Composite Turbine Blade Platform with Identical Overhangs
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Integrated platforms in aircraft turbine engine blades fail to meet aerodynamic criteria under centrifugal forces, leading to significant radial movements and potential flow disturbances due to uneven width variations between platform portions.
Innovation Solution
Designing the platform with identical overhangs on both the pressure-face and suction-face sides, ensuring equal deformation stresses under centrifugal forces by maintaining consistent width variations along the axis of elongation, and using a method for assembling the blades into a wheel that includes pre-mounting on a variable diameter ring for precise axial alignment and attachment.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If the platform portions have different widths on pressure-face and suction-face sides, then the blade structure can accommodate asymmetric aerodynamic requirements, but significant radial movements occur under centrifugal forces
Solution Approach 1:
The patent applies asymmetry by giving different widths to the first platform portion (on pressure-face side) and second platform portion (on suction-face side). The first portion has a greater width than the second portion, allowing each side to be optimized for its specific aerodynamic requirements while maintaining overall structural balance under centrifugal forces
2Adaptability or versatility
If the platform portions have greater overhang, then aerodynamic performance is improved, but radial movements increase significantly under centrifugal forces
Solution Approach 1:
The patent applies local quality by varying the width of different platform portions according to their specific functional requirements. The first platform portion has a greater width to handle higher stresses on the pressure-face side, while the second portion has a smaller width sufficient for the suction-face side, optimizing both aerodynamic performance and structural stability
3Adaptability or versatility
If the platform width varies unevenly between portions, then structural flexibility is increased, but flow path continuity is compromised due to play or steps formation
Solution Approach 1:
The patent applies parameter changes by carefully controlling the width parameters of different platform portions. The first portion has a greater width than the second portion, with specific width relationships that ensure both structural flexibility and flow path continuity. The width parameters are optimized to prevent play or steps formation while maintaining the necessary structural adaptability
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 solution reduces radial movements by half, optimizes platform joint stress, and enhances aerodynamic performance by ensuring balanced movements and improved holding of platform joints between adjacent blades.
Implementation Method 1
the portions Z (FIG. 2) having greater width and thus having greater overhang are subject to significant movements when the blade is subjected to the centrifugal forces (FIG. 2)
Data Source
AI summary
Blade made of composite material, with an integrated platform, for an aircraft turbine engine, including a root connected to an aerofoil and having a connection platform between the root and the aerofoil, the root having a generally elongate shape along an axis (A) of elongation, the aerofoil having a curved cross-sectional shape and including a pressure face and a suction face, the platform including a first portion extending on the pressure-face side of the aerofoil and including a first longitudinal free edge and a second opposite longitudinal edge for connecting to the rest of the blade, the platform including a second portion extending on the suction-face side of the aerofoil and comprising a third longitudinal free edge and an opposite fourth longitudinal edge for connecting to the rest of the blade, wherein the first longitudinal free edge is concave and the third longitudinal free edge is convex, and, for any plane (P, P′) perpendicular to the axis of elongation and intersecting the platform, the distance (L1, L2; L1′, L2′) between the first and second edges, on the one hand, and the distance between said third and fourth edges, on the other hand, are identical in the plane considered.