Compressor Fluid Distribution via Staggered Spray Rings
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Solution Overview
Problem
Existing gas turbine systems face inefficiencies due to thermal gradients and uneven distribution of fluid droplets during wet compression and water wash processes, which affect the compressor's performance and output.
Innovation Solution
A circumferentially arranged, axially staggered fluid distribution system with multiple spray rings positioned near the compressor inlet, equipped with both wet compression and water wash nozzles, reduces thermal gradients and ensures comprehensive blade coverage by dispersing fluid droplets uniformly across the compressor blades.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If fluid is injected into the compressor inlet to cool air and clean blades, then efficiency and output increase, but thermal gradients and uneven fluid distribution occur
Solution Approach 1:
The fluid distribution system is segmented into multiple spray rings arranged circumferentially around the compressor inlet, with each spray ring containing multiple nozzles. This segmentation allows fluid to be distributed from multiple locations simultaneously, creating a more uniform fluid distribution pattern across the compressor inlet area and reducing localized thermal gradients.
Solution Approach 2:
The spray rings are positioned at different axial locations and angled to target specific regions of the compressor inlet. This local quality approach ensures that fluid is delivered precisely where needed on the compressor blades and air flow path, optimizing cooling and cleaning effects while minimizing unnecessary fluid application in other areas.
2Area of stationary object
If spray rings are positioned to maximize blade coverage, then cleaning area increases, but intake air flow obstruction increases
Solution Approach 1:
The spray rings are arranged in multiple axial planes rather than a single plane, creating a three-dimensional distribution pattern. This dimensional arrangement allows fluid to be applied to compressor blades from different axial positions, maximizing blade surface coverage while distributing the obstruction effect across multiple locations, reducing overall flow resistance.
Solution Approach 2:
The spray rings are designed with adjustable positioning and angling capabilities, allowing the system to be optimized for different operating conditions. This dynamic adjustment enables maximum blade coverage during water wash operations while minimizing air flow obstruction during normal compression operations.
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 configuration enhances the efficiency and output of the gas turbine system by minimizing thermal distortions and increasing the area of compressor blades that can be cleaned, leading to improved performance and potentially reducing the need for additional cooling mechanisms.
Implementation Method 1
The multiple spray rings are configured to spray fluid droplets into the intake air flow to be carried into the compressor
Implementation Method 2
reduces thermal gradients inside the compressor caused by evaporation of fluid during compression of the flow of air
Data Source
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AI summary
A system includes a fluid distribution system (32). The fluid distribution system (32) includes multiple spray rings (56) disposed upstream of an inlet (57) of a compressor (20). The multiple spray rings (56) include a first spray ring (70) disposed about an axis (52) of the compressor (20) in a first plane substantially perpendicular to the axis (52). The first spray ring (70) includes a first set of nozzles (104) disposed about the axis (52) and configured to spray a first fluid flow toward the compressor inlet (57). The multiple spray rings (56) further include a second spray ring (74) disposed about the axis (52) of the compressor (20) in a second plane substantially perpendicular to the axis (52). The second spray ring (74) includes a second set of nozzles (104) disposed about the axis (52) and configured to spray a second fluid flow toward the compressor inlet (57). The first plane is different than the second plane.