Aircraft Turbine Vane with Nested Cores for Shock Resistance
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Conventional receiver vanes in aircraft turbine engines lack sufficient shock resistance, particularly against projectile impacts, which can compromise their structural integrity and safety during flight or ground operations.
Innovation Solution
The vane design incorporates a secondary structural assembly enveloped by a principal hollow structural core, with shock-absorbing materials between the core's longerons and the secondary assembly, allowing energy absorption and maintaining structural function even if the primary core is damaged, enhancing shock resistance without increasing overall mass.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If a single hollow structural core is used in the blade part, then the vane achieves acceptable rigidity, but its shock resistance is insufficient
Solution Approach 1:
The patent implements a nested structural configuration where a secondary structural assembly is positioned inside the principal hollow structural core. The secondary assembly includes inner longerons that are nested within the space defined by the outer longerons of the principal core, creating a concentric structural arrangement that enhances shock resistance without proportionally increasing overall mass.
Solution Approach 2:
The structural core is divided into two distinct functional assemblies: a principal hollow structural core providing basic structural support and rigidity, and a secondary structural assembly providing enhanced shock absorption. This segmentation allows each component to be optimized for its specific function while working together as an integrated system.
2Loss of energy
If shock-absorbing material is added between longerons and secondary assembly, then impact energy is absorbed, but the vane mass increases
Solution Approach 1:
Shock-absorbing material is selectively positioned only in specific critical areas where impact forces are most likely to occur, namely between the longerons of the principal core and the corresponding longerons of the secondary assembly. This localized application of damping material provides targeted energy absorption without requiring uniform distribution throughout the entire structure, thereby minimizing unnecessary mass increase.
Solution Approach 2:
The shock-absorbing material utilized in the patent exhibits porous characteristics, allowing it to provide high energy absorption capacity relative to its mass. The porous structure enables the material to deform and dissipate impact energy through viscous damping and structural collapse mechanisms, achieving effective shock absorption with minimal added weight compared to solid alternative materials.
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 design significantly improves shock resistance by absorbing impact energy, ensuring the vane's integrity and safety through a 'Fail Safe' mechanism, where the secondary assembly takes over if the primary core is compromised, effectively limiting damage and maintaining structural function.
Implementation Method 1
a first coating made of shock-absorbing material arranged between the fourth longeron and said secondary structural assembly, and a second coating made of shock-absorbing material arranged between said first longeron and this same assembly
Implementation Method 2
the latter retains its integrity even after having undergone projectile shock. In fact, shocks occurring on the vane in flight or on the ground, for the most part occur between the leading edge and a rear part of the extrados. Consequently, in the case of such a shock occurring in this prime impact zone, the projectile colliding with the aerodynamic shell initially stresses the principal core, then crushes one of the two coatings according to the present invention. During this preferred crushing, part of the impact energy of the flying object and of the shockwave is absorbed
Data Source
AI summary
The invention relates to a vane (200) for an aircraft turbine engine receiver. The vane is a blade (14) having an aerodynamic shell (24) enveloping a principal hollow structure core (34) extending in the direction of wingspan of the blade. The vane further has a secondary structural assembly (34′) enveloped by the hollow core (34) and extending also in the direction of wingspan, as well as a first coating made of shock-absorbing material (50) arranged between a longeron (44) of the core (34) and the assembly (34′), and a second coating made of shocking-absorbing material (52) arranged between another longeron (38) of the core (34) and this same assembly (34′).