Gas Turbine Cover Plate Retention via Interlocking Flanges
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Solution Overview
Problem
Existing gas turbine engine designs face inefficiencies in cooling air distribution due to the axial room and multiple pieces required by the conventional cover plate and rotor disk configuration, which affects the sealing and attachment of cooling passages.
Innovation Solution
A cover plate retention mechanism with interlocking flanges and a retention ring that axially, radially, and angularly attaches cover plates and rotor disks, optimizing the attachment and sealing of cooling passages while reducing axial space usage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional cover plate and rotor disk configuration is used, then cooling passages can be sealed and attached, but significant axial room is required and multiple pieces are involved
Solution Approach 1:
The patent merges the cover plate and rotor disk into a single integrated component. The cover plate is formed as an integral part of the rotor disk, eliminating the need for separate attachment mechanisms and reducing axial space requirements while maintaining the sealing function of cooling passages.
Solution Approach 2:
The cooling passages are nested within the integrated rotor disk structure, with the cover plate forming part of the rotor disk body. This nesting arrangement allows the cooling passages to be contained within the component itself, eliminating the need for separate sealing mechanisms and reducing overall axial dimensions.
2Strength
If conventional cover plate and rotor disk configuration with bolts is used, then attachment is achieved, but the configuration involves multiple pieces and complex assembly
Solution Approach 1:
The cover plate and rotor disk are merged into a single integral component, eliminating bolts and multiple parts. This integration maintains structural strength while dramatically reducing device complexity and assembly requirements.
Solution Approach 2:
The integrated rotor disk is designed with internal segmentation to accommodate cooling passages and functional zones, allowing complex internal structures to be achieved without requiring separate external components or fasteners.
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 enhances the sealing and distribution of cooling air, reducing axial space requirements and simplifying assembly, thereby improving the efficiency of cooling in gas turbine engines.
Implementation Method 1
cover plates typically follow the contour of the disk to create a boundary layer effect that pumps cooling air from the central location to the radially outward location while the cover plate and rotor disk rotate
Data Source
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AI summary
A mechanism for use in a gas turbine engine has a cover plate (15), a rotor disk (10), a first slot (115) in the cover plate (15), a second slot (120) in the rotor disk (10), a first finger (130) in the cover plate (15) extending through the second slot (120), and a second finger (145) in the rotor disk (10) extending through the first slot (115). The first finger (130) and the second finger (145) form a channel (135) and a holder (140) is disposed in the channel (135) for locking the rotor disk (10) and the cover plate (15) together.