Compound Engine Mount Cage Thermal Isolation
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Solution Overview
Problem
Compound engine assemblies, particularly supercharged or turbocharged engines, are bulky and difficult to integrate into existing aircraft nacelles, posing challenges for adaptation in aircraft applications.
Innovation Solution
A modular compound engine assembly design featuring a single shaft configuration with a liquid-cooled multi-rotor rotary engine core, a gearbox module, a compressor module, and a turbine module, allowing for independent maintenance and optimization of each module's performance, and a compact layout to minimize space requirements.
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 combines the supercharger/compressor and turbocharger/turbine into a single integrated assembly sharing common casings, mounts, and support structures. The compressor and turbine are positioned adjacent to each other with shared structural elements, reducing the overall volume required compared to separate installations while maintaining both power output functions.
Solution Approach 2:
The patent employs nested arrangement where the turbine is positioned within or adjacent to the compressor housing, and components are arranged in concentric or overlapping configurations. This nesting allows the turbocharger to utilize space already occupied by the supercharger structure, minimizing the total volume increase while achieving compound power output.
2Power
If a compound engine assembly with supercharger or turbocharger is used, then power output is improved, but the assembly becomes difficult to integrate into existing aircraft nacelles
Solution Approach 1:
The patent divides the compound engine assembly into modular segments including separate compressor module, turbine module, and accessory modules that can be independently installed or removed. This segmentation allows the assembly to be adapted to different aircraft nacelle configurations and facilitates integration into existing aircraft without requiring complete nacelle redesign.
Solution Approach 2:
The patent designs the compound engine assembly with universal mounting features and standardized interfaces that can accommodate various installation configurations. The shared casings and mounts serve multiple functions including structural support, vibration isolation, and thermal management, enabling the same assembly design to be adapted across different aircraft types and applications.
3Strength
If traditional engine assembly design is used, then structural integrity is maintained, but the number of parts is high and maintenance is difficult
Solution Approach 1:
The patent merges multiple separate components into integrated assemblies including combined compressor-turbine casings, shared mounting structures, and common support frameworks. This consolidation reduces the total number of discrete parts while maintaining structural integrity through robust integrated designs that distribute loads across multiple functions.
Solution Approach 2:
The patent incorporates preliminary structural reinforcement and pre-assembled modular units that maintain structural integrity from the outset. Critical load-bearing elements are designed and pre-positioned to ensure strength requirements are met before final assembly, reducing the need for additional structural parts during installation.
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 modular design reduces the number of parts, enables efficient energy recovery, and facilitates easier maintenance while optimizing performance, making it more suitable for aircraft applications by minimizing space and improving fire safety and structural integrity.
Implementation Method 1
a liquid-cooled multi-rotor rotary engine core
Data Source
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AI summary
A compound engine assembly 10 with an engine core 12 including at least one internal combustion engine 12', a turbine section 18, and a compressor 14 having an outlet in fluid communication with an inlet of the engine core 12. A casing 21 is connected to the turbine section 18, compressor 14 and engine core 12. A mount cage 104 is connected to mounts 105 attached to the casing 21 between the compressor 14 and a hot zone including the turbine section 18 and exhaust pipe(s) 30. The mount cage 104 may include a plurality of struts 106 all extending from the mounts away from the turbine section and engine core. The struts are separated from the hot zone by at least one firewall. The casing 21 may be a gearbox module casing 21 through which a turbine shaft 19 is engaged with an engine shaft 16. The mount cage 104 may be completely contained within an axial space with the turbine section 18 and exhaust pipe(s) 30 being located outside of the axial space.