Coaxial Compressor Offset Turbine Compact Engine Assembly
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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 aircraft applications.
Innovation Solution
A compound engine assembly comprising a liquid-cooled multi-rotor rotary engine core with a turbine section as an exhaust energy recovery system, utilizing a Wankel engine with a compressor and turbine configuration optimized for compactness and efficiency, along with a modular turbine section to facilitate installation within aircraft nacelles.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If a compound engine assembly with supercharger or turbocharger is used, then power and efficiency are improved, but the assembly becomes bulky and difficult to fit into existing aircraft nacelles
Solution Approach 1:
The compressor is positioned coaxially within the turbine housing, with the compressor inlet at the front and compressor outlet at the rear. The turbine wheel is arranged concentrically around the compressor, allowing the compressor to be nested within the turbine assembly. This nested configuration significantly reduces the overall volume of the compound engine assembly while maintaining both compression and expansion functions.
Solution Approach 2:
The invention transitions from a conventional side-by-side or inline arrangement of compressor and turbine to a three-dimensional concentric configuration. The compressor is placed along the axial dimension within the radial space of the turbine housing, effectively utilizing vertical and radial dimensions to minimize the horizontal footprint and overall assembly volume.
2Power
If a compound engine assembly with supercharger or turbocharger is used, then power and efficiency are improved, but the assembly becomes difficult to integrate into existing aircraft nacelles
Solution Approach 1:
The nested concentric arrangement of compressor within turbine housing creates a compact, integrated unit with reduced external dimensions. This configuration allows the compound engine assembly to be adapted to existing aircraft nacelles that would otherwise be too small to accommodate separate compressor and turbine installations.
Solution Approach 2:
The compound engine assembly is designed as a modular integrated unit with distinct functional sections (compressor section, turbine section, common housing) that can be manufactured separately and assembled. This segmentation facilitates integration into existing aircraft nacelles by allowing the entire compact assembly to be installed as a unified component package.
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 configuration allows for a compact and efficient engine assembly that can drive propellers or other loads, enhancing aircraft propulsion while accommodating the spatial constraints of nacelles, thereby improving adaptability and performance.
Implementation Method 1
a turbine section (18) used as an exhaust energy recovery system
Implementation Method 2
a compressor (14), the inlet of which is configured to be in fluid communication with the outlet of the turbine section
Implementation Method 3
a liquid cooled heavy fueled multi-rotor rotary engine core (12)
Data Source
Figure 1
Figure 2
Figure 3
AI summary
A compound engine assembly having an engine core 12 including at least one internal combustion engine in driving engagement with an engine shaft 16, a compressor 14having an outlet in fluid communication with an inlet of the engine core and including at least one rotor rotatable about an axis coaxial with the engine shaft, the engine shaft in driving engagement with the compressor rotor, and a turbine section 18 having an inlet in fluid communication with an outlet of the engine core and including at least one rotor engaged on a rotatable turbine shaft, the turbine shaft configured to compound power with the engine shaft. The turbine and engine shafts are parallel to and radially offset from one another, and the turbine shaft and the axis of the compressor rotor are parallel to and radially offset from one another. A method of driving a rotatable load of an aircraft is also discussed.