Aircraft Turbine Stator Ring Recesses for Vibration Attenuation
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Aircraft turbomachine rectifiers experience high vibration levels due to complex mechanical environments, leading to significant mechanical loads and potential cracking, which existing designs fail to adequately address without impacting aerodynamic or integration specifications.
Innovation Solution
The rectifier features coaxial annular shells connected by blades with recesses at the ends, making the ferrules more flexible and reducing vibration propagation through localized softening, while maintaining airflow channel design and interface integrity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If the rectifier uses rigid inner and outer shells to maintain structural integrity, then strength is improved, but vibration propagation increases
Solution Approach 1:
The patent introduces recesses at specific locations on the inner and outer shells to create localized flexibility where needed, while maintaining overall structural integrity. This allows different parts of the shell to have different mechanical properties - rigid in most areas for strength, and flexible at recess locations for vibration attenuation.
Solution Approach 2:
The patent modifies the shell structure by creating recesses that change the local thickness parameter, thereby altering the mechanical properties from completely rigid to having controlled flexible zones. This parameter change enables the shell to attenuate vibrations while maintaining sufficient strength.
2Object-generated harmful factors
If the rectifier shells are made thicker to reduce vibration, then vibration attenuation is improved, but mass increases
Solution Approach 1:
Instead of uniformly thickening the entire shell, the patent introduces recesses that create localized flexibility only where needed for vibration attenuation. This avoids the mass penalty of global thickening while achieving the desired vibration reduction at critical locations.
Solution Approach 2:
The patent employs the concept of flexible zones within the shell structure through recesses, allowing the shell to have controlled flexibility for vibration attenuation without requiring overall increased thickness, thus avoiding mass increase.
3Reliability
If the rectifier design is modified to reduce vibrations, then vibration resistance is improved, but aerodynamic or integration specifications may be impacted
Solution Approach 1:
The recesses are strategically positioned at specific locations on the shells to provide vibration attenuation while minimizing impact on the overall aerodynamic shape and flow characteristics. This localized modification approach preserves aerodynamic performance while improving vibration resistance.
Solution Approach 2:
The patent segments the shell structure by introducing discrete recesses rather than modifying the entire shell geometry. This segmentation allows vibration control to be achieved through localized features that do not interfere with the overall aerodynamic design and integration requirements.
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 reduces static stresses and attenuates vibration propagation, minimizing mechanical loads and mass, without altering aerodynamic or integration specifications, thus enhancing structural integrity and reducing rectifier mass.
Implementation Method 1
The recesses located at the ends of the blades at the level of the inner and outer ferrules thus make it possible to dampen the vibratory and static responses by local softening of the inner and outer ferrules
Implementation Method 2
reduction of static stresses; attenuation of vibration propagation within the rectifier
Data Source
Figure 1~2
Figure 3
Figure 4
AI summary
The invention relates to a stator ring (10) for an aircraft turbine engine, said stator ring (10) comprising two coaxial annular shrouds (20, 30), an inner shroud (20) and an outer shroud (30) respectively, which are connected to each other by vanes (11) that are each fully integral with the shrouds (20, 30), the outer shroud (30) comprising an outer annular surface (31) connected to at least one catch (32) for attaching the stator ring (10), and the inner shroud (20) comprising an inner annular surface (21) connected to a support member (22) with an abradable coating, characterised in that at least one of the inner (21) and outer (31) surfaces comprises recesses (42", 43") that are situated in line with the vanes (11) and are configured such that the vanes (11) are connected to the corresponding shroud (20, 30). The invention also relates to an aircraft turbine engine comprising at least one stator ring (10) as described above.