Turbomachine Cooling Insert Combustor Nozzle Efficiency
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Solution Overview
Problem
Gas turbine engines face efficiency losses due to the need to divert a large portion of compressed working fluid for cooling, which reduces the amount available for energy transfer in the turbine section, leading to durability issues like erosion and fatigue in combustor components.
Innovation Solution
An integrated combustion nozzle system with a cooling insert that directs coolant flow through impingement apertures towards the combustion liner walls, utilizing a flange and passages to efficiently distribute coolant and collect spent cooling air for reuse in combustion, thereby minimizing coolant wastage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a large portion of compressed working fluid is routed to cool combustor components, then the durability of combustor components is improved, but the overall operating efficiency of the turbomachine deteriorates
Solution Approach 1:
The cooling insert captures spent cooling air after it has cooled the combustion liner and redirects it back into the combustion process through the turbine section. This recovery and reuse of the cooling medium eliminates waste, improves overall efficiency, and allows for effective cooling without permanently losing the working fluid.
Solution Approach 2:
The system creates a closed-loop feedback mechanism where the cooling medium is continuously circulated from the combustion section through the turbine section and back to the combustion section. This feedback loop ensures efficient utilization of the cooling fluid while maintaining both component durability and overall system efficiency.
2Power
If high combustion gas temperatures are maintained to enhance power output, then the energy transfer between combustion gases and turbine is improved, but the durability of combustor components deteriorates due to erosion, creep, and fatigue
Solution Approach 1:
The cooling insert provides localized cooling to specific high-temperature zones of the combustion liner through strategically positioned cooling passages and impingement holes. This allows different regions of the combustor to have different thermal conditions, protecting critical areas from excessive heat while maintaining high temperatures in the combustion chamber for power generation.
Solution Approach 2:
The cooling insert divides the cooling function into multiple separate passages and channels that can independently cool different sections of the combustion liner. This segmentation allows for targeted cooling of specific hot spots without requiring cooling of the entire combustor structure, improving both efficiency and durability.
3Temperature
If more compressed working fluid is used for cooling, then the cooling effectiveness of combustor components is improved, but the amount of working fluid available for turbine energy transfer decreases
Solution Approach 1:
The cooling insert captures and recovers spent cooling air after it has performed its cooling function, redirecting it back into the combustion process. This recovery mechanism ensures that the cooling fluid is not lost but rather reused, allowing effective cooling without reducing the overall quantity of working fluid available for energy transfer.
Solution Approach 2:
The cooling medium serves dual functions: first as a cooling agent for the combustion liner, and then as additional combustion air when redirected back into the burn section. This multi-functionality maximizes the utility of each unit of compressed working fluid, improving both cooling effectiveness and overall system efficiency.
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 enhances the durability of combustor components by efficiently cooling the nozzle while maximizing the use of compressed working fluid for both cooling and energy production, improving overall gas turbine efficiency and performance.
Implementation Method 1
The cooling insert configured to direct a flow of coolant towards one of a first side wall and a second side wall of a combustion liner
Implementation Method 2
efficiently cooling the nozzle while maximizing the use of compressed working fluid for both cooling and energy production
Data Source
AI summary
Integrated combustor nozzles and turbomachines are provided. An integrated combustor nozzle includes a cooling insert having a flange. The cooling insert further includes a first wall and a second wall that each define respective passages therein. The first wall and the second wall each extend from an open end defined within the flange to a closed end. The first wall and the second wall each include an impingement side spaced apart from a solid side. Each impingement side defines a plurality of impingement apertures configured to direct coolant from the respective passage towards a side wall of the combustion liner. The cooling inserts further includes a collection passageway that is defined between the solid sides of the first wall and the second wall.