Segmented Rotor Blade Carrier with Integrated MMC Stiffening
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Solution Overview
Problem
The existing rotor blade assembly groups for engines, particularly in gas turbines, face challenges with weight reduction and complex, laborious assembly processes due to the use of metal matrix composite (MMC) stiffening elements, which are independently secured and require form-fit axial fixation, increasing manufacturing costs and complexity.
Innovation Solution
A rotor blade assembly group with a ring-segment-shaped or disc-segment-shaped blade carrier featuring stiffening elements connected to each other and the carrier section, utilizing a connection appliance that secures them axially, eliminating the need for individual axial securing of each element, and incorporating a metal matrix composite for weight reduction and enhanced stiffness.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If stiffening elements are independently secured at each face side of the blade carrier, then the blade carrier can withstand higher loads with reduced weight, but the assembly process becomes laborious and complex
Solution Approach 1:
The patent combines multiple stiffening elements into a single integrated stiffening structure that spans both face sides of the blade carrier. This merging eliminates the need for separate securing operations at each face side, reducing assembly complexity while maintaining the weight reduction benefits of the MMC material.
Solution Approach 2:
The integrated stiffening structure serves multiple functions simultaneously: it provides stiffening at both face sides, acts as a single securing unit, and eliminates the need for separate axial securing mechanisms. This multi-functionality reduces the number of assembly steps and simplifies the overall process.
2Strength
If form-fit axial securing is used for each stiffening element, then the structural integrity is improved, but the manufacturing cost and complexity increase
Solution Approach 1:
The patent merges the axial securing function into a single operation that secures the entire integrated stiffening structure, rather than performing separate form-fit axial securing for each individual stiffening element. This maintains structural integrity while significantly reducing manufacturing complexity and cost.
Solution Approach 2:
The patent extracts the individual stiffening elements from separate components and integrates them into a single structure, thereby eliminating the need for repeated axial securing operations. The integrated structure is secured as one unit, simplifying the manufacturing process.
3Force
If the carrier section has a large surface area, then it can withstand higher loads from fast rotation, but the weight of the blade carrier increases
Solution Approach 1:
The patent uses metal matrix composite (MMC) material for the integrated stiffening structure, which provides high strength and stiffness-to-weight ratio. This allows the carrier section to maintain load-bearing capacity while reducing overall weight, as the MMC material can provide equivalent structural performance with less mass.
Solution Approach 2:
The patent introduces an integrated stiffening structure as a distinct component that segments the load-bearing function from the carrier section. The stiffening structure specifically targets areas requiring high strength, allowing the carrier section to be optimized for weight reduction while maintaining overall load-bearing capacity.
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 simplifies the assembly and securing of stiffening elements, reduces the weight of rotor blade rows, and improves the structural integrity while maintaining torque-proof connections between blade carriers, thereby enhancing the efficiency and cost-effectiveness of the rotor blade assembly group.
Implementation Method 1
utilizing a connection appliance that secures them axially, eliminating the need for individual axial securing of each element, and incorporating a metal matrix composite for weight reduction and enhanced stiffness
Data Source
AI summary
A rotor blade assembly group for an engine with at least one blade carrier having at least one rotor blade that is provided with multiple rotor blades along a circle line about a central axis of the rotor blade assembly group, wherein the blade carrier has a carrier section that extends radially inwards in the direction of the central axis with respect to the rotor blade, the carrier section comprises a connection area at which a stiffening structure with at least two, first and second, stiffening elements is fixedly attached, and the stiffening element is arranged at a first face side of the blade carrier, and the second stiffening element is arranged at a second face side that is facing away from the first face side. The blade carrier is formed in a ring-segment-shaped or disc-segment-shaped-manner.