Gas Turbine Reverse Flow Combustor Load Distribution
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
The reverse flow combustor in gas turbine engines experiences deformation due to pressure imbalances, leading to degraded combustion performance and reduced durability due to bending moments on support parts and potential air leakage from wear at narrow contact points.
Innovation Solution
Engaging the inside turn duct portion and nozzle guide vane via an engagement part that transmits axially forward-facing loads to counteract backward-facing loads, reducing bending moments on support parts and enhancing durability by distributing loads through a wider contact area, and positioning support parts close to each other to minimize thermal expansion-induced displacement.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If a circular section support pin and receiving hole are used to support the reverse flow combustor, then the structure is simple and easy to manufacture, but the contact face is narrow causing wear and air leakage that degrades combustion performance
Solution Approach 1:
The invention transitions from a point/line contact support (circular pin and hole) to a surface contact support by adding an engagement surface that extends in the radial direction. This dimensional change increases the contact area from a narrow line to a broader surface, reducing wear and preventing air leakage while maintaining manufacturing simplicity.
2Device complexity
If the nozzle guide vane is supported on the stationary member via a support part, then the assembly is simplified, but a bending moment acts on the support part degrading its durability
Solution Approach 1:
The invention introduces an engagement part as an intermediary between the nozzle guide vane and the stationary member. This engagement part with its extended engagement surface distributes the load and reduces the bending moment on the support part, thereby improving durability while keeping the overall assembly structure simple.
3Use of energy by moving object
If the reverse flow combustor is subjected to axially forward-facing load from compressed air, then the combustor operates under normal pressure conditions, but the combustor deforms due to pressure imbalance degrading mixing and combustion performance
Solution Approach 1:
The invention employs the engagement surface extending in the radial direction to provide counterbalancing support against the axially forward-facing load from compressed air. This additional support structure acts as a counterweight to the pressure-induced deformation, maintaining combustor shape stability and preventing degradation of mixing and combustion performance.
Data Source
AI summary
In a gas turbine engine, an inside turn duct portion and a nozzle guide vane are engaged together via an engagement part. An axially forward-facing load acting on a reverse flow combustor is transmitted to the vane via the engagement part. Therefore, it is possible to counteract an axially backward-facing load acting on the vane from combustion gas with the axially forward-facing load, thus reducing a bending moment acting on a support part of the vane and enhancing durability. Furthermore, part of the axially forward-facing load acting on the combustor acts on the support part via the vane. The axially forward-facing load acting on the support part of the combustor without via the vane is decreased by the above-mentioned part. Thus, it is possible to reduce bending moments acting on an outside turn duct portion and dome portion of the combustor and enhance durability, thereby preventing degradation of combustion performance.