method 3
fluidly couple impingement apertures defined in the shell with effusion apertures defined in the heat shield
Data Source
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AI summary
A multi-walled structure is provided for a turbine engine. This structure includes a shell with a textured first surface, and a heat shield with a second surface. The heat shield is attached to the shell. The first and the second surfaces vertically define a cooling cavity between the shell and the heat shield. The cooling cavity fluidly couples a plurality of cooling apertures defined in the shell with a plurality of cooling apertures defined in the heat shield.