Torque Pin Assembly for Gas Turbine Blade Ring Positioning
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Solution Overview
Problem
The existing methods for adjusting the position of a blade ring relative to a rotor in a gas turbine engine are time-consuming and costly, as they require machining torque pins to reduce thickness for moving the blade ring away from the rotor or replacing them for moving closer, which is inefficient and costly.
Innovation Solution
A torque pin assembly with a variable thickness defining structure, comprising shims and a puck, is used to adjust the vertical spacing between the blade ring and the rotor by calculating and adjusting the thickness of the torque pin assembly using the equation SD=ΔY/sin θ, allowing for precise adjustment without the need for machining or replacing torque pins.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If torque pins are machined to reduce thickness for moving the blade ring away from the rotor, then the blade ring position can be adjusted, but the process becomes time-consuming and costly
Solution Approach 1:
The torque pin assembly is segmented into multiple components: a base torque pin, variable thickness defining structures (shims), and securing structures. This segmentation allows the thickness to be adjusted by adding or removing shims rather than machining the entire torque pin, significantly reducing adjustment time and complexity
Solution Approach 2:
The torque pin assembly incorporates a variable thickness defining structure that enables dynamic adjustment of the blade ring position. The thickness can be changed by adding or removing shims, allowing the system to adapt to different position requirements without permanent modification to the torque pin itself
2Ease of operation
If new torque pins are used for moving the blade ring closer to the rotor, then the position adjustment is achieved, but the cost increases significantly
Solution Approach 1:
By segmenting the torque pin assembly into a reusable base torque pin and adjustable shims, the solution allows the same torque pin to be used repeatedly with different thickness configurations. This eliminates the need to discard and replace entire torque pins, reducing material loss and costs
Solution Approach 2:
The invention enables recovery and reuse of the torque pin body after position adjustments. Instead of discarding the torque pin after machining or replacement, the same torque pin can be reused with different shim configurations, maximizing material utilization and reducing costs
3Adaptability or versatility
If torque pins are machined to adjust thickness, then position adjustment is possible, but the manufacturing complexity and cost increase
Solution Approach 1:
The manufacturing process is segmented into producing a standard torque pin body and separate shims of various thicknesses. This allows the torque pin body to be manufactured once and reused, while only simple shims need to be produced in different thicknesses, significantly simplifying the overall manufacturing process
Solution Approach 2:
The invention changes the approach from modifying the torque pin's physical dimensions through machining to changing the effective thickness parameter by adding or removing shims. This parameter change approach simplifies manufacturing as it avoids complex machining operations and allows for easier standardization
Data Source
AI summary
A method is provided for adjusting a position of a blade ring relative to a rotor in a gas turbine engine. An outer casing surrounds the blade ring and the blade ring surrounds the rotor. The method comprises: determining an amount of vertical movement needed to reposition the blade ring relative to the rotor so that the blade ring is at a desired position relative to the rotor; providing at least one torque pin assembly comprising a torque pin and a variable thickness defining structure; determining a change in the thickness of the variable thickness defining structure so as to effect the necessary vertical movement of the blade ring; changing the thickness of the variable thickness defining structure; and coupling the at least one torque pin assembly to the outer casing such that at least one torque pin engages the blade ring. A gas turbine engine is provided having structure for adjusting a position of a blade ring relative to a rotor.