Turbine Engine Aerodynamic Sensor With Segmented Flexible Fairing
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Solution Overview
Problem
Measuring devices in turbine engine flow passages face aerodynamic losses and vibratory stresses, leading to disruption and potential mechanical failure due to resonance with the engine's vibration frequencies, which can result in debris damaging downstream components.
Innovation Solution
A device with a downstream fairing split into independently fixed sections connected by a flexible junction, which reduces vibratory response and resonance frequencies by introducing stiffness disruption, and is positioned to avoid coinciding with engine vibration frequencies, using materials with varying Young's moduli and pin placement to optimize resonance frequencies.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If the measuring device is placed in the flow passage to measure aerodynamic magnitudes, then measurement capability is provided, but aerodynamic losses occur and flow disruption ensues
Solution Approach 1:
The measuring device is divided into multiple sections (first section, second section, third section) connected by flexible junctions. This segmentation allows each section to be optimized for specific functions while reducing overall aerodynamic interference with the flow passage.
Solution Approach 2:
Flexible junctions connect the rigid sections of the measuring device, allowing these thin flexible elements to accommodate flow disturbances while maintaining structural integrity, thereby reducing aerodynamic losses and flow disruption.
2Strength
If the measuring device structure is made rigid to ensure mechanical strength, then structural integrity is improved, but resonance risk increases under vibratory stresses
Solution Approach 1:
Dividing the measuring device into multiple rigid sections connected by flexible elements reduces the overall structural rigidity, thereby lowering the natural frequencies and avoiding resonance with engine vibratory stresses while maintaining local structural integrity where needed.
Solution Approach 2:
The flexible junctions change the stiffness parameters of the overall structure, reducing the natural frequencies of the measuring device to avoid coincidence with engine vibration frequencies, thus preventing resonance while maintaining mechanical strength in critical areas.
3Device complexity
If the downstream fairing is made as a single piece to simplify structure, then device complexity is reduced, but vibratory response and resonance risk increase
Solution Approach 1:
The downstream fairing is segmented into multiple sections connected by flexible junctions, which simplifies manufacturing and assembly while simultaneously reducing vibratory response and resonance risk through the flexible connections.
Solution Approach 2:
The flexible junctions introduce dynamic flexibility to the downstream fairing structure, allowing it to adapt to vibratory stresses and reduce resonance responses while maintaining the overall structural form.
4Reliability
If the measuring device is positioned to avoid resonance frequencies, then reliability is improved, but positioning flexibility and adaptability are reduced
Solution Approach 1:
By modifying the structural parameters (adding flexible junctions and sections), the natural frequencies of the measuring device are changed to avoid resonance with engine vibrations, while the modular design maintains positioning flexibility.
Solution Approach 2:
The segmented design with flexible junctions allows the measuring device to be positioned in various locations while maintaining reliability, as each section can independently accommodate positioning variations without compromising overall structural integrity or resonance avoidance.
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 device enhances mechanical strength and reduces the risk of resonance-induced failure by minimizing vibratory response and adjusting resonance frequencies to match the engine's operational conditions, thereby preventing damage to turbine engine components.
Implementation Method 1
The measuring device 1 undergoes strong vibratory stresses. A first vibratory source is for example consecutive of the residual imbalance of assemblies in rotation
Implementation Method 2
When the vibration frequency of the device 1 is close to its resonance frequency of rank 1 or its specific harmonic frequencies for example that of rank 2, the risk of resonance of the device becomes high
Implementation Method 3
two successive sections being connected by a junction which in the longitudinal direction of the upstream body is more flexible than the sections
Data Source
AI summary
The present invention relates to a device for measuring aerodynamic magnitudes (1) intended to be placed transversally in a flow passage (12, 13) of a turbine engine comprising:an upstream body (2) having a profile of general cylindrical shape defining a leading edge (5)a plurality of sensors (4), the instrumentation lines (45) of the sensors being placed in the body (2), the sensitive elements (41) of the sensors extending at the leading edge (5);a downstream fairing (3) mounted on the upstream body (2) and defining a trailing edge (6);the downstream fairing (3) comprising, in the longitudinal direction of the upstream body (2), several sections (35) fixed independently of each other to the body (2), two successive sections (35) being connected by a flexible junction (37).