Jet Engine Flame Stabilizer with Ablation Vanishment Section
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Solution Overview
Problem
Jet engines face challenges in maintaining combustion stability at varying flight speeds, particularly due to the high-pressure region extending to the inlet, leading to countercurrent flow and potential engine shutdown at slow speeds, and increased heat load and fuselage size issues with existing variable flame holder mechanisms.
Innovation Solution
The implementation of a jet engine design with multiple flame stabilizers and a vanishment section that adjusts its shape over time, using ablation materials for the vanishment member to prevent high-pressure regions from reaching the inlet, allowing for stable combustion across a wide speed range without significant fuselage modifications.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stress or pressure
If the high-pressure region extends to the inlet at slow flight speeds, then combustion pressure is maintained, but countercurrent flow occurs causing potential engine shutdown
Solution Approach 1:
The flame holder is designed as a variable type that can change its shape dynamically. It includes a movable flame holder portion that can adjust its position and a vanishment section that changes shape over time during flight, allowing the flame holder to adapt to different flight conditions and prevent countercurrent flow at slow speeds while maintaining combustion pressure
Solution Approach 2:
The invention changes the shape parameter of the flame holder over time during flight. The vanishment section is designed to vanish or change shape as flight time progresses, transforming the flame holder configuration to suit different flight stages and prevent the high-pressure region from reaching the inlet at slow speeds
2Reliability
If a variable flame holder mechanism is implemented to prevent countercurrent, then engine reliability improves, but device complexity and mechanical mechanism requirements increase
Solution Approach 1:
The flame holder utilizes the existing aerodynamic forces and combustion pressure within the engine to automatically adjust its configuration. The movable flame holder portion and vanishment section respond passively to changes in flight conditions and pressure distributions, eliminating the need for external actuators or complex control systems
Solution Approach 2:
The invention replaces complex mechanical actuation systems with aerodynamic and thermal fields. The variable flame holder configuration is achieved through aerodynamic forces acting on the movable portions and thermal effects on the vanishment section, rather than through mechanical motors or actuators
3Reliability
If the flame holder shape is changed to prevent high-pressure region extension, then countercurrent is prevented, but heat load on fuselage increases
Solution Approach 1:
The flame holder design concentrates the flame stabilization function in specific localized regions through the dent portions and movable flame holder sections. This localized flame holding approach prevents the need for extensive fuselage modifications and reduces the overall heat load distribution on the fuselage structure
Solution Approach 2:
The dynamic adjustment of the flame holder configuration allows optimal positioning of flame stabilization zones. The movable and vanishing sections adapt the flame holder shape to maintain combustion efficiency while minimizing heat transfer to the fuselage at different flight stages
4Adaptability or versatility
If fuselage is remodeled to accommodate variable flame holder, then combustion stability across speed ranges improves, but manufacturing complexity and cost increase
Solution Approach 1:
The flame holder is divided into distinct modular sections: a fixed flame holder portion, a movable flame holder portion, and a vanishment section. This segmentation allows each component to be manufactured separately and assembled into the fuselage, simplifying manufacturing while enabling complex overall functionality for adaptability across speed ranges
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 prevents countercurrent flow and maintains stable combustion from low to high speeds without lengthening the combustor or nozzle, reducing the size of the rocket motor and enhancing acceleration performance, while minimizing heat load on the fuselage.
Implementation Method 1
using ablation materials for the vanishment member to prevent high-pressure regions from reaching the inlet
Implementation Method 2
The plurality of flame stabilizers 21 can maintain the flame F used for combustion in the combustor 12
Data Source
AI summary
A jet engine includes an inlet (11) which takes in air and a combustor (12) which combusts fuel with the air. The combustor (12) has an injector (20), a plurality of flame stabilizers (21, 22) and a vanishment section (31). The injector (20) injects the fuel. The plurality of flame stabilizers (21, 22) can maintain the flame (F) used for combustion in the combustor (12). The vanishment section (31) is provided to cover the dent of the first flame stabilizer (21) which is situated on the side near to the inlet in the plurality of flame stabilizers (21, 22), and vanishes with the passage of time in the flight.