Gas Turbine Combustor Cooling Sleeve Flow Management
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
The existing gas turbine combustor liners experience reduced cooling efficiency due to interference between jet flows and cross flows, leading to high surface temperatures and shortened lifespan, necessitating frequent replacements and increased maintenance costs.
Innovation Solution
A cooling sleeve with convex and concave portions is integrated into the liner and flow sleeve, guiding jet flows and allowing cross flows to move through concave passages, reducing flow interference and pressure loss, while enhancing mixing and vortex generation for improved cooling performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling holes are formed in the flow sleeve to allow jet flows to collide against the liner, then cooling performance is improved, but cross flows from the transition piece interfere with the jet flows causing reduced cooling efficiency and high surface temperatures
Solution Approach 1:
The flow sleeve is segmented into multiple functional zones: an upper portion with cooling holes for jet flow generation, a lower portion with spiral grooves for cross flow management, and a transition zone with convex-concave structures. This segmentation allows each zone to perform its specific function without interfering with others, resolving the contradiction between cooling effectiveness and flow interference.
Solution Approach 2:
Different regions of the flow sleeve are given different surface qualities and flow characteristics. The upper portion has smooth cooling holes for effective jet cooling, while the lower portion has spiral grooves for controlled cross flow. The convex-concave transition zone creates localized vortex patterns that prevent flow interference at the critical interface between jet flows and cross flows, thereby maintaining high cooling efficiency while managing temperature distribution.
2Temperature
If cross flows are introduced from the transition piece into the space between the liner and flow sleeve, then the transition piece is cooled, but the cross flows interfere with jet flows colliding against the liner surface reducing overall cooling performance
Solution Approach 1:
Spiral grooves with curved surfaces are introduced in the lower portion of the flow sleeve to guide cross flows in a rotational pattern. This curvature design allows cross flows to move smoothly along the liner surface without directly interfering with the axial jet flows from cooling holes, reducing turbulence and pressure loss while maintaining effective cooling of both the transition piece and liner.
Solution Approach 2:
The convex-concave structures act as intermediary elements between the jet flow region and cross flow region. These structures create localized vortex patterns that mediate the interaction between the two flow types, preventing direct interference while allowing both flows to perform their cooling functions effectively, thereby minimizing pressure loss.
3Ease of manufacture
If a simple flow sleeve structure is used, then manufacturing is easier, but flow interference between jet flows and cross flows reduces cooling efficiency and requires frequent liner replacement
Solution Approach 1:
The flow sleeve is divided into distinct functional segments (upper cooling zone, lower cross flow zone, and transition zone with convex-concave structures) that can be manufactured using standard machining processes. Each segment performs a specific function, and the overall structure remains relatively simple despite the complex flow patterns it generates, balancing manufacturability with extended liner lifespan.
4Temperature
If cooling air is supplied through cooling holes in the flow sleeve, then the liner is cooled, but pressure loss increases due to flow interference in the space between liner and flow sleeve
Solution Approach 1:
The spiral grooves with curved surfaces in the lower portion of the flow sleeve guide cross flows in a rotational pattern that follows the natural flow direction, reducing turbulence and pressure loss. This curved geometry allows efficient use of cooling air while minimizing energy waste due to flow interference.
Solution Approach 2:
The design utilizes fluid dynamic principles to create vortex patterns through the convex-concave structures and spiral grooves. These pneumatic features manipulate the cooling air flow to reduce interference between jet flows and cross flows, thereby minimizing pressure loss while maintaining effective heat transfer from the liner surface.
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
The solution effectively increases cooling efficiency, reduces pressure loss, and extends the lifespan of the combustor liners by improving heat transfer and mixing, thereby lowering maintenance costs.
Implementation Method 1
The flow sleeve 120 has cooling holes 130 formed therein to allow air (hereinafter, referred to as jet flows) introduced through the cooling holes 130 to vertically collide against the liner 110, thus cooling the liner 110.
Implementation Method 2
A cooling sleeve with convex and concave portions is integrated into the liner and flow sleeve, guiding jet flows and allowing cross flows to move through concave passages, reducing flow interference and pressure loss, while enhancing mixing and vortex generation for improved cooling performance.
Data Source
Figure 1~2
Figure 3~4
Figure 5~7
AI summary
A gas turbine combustor includes a liner and a transmission piece. Fuel injected in the liner from a fuel nozzle of a gas turbine mixes with compressed air. High temperature gas produced in the liner is transmitted through the transmission piece. The liner is disposed in a flow sleeve in which cooling holes are formed. The transition piece is disposed in a perforated sleeve. Compressed air supplied through holes formed in the perforated sleeve collides with the transition piece. The liner includes a cooling sleeve disposed thereon that divides the air supplied through the cooling holes of the flow sleeve and the compressed air flowing to a space portion between the liner and the flow sleeve.