CMC Rotor Blade Root Attachment with Sacrificial Datum Machining
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Solution Overview
Problem
The manufacturing process of ceramic matrix composite (CMC) turbine blade assemblies faces challenges in achieving precise attachment profile tolerances, which are typically an order of magnitude smaller than the CMC tow size, leading to reduced strength and reliability due to cutting composite plies.
Innovation Solution
A sacrificial datum system is employed, involving machining of an oversized root region with V-notches to form a sacrificial system, followed by application and machining of an oversized coating layer to maintain accurate tolerances and avoid cutting critical composite plies, ensuring precise positioning of outer composite plies within tight tolerances.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Manufacturing precision
If conventional machining methods are used to achieve precise attachment profile tolerances, then manufacturing precision is improved, but composite plies are cut which reduces strength and reliability
Solution Approach 1:
The patent applies preliminary action by pre-forming the root region with an oversized geometry that includes built-in datums and attachment fillet radii during the CMC manufacturing process itself. This preliminary formation of precise geometric features eliminates the need for subsequent machining that would cut through critical composite plies, thereby maintaining both manufacturing precision and structural reliability.
Solution Approach 2:
The patent changes the size parameter of the root region by forming it oversized relative to the final attachment interface. This parameter change allows the use of non-cutting removal methods (such as abrasion or chemical etching) to achieve final dimensions without cutting through plies, thus resolving the contradiction between achieving tight tolerances and maintaining ply integrity.
2Manufacturing precision
If CMC processing variation and tow size are reduced to achieve tighter tolerances, then manufacturing precision is improved, but processing complexity and cost increase
Solution Approach 1:
The patent embeds the datum features and attachment fillet radii directly into the CMC root region during the manufacturing process itself, rather than requiring subsequent complex machining operations. This preliminary action transfers the precision requirements to the molding/forming stage where CMC processes can more easily achieve the required tolerances without excessive complexity.
Solution Approach 2:
The patent introduces an oversized root region as an intermediary form between the CMC manufacturing process and the final attachment interface. This intermediary allows the CMC process to work with larger, more tolerable dimensions while still achieving the final precise fit through non-cutting removal methods, thereby reducing processing complexity.
3Manufacturing precision
If outer composite plies are cut to achieve profile tolerances, then manufacturing precision is improved, but attachment strength is reduced
Solution Approach 1:
The patent pre-forms the outer composite plies with the correct geometry and attachment fillet radii during the CMC manufacturing process. This preliminary action ensures that the plies are never cut or damaged during subsequent machining operations, thereby preserving the full strength of the outer plies while still achieving the required attachment profile tolerances.
Solution Approach 2:
The patent changes the approach from cutting-based precision achievement to abrasion/etching-based precision achievement. By using parameter changes in the material removal method (from mechanical cutting to surface abrasion or chemical etching), the outer plies can be precisely shaped without compromising their structural integrity and attachment strength.
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 method ensures accurate manufacturing of CMC blade attachment fillet radii, maintaining structural integrity and minimizing part-to-part variation, thereby enhancing attachment strength and reliability while avoiding damage to critical plies.
Implementation Method 1
silicon plasma spraying the oversized coating layer
Data Source
AI summary
A process for manufacturing a composite rotor blade (84) includes manufacturing an oversized root region (88A) of a root region (88) of a composite rotor blade (84); fixturing the CMC blade (84) into a machining fixture at a primary Y and Z axis datum located at an attachment fillet radii (124) of the root region (88); machining V-notches (140, 142) into the oversized root region (88A) to form a Y' and Z' axis datum of a sacrificial datum system (144) in relation to the primary Y and Z axis datum; applying an oversized coating layer (160) over the attachment fillet radii (124) of the root region (88); fixturing the CMC blade (84) into a machining fixture at the Y' and Z' axis datum of the sacrificial datum system (144); machining the oversized coating layer (160) to a machined coating layer (170) forming a Y" and Z" axis datum with respect to the Y' and Z' axis datum of the sacrificial datum system (144); fixturing the CMC blade (84) into a machining fixture at the Y" and Z" axis datum; and machining off the sacrificial datum system (144) removing the V-notches (140, 142).