Composite Turbine Blade Platform Stiffener for Deformation Control
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Solution Overview
Problem
Turbine engine blades made from composite materials using 3D weaving techniques experience irregular deformations under centrifugal forces, leading to aerodynamic inefficiencies and potential overlap issues between suction and pressure side platforms during operation.
Innovation Solution
A fiber preform with a stiffener strip extending radially from the distal edge of the platform, varying in width and thickness to balance deformations, ensuring uniform deformation and maintaining aerodynamic regularity, and preventing platform overlap in case of impact.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If 3D weaving techniques are used to fabricate composite blades, then weight is reduced and manufacturing efficiency is improved, but platform deformation irregularities occur under centrifugal forces
Solution Approach 1:
The platform is divided into multiple zones with different fiber orientations and densities. The first zone has fibers oriented in the first direction while the second zone has fibers oriented in the second direction, creating segmented structural characteristics that allow differential deformation control under centrifugal loads.
Solution Approach 2:
Different regions of the platform are given different material properties through varying fiber orientations and densities. The first zone near the blade root has different structural characteristics than the second zone near the tip, allowing each region to be optimized for its specific deformation behavior under centrifugal forces.
2Shape
If platform thickness is increased to reduce deformation, then shape regularity is improved, but weight increases
Solution Approach 1:
Instead of uniformly increasing platform thickness, the invention varies fiber orientation and density locally across different zones. This allows deformation control without uniform weight increase, as each zone is optimized for its specific structural requirements rather than using a blanket thickness increase.
Solution Approach 2:
The platform uses composite construction with fibers oriented in multiple directions and varying densities. This composite approach allows tailored mechanical properties in different regions, achieving deformation control through material composition rather than simply increasing overall thickness and weight.
3Length of moving object
If suction side platforms are made longer to improve aerodynamics, then aerodynamic performance is improved, but overlap with adjacent blades occurs
Solution Approach 1:
The platform is divided into zones with different fiber orientations to control deformation characteristics. This allows the platform to maintain its aerodynamic length while the structured deformation control prevents overlap with adjacent blades during operation.
Solution Approach 2:
The invention accounts for dynamic deformation under centrifugal forces by structuring the platform with varying fiber orientations. This dynamic consideration allows the platform to be designed at its optimal aerodynamic length while compensating for the expected deformation during operation to prevent blade overlap.
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 solution achieves regular platform deformation, reducing aerodynamic distortion and preventing platform overlap, while maintaining the weight-saving benefits of 3D woven single-piece blades.
Implementation Method 1
the deformation of a zone of the platform increases with increasing offset from the airfoil... the platforms present irregularities of shape that might disturb the stream of air... suction side platforms, which are generally the longer platforms, are subjected to greater bending than pressure side platforms
Data Source
AI summary
A fiber preform for a turbine engine blade and also a single-piece blade suitable for being formed using such a preform, a rotor wheel, and a turbine engine including such a blade, the fiber preform being obtained by three-dimensional weaving and comprising a first longitudinal segment suitable for forming a blade root (21), a second longitudinal segment extending the first longitudinal segment upwards and suitable for forming an airfoil portion (22), a first transverse segment extending transversely from the junction between the first and second longitudinal segments and suitable for forming a first platform (23), and a first stiffener strip extending downwards from the distal edge of the first transverse portion and suitable for forming a first platform stiffener (25).