Helicopter Turboshaft Engine Speed Control for Fuel Efficiency
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Solution Overview
Problem
Helicopter turbine engines operate inefficiently during cruising flight, leading to high fuel consumption, and are oversized for critical flight situations, which increases mass and fuel consumption, while current methods for placing engines in standby mode are not compatible with safety standards and certification rules.
Innovation Solution
A method to automatically control the operating speed of turbine engines by selecting from predetermined speeds based on flight data, allowing adaptation to changing conditions and prioritizing safety and fuel efficiency, including the ability to switch between standby regimes and nominal operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If turbine engines operate at low power levels during cruising flight, then the helicopter can maintain normal flight conditions, but fuel consumption increases by 30% compared to maximum continuous power
Solution Approach 1:
The patent implements dynamic engine speed control that automatically adjusts turbine engine operating speed based on real-time flight conditions. The control system monitors flight parameters and dynamically selects optimal engine speeds from predetermined values, transitioning between idle, standby, and nominal operating modes to optimize fuel consumption while maintaining required thrust levels during different flight phases.
Solution Approach 2:
The patent changes the operating speed parameter of the turbine engine from fixed to variable. By selecting from multiple predetermined engine speeds (idle, standby, nominal) based on flight conditions, the system optimizes the balance between fuel consumption and thrust provision. The control method modifies engine operational parameters dynamically rather than maintaining a fixed operating point.
2Adaptability or versatility
If turbine engines are oversized to ensure flight capability in critical situations and high altitudes, then the helicopter can operate in the entire flight envelope, but mass and fuel consumption increase
Solution Approach 1:
The patent applies partial action by placing one turbine engine in standby mode with reduced power output while the other engine operates at nominal power. This partial utilization of engine capacity allows the helicopter to maintain flight capability in critical situations without requiring both engines to be continuously oversized. The standby engine provides sufficient power for emergency situations while consuming less fuel during normal operation.
3Use of energy by moving object
If one turbine engine is placed in standby mode to reduce fuel consumption, then specific consumption decreases, but restart reliability may not meet safety standards
Solution Approach 1:
The patent implements a feedback-based control system that continuously monitors flight conditions and engine status to dynamically adjust the number of engines in standby mode. The control system receives feedback from flight parameters and automatically transitions engines between idle, standby, and nominal modes. This feedback mechanism ensures that sufficient engines remain operational to meet safety requirements while optimizing fuel consumption when conditions allow.
Solution Approach 2:
The system dynamically adjusts engine operational modes based on real-time assessment of safety requirements and flight conditions. Rather than statically placing engines in standby, the control method continuously evaluates whether the standby configuration maintains adequate restart reliability, transitioning engines between modes as needed to balance fuel efficiency with safety standards.
4Ease of operation
If turbine engines operate at ground idle during waiting phases, then the helicopter can be ready for immediate takeoff, but fuel consumption continues despite no power provision
Solution Approach 1:
The patent implements periodic monitoring and adjustment of engine operating modes during ground waiting phases. Rather than maintaining continuous ground idle operation, the control system periodically assesses flight conditions and transitions engines between idle and standby modes as appropriate. This periodic control reduces fuel consumption during ground operations while maintaining the ability to quickly transition to nominal power when takeoff is required.
Data Source
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Figure 3~6
AI summary
The invention relates to a method for automatically controlling an operating speed of a helicopter turboshaft engine, including a step (10) of receiving data (27, 28, 29) that represent the flight of the helicopter; a step (11) of selecting the turboshaft engine for which a change in speed would be more relevant; a step (12) of determining an operating speed of said turboshaft engine, referred to as chosen speed, selected among a plurality of predetermined operating speeds; and a step (14) of controlling the operating speed of said turboshaft engine to said chosen speed. The invention also relates to a corresponding control device.