Open Rotor Fixed Stator Geometry for Lower-Complexity Thrust Recovery
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing aircraft propulsion systems with variable geometry guide vanes/stators increase complexity and weight, outweighing the benefits of thrust recovery, and require costly actuation systems for flight adjustments.
Innovation Solution
Implementing a fixed guide vane structure with manual adjustment capabilities by ground personnel, allowing for geometry changes before and after flights, combined with variable rotor blades to optimize performance for different flight missions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If variable geometry/pitch stators are incorporated downstream of the rotor to convert swirl to thrust, then efficiency and performance are increased, but complexity and weight increase due to variable geometry mechanisms and actuation systems
Solution Approach 1:
The patent applies dynamics by enabling the guide vanes to change geometry from a fixed state during flight to an adjustable state on the ground. The variable geometry mechanism allows the stators to adapt their pitch angle between different flight missions, optimizing thrust efficiency for each mission type while maintaining structural simplicity during actual flight operations.
Solution Approach 2:
The patent implements parameter changes by modifying the pitch angle parameter of the guide vanes between different flight missions. By adjusting this geometric parameter on the ground before flights, the system optimizes performance for different mission profiles without requiring complex real-time actuation systems during flight, thus resolving the contradiction between efficiency and complexity.
2Productivity
If variable geometry/pitch stators are incorporated downstream of the rotor to convert swirl to thrust, then efficiency and performance are increased, but weight increases due to actuation systems
Solution Approach 1:
The patent applies preliminary action by pre-adjusting the guide vane geometry on the ground before each flight mission. This advance adjustment eliminates the need for heavy in-flight actuation systems, as all geometry changes are performed beforehand. The system achieves optimal thrust efficiency for each mission type while keeping the aircraft weight low during flight operations.
Solution Approach 2:
The patent extracts the geometry adjustment function from the in-flight operational phase and relocates it to the ground preparation phase. By removing the actuation system from the moving aircraft and performing adjustments only on the ground, the patent significantly reduces the weight penalty associated with variable geometry mechanisms while maintaining thrust efficiency benefits.
3Productivity
If variable geometry/pitch stators are incorporated downstream of the rotor to convert swirl to thrust, then efficiency and performance are increased, but costly actuation systems are required for in-flight adjustments
Solution Approach 1:
The patent applies preliminary action by performing all guide vane geometry adjustments on the ground before flights. This eliminates the need for expensive in-flight actuation systems and their associated control mechanisms, significantly reducing manufacturing costs while maintaining the ability to optimize thrust efficiency for different mission profiles through pre-flight configuration changes.
4Device complexity
If fixed guide vane structure with manual adjustment is used, then system complexity and weight are reduced, but in-flight adjustment capability is lost
Solution Approach 1:
The patent resolves this contradiction by performing all necessary geometry adjustments as preliminary actions on the ground before each flight mission. The fixed guide vane structure during flight maintains simplicity and reduces weight, while the manual ground adjustment capability provides the necessary adaptability for different mission profiles. This temporal separation of adjustment and operation phases satisfies both requirements.
Data Source
AI summary
An assembly for an aircraft propulsion system includes an open propulsor rotor having variable geometry propulsor blades and an open guide vane/stator assembly having a plurality of guide vanes (stator blades) in a fixed position relative to the rotor and assembly. The geometry (e.g., pitch, camber, etc.) of the guide vanes can be manually adjusted by ground personnel but are incapable of adjustment during a flight mission (a flight). The open propulsor rotor is configured to rotate about an axis, and the guide vane assembly includes the plurality of guide vanes arranged circumferentially about the axis and is disposed axially next to and downstream of the propulsor rotor.