Hydrogen Combustion Steam De-Icing for Aircraft Engine Surfaces
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Solution Overview
Problem
Ice formation on aircraft surfaces, particularly on propellers, inlet guide vanes, and engine components, leads to weight increase, airflow disruption, and potential damage to engine blades, posing flight safety risks.
Innovation Solution
An ice protection system utilizing hydrogen fuel combustion byproducts, specifically water vapor (steam), to prevent and remove ice buildup on aircraft surfaces, particularly inlet guide vanes and engine nacelles, by leveraging steam for de-icing and anti-icing purposes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional de-icing systems are used, then ice removal is achieved, but system complexity and weight increase
Solution Approach 1:
The patent converts the harmful effect of cold hydrogen fuel (which can cause ice formation) into a beneficial de-icing mechanism. The cold fuel is routed through heat exchangers that transfer coldness to ice-affected surfaces, melting ice without requiring separate heating systems. This eliminates the need for complex pneumatic or electrical de-icing systems while utilizing the fuel's inherent cold properties.
Solution Approach 2:
The hydrogen fuel serves multiple functions: it acts as both the propulsion fuel and the de-icing agent. The same fuel that powers the engine also provides the cold thermal energy needed for ice removal through the heat exchanger network. This multi-functionality reduces system complexity by eliminating dedicated de-icing equipment.
2Object-generated harmful factors
If hydrogen fuel is used, then carbon dioxide emissions are reduced, but ice formation risks increase
Solution Approach 1:
The patent transforms the potential harm of cold hydrogen fuel causing ice formation into a beneficial de-icing mechanism. The cold fuel is deliberately routed through heat exchangers to extract heat from ice-affected surfaces, using the fuel's cold temperature as a resource rather than a problem. This converts the harmful cold effect into a useful thermal energy transfer for ice removal.
Solution Approach 2:
The patent introduces heat exchangers as intermediary components between the cold hydrogen fuel and the ice-affected surfaces. These heat exchangers mediate the thermal energy transfer, allowing the cold fuel to indirectly cool and melt ice on surfaces without the fuel directly contacting the surfaces. This intermediary approach enables controlled heat transfer while preventing unwanted side effects.
3Reliability
If steam from combustion is used for de-icing, then ice removal is effective, but energy loss from combustion increases
Solution Approach 1:
The patent performs de-icing action before combustion occurs by using the cold hydrogen fuel directly in heat exchangers upstream of the combustion chamber. This preliminary de-icing prevents ice formation on critical surfaces before the fuel is combusted, eliminating the need to use combustion products (steam) for de-icing. The cold fuel's thermal energy is utilized before the chemical energy is released through combustion.
Solution Approach 2:
The patent maintains continuous useful action by using the cold fuel's thermal energy for de-icing throughout the fuel delivery process. The cold fuel continuously absorbs heat from ice-affected surfaces as it flows through the heat exchangers, providing ongoing protection without interrupting the fuel supply or combustion process. This continuous thermal energy transfer eliminates the need for periodic steam injection that would interrupt combustion.
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 prevents and removes ice accumulation, maintaining airflow stability and reducing the risk of engine damage, while also reducing carbon dioxide emissions through the use of hydrogen fuel.
Implementation Method 1
The conduit is thermally coupled to the external surface to heat the external surface as the combustion gases flow through the conduit
Implementation Method 2
The combustor is located in the core air passage and is fluidly coupled to a hydrogen fuel source to receive the hydrogen fuel and to combust the hydrogen fuel producing combustion gases including water vapor
Data Source
AI summary
A gas turbine engine including a core air passage, a combustor, and a steam line. The combustor is located in the core air passage and combusts hydrogen fuel producing combustion gases. The steam line is fluidly coupled to the core air passage at a position downstream of the combustor to receive a portion of the combustion gases. A conduit thermally coupled to an external surface of an aircraft may be fluidly coupled to the steam line to receive the combustion gases and to heat the external surface. The gas turbine engine may also include a water vapor condenser fluidly connected to the steam line to receive the combustion gases and to condense the water vapor of the combustion gases. At least one nozzle may be fluidly coupled to the water vapor condenser to inject the condensed water into the core air passage.