Solid-Propellant Emergency Starter for Aircraft Turbomachines
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Solution Overview
Problem
Current emergency start systems for turbine engines in aircraft, particularly in helicopters, are inadequate for rapid restarts during critical situations due to their slow performance and reliance on expensive and complex electrical systems, which can be detrimental in situations requiring immediate action.
Innovation Solution
An emergency start system utilizing a compact solid-propellant gas generator, an electrically controlled ignition device, and a starter motor with a turbine, where the gas generator's output is connected to the turbine engine's inlet, allowing for quick and autonomous startup independent of the aircraft's electric network, controlled by a computer that activates the ignition upon detecting an emergency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If a conventional electric starter motor powered by the helicopter's on-board power supply is used, then the starting system is simple and integrates with existing electrical infrastructure, but the reaction time is too slow (around 30 seconds) for emergency situations
Solution Approach 1:
The patent replaces the conventional electric motor-based starting system with a solid-propellant gas generator that produces high-pressure gases to directly drive the turbine. This substitution of the power generation mechanism eliminates the need for complex electrical power systems (synchronous machines with permanent magnets, power electronics, dedicated battery packs) and achieves rapid response in seconds rather than 30 seconds.
Solution Approach 2:
The invention changes the fundamental operating parameters of the starting system by using solid propellant combustion to generate high-pressure gases at extremely high temperatures and pressures. This parameter change enables the system to deliver the required power density and response time for emergency starting while maintaining simplicity through the use of proven solid-propellant technology.
2Speed
If the electrical system is adapted to provide faster starting performance, then the reaction time improves for emergency situations, but the system becomes more expensive and complex requiring synchronous machines with permanent magnets, power electronics and dedicated battery packs
Solution Approach 1:
The patent replaces the conventional electric motor-based starting system with a solid-propellant gas generator that produces high-pressure gases to directly drive the turbine. This substitution of the power generation mechanism eliminates the need for complex electrical power systems (synchronous machines with permanent magnets, power electronics, dedicated battery packs) and achieves rapid response in seconds rather than 30 seconds.
3Reliability
If a conventional start sequence is used taking around 30 seconds, then the system is simple and reliable, but it is too slow for emergency situations at low altitude requiring immediate engine restart
Solution Approach 1:
The solid-propellant gas generator is pre-loaded and ready for immediate activation in emergency situations. The propellant is prepared in advance in a stable, storable form that can be rapidly ignited to produce the required high-pressure gases, eliminating the need for time-consuming electrical system activation and power buildup.
Solution Approach 2:
The invention changes the fundamental operating parameters of the starting system by using solid propellant combustion to generate high-pressure gases at extremely high temperatures and pressures. This parameter change enables the system to deliver the required power density and response time for emergency starting while maintaining simplicity through the use of proven solid-propellant technology.
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 rapid and reliable emergency starts of turbine engines, reducing reaction time and ensuring safety margins in critical situations, with high power density and autonomy from the electric network, suitable for various aircraft configurations.
Implementation Method 1
A solid propellant is an energetic material containing the oxidiser elements (combustion agent) and reducing elements (fuel), which allow for high-energy gaseous combustion products to be generated by combustion (redox reaction).
Implementation Method 2
at least one starter motor comprising a turbine for driving a shaft intended for being coupled to a shaft of the turbine engine, the gas outlet of the generator being connected to the inlet of the turbine of the starter motor
Data Source
AI summary
An emergency start system for a turbine engine of an aircraft including at least one solid propellant gas generator, an electrically controlled ignition device, a computer connected to the ignition device, and at least one starter motor comprising a turbine for driving a shaft which is for coupling to a shaft of the turbine engine The outlet of the gases from the generator are connected to the inlet of the turbine of the starter motor.