Impingement Cooling Apparatus for Combustor Liner Thermal Management
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Solution Overview
Problem
Current gas turbine combustors face durability issues due to high combustion gas temperatures, leading to erosion, creep, and low cycle fatigue, which necessitate cooling but at the cost of reducing the working fluid available for energy transfer, thus impacting efficiency.
Innovation Solution
An integrated combustor nozzle with an impingement cooling apparatus that directs compressed air to impinge on the inner and outer liner segments, enhancing heat transfer while minimizing the use of cooling fluid by reusing it for combustion, utilizing additive manufacturing for efficient fabrication.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If a large portion of compressed working fluid is routed to cool the combustion liner, then the cooling effectiveness is improved, but the amount of working fluid available for the turbine section is reduced, negatively impacting overall operating efficiency
Solution Approach 1:
The combustion liner is divided into multiple zones (primary combustion zone, secondary combustion zone, and turbine section) with distinct cooling requirements. The impingement cooling apparatus is segmented into multiple impingement members positioned at different locations, allowing differential cooling of each zone while optimizing working fluid utilization.
Solution Approach 2:
Different portions of the combustion liner are provided with different cooling intensities based on their thermal exposure. The impingement cooling apparatus directs cooling fluid to specific high-temperature zones (primary and secondary combustion zones) while the turbine section receives minimal cooling, matching the actual thermal needs of each component.
2Power
If high combustion gas temperatures are maintained to enhance thermal and kinetic energy transfer to the turbine, then power output is improved, but erosion, creep, and low cycle fatigue increase, reducing component durability
Solution Approach 1:
The cooling fluid is directed to impinge on the combustion liner surfaces before the high-temperature combustion gases can cause thermal damage. This preliminary cooling action protects the liner from erosion, creep, and fatigue while allowing the turbine section to operate at high temperatures for maximum power output.
Solution Approach 2:
The impingement cooling apparatus acts as an intermediary between the compressed working fluid and the combustion liner. It transfers thermal energy from the combustion gases to the cooling fluid in a controlled manner, protecting the liner without significantly cooling the turbine section.
3Reliability
If the combustion liner is cooled to reduce thermal stress and improve durability, then component reliability is improved, but the working fluid is consumed, reducing efficiency
Solution Approach 1:
The cooling fluid that impinges on the combustion liner and absorbs thermal energy is not discarded but is instead recovered and reused in the combustion process. The heated cooling fluid is directed back to the combustion zones to assist in combustion while continuing to provide cooling, eliminating working fluid loss.
Solution Approach 2:
The compressed working fluid serves multiple functions: it cools the combustion liner through impingement cooling, provides combustion air for the combustion process, and maintains pressure in the system. This multi-functionality eliminates the need for separate cooling systems and working fluid consumption.
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 cools the combustor components, reducing thermal stress and increasing the overall efficiency of the gas turbine by utilizing the cooling air for both cooling and combustion, thereby enhancing durability and performance.
Implementation Method 1
an impingement cooling apparatus positioned within the cavity. The impingement cooling apparatus includes a flange. The impingement cooling apparatus further includes a plurality of impingement members that each extend from a respective opening defined in the flange to a respective closed end. Each impingement member defines a plurality of impingement apertures that direct air to impinge upon one of the first side wall and the second side wall.
Implementation Method 2
enhancing heat transfer while minimizing the use of cooling fluid by reusing it for combustion
Data Source
AI summary
An integrated combustor nozzle includes a combustion liner that extends radially between an inner liner segment and an outer liner segment. The combustion liner includes a forward end portion, an aft end portion, a first side wall, and a second side wall. The integrated combustor nozzle further includes an impingement cooling apparatus positioned within the cavity. The impingement cooling apparatus includes a flange. The impingement cooling apparatus further includes a plurality of impingement members that each extend from a respective opening defined in the flange to a respective closed end. Each impingement member defines a plurality of impingement apertures that direct air to impinge upon one of the first side wall and the second side wall. The impingement cooling apparatus further includes stand-offs extending from each impingement member of the plurality of impingement members. The stand-offs space apart each impingement member of the plurality of impingement members from surrounding surfaces.