Gas Turbine Combustor Fuel Distributor for NOx Reduction
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Solution Overview
Problem
The implementation of composite combustion systems in gas turbine engines for small-size airplanes is hindered by the significant weight and cost of flow control valves and controllers required for fuel distribution, which complicates the transition between lower and higher intensity combustion modes and increases NOx emissions.
Innovation Solution
A combustor design that incorporates a fuel distributor with a movable piston mechanism to automatically control fuel distribution between pilot and main fuel passages based on pressure, eliminating the need for flow control valves and simplifying the control circuit, allowing for seamless transition between combustion modes while reducing NOx emissions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If flow control valves and controllers are provided to control fuel distribution between pilot and main fuel passages, then the transition between combustion modes can be controlled, but the weight and cost of the system increases significantly
Solution Approach 1:
The fuel distributor automatically controls fuel distribution between pilot and main fuel passages based on fuel pressure variations, eliminating the need for external flow control valves and controllers. The system uses the inherent pressure changes during combustion mode transition to drive the piston mechanism, which automatically opens or closes ports to direct fuel flow to the appropriate passage.
Solution Approach 2:
The patent replaces the electronic control system (controllers and flow control valves) with a purely mechanical fuel distributor mechanism. The piston, ports, and fuel pressure work together to automatically switch between combustion modes without electronic intervention, significantly reducing system weight and complexity.
2Ease of operation
If flow control valves and controllers are provided to control fuel distribution, then the combustion mode transition can be managed, but the device complexity increases
Solution Approach 1:
The fuel distributor automatically controls fuel distribution between pilot and main fuel passages based on fuel pressure variations, eliminating the need for external flow control valves and controllers. The system uses the inherent pressure changes during combustion mode transition to drive the piston mechanism, which automatically opens or closes ports to direct fuel flow to the appropriate passage.
Solution Approach 2:
The patent extracts and removes the complex electronic control system (controllers and flow control valves) from the fuel distribution mechanism. By using only the fuel distributor with piston and ports that respond passively to fuel pressure, the system achieves mode transition control with minimal components.
3Power
If higher temperature and pressure operation is employed to elevate output, then the fuel consumption is reduced, but the combustion temperature increases leading to higher NOx emissions
Solution Approach 1:
The fuel injection system is segmented into two separate passages: pilot fuel passage for diffusion combustion and main fuel passage for pre-mixture combustion. This allows the system to use different combustion modes for different operating conditions, enabling high power output while controlling NOx emissions by selecting the appropriate combustion mode.
Solution Approach 2:
The system changes the combustion mode parameter based on operating conditions. At high power settings, the system can use pre-mixture combustion with controlled air-fuel ratios to maintain lower combustion temperatures and reduce NOx, while still achieving high output through optimized fuel injection and combustion chamber design.
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
This design simplifies the structure and reduces costs by automating fuel distribution based on pressure, ensuring stable combustion and effective NOx reduction without the need for complex control systems, making it more feasible for small-size gas turbine engines.
Implementation Method 1
the movable body is configured to be moved in accordance with the pressure of the fuel at the fuel inlet
Implementation Method 2
the fuel distributor being configured to automatically control amounts of the fuel to be distributed to the pilot fuel passage and to the main fuel passage in accordance with a pressure of the fuel
Data Source
Figure 1
Figure 2
Figure 3
AI summary
The present combustor of gas turbine engine includes: a fuel injection unit (2) including a fuel spray part to spray a fuel so that a diffusion combustion region is formed in a combustion chamber, and a pre-mixture supply part to supply a pre-mixture of a fuel and an air so that a pre-mixture combustion region is formed in the combustion chamber; and a fuel supply unit to supply the fuel to the fuel spray part and pre-mixture supply part. The fuel supply unit includes: a pilot fuel passage (64) and a main fuel passage (65) to supply the fuel to the fuel spray part and the pre-mixture supply part, respectively; an assembled fuel passage to supply the fuel to the pilot and main fuel passages; and a fuel distributor (66) disposed at a branch point where the assembled fuel passage is connected to both the pilot and main fuel passages. The fuel distributor is configured to automatically control amounts of the fuel to be distributed to the pilot fuel passage and to the main fuel passage in accordance with the fuel pressure.