Partial Superheat Cycle for Rocket Pump Drive
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Solution Overview
Problem
Existing rocket engine propulsion systems face inefficiencies when using propellant combinations other than liquid hydrogen, as they struggle to adapt due to issues like undesirable chemical changes and deposit formation when evaporating fuels like kerosene, making it impractical to use these fuels as working fluids for driving pumps.
Innovation Solution
A propulsion system that includes a rocket engine with a combustion chamber, a heat exchanger, an oxidizer pump, and a motor, where a portion of the oxidizer is combusted to generate heat, converting another portion into a super-heated gaseous state to drive the motor and pump, with the motor exhaust being cooled and returned to the oxidizer supply, allowing for efficient operation with various propellant combinations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If fuel is evaporated to drive the motor, then power for the pump is generated, but undesirable chemical changes and deposit formation occur with fuels like kerosene
Solution Approach 1:
The patent introduces a heat exchanger as an intermediary device that transfers heat from the combusted first portion of oxidizer to the second portion of oxidizer, converting it to superheated gas for motor operation. This mediator approach allows energy transfer without directly evaporating the fuel, avoiding harmful chemical changes and deposit formation while still generating the necessary power for pump operation.
Solution Approach 2:
The patent changes the physical state and temperature parameters of the oxidizer by heating it to a superheated gaseous state through controlled heat transfer. This parameter change enables the oxidizer to serve as an effective working fluid for the motor without undergoing undesirable chemical decomposition, thus generating power while avoiding harmful effects.
2Stress or pressure
If pressurization system and tank mass are used, then sufficient pressure is achieved, but rocket system mass significantly increases
Solution Approach 1:
The patent implements a self-service system where the rocket engine's own combustion process generates heat that is used to drive the pump through a motor. The first portion of oxidizer is combusted to produce heat, which then drives the motor to power the pump, creating a self-contained pressurization system that eliminates the need for separate heavy pressurization tanks and systems.
Solution Approach 2:
The patent merges the pressurization function with the combustion process by using the heat from oxidizer combustion to drive the pump motor. This integration combines what were previously separate functions (combustion for thrust and separate pressurization system) into a unified system, reducing overall mass while achieving sufficient pressurization.
3Temperature
If fuel is used as coolant, then engine cooling is achieved, but the fuel cannot be used to drive the motor due to impracticality with certain propellant combinations
Solution Approach 1:
The patent segments the oxidizer flow into two distinct portions: the first portion is combusted to generate heat, and the second portion is heated by this combustion to become superheated gas for motor operation. This segmentation allows the system to achieve both cooling and power generation functions while adapting to various propellant combinations, as the heat transfer process works with different fuels including kerosene without requiring evaporation.
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 solution enables efficient propulsion systems capable of adapting to different propellant combinations, such as kerosene and oxygen, by effectively using the oxidizer to drive the pump and maintain engine cooling, reducing mass and increasing thrust efficiency compared to conventional systems.
Implementation Method 1
transferring heat from the combustion of the first portion of the oxidizer to a second portion of the pumped oxidizer to convert the second portion of the oxidizer to a super-heated gaseous oxidizer
Implementation Method 2
combusting a first portion of the oxidizer in the rocket engine
Implementation Method 3
the motor exhaust being cooled by heat exchange with the oxidizer flow
Data Source
AI summary
A system and method of driving a fuel pump and/or an oxidizer pump in a propulsion system includes pumping an oxidizer from an oxidizer supply to a rocket engine with the oxidizer pump. A first portion of the pumped oxidizer is used for combustion in the rocket engine. The heat from the combustion of the first portion of the oxidizer is then transferred to a second portion of the pumped oxidizer to convert the second portion of the oxidizer to a super-heated gaseous oxidizer. The super-heated gaseous oxidizer operates a motor, which drives the oxidizer pump and/or the fuel pump.