Integrated Impingement-Effusion Cooling for Gas Turbine Combustor Liners
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Solution Overview
Problem
Gas turbine combustors face challenges with high temperature exposure leading to limited service life, heat release rates, and the need for improved cooling methods that are cost-effective and lightweight, with existing approaches separating impingement and effusion cooling mechanisms.
Innovation Solution
An integrated impingement-effusion cooling configuration within a single combustor liner using additive manufacturing techniques, where compressor discharge air enters through a metering orifice, impinges on the hot side, and is then discharged through a film cooling passage to provide enhanced convective cooling, reducing the need for compliant joints and optimizing heat transfer.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional separate impingement and effusion cooling mechanisms are used, then cooling effectiveness is achieved, but device complexity increases and manufacturing cost increases
Solution Approach 1:
The patent combines separate impingement cooling and effusion cooling mechanisms into a single integrated liner structure. The liner includes both impingement holes and effusion holes formed as one unified component, eliminating the need for separate cooling systems and reducing overall device complexity while maintaining cooling effectiveness.
Solution Approach 2:
The single liner structure performs multiple cooling functions simultaneously - it provides both impingement cooling through dedicated impingement holes and effusion cooling through effusion holes. This multi-functional design consolidates what were previously separate cooling systems into one universal component.
2Reliability
If traditional separate impingement and effusion cooling mechanisms are used, then cooling effectiveness is achieved, but manufacturing cost increases
Solution Approach 1:
By merging impingement and effusion cooling into a single liner, the patent reduces the total number of parts that need to be manufactured, assembled, and maintained. This consolidation simplifies the manufacturing process and reduces overall production costs while achieving the same cooling effectiveness.
Solution Approach 2:
The universal liner design that performs both cooling functions reduces inventory requirements, simplifies supply chain management, and decreases assembly operations, all of which contribute to lower manufacturing costs while maintaining reliable cooling performance.
3Reliability
If traditional separate impingement and effusion cooling mechanisms are used, then cooling effectiveness is achieved, but weight increases
Solution Approach 1:
The integration of impingement and effusion cooling features into a single liner eliminates redundant materials and structural components. By combining what were previously separate cooling systems into one unified structure, the overall weight is reduced while maintaining the same cooling effectiveness.
4Power
If high temperature exposure is endured, then engine power is maintained, but service life decreases
Solution Approach 1:
The patent replaces passive thermal insulation with active convective cooling systems - impingement cooling and effusion cooling - that actively remove heat from the liner. This allows the liner to withstand high temperatures required for engine power while the cooling systems extend the service life by preventing thermal degradation.
Solution Approach 2:
The cooling systems change the thermal parameters of the liner by actively lowering its temperature through forced convection. This allows the engine to operate at high temperatures for power generation while the liner experiences lower temperatures that extend its service life.
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 configuration enhances cooling effectiveness, increases durability, and reduces manufacturing costs and weight, enabling higher cycle temperatures or equal durability at a lower cost of ownership.
Implementation Method 1
a plurality of 'effusion holes', which are formed through the combustor liner, direct cooling air from outside of the combustor liner to an inner surface of the combustor liner... the liner is cooled as air flows through each effusion hole and enters the combustor to form an air film
Implementation Method 2
Impingement cooling works by blowing onto the inner surface of the combustor with high velocity air. This allows more heat to be transferred by convection than regular convection cooling does.
Data Source
Figure 1
Figure 2~3
Figure 4A~4B
AI summary
Disclosed in various exemplary embodiments are turbine engine combustors with effusion and impingement cooling and methods for manufacturing the same. In one exemplary embodiment, disclosed is a combustor for a turbine engine that includes an annular liner portion including a first metering hole positioned on a cold side annular surface of the annular liner portion and an impingement chamber positioned in the annular liner. The impingement chamber connects to an entry hole on the cold side annular surface and includes a cooling air outlet passageway that is angled with respect to a hot side annular surface of the annular liner portion and that connects to an exit hole positioned on the hot side annular surface of the annular liner portion. The first metering hole is connected to the impingement chamber. The cooling air outlet passageway directs the air onto the hot side annular surface and spreads the airflow axially and laterally parallel to the hot side annular surface. Furthermore, a ratio of a radial thickness of the annular liner portion to a diameter of the entry hole is from about 2 to about 6.