Reverse Flow Combustor Liner with Compound-Angle Frustoconical Geometry
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Solution Overview
Problem
Existing gas turbine combustors face challenges in optimizing both combustion characteristics and airflow around the combustor due to engine configuration constraints, often requiring trade-offs that affect efficiency and performance while increasing costs and weight.
Innovation Solution
A reverse flow combustor design featuring an outer and inner liner with a compound-angle frustoconical portion, where the first conical slope is greater than the second, optimizing airflow and combustion volume by maintaining clearance between the liner and diffuser, and incorporating effusion cooling and butt welds for manufacturing efficiency and lightweight construction.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If a conventional combustor design is used, then the combustion volume can be optimized, but the airflow around the combustor cannot be optimized simultaneously
Solution Approach 1:
The outer liner is segmented into multiple sections with different geometric characteristics: a cylindrical section for combustion volume optimization and a compound-angle frustoconical section for airflow optimization. This segmentation allows each section to be optimized for its specific function independently.
Solution Approach 2:
The transition from cylindrical to frustoconical geometry introduces a dimensional change in the liner shape, enabling the combustor to adapt to different functional requirements in different spatial regions while maintaining both combustion volume and airflow efficiency.
2Productivity
If the combustor design is made more complex to optimize both combustion and airflow, then performance improves, but manufacturing cost and weight increase
Solution Approach 1:
The design uses parameter changes in the geometric configuration, specifically the compound-angle frustoconical section with varying conical slopes, to optimize airflow while maintaining manufacturing simplicity. This allows performance improvement without proportionally increasing structural complexity.
3Productivity
If the combustor design is made more complex to optimize both combustion and airflow, then performance improves, but manufacturing cost increases
Solution Approach 1:
The compound-angle frustoconical section uses straightforward geometric parameter changes that can be efficiently manufactured using conventional machining operations, avoiding the need for complex manufacturing processes while still achieving airflow optimization.
4Productivity
If the combustor design is made more complex to optimize both combustion and airflow, then performance improves, but weight increases
Solution Approach 1:
The design optimizes the geometric parameters of the outer liner sections to achieve the required functional performance with minimal material usage, thereby reducing weight while maintaining or improving engine 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 design enhances the overall efficiency and performance of the gas turbine engine by optimizing airflow and combustion, reducing weight and manufacturing costs through a low-cost, lightweight sheet metal solution that maintains airflow integrity and provides localized cooling.
Implementation Method 1
the compound-angle frustoconical portion including a first frustoconical portion extending from the cylindrical head portion and having a first conical slope towards an engine centreline and a second frustoconical portion extending from the first frustoconical portion and having a second conical slope towards the engine centreline, the first conical slope being greater than the second conical slope
Implementation Method 2
incorporating effusion cooling and butt welds for manufacturing efficiency and lightweight construction
Data Source
AI summary
A reverse flow combustor for a gas turbine engine having an outer combustor liner and an inner combustor liner defining an annular combustion chamber, and a compound-angle frustoconical portion in the outer liner having a first and second conical slopes towards an engine centerline.