Gas Turbine Combustor Liner With Corrugated Intermediate Member
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Solution Overview
Problem
Gas turbine engine combustor components face challenges in withstanding high temperatures and forces during combustion, requiring effective insulation and positioning of insulating materials to prevent heat transfer and movement.
Innovation Solution
The use of ceramic matrix composite (CMC) materials for the combustor liner, combined with an intermediate member featuring gas passages and a support structure, to reduce heat transfer and maintain the position of insulating materials amidst high temperatures and forces.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If insulating materials are included in the combustor liner to shield other components from heat, then heat transfer to other components is reduced, but the insulating materials are exposed to high temperatures and combustion forces that may cause movement or failure
Solution Approach 1:
The liner is divided into multiple segments or sections, each with its own positioning features. The corrugated intermediate member is also segmented with multiple protrusions and recesses that correspond to different sections of the liner, allowing independent positioning and thermal expansion management for each segment.
Solution Approach 2:
The corrugated intermediate member is nested between the support member and the liner, creating a layered structure. The protrusions of the intermediate member fit into recesses of the liner, while the intermediate member itself is supported by the support member, forming a nested arrangement that provides both positioning and thermal protection.
2Object-affected harmful factors
If CMC materials are used in the liner to reduce thermal conductivity, then heat shield performance is improved, but the materials require cooling to withstand the high temperatures generated in the combustion chamber
Solution Approach 1:
The corrugated intermediate member acts as a thermal intermediary between the hot combustion chamber and the CMC liner. It provides a pathway for cooling air to reach the liner while also providing mechanical support and positioning, mediating the thermal and mechanical loads on the CMC materials.
Solution Approach 2:
A cooling system using pressurized air or gas is implemented, with cooling passages directing fluid flow through or along the liner and intermediate member. The pneumatic cooling system removes heat from the CMC materials, allowing them to maintain low thermal conductivity while withstanding high external temperatures.
3Reliability
If an intermediate member with protrusions and recesses is used to position the liner, then position stability is improved, but the device complexity increases
Solution Approach 1:
The intermediate member utilizes changes in its geometric parameters, specifically the corrugated profile with alternating protrusions and recesses. This geometric parameter variation provides multiple positioning contact points without requiring additional components, achieving stable positioning through shape rather than complexity.
Solution Approach 2:
The corrugated structure of the intermediate member creates a series of voids and cavities between the protrusions and recesses. This porous-like structure provides cooling pathways and reduces the amount of material needed, achieving positioning functionality with reduced material usage and simplified manufacturing.
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 effectively shields other engine components from heat, reduces thermal conductivity, and ensures the stability and cooling of CMC materials through airflow, enhancing the durability and efficiency of the gas turbine engine.
Implementation Method 1
cooling air flow through the liner to decrease the temperature of the CMC materials
Implementation Method 2
CMC materials have lower thermal conductivities. Therefore, by including a CMC material in or on the liner of the combustor, heat transfer to other components of the combustor and/or the gas turbine engine may be reduced
Data Source
AI summary
A liner for a combustor includes a support member, an intermediate member, and a liner member. The intermediate member is positioned intermediate the support member and the liner member and has a plurality of protrusions and a plurality of recesses. The support member is coupled to the intermediate member at a tangent of each protrusion. Additionally, the liner member is comprised of a ceramic matrix composite material. The liner member is coupled to the intermediate member at a tangent of each recess.