Gas Turbine Combustor Outer Support Cooling Air Distribution
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Solution Overview
Problem
The aft-most panel in gas turbine engine combustors receives insufficient convective cooling due to the outer support directing cooling air downstream, leading to operating temperature exceedance and reduced useful life.
Innovation Solution
Incorporating a radial outer support with cooling openings that channel cooling air obliquely towards the aft-most panel, enhancing backside convective and impingement cooling to reduce operating temperatures.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If the outer support directs cooling air downstream through turbine cooling feed windows, then the turbine cooling is improved, but the aft most panel receives significantly less convective cooling air
Solution Approach 1:
The outer support is segmented with multiple cooling openings distributed along its length, allowing cooling air to be delivered to different sections of the liner including the aft most panel, rather than directing all cooling air downstream to the turbine
Solution Approach 2:
Cooling openings are strategically positioned on the outer support to provide localized cooling air delivery to the aft most panel which has specific cooling needs, while other portions of the outer support continue to direct cooling air to different areas
2Use of energy by moving object
If cooling air is channeled through the outer support to turbine cooling feed windows, then turbine cooling is enhanced, but the cooling air availability for liner panels is reduced
Solution Approach 1:
The cooling air flow path is segmented into multiple branches: one branch continues to the turbine cooling feed windows, while another branch is directed through cooling openings in the outer support to the liner panels, allowing both cooling functions to be satisfied simultaneously
Solution Approach 2:
The outer support acts as an intermediary component that receives cooling air and redistributes it to multiple destinations including both the turbine cooling feed windows and the liner panels through its cooling openings
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 enhanced cooling mechanism effectively reduces the operating temperature of the aft-most panel, increasing its heat transfer coefficient and extending the combustor's useful life.
Implementation Method 1
backside convection cooling from the cooling passage flow
Implementation Method 2
hot-side film cooling, to facilitate enhancing extending the useful life of the panels
Data Source
AI summary
A method enables a combustor for a gas turbine engine to be assembled. The method includes coupling an inner liner to an outer liner such that a combustion chamber is defined therebetween, wherein the outer liner is fabricated from a plurality of panels coupled together, and coupling an outer support radially outward from the outer liner such that an outer passageway is defined between the outer liner and the outer support, wherein the outer support is configured to channel cooling air from the outer passageway towards at least a portion of the outer liner.