Turbine Combustor Heat Shield Overlap Joint Leakage
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Solution Overview
Problem
Existing turbine engine combustors face issues with air leakage and stagnation between heat shield panels, leading to high temperatures and reduced durability, due to multiple leakage paths and air stagnation in channels between panels.
Innovation Solution
The combustor design incorporates a sealing overlap joint between heat shield panels, reducing leakage paths and stagnation by mechanically biasing the panels and using cooling features like cooling pins to direct air effectively within the cooling cavity, thereby minimizing air entry into the combustion chamber.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If heat shield panels are arranged adjacent to each other to form a heat shield, then the heat shield can be constructed, but multiple leakage paths are created for cooling air to leak from cooling cavities into the combustion chamber
Solution Approach 1:
The patent merges adjacent heat shield panels into an integrated structure with interlocking features. The panels include interlocking tabs and slots that combine to form a unified sealing surface, eliminating the leakage paths that would exist between separate adjacent panels while maintaining the modular panel construction for manufacturing benefits.
Solution Approach 2:
The patent implements nested interlocking features where tabs on one panel fit into slots on adjacent panels, creating a nested configuration. This nesting arrangement provides sealing surfaces that prevent cooling air leakage while allowing the panels to be assembled in a modular manner.
2Temperature
If cooling air is directed through cooling cavities to cool the heat shield, then the heat shield temperature is reduced, but air stagnation occurs in channels between adjacent panels subjecting edges to high temperatures
Solution Approach 1:
The patent extracts or removes the stagnant channel spaces between adjacent panels by implementing interlocking features that eliminate gaps. The interlocking tabs and slots configuration removes the void spaces where air stagnation would occur, ensuring cooling air flows continuously across the entire heat shield surface including panel edges.
Solution Approach 2:
The patent incorporates preliminary cooling features in the form of interlocking structures with integrated cooling passages. These passages are pre-configured to direct cooling air to panel edges and interlocking surfaces before high-temperature combustion gases can cause overheating, ensuring uniform cooling across all panel surfaces.
3Ease of manufacture
If multiple heat shield panels are used to form the heat shield, then manufacturing and assembly are facilitated, but leakage paths and air stagnation channels are created
Solution Approach 1:
The patent combines multiple manufacturing benefits into a unified interlocking panel design. The modular panels can be manufactured separately using standard fabrication processes, then assembled with interlocking features that simultaneously provide structural connection and sealing functionality, eliminating leakage paths while maintaining manufacturing ease.
Solution Approach 2:
The patent uses nested interlocking features where tabs and slots fit together to create both mechanical connection and sealing. This nested configuration allows modular assembly for ease of manufacture while the interlocking surfaces eliminate gaps that would create leakage paths and air stagnation, thus maintaining reliability.
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 enhances engine efficiency and performance by reducing air leakage and heat shield exposure to high temperatures, increasing the durability of the heat shield and overall engine performance.
Implementation Method 1
The cooling cavities are fluidly coupled with impingement apertures in the shell and effusion apertures in the heat shield
Implementation Method 2
impingement apertures in the shell and effusion apertures in the heat shield
Implementation Method 3
The second panel may be mechanically biased against the first panel at the overlap joint
Implementation Method 4
One or more of the apertures in the shell may direct cooling air into the cooling cavity to impinge against one or more of the cooling features
Data Source
AI summary
A combustor wall is provided for a turbine engine. The combustor wall includes a combustor shell and a combustor heat shield that is attached to the shell. The heat shield includes a first panel and a second panel that sealingly engages the first panel in an overlap joint. A cooling cavity extends between the shell and the heat shield and fluidly couples a plurality of apertures in the shell with a plurality of apertures in the heat shield.