Helicopter Turbine Starter Supercapacitor Module
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Solution Overview
Problem
Starting turbine engines in helicopters is challenging due to the high resistive torque required, especially at low temperatures, which demands significant energy from batteries that are limited and heavy, and existing solutions do not efficiently manage energy distribution during startup.
Innovation Solution
Incorporating supercapacitors as discharge members in the electrical network to provide a high-power pulsed energy boost to the starter motor, controlled by measurement and control means to adapt energy supply based on resistive torque and startup phase requirements, reducing the energy reserve needed from batteries and allowing operation in adverse conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If batteries are used as the electrical energy source to power the starter during turbine engine startup, then the starter can be supplied with energy, but the battery mass and size increase to provide sufficient energy reserve, especially for extreme temperatures
Solution Approach 1:
The electrical energy source is segmented into two distinct components: a battery for baseline energy supply and a supercapacitor module for peak power delivery. This segmentation allows each component to be optimized for its specific function, with the supercapacitor handling the high-current demands during startup while the battery provides sustained energy, thereby reducing the overall battery mass required
Solution Approach 2:
The supercapacitor module provides excessive action by delivering more than 100% of the starter's power requirement during critical startup phases. This partial action approach allows the battery to be downsized since it only needs to supply the remaining baseline power, not the full peak power demand
2Reliability
If batteries are used to supply energy during startup, then the turbine engine can be started, but the batteries must meet operating requirements at low temperatures which increases their energy reserve and mass
Solution Approach 1:
The invention changes the electrical parameters available during startup by introducing a supercapacitor module that can deliver high current at low temperatures without the performance degradation that affects batteries. This parameter change allows reliable operation in extreme conditions while reducing battery mass requirements
3Power
If a high-power pulsed energy boost is provided to the starter, then the resistive torque can be overcome, but additional energy storage components are required
Solution Approach 1:
The supercapacitor module is designed with multi-functionality: it provides peak power during startup, can be recharged from the battery or aircraft electrical system, and can operate independently if the battery fails. This universality justifies the added complexity by providing multiple benefits within a single integrated component
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 efficient startup of turbine engines by providing high-power pulses to overcome resistive torque, reducing battery energy requirements, minimizing battery mass and size, and ensuring reliable operation in extreme conditions.
Implementation Method 1
Incorporating supercapacitors as discharge members in the electrical network to provide a high-power pulsed energy boost to the starter motor
Data Source
Figure 1~3
Figure 4~5
AI summary
The device has a starter (6) powered with electrical energy from an electricity network (8). Discharge members (10) i.e. supercapacitors, are incorporated in the electricity network and grouped into a module. The members of the module are grouped by a dozen, and have individual capacitance in the order of 3000 farads for a unit voltage of about 2.7 voltage direct current (Vdc). The members are connected in series to make the module suitable for use on a network having a voltage of about 28 Vdc. The members partially form an accessory that is removably mounted in the electricity network. An independent claim is also included for a method of starting a turbine engine of a helicopter.