Combustor Flow Sleeve Vanes for Airflow Distribution
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Solution Overview
Problem
Gas turbine combustors using premix combustion face instability and increased pressure drop due to non-uniform air flow and swirl, leading to combustion instability and elevated NOx emissions, which negatively impact efficiency and emissions compliance.
Innovation Solution
A gas turbine combustor design featuring a flow sleeve with radially fixed vanes that direct air flow in a substantially axial direction, reducing tangential velocity and swirl, thereby achieving a more uniform air distribution and minimizing pressure drop.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-generated harmful factors
If premix combustion is used to reduce emissions, then NOx and CO emissions are reduced, but combustion stability deteriorates due to fuel-lean mixture instability
Solution Approach 1:
The patent applies local quality by creating different flow conditions in different regions of the combustor. The swirl generator creates a controlled swirl zone near the injector to stabilize the flame, while the diffuser creates a low-swirl zone further downstream. This spatial variation in flow quality allows the fuel-lean mixture to burn stably without increasing overall emissions.
2Stability of the object's composition
If greater pressure drop is taken across the combustor to reduce swirl effects, then combustion stability improves, but gas turbine efficiency deteriorates
Solution Approach 1:
The patent replaces the purely mechanical pressure-drop-based swirl reduction with a geometric flow control system. The diffuser geometry passively converts kinetic energy from the swirl flow into pressure, reducing swirl velocity without requiring additional pressure drop across the combustor. This substitution maintains combustion stability while preserving gas turbine efficiency.
3Stress or pressure
If non-uniform air flow with swirl is allowed, then pressure drop is reduced, but combustion stability deteriorates due to fluctuating fuel-air ratio
Solution Approach 1:
The patent applies preliminary action by pre-conditioning the air flow before it reaches the combustion zone. The swirl generator and diffuser are positioned upstream to establish the desired flow pattern (controlled swirl followed by swirl reduction) before the fuel-air mixture enters the main combustion region. This preliminary flow conditioning ensures stable combustion without requiring high pressure drop.
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 enhances combustion stability, reduces NOx emissions, and improves gas turbine efficiency by minimizing pressure drop, resulting in increased power output and lower fuel costs.
Implementation Method 1
a plurality of vanes fixed to the flow sleeve radially between the flow sleeve and combustion liner. The plurality of vanes serve to mechanically direct a flow of air entering the region between the flow sleeve and combustion liner in a substantially axial direction, such that components of tangential velocity are removed
Implementation Method 2
fuel and compressed air are mixed together prior to ignition to form as homogeneous a mixture as possible
Implementation Method 3
fuel and compressed air are mixed together and ignited to produce hot combustion gases that drive a turbine
Data Source
AI summary
An apparatus and method of providing a gas turbine combustor having increased combustion stability and reducing pressure drop across a gas turbine combustor is disclosed. A plurality of vanes is fixed to a flow sleeve radially between the flow sleeve and a combustion liner. The plurality of vanes serve to direct a flow of air entering the region between the flow sleeve and combustion liner in a substantially axial direction, such that components of tangential velocity are removed thereby providing a more uniform flow of air the combustion chamber and reducing the amount of pressure lost due attempting to straighten the airflow by pressure drop alone.