Gas Turbine Disc Hub Groove for Retaining Ring Integration
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Solution Overview
Problem
Existing methods for attaching a disc and cover plate in gas turbine engines face challenges such as occupying valuable space with protrusions, increasing manufacturing complexity, and limiting structural strength due to the need for retaining rings between the disc and cover plate.
Innovation Solution
A disc design featuring a groove cut into the disc hub that accommodates a retaining ring, allowing the cover plate and disc to securely engage without protrusions on the disc web, thereby optimizing space usage and structural integrity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If protrusions are used to connect the disc and cover plate, then the connection is achieved, but valuable space is occupied and structural strength is limited
Solution Approach 1:
Instead of extending protrusions outward from the disc web to connect with the cover plate, the invention inverts the approach by cutting grooves into the disc hub. The retaining ring is received within these grooves, eliminating the need for outward protrusions and thereby saving valuable space while achieving the same connection function.
2Ease of manufacture
If protrusions are used to connect the disc and cover plate, then the connection is achieved, but manufacturing complexity increases
Solution Approach 1:
The invention simplifies the structure by inverting the connection approach: instead of adding outward protrusions that increase complexity, grooves are cut into the disc hub to receive the retaining ring. This inverted approach reduces structural complexity while maintaining the connection function.
3Ease of manufacture
If retaining rings are used between disc and cover plate, then the connection is achieved, but structural strength is limited
Solution Approach 1:
The retaining ring is nested within the grooves cut into the disc hub, creating a more integrated and structurally sound connection. This nesting approach allows the retaining ring to be embedded within the disc structure rather than merely attached to the exterior, thereby enhancing structural strength while maintaining ease of manufacture.
Data Source
Figure 1
Figure 2~3
Figure 4A~4B
AI summary
A disc of a gas turbine engine (10) system is provided. The disc includes a disc hub (203; 403; 603) including, an interstage coupling (207; 307; 407; 607) disposed on an axially extending surface (212; 312; 412; 612) at a peripheral edge of the disc hub that includes a protrusion that extends axially beyond an outer surface of the disc hub, and a groove (233; 333; 533; 633) formed on the axially extending surface of the disc hub wherein an aft surface (216; 316; 416; 516; 616) of the groove is also a forward surface of the interstage coupling, wherein the groove includes a forward surface (213; 313; 413; 513; 613) that extends radially into the disc hub to a groove floor (214; 314; 414; 514; 614) that is cut into the disc hub and extends axially to the aft surface that extends radially outward to at least the axially extending surface of the disc hub, and a disc web (202; 602) that extends radially outward from the disc hub, relative to an axis of rotation of the gas turbine engine.