Ramjet Fuel Nozzle Assembly for Dynamic Thrust Control
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Solution Overview
Problem
Ramjet engines' combustion efficiency and operability are limited by their velocity and the velocity of air entering the engine, making them dependent on forward motion, which restricts independent operation.
Innovation Solution
A ramjet engine design with a moveable fuel nozzle assembly that adjusts the nozzle throat area based on pressure differences and Mach number of inlet air flow, allowing modulation of shockwave geometry and stoichiometry to maintain constant dynamic pressure and decouple thrust output from engine velocity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If the ramjet operates at higher velocities to improve thrust output, then the thrust increases, but the combustion efficiency becomes dependent on velocity and operational range is limited
Solution Approach 1:
The fuel nozzle assembly is made movable along the radial direction, allowing dynamic adjustment of the nozzle throat area based on operating conditions. This dynamic configuration enables the combustion section to maintain optimal performance across a range of velocities, decoupling combustion efficiency from engine velocity while preserving thrust output capability.
2Device complexity
If the nozzle throat area is fixed to simplify the system, then the device complexity is reduced, but the ability to maintain constant dynamic pressure and adjust thrust output is limited
Solution Approach 1:
The fuel nozzle assembly is made movable along the radial direction, allowing dynamic adjustment of the nozzle throat area based on operating conditions. This dynamic configuration enables the combustion section to maintain optimal performance across a range of velocities, decoupling combustion efficiency from engine velocity while preserving thrust output capability.
3Productivity
If the combustion section is designed for optimal performance at a specific velocity, then the combustion efficiency is maximized, but the operability is restricted to a narrow velocity range
Solution Approach 1:
The fuel nozzle assembly is made movable along the radial direction, allowing dynamic adjustment of the nozzle throat area based on operating conditions. This dynamic configuration enables the combustion section to maintain optimal performance across a range of velocities, decoupling combustion efficiency from engine velocity while preserving thrust output capability.
Solution Approach 2:
The nozzle throat area is adjusted as a variable parameter based on the difference in pressure between the inlet and the fuel nozzle assembly, and on the Mach number of inlet air flow. By changing this geometric parameter, the system adapts to different velocity conditions while maintaining optimal combustion efficiency.
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
Enables independent operation of the combustion section from ramjet engine velocity, improving efficiency and performance by maintaining constant dynamic pressure and adjusting thrust output, thus enhancing ramjet engine operation and stability.
Implementation Method 1
The fuel nozzle assembly is moveable along a radial direction to adjust the nozzle throat area based at least on a difference in pressure of a flow of fluid at an inlet of the inlet section and a pressure of the flow of fluid at the fuel nozzle assembly
Implementation Method 2
modulating the nozzle throat area to change a geometry of shockwaves from the inlet section downstream to the fuel nozzle assembly
Implementation Method 3
Rotating detonation combustion (RDC) systems utilize a continuous detonation wave produced from a mixture of fuel and oxidizer
Data Source
AI summary
A ramjet engine and system and method for operation is generally provided. The ramjet includes a longitudinal wall extended along a lengthwise direction. The longitudinal wall defines an inlet section, a combustion section, and an exhaust section. A fuel nozzle assembly is extended from the longitudinal wall. The fuel nozzle assembly defines a nozzle throat area. The fuel nozzle assembly is moveable along a radial direction to adjust the nozzle throat area based at least on a difference in pressure of a flow of fluid at an inlet of the inlet section and a pressure of the flow of fluid at the fuel nozzle assembly.