Dual-Nozzle Lance Injector for Gas Turbine Fuel Supply
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing gas turbine fuel oil supply systems are complex, requiring multiple components and additional lines, which increase design, construction, and maintenance costs, as well as complexity in piping and distribution, especially when dealing with varying fuel flow rates across different load conditions.
Innovation Solution
A dual-nozzle lance injector design for gas turbines that eliminates the need for a return line and atomization air, featuring two independent inner supply conduits with nozzles and swirlers to manage fuel flow effectively across different load conditions, allowing for optimal injection and atomization without additional infrastructure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a return line is added to enable wide range fuel flow supply, then the fuel flow control range is improved, but the system complexity and piping requirements increase
Solution Approach 1:
The single fuel supply line is segmented into multiple independent inner supply conduits (first inner supply conduit, second inner supply conduit, etc.), each capable of independent fuel delivery. This segmentation allows the system to achieve wide flow control range without requiring a return line, as each conduit can be independently regulated to meet different load conditions.
Solution Approach 2:
The multiple inner supply conduits serve universal fuel supply functions across different operating conditions. Each conduit can independently handle different flow rates, making the system universally adaptable to various load conditions without requiring additional specialized components like return lines or complex atomization systems.
2Manufacturing precision
If complex atomization systems with air are used, then fuel atomization quality is improved, but the device complexity and air supply infrastructure increase
Solution Approach 1:
The fuel injection system performs self-atomization through the design of the nozzles at the ends of the inner supply conduits. The fuel is atomized purely by the pressure and velocity of the fuel flow itself, without requiring external air supply systems. This self-service approach maintains high atomization quality while eliminating the need for complex air atomization infrastructure.
Solution Approach 2:
The air atomization function is extracted and removed from the system. Instead of using complex air supply systems to achieve atomization, the invention relies solely on fuel pressure and nozzle design to accomplish atomization, thereby simplifying the overall system while maintaining effective fuel delivery.
3Ease of operation
If multiple components and additional lines are used for fuel supply, then fuel delivery control is improved, but construction and maintenance costs increase
Solution Approach 1:
Multiple fuel supply functions are merged into a single integrated fuel supply line that contains multiple inner supply conduits. This consolidation maintains the ability to control fuel delivery across different loads while reducing the total number of separate components, piping connections, and distribution manifolds required, thereby lowering construction and maintenance costs.
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 dual-nozzle lance injector ensures optimal fuel injection and atomization across a wide range of loads, simplifying the system by eliminating the need for a return line and atomization air, reducing complexity and costs while maintaining effective operation.
Implementation Method 1
The delivery line receives a flow of fuel oil at a pressure much higher than the combustion chamber
Implementation Method 2
two independent inner supply conduits with nozzles and swirlers to manage fuel flow effectively
Data Source
Figure 1
Figure 2
Figure 3
AI summary
A lance injector for injecting fuel oil into a gas turbine combustion chamber includes: a tubular casing (33), extending along a main axis (A); a first inner supply conduit (35) housed in the casing (33) and coupled, at a respective supply end (35a), to a first supply inlet (44); a first nozzle (40), at a respective injection end (35b) of the first inner supply conduit (35); a second inner supply conduit (36) housed in the casing (33) and coupled, at a respective supply end (36a), to a second supply inlet (45), accessible from the outside independently of the first supply inlet (44); and a second nozzle (41), at a respective injection end (36a) of the second inner supply conduit (36).