Tangential Combustor with Corrugated Geometry Eliminates Vane Nozzles
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Solution Overview
Problem
Gas turbine engines face inefficiencies and high costs due to the need for first stage vane nozzles, which contribute to flow losses and increased manufacturing costs, while also emitting pollutants like NOx and CO.
Innovation Solution
A novel combustor design with corrugated geometry and tangentially firing fuel-air nozzles eliminates the need for first stage vane nozzles by accelerating hot gases to ideal velocities, incorporating corrugations that mimic the function of vane nozzles and utilizing premixed fuel-air nozzles and dilution holes for enhanced mixing and cooling.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If first stage vane nozzles are used to accelerate and redirect hot gases, then the hot gases can be directed to ideal velocities for turbine inlet, but flow losses increase and manufacturing costs increase
Solution Approach 1:
The patent removes the first stage vane nozzles from the gas turbine system entirely. The combustor liner is redesigned with integrated corrugated geometry that performs the acceleration and redirection function previously requiring separate vane nozzles, thereby eliminating the source of flow losses associated with those components.
Solution Approach 2:
The patent combines the functions of the combustor liner and the vane nozzles into a single integrated structure. The corrugated combustor liner directly accelerates and redirects hot gases toward the turbine inlet, merging what were previously separate functional elements into one component.
2Speed
If first stage vane nozzles are used to manipulate hot gas flow, then ideal velocity distribution is achieved, but manufacturing costs increase
Solution Approach 1:
The patent merges the combustor liner and vane nozzles into a single integrated component with corrugated geometry. This reduces the total number of parts that need to be manufactured, assembled, and maintained, thereby reducing manufacturing costs while preserving the velocity distribution function.
Solution Approach 2:
The corrugated combustor liner performs multiple functions: it contains the combustion process, accelerates hot gases to ideal velocities, redirects flow toward the turbine inlet, and provides structural support. This multi-functionality eliminates the need for separate vane nozzle components.
3Productivity
If premixed fuel-air nozzles with swirl are used, then mixing and combustion are enhanced, but flame blow out risk increases without swirl stabilization
Solution Approach 1:
The patent introduces swirl vanes that create a rotational component in the fuel-air mixture flow. This swirl stabilization prevents flame blowout by anchoring the combustion process, while the curved corrugated combustor liner enhances mixing through its geometric features.
Solution Approach 2:
The patent implements premixed fuel-air nozzles that prepare the combustible mixture before it enters the combustion chamber. This preliminary mixing enhances combustion efficiency, while the subsequent swirl stabilization ensures the premixed flame remains stable during operation.
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 reduces manufacturing costs, minimizes flow losses, and enhances combustion efficiency, reducing NOx and CO emissions by optimizing the combustion process and eliminating the need for emission control devices.
Implementation Method 1
A novel combustor design with corrugated geometry and tangentially firing fuel-air nozzles eliminates the need for first stage vane nozzles by accelerating hot gases to ideal velocities
Implementation Method 2
It is in this component that the compressed fuel-air mixture passes through fuel-air nozzles and a combustion reaction of the mixture takes place... A fuel air nozzle can take on different configurations such as single to multiple annular inlets with swirling vanes on each one
Implementation Method 3
A typical method for cooling the combustor is effusion cooling, implemented by surrounding the combustion liner with an additional, offset liner, which between the two, compressor discharge air passes through and enters the hot gas flow path through dilution holes and cooling passages
Implementation Method 4
The compressed air is then mixed at a specified fuel-air ratio in a combustor wherein its temperature is increased
Data Source
AI summary
A combustion device used in gas turbine engines includes an annular combustor that contains the combustion process of air and fuel and then guides the hot gas products to a first stage turbine subsection of a gas turbine engine. The annular combustor has an inner/outer shell having corrugated surfaces that extend radially outward and inward across an entire hot gas stream inside the annular combustor. The corrugations twist about the engine centerline in a longitudinal direction of travel of the engine. The resulting flow path accelerates and turns the hot gas stream to conditions suitable for introduction into the first stage turbine blades, which eliminate the need for first stage turbine vanes. The annular combustor is configured with a system of fuel and air inlet passages and nozzles that results in a staged combustion of premixed fuel and air.