Movable Nozzle for Aircraft Turbomachine Thrust Distribution
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Solution Overview
Problem
Conventional turbomachines with propellers for aircraft face inefficiencies in thrust distribution across different flight phases, as the nozzle cross section is fixed, leading to suboptimal noise reduction and fuel efficiency during takeoff and cruise phases.
Innovation Solution
A turbomachine design featuring a moveable nozzle with adjustable annular cross section, allowing the thrust distribution between propellers and the nozzle to be dynamically altered based on flight phases, using actuators or shape-memory materials to change the nozzle's position and cross section.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If the nozzle cross section is fixed, then the device complexity is reduced, but the adaptability to different flight phases deteriorates
Solution Approach 1:
The nozzle cross section is made variable through a movable nozzle assembly that can adjust its position along the turbine exhaust cone. This dynamic adjustment allows the thrust distribution between propellers and nozzle to be optimized for different flight phases (takeoff, climb, cruise, descent), resolving the contradiction between adaptability and device complexity by introducing a controlled degree of mobility rather than a fully fixed structure.
2Productivity
If the propeller thrust contribution is increased, then the propulsive efficiency in cruise phase is improved, but the noise impact during takeoff increases
Solution Approach 1:
The invention changes the operational parameters of the thrust distribution system by varying the nozzle cross section area through movable nozzle positioning. During takeoff, the nozzle cross section is reduced to increase jet thrust contribution and decrease propeller load, thereby reducing noise. During cruise, the nozzle cross section is increased to allow propellers to operate at optimal efficiency. This parameter adjustment resolves the contradiction between propulsive efficiency and noise impact.
3Power
If the nozzle cross section is reduced, then the thrust contribution from combustion gases increases, but the thrust contribution from propellers decreases
Solution Approach 1:
The system dynamically balances the thrust contribution between nozzle and propellers by adjusting the movable nozzle position. When the nozzle cross section is reduced, combustion gas expansion and jet thrust increase, while propeller thrust decreases accordingly. This dynamic redistribution allows optimization of total thrust for different flight conditions, resolving the contradiction between maximizing jet thrust and maintaining propeller thrust by making the nozzle geometry adaptable rather than fixed.
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
This design optimizes thrust distribution, reducing noise and fuel burn by increasing nozzle thrust during takeoff and maximizing propeller thrust during cruise, thereby enhancing overall thermopropulsive efficiency and reducing propeller stress.
Implementation Method 1
produce their overall thrust through the combination of the traction produced by the propellers and the thrust delivered by the nozzle of the gas generator or turbine, making use of the expansion of the combustion gases
Implementation Method 2
comprising at least one turbine designed for driving the propeller in rotation
Data Source
AI summary
A turbomachine for an aircraft including at least one turbine driving rotation of a fan, and a jet nozzle coaxially extending a turbine and creating, with an outlet cone that terminates the turbine, a passage of annular cross section for combustion gases that pass through the turbine. The jet nozzle can be mounted so that it can move between two extreme positions for which under action of a controller, an annular cross section of the passage for the gases is respectively at its minimum or maximum, making it possible to vary the cross section according to phases of operation of the aircraft and distribute thrust between the fan and the jet nozzle.