Compound Engine Inlet Lip Anti-icing via Exhaust Conduit Routing
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Solution Overview
Problem
Compound engine assemblies, particularly supercharged or turbocharged ones, are bulky and difficult to integrate into existing aircraft nacelles, posing challenges for adaptation in aircraft applications.
Innovation Solution
A compound engine assembly design featuring an inlet duct with a conduit, a compressor, an engine core with internal combustion engines, a turbine section, and exhaust ducts that allow for efficient air flow and energy recovery, enabling a compact and modular configuration that can be easily maintained and adapted for aircraft use.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If a compound engine assembly with supercharger or turbocharger is used, then power output is improved, but the assembly becomes bulky and difficult to fit into existing aircraft nacelles
Solution Approach 1:
The patent merges the supercharger and turbocharger into a single integrated compound engine assembly, combining their functions in one compact unit. The supercharger is driven by the engine crankshaft while the turbocharger is driven by exhaust gases, and both are integrated within the same assembly structure, allowing space-efficient installation in aircraft nacelles while maintaining high power output
Solution Approach 2:
The compound engine assembly performs multiple functions simultaneously: the supercharger provides forced induction for improved power output, the turbocharger recovers exhaust energy to drive the compressor, and the integrated design serves as both a power-generating system and a space-efficient package for aircraft applications
2Adaptability or versatility
If a compact engine assembly design is used, then adaptability to aircraft nacelles is improved, but the complexity of integrating multiple components (compressor, engine core, turbine section) increases
Solution Approach 1:
The compound engine assembly is segmented into distinct functional modules: an inlet duct with inlet lip, a compressor section, an engine core with internal combustion engines, a turbine section, and an exhaust duct. Each module is designed as a separate component that can be manufactured and tested independently, then assembled into the compact configuration, reducing overall integration complexity while maintaining adaptability
Solution Approach 2:
The patent employs a nested arrangement where the compressor is positioned within the inlet duct, the engine core is surrounded by the turbine section, and exhaust conduits are routed through the assembly structure. This nesting of components within each other's spatial envelopes achieves compactness without proportionally increasing integration complexity
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 design allows for a compact and efficient engine assembly that can be easily integrated into aircraft nacelles, improving adaptability and reducing the number of parts while maintaining optimal performance conditions, thus addressing the bulkiness issue of traditional compound engines.
Implementation Method 1
circulating part of an exhaust of the turbine section around the inlet lip
Implementation Method 2
directing the air from the inlet duct to an inlet of a compressor; directing compressed air from an outlet of a compressor
Implementation Method 3
driving rotation of a turbine shaft of a turbine section of the compound engine assembly by circulating an exhaust of the at least one internal combustion engine to an inlet of the turbine section
Data Source
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AI summary
A compound engine assembly with an inlet duct having an inlet surrounded by an inlet lip including at least one conduit extending therethrough, a compressor, an engine core including at least one internal combustion engine, a turbine section having a turbine shaft in driving engagement with the engine shaft, and an exhaust conduit providing a fluid communication between the outlet of the turbine section and the conduit(s) of the inlet lip. An exhaust duct and an exhaust conduit providing a fluid communication between the outlet of the turbine section and the exhaust duct may also be provided. The internal combustion engine(s) may be rotary engine(s). A method of driving a rotatable load of an aircraft is also discussed.