Turboshaft Engine Plenum Heating Using Hot-Air Heat Exchange
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Solution Overview
Problem
Existing aircraft turboshaft engines face issues with ice and snow accumulation in the plenum, which can lead to damage or extinguish the combustion chamber, particularly in icing conditions, and current de-icing systems are complex and energy-intensive.
Innovation Solution
A heating system is integrated into the plenum using a heat exchanger supplied with hot air from the turboshaft engine, which heats the plenum to melt ice and snow, minimizing ingestion into the engine.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If electric heating strips are used to combat ice and snow formation, then ice and snow accumulation is reduced, but device complexity and electrical energy consumption increase
Solution Approach 1:
The system uses the engine's own hot exhaust gases to heat the plenum through a heat exchanger, making the system self-sufficient and eliminating the need for external electric heating power sources. The harmful cold environment is counteracted by the system's own thermal resources.
Solution Approach 2:
A heat exchanger is introduced as an intermediary component that transfers thermal energy from the hot exhaust gases to the plenum air. This mediator enables indirect heating, avoiding direct contact between exhaust gases and the plenum while achieving effective thermal transfer to prevent ice and snow accumulation.
2Object-affected harmful factors
If electric heating strips are used to combat ice and snow formation, then ice and snow accumulation is reduced, but electrical energy consumption increases
Solution Approach 1:
The system uses the engine's own hot exhaust gases to heat the plenum through a heat exchanger, making the system self-sufficient and eliminating the need for external electric heating power sources. The harmful cold environment is counteracted by the system's own thermal resources.
Solution Approach 2:
The hot exhaust gases, which would otherwise be wasted thermal energy, are redirected to heat the plenum and prevent ice and snow formation. The system converts the potentially harmful hot exhaust into a beneficial heating resource, eliminating the need for additional energy input.
3Object-affected harmful factors
If a heating system is integrated into the plenum, then ice and snow accumulation is reduced, but device complexity increases
Solution Approach 1:
The heat exchanger serves multiple functions: it heats the plenum to prevent ice and snow accumulation, and simultaneously manages the thermal energy from exhaust gases. This multi-functionality reduces the need for separate dedicated heating components, thereby limiting the increase in system complexity.
Solution Approach 2:
A heat exchanger is introduced as an intermediary component that transfers thermal energy from the hot exhaust gases to the plenum air. This mediator enables indirect heating, avoiding direct contact between exhaust gases and the plenum while achieving effective thermal transfer to prevent ice and snow accumulation.
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
The system effectively reduces ice and snow accumulation with minimal impact on engine operation, being simple and energy-efficient, while maintaining flight safety and performance.
Implementation Method 1
a heating system (50) for heating the plenum (40), the heating system (50) comprising a heat exchanger (60) arranged in a volume delimited by the plenum (40)
Implementation Method 2
the heating system comprising a fluid supply connection (70) and a fluid discharge connection (80) connected to the heat exchanger (60), the fluid supply connection (70) conveying hot air from the turboshaft engine into the heat exchanger (60)
Data Source
AI summary
An aircraft provided with a turboshaft engine comprising a gas generator, the gas generator comprising a compression assembly supplying air to a combustion chamber and a turbine assembly supplied with gas by the combustion chamber, the aircraft having a plenum supplying air to the compression assembly. The aircraft comprises a heating system, the heating system comprising a heat exchanger arranged in the plenum, the heating system comprising a fluid supply connection and a fluid discharge connection connected to the heat exchanger, the fluid supply connection conveying hot air from the turboshaft engine into the heat exchanger.