Multifluid Fuel Supply System for Gas Turbine Burners
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Solution Overview
Problem
Gas turbine units face a challenge in reducing pollutant emissions, particularly NOx, while maintaining flame stability across varying operating conditions, as existing burner technologies often compromise between these two goals.
Innovation Solution
A gas turbine unit with a multifluid fuel supply system that utilizes a combination of primary and secondary fuels, along with an inert fluid, managed by a sophisticated regulating system, including lance injectors and swirler designs, to control flame stability and emissions. The system adjusts fuel flow rates and inert fluid injection to minimize pollutant emissions while preserving combustion stability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a diffusion pilot burner is used, then flame stability is improved, but pollutant emissions worsen
Solution Approach 1:
The pilot burner is segmented into multiple injection points arranged circumferentially, with each point receiving fuel through separate channels. This segmentation allows different portions of the pilot flame to be controlled independently, enabling stable combustion while reducing localized NOx formation through distributed heat release
Solution Approach 2:
The invention applies local quality by creating a non-uniform fuel distribution pattern through the circumferential arrangement of injection points. Different angular positions receive fuel at different rates, creating zones of varying combustion intensity that collectively provide stability while minimizing peak temperatures that generate NOx
2Object-generated harmful factors
If a partial premix pilot burner is used, then pollutant emissions are improved, but flame stability worsens
Solution Approach 1:
The invention merges diffusion combustion and premix combustion modes within a single pilot burner system. Fuel is introduced through multiple channels that combine premixed combustion (for low emissions) with controlled diffusion elements (for stability), creating a hybrid approach that achieves both emission reduction and flame stabilization
Solution Approach 2:
The system dynamically adjusts the fuel distribution pattern among the circumferential injection points based on operating conditions. The control system modulates fuel flow rates to different channels, transitioning between premix and diffusion modes as needed to maintain stability while minimizing emissions across varying load conditions
3Reliability
If uncontrolled diffusion flame is generated, then flame stability is improved, but pollutant emissions worsen
Solution Approach 1:
The control system continuously monitors combustion parameters and adjusts the fuel distribution to the circumferential injection points in real-time. This feedback control ensures that diffusion flames are generated only when and where needed for stability, while premix combustion handles the majority of heat release, thereby minimizing NOx emissions while maintaining flame stability
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 pollutant emissions by optimizing fuel and inert fluid distribution, maintaining flame stability across a wide range of operating conditions, and enhancing the efficiency and flexibility of the burner assemblies without compromising performance.
Implementation Method 1
Each burner assembly comprises a swirler, a main burner and a pilot burner arranged on an axis of the swirler
Implementation Method 2
EP 2 487 419 A2 discloses a gas turbine unit comprising a combustion chamber and a supply system. The combustion chamber is provided with a plurality of burner assemblies, each of which comprises a respective lance injector
Implementation Method 3
The supply system is configured to supply fuel to the burner assemblies
Data Source
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AI summary
A gas turbine unit including a combustion chamber (5) provided with a plurality of burner assemblies (15) and a supply system (8), configured to supply fuel to the burner assemblies (15). Each burner assembly (15) includes a respective lance injector (20; 120) having a plurality of first nozzles (60; 160) and a first internal fluid line (58; 158) fluidically coupled with the first nozzles (60; 160). The supply system (8) includes a first fuel supply line (10) and an inert supply line (12), configured to respectively supply a primary fuel and an inert fluid to the first nozzles (60; 160) through the first internal fluid line (58; 158).