Perpendicular Fuel Injector with Segmented Openings for Jet Engine Combustion
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Solution Overview
Problem
Existing jet engines face instability and limited speed range due to insufficient fuel-air mixing, leading to inefficient combustion and increased fuel consumption, particularly at supersonic velocities.
Innovation Solution
The jet engine incorporates a combustor with a fuel injector featuring multiple openings arranged almost perpendicular to the air flow direction, with varying opening areas to promote uniform fuel distribution and mixing, allowing for efficient fuel injection and combustion across a broader speed range.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If fuel is injected perpendicular to air flow direction with varying opening areas, then fuel-air mixing efficiency is improved, but device complexity increases
Solution Approach 1:
The fuel injector is segmented into multiple openings with different areas rather than using a single uniform opening. This segmentation allows different portions of fuel to be injected at different rates, improving mixing efficiency with the supersonic air flow while maintaining a relatively simple overall injector structure.
Solution Approach 2:
Different openings in the injector are given different local qualities (different areas) to optimize fuel distribution. The varying opening areas create localized differences in fuel injection characteristics, enabling better adaptation to the supersonic flow conditions and improving overall mixing efficiency.
2Reliability
If multiple openings with different areas are used in the injector, then combustion stability is improved, but manufacturing precision requirements increase
Solution Approach 1:
The injector is divided into multiple openings that can be manufactured as standardized segments. This segmentation approach allows for modular manufacturing where each opening can be produced with consistent precision requirements, making the overall system more manufacturable despite the varying areas.
Solution Approach 2:
The opening areas are designed with specific parameter variations that balance combustion stability requirements with manufacturing capabilities. By carefully selecting the area ratios and distributions, the design achieves stable combustion while maintaining feasibility for standard manufacturing processes.
3Adaptability or versatility
If fuel injection is optimized for supersonic speeds, then speed range limitation is reduced, but fuel consumption increases
Solution Approach 1:
The injector design incorporates dynamic characteristics through varying opening areas that adapt to different flow conditions. The perpendicular injection direction and area variations create a more dynamic fuel distribution pattern that maintains effectiveness across a broader speed range while optimizing fuel utilization to minimize consumption.
Solution Approach 2:
The injector parameters (opening areas, directions) are optimized to change the fuel injection characteristics in response to varying flight speeds. This parameter optimization allows the system to maintain stable combustion across an extended speed range while managing fuel consumption through efficient mixing achieved by the perpendicular injection geometry.
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 configuration enhances stability, reduces fuel consumption, and extends the usable speed range by ensuring efficient fuel-air mixing, leading to improved combustion and reduced engine size and weight.
Implementation Method 1
a part of the fuel G is supplied and diffused toward a low-speed region which exists in the boundary layer developed on the wall surface 121 of the combustor 112
Implementation Method 2
The plurality of openings are arranged in a direction perpendicular to a direction of a flow path of the air in the combustor. The plurality of openings include two types of openings having different areas.
Data Source
AI summary
A jet engine includes an inlet and a combustor. the inlet takes in air. The combustor combusts fuel with the air. The combustor (12) includes an injector (20) having a plurality of openings (31a, 31b) from which the fuel is injected. The plurality of openings (31a, 31b) are arranged in a direction perpendicular to a direction of a flow path of the air in the combustor (12). The plurality of openings (31a, 31b) include two types of openings different in area.