Turbo Engine Fluid Duct System for Stationary Thermal Management
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Solution Overview
Problem
Turbo engines, especially aircraft engines, face challenges in thermal management and ventilation when stationary, leading to potential overheating and fire hazards due to the accumulation of flammable vapors, as existing solutions rely on relative motion with the surrounding fluid.
Innovation Solution
A fluid duct system within the turbofan engine that creates a pressure gradient between the bypass duct and the freestream zone, utilizing air flow to suck in surrounding air and eject it into the compartment, providing thermal management and ventilation independent of engine motion, with adjustable configurations for cooling or heating.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If NACA inlets and outlets are used for thermal management, then thermal management is achieved during flight, but thermal management fails when the engine is stationary
Solution Approach 1:
The patent employs a dynamic thermal management system that adapts its operation mode based on engine state. During flight, NACA inlets provide passive cooling. When the engine is stationary, the system automatically activates active ventilation using fans or blowers to maintain thermal management effectiveness across both operational states.
Solution Approach 2:
The patent introduces intermediary active ventilation devices (fans, blowers) that mediate between the NACA inlet system and the compartment environment. These intermediaries enable thermal management to function during stationary operation by actively forcing air flow through the compartment, compensating for the lack of natural airflow when the engine is not moving.
2Device complexity
If no active ventilation is used in motionless state, then device complexity is reduced, but temperature sensitive components overheat and flammable vapors accumulate
Solution Approach 1:
The patent implements a self-service thermal management system where the engine's own operational states (intake air flow, exhaust gas flow) are utilized to drive ventilation. During operation, the engine's airflow automatically ventilates the compartment. When stationary, simple active devices activate only when needed, making the system self-regulating and minimizing complexity while ensuring reliability.
Solution Approach 2:
The patent changes the operational parameters of the ventilation system based on engine state. During flight, high-velocity natural airflow provides cooling. When stationary, the system transitions to low-velocity active ventilation using fans or blowers, adjusting the flow parameters to match the reduced ambient airflow conditions and maintain effective thermal management.
3Temperature
If active ventilation is added to handle stationary operation, then thermal management in motionless state is improved, but fuel consumption increases and engine cycle is disturbed
Solution Approach 1:
The patent employs periodic or conditional activation of active ventilation devices rather than continuous operation. The system monitors engine state and activates fans or blowers only when the engine is stationary and thermal management is needed, minimizing energy consumption while maintaining effectiveness during critical periods.
Solution Approach 2:
The patent ensures continuous thermal management effectiveness by seamlessly transitioning between passive NACA inlet cooling during flight and active ventilation during stationary operation. This continuous action eliminates gaps in cooling protection without requiring both systems to operate simultaneously, thereby reducing overall energy consumption.
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
Effectively cools temperature-sensitive components and evacuates flammable vapors, preventing overheating and fire risks, while maintaining engine operation without increasing fuel consumption or disturbing the engine cycle, even when the engine is stationary.
Implementation Method 1
the second spatial area lying in a freestream zone of the turbofan engine and having a lower pressure than the first spatial area during operation of the turbo engine. Due to the pressure difference a pressure gradient is present in the fluid duct device and a flow of fluid from the first spatial area towards the second spatial area is generated
Implementation Method 2
resulting in a pressure gradient in the compartment and in a suction in order to suck a fluid surrounding the at least one opening into the fluid duct device through the at least one opening thereby generating a flow of fluid in the compartment for thermal management and or ventilation of the compartment
Data Source
Figure 1
Figure 2A~2B
Figure 3
AI summary
The invention relates to a fluid duct system for thermal management and/or ventilation in a compartment containing at least one temperature sensitive target within a turbo engine, said turbo engine comprising a first spatial area within the turbo engine through which a fluid flows during operation of the turbo engine, characterized by a fluid duct device (3) connecting the first spatial area (1) with a second spatial area (2) having a lower pressure than the first spatial area (1) during operation of the turbo engine (7), so that a pressure gradient is present in the fluid duct device (3) and a flow of fluid from the first spatial area (1) towards the second spatial area (2) is generated resulting in a pressure gradient in the compartment (11) and therefore in a flow of fluid for thermal management and/or ventilation of the compartment (11).