Refractory Metal Core Microcircuits for Combustor Hot Spot Cooling
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Solution Overview
Problem
Gas turbine combustors face durability issues due to local hot spots causing stress and cracking, particularly at junctions and lips, where conventional cooling methods can negatively impact emissions and profile, and are limited by space restrictions.
Innovation Solution
The implementation of refractory metal core (RMC) microcircuits within heat shield panels and bulkhead panels, which utilize impingement and film cooling techniques, along with flow swirler designs to enhance cooling efficiency and distribute cooling air effectively, reducing cooling flux by approximately 40% compared to conventional methods.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If additional cooling air is used to combat hot spots, then hot spot temperature is reduced, but combustor emissions and profile are negatively affected
Solution Approach 1:
The patent applies local quality by implementing dedicated cooling channels specifically at hot spot locations (junctions and lips) rather than uniform cooling throughout the combustor. This localized cooling approach reduces hot spot temperatures without adding excess cooling air that would negatively affect emissions and profile.
Solution Approach 2:
The cooling system is segmented into dedicated cooling channels separated from the main combustion chamber. These channels are embedded within the liner panels and bulkheads, allowing independent control of cooling air flow to specific hot spot regions without interfering with the overall combustion process and emissions.
2Reliability
If dedicated cooling is added to address hot spots, then cooling effectiveness is improved, but space limitations restrict cooling air distribution
Solution Approach 1:
The dedicated cooling channels are nested within the existing liner panels and bulkhead structures. The cooling channels are embedded inside the walls of the combustor, utilizing the existing structural space rather than adding external cooling components that would require additional space.
Solution Approach 2:
The cooling system transitions from a two-dimensional surface cooling approach to a three-dimensional embedded channel network within the liner panels. This allows cooling air to be distributed through the thickness of the panels, effectively utilizing the available volume to overcome space limitations.
3Temperature
If conventional cooling methods are used, then cooling is provided, but cooling flux is high causing increased emissions
Solution Approach 1:
The patent changes the parameters of the cooling system by implementing dedicated cooling channels with optimized geometry and distribution. This reduces the cooling flux requirement by approximately 40% compared to conventional cooling methods while maintaining effective temperature control, thereby reducing energy loss and emissions.
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 provides enhanced durability and reduced emissions by optimizing cooling distribution and heat transfer within the combustor chamber, maintaining effective film coverage and improving turbine durability.
Implementation Method 1
The implementation of refractory metal core (RMC) microcircuits within heat shield panels and bulkhead panels, which utilize impingement and film cooling techniques
Implementation Method 2
The implementation of refractory metal core (RMC) microcircuits within heat shield panels and bulkhead panels, which utilize impingement and film cooling techniques
Implementation Method 3
along with flow swirler designs to enhance cooling efficiency and distribute cooling air effectively
Data Source
Figure 1
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Figure 3
AI summary
A combustor component (72,74) of a gas turbine engine includes a refractory metal core (RMC) microcircuit (90).