Combustor Jet Nozzle With Vortex Baffle for Secondary Mixing
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing turbomachines, particularly gas turbines, face challenges in increasing the mixing rate of combustion gases and fluids for secondary combustion, which affects combustion efficiency.
Innovation Solution
A jet nozzle is integrated into the combustor's inner surface to supply fluid into the liner, generating a vortex and enhancing a counter-rotary shear layer vortex through a baffle section, intersecting with the primary combustion gases' direction to facilitate secondary combustion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If a conventional nozzle structure is used to supply fluid for secondary combustion, then the structure is simple, but the mixing rate of combustion gases and fluid is insufficient
Solution Approach 1:
The nozzle body section is designed with a curved inner peripheral surface that generates a vortex flow when fluid passes through. This curvature creates rotational flow patterns that enhance mixing between the injected fluid and combustion gases, directly addressing the insufficient mixing rate problem while maintaining a relatively simple integrated nozzle structure.
Solution Approach 2:
The baffle section extends in the radial direction from the nozzle body, creating a three-dimensional flow structure. This additional dimensional element introduces counter-rotary shear layer vortices that enhance mixing in multiple directions, improving the mixing rate without requiring a completely complex multi-component nozzle assembly.
2Use of energy by moving object
If fluid is injected without vortex generation, then the nozzle structure is simple, but the combustion efficiency is reduced
Solution Approach 1:
The curved inner peripheral surface of the nozzle body section generates vortex flow that enhances combustion efficiency by improving fuel-air mixing. The vortex structure creates turbulent flow patterns that promote more complete and efficient combustion of the injected fluid with the surrounding combustion gases.
Solution Approach 2:
The counter-rotary shear layer vortices created by the baffle section introduce rotational motion and turbulence into the flow. This mechanical motion enhances the mixing and combustion processes by creating dynamic flow patterns that increase the contact between fuel and oxidizer, thereby improving combustion efficiency.
3Productivity
If the fluid discharge direction is parallel to combustion gases, then the structure is simple, but the mixing rate is low
Solution Approach 1:
The curved nozzle geometry transforms the fluid discharge into a vortex flow pattern that intersects with the combustion gas flow direction. This curved flow path creates natural mixing zones where the injected fluid and combustion gases interact more effectively, increasing the mixing rate without requiring complex directional control mechanisms.
Solution Approach 2:
The baffle section introduces radial flow components that create counter-rotary vortices, adding a rotational dimension to the fluid discharge. This multi-directional flow structure causes the injected fluid to intersect with combustion gases from multiple angles, significantly enhancing the mixing rate compared to simple parallel flow configurations.
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 increases the mixing rate of combustion gases and fuel, enhancing combustion efficiency by promoting a second combustion process within the liner, thereby improving overall gas turbine performance.
Implementation Method 1
a fluid outlet on a second end, through which fluid introduced through the fluid inlet is discharged while generating a vortex
Implementation Method 2
a baffle section formed on an inner peripheral surface of the second end of the body section and configured to enhance the generation of a counter-rotary shear layer vortex in the fluid discharged out of the fluid outlet
Implementation Method 3
supply fluid into an interior of a liner of the combustor in a direction intersecting with a progress direction of combustion gases primarily combusted in a combustion chamber
Data Source
AI summary
Proposed are a jet nozzle, and a combustor and a gas turbine including the jet nozzle. The jet nozzle is formed on an inner surface of a combustor to supply fluid into an interior of a liner of the combustor in a direction intersecting with a progress direction of combustion gases primarily combusted in a combustion chamber in the interior of the liner. The jet nozzle includes a body section provided with a fluid inlet on a first end, through which fluid is introduced, and a fluid outlet on a second end, through which the fluid introduced through the fluid inlet is discharged while generating a vortex, and a baffle section formed on an inner peripheral surface of the second end of the body section and configured to enhance the generation of a counter-rotary shear layer vortex in the fluid discharged out of the fluid outlet through the body section.