Aircraft Propulsion Engine With Offset Rotors for Modular Repair
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Solution Overview
Problem
Existing aircraft propulsion systems lack efficiency and modularity, with rotating structures often nested and requiring complex interdependencies that hinder scalability and maintenance.
Innovation Solution
Aircraft propulsion systems with independently rotating structures, including a propulsor rotor, engine core, and flowpath, where rotating structures such as the LPC and HPC are laterally and angularly offset from the propulsor axis, allowing for modular construction and improved efficiency through independent operation and reduced size.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If rotating structures are nested within each other in conventional propulsion systems, then the system can be compact, but the device complexity increases and maintenance becomes difficult
Solution Approach 1:
The propulsion system divides the rotating structures into separate, independent modules (propulsor rotor assembly and engine core assembly) rather than nesting them. Each assembly has its own rotating components that operate independently, reducing structural complexity while maintaining compact overall system volume through side-by-side arrangement rather than nested configuration.
2Volume of moving object
If rotating structures are nested within each other, then the system occupies less space, but ease of repair deteriorates due to inaccessibility of components
Solution Approach 1:
The system segments rotating components into separate accessible modules. The propulsor rotor assembly and engine core assembly are positioned adjacent to each other rather than nested, allowing each module to be independently accessed for inspection, maintenance, and repair while maintaining a compact overall system footprint.
3Productivity
If rotating structures operate independently with offset axes, then productivity and efficiency improve through modular operation, but device complexity increases
Solution Approach 1:
The propulsion system segments the rotating structures into independent modules with offset axes (propulsor rotor on one axis, engine core rotors on another axis). This segmentation enables modular operation where each assembly can be optimized independently for efficiency while the overall mechanical complexity is managed through standardized coupling mechanisms.
Solution Approach 2:
The system transitions from a single-axis nested configuration to a multi-axis arrangement where the propulsor rotor and engine core rotors operate on offset axes. This dimensional change allows independent rotation of each module, improving productivity and efficiency through specialized optimization of each rotating assembly while maintaining manageable complexity through modular design.
4Ease of manufacture
If rotating structures are separated into independent modules, then ease of manufacture improves through modular construction, but the volume of the system increases
Solution Approach 1:
The system segments rotating components into independent manufacturable modules that can be produced separately and assembled. The propulsor rotor assembly and engine core assembly are designed as separate modules with standardized interfaces, improving ease of manufacture through modular construction while minimizing system volume through efficient spatial arrangement of the modules adjacent to each other rather than nested.
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
Enhances turbine engine efficiency and rotor-dynamic stability, facilitating easier maintenance and scalability by separating rotating structures, promoting a more efficient and modular design.
Implementation Method 1
The turbine rotor is coupled to and is configured to drive rotation of the second compressor rotor
Implementation Method 2
The power turbine rotor is coupled to and is configured to drive rotation of the propulsor rotor
Implementation Method 3
The electric machine is coupled to and is configured to drive rotation of the first compressor rotor
Implementation Method 4
a core combustor section
Data Source
AI summary
A turbine engine is provided that includes a propulsor rotor and an engine core. The propulsor rotor is rotatable about a propulsor axis. The engine core is configured to power operation of the propulsor rotor. The engine core includes a core compressor section, a core combustor section, a core turbine section, a first rotating structure and a second rotating structure. The first rotating structure includes a first compressor rotor arranged within the core compressor section. The first rotating structure is rotatable about a first structure axis which is offset from the propulsor rotor axis. The second rotating structure includes a second compressor rotor arranged within the core compressor section. The second rotating structure is rotatable about a second structure axis which is offset from the propulsor rotor axis and the first structure axis.