Dual Fuel Combustor Injection Locations for Emissions Control
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Solution Overview
Problem
Gas turbine combustors face limitations in versatility due to their inability to efficiently operate with both gaseous and liquid fuels, leading to higher emissions when using liquid fuels, which can be dictated by fuel availability and emissions requirements.
Innovation Solution
A dual fuel combustion system for gas turbine combustors is developed, featuring a cylindrical combustion liner, main mixer, radial inflow swirler, and fuel cartridge assembly with adjustable fuel injection locations, allowing operation with either gaseous or liquid fuel, or a combination of both, to provide operational flexibility with minimal component transition.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If liquid fuel is used in gas turbine combustors, then fuel availability and operational flexibility are improved, but emissions increase due to incomplete combustion
Solution Approach 1:
The fuel injection system is segmented into multiple injection locations along the combustor flow path, including primary injection at the combustor inlet and secondary injection downstream. This segmentation allows liquid fuel to be injected at different stages, improving vaporization and mixing with air to reduce emissions while maintaining operational flexibility
Solution Approach 2:
Different regions of the combustor are provided with different injection characteristics - the primary injection location provides coarse spray for initial vaporization, while secondary injection locations provide finer spray patterns for complete combustion. This local differentiation optimizes combustion efficiency and reduces emissions for liquid fuel operation
2Object-generated harmful factors
If gaseous fuel is used in gas turbine combustors, then emissions are reduced due to pre-mixing and complete combustion, but fuel availability is limited
Solution Approach 1:
The combustor system is designed with universal fuel injection capability that can accommodate both gaseous and liquid fuels through the same hardware platform. The injection system can switch between fuel types by activating different injection locations, providing multi-functionality without requiring separate combustor designs for each fuel type
Solution Approach 2:
The fuel injection system is made dynamic and adjustable, allowing operators to select and switch between different fuel types (gaseous or liquid) and different injection locations based on fuel availability and emissions requirements. This dynamic adaptability enables the system to optimize performance for whatever fuel is currently available
3Adaptability or versatility
If multiple fuel injection locations are provided in the combustor, then fuel type versatility and emissions control are improved, but device complexity increases
Solution Approach 1:
The multiple fuel injection locations are nested within a single integrated combustor assembly, with injection points positioned at different stages along the flow path. This nested arrangement allows multiple injection functions to be contained within one compact structure, providing fuel versatility without proportionally increasing overall system complexity
Solution Approach 2:
The fuel injection system merges multiple injection locations and fuel delivery paths into a unified control architecture. By combining the control of primary and secondary injection locations under a single system, the patent reduces operational complexity while maintaining the versatility benefits of multiple injection points
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 system enables flexible fuel operation, reducing emissions by allowing for optimal fuel type selection based on availability and emissions requirements, while maintaining efficient combustion and emissions control through staged fuel delivery and water-fuel mixture management.
Implementation Method 1
a radial inflow swirler coupled to the cylindrical combustion liner and providing fluid communication between an inside and an outside of the cylindrical combustion liner
Implementation Method 2
Each of these components may further include various fuel injection locations configured to introduce liquid or gaseous fuel into the combustor, to provide a desired fuel source for combustion
Data Source
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AI summary
Systems and methods for dual-fuel operation of a gas turbine combustor are provided. An exemplary gas turbine combustor may comprise one or more components, such as a cylindrical combustion liner, a flow sleeve, a main mixer, a radial inflow swirler, a combustor dome, and a fuel cartridge assembly, one or more of which may be configured to supply either a gaseous or a liquid fuel to the combustion liner, depending on whether gaseous fuel operation or liquid fuel operation of the combustor is desired.