Spherical Rocket Combustion Chamber Cooling via Propellant Injector
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Solution Overview
Problem
Rocket propulsion systems face challenges in reducing system weight and complexity, providing adequate cooling, and achieving efficient combustion and thrust across varying altitudes, particularly due to the use of conventional combustion chambers with cooling ducts that add weight and complexity and are prone to clogging.
Innovation Solution
The implementation of a rocket propulsion system with a spherical combustion chamber that uses a propellant injector to direct a cooling flow along the chamber walls without ducts, enhancing cooling efficiency and reducing weight and complexity, while also controlling exhaust flow through nozzle injection ports to adapt to altitude changes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If conventional combustion chambers with cooling ducts are used, then cooling function is provided, but system weight and complexity increase
Solution Approach 1:
The patent combines the cooling flow delivery function and main propellant delivery function into a single injector component. The injector delivers both the cooling flow that contacts the combustion chamber walls and the main propellant flow into the combustion zone, eliminating the need for separate cooling ducts and reducing system complexity
Solution Approach 2:
The injector is designed to perform multiple functions: it serves as both the cooling flow delivery system and the main propellant injection system. This multi-functional design eliminates redundant components and reduces overall system complexity while maintaining effective cooling
2Temperature
If conventional combustion chambers with cooling ducts are used, then cooling function is provided, but system weight increases
Solution Approach 1:
The patent combines the cooling flow delivery function and main propellant delivery function into a single injector component. The injector delivers both the cooling flow that contacts the combustion chamber walls and the main propellant flow into the combustion zone, eliminating the need for separate cooling ducts and reducing system complexity
Solution Approach 2:
The patent extracts and eliminates the cooling ducts from the combustion chamber design. By removing these unnecessary components and relying on the injector to deliver cooling flow directly, the overall system weight is reduced while maintaining cooling effectiveness
3Temperature
If cooling ducts are used in combustion chambers, then cooling is provided, but clogging occurs
Solution Approach 1:
The patent extracts and eliminates the cooling ducts from the combustion chamber design. By removing these unnecessary components and relying on the injector to deliver cooling flow directly, the overall system weight is reduced while maintaining cooling effectiveness
Solution Approach 2:
The cooling flow is delivered directly into the combustion chamber where it naturally contacts the chamber walls and provides cooling. The system uses the combustion chamber environment itself to deliver cooling without requiring complex ductwork, reducing clogging risks
4Device complexity
If fixed nozzle area is used, then simple structure is maintained, but thrust efficiency varies with altitude
Solution Approach 1:
The patent employs a dynamic nozzle area ratio adjustment system that modifies the effective nozzle area based on operating conditions. Injection ports can be activated or deactivated to change the effective nozzle area ratio, allowing the system to optimize thrust efficiency for different altitudes and pressure conditions
Solution Approach 2:
The system changes the effective nozzle area ratio parameter in response to varying operating conditions. By activating or deactivating injection ports, the system adjusts the effective nozzle area ratio to match ambient pressure conditions, optimizing performance across different altitudes
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 results in a lighter, less complex propulsion system with improved cooling efficiency and thrust performance across altitudes, reducing the risk of clogging and enhancing overall system efficiency and reliability.
Implementation Method 1
an injector that directs a cooling flow of rocket fuel along the walls of a spherical combustion chamber
Implementation Method 2
The injector can be configured to deliver not only the cooling flow, but the main propellant flow into the combustion chamber, and can sequence the flows to enhance cooling
Implementation Method 3
The resulting exhaust flow, exiting the combustion chamber through a nozzle
Data Source
AI summary
Rocket propulsion systems and associated methods are disclosed. A representative system includes a combustion chamber having an inwardly-facing chamber wall enclosing a combustion zone. The chamber has a generally spherical shape and is exposed to the combustion zone. A propellant injector is coupled to the combustion chamber and has at least one fuel injector nozzle positioned to direct a flow of cooling fuel radially outwardly along the inwardly-facing chamber wall. In addition to or in lieu of the foregoing features, the injector can include an oxidizer piston and a fuel piston that deliver oxidizer and fuel, respectively, to the combustion chamber, in a sequenced manner so that the oxidizer is introduced prior to the fuel.