Gas Turbine Combustor Barrier for EGR Flow Control
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Solution Overview
Problem
Gas turbine engines face challenges in reducing emissions and extending component life due to high temperatures, with existing cooling methods increasing oxidant concentrations in exhaust gases and potentially leading to increased nitrogen oxide emissions.
Innovation Solution
A system and method involving a turbine combustor with a combustor liner, a flow sleeve, and a barrier to direct oxidant and fuel flows, using inert gases for cooling and separating oxidant from inert gases to control combustion temperatures and emissions, achieving stoichiometric combustion with exhaust gas recirculation to enhance carbon dioxide production and reduce nitrogen oxide emissions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of stationary object
If cooling components or combustion gases with oxidant is used, then component life is extended through temperature management, but oxidant concentration in exhaust gas increases leading to increased nitrogen oxide emissions
Solution Approach 1:
The patent introduces an inert gas as an intermediary cooling medium instead of using oxidant for cooling components and combustion gases. This inert gas absorbs heat and extends component life while not increasing oxidant concentration in the exhaust stream, thereby avoiding increased nitrogen oxide emissions.
Solution Approach 2:
The patent employs an inert gas environment for cooling purposes, creating an atmosphere that does not promote oxidation reactions. This inert cooling approach allows temperature management of components without introducing additional oxidant that would lead to harmful nitrogen oxide formation in the exhaust.
2Temperature
If exhaust gas recirculation is used to cool combustion gases, then combustion temperatures are reduced extending component life, but oxidant concentration in exhaust gas increases
Solution Approach 1:
The patent uses inert gas as an intermediary substance to achieve exhaust gas recirculation for cooling purposes. This inert gas mediates the heat transfer process, reducing combustion temperatures to extend component life while maintaining low oxidant concentration in the recirculated exhaust stream.
Solution Approach 2:
The patent changes the composition parameter of the recirculated exhaust gas by using inert gas instead of oxidant-rich exhaust. This parameter change allows temperature reduction through recirculation while controlling oxidant concentration to prevent increased nitrogen oxide emissions.
3Object-generated harmful factors
If stoichiometric combustion is achieved to reduce emissions, then nitrogen oxide emissions are reduced, but control precision requirements increase
Solution Approach 1:
The patent implements feedback control mechanisms to monitor and adjust combustion parameters in real-time. This feedback system maintains stoichiometric combustion conditions, reducing nitrogen oxide emissions while adapting to varying operating conditions to manage the precision requirements.
Solution Approach 2:
The patent adjusts combustion parameters dynamically to achieve and maintain stoichiometric conditions. By controlling the air-fuel ratio and other combustion parameters with precision, the system reduces nitrogen oxide emissions while managing the complexity of control requirements through optimized parameter management.
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 effectively reduces nitrogen oxide emissions, increases carbon dioxide production for carbon sequestration, and extends component life by managing combustion temperatures and oxidant concentrations, while maintaining low levels of oxygen and fuel in exhaust gases for enhanced oil recovery applications.
Implementation Method 1
The barrier is configured to block the portion of the oxidant flow toward the turbine end and to block the gas flow toward the head end within the passage
Implementation Method 2
The inert gas is configured to cool the combustor liner and the combustion gases in the combustion chamber
Implementation Method 3
The passage is configured to direct a gas flow toward the head end and to direct a portion of the oxidant flow toward a turbine end of the turbine combustor
Data Source
AI summary
In one embodiment, a system includes a turbine combustor having a combustor liner disposed about a combustion chamber, a head end upstream of the combustion chamber relative to a downstream direction of a flow of combustion gases through the combustion chamber, a flow sleeve disposed at an offset about the combustor liner to define a passage, and a barrier within the passage. The head end is configured to direct an oxidant flow and a first fuel flow toward the combustion chamber. The passage is configured to direct a gas flow toward the head end and to direct a portion of the oxidant flow toward a turbine end of the turbine combustor. The gas flow includes a substantially inert gas. The barrier is configured to block the portion of the oxidant flow toward the turbine end and to block the gas flow toward the head end within the passage.