Gas Turbine Compressor Inner Ring Biasing Assembly
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Solution Overview
Problem
The existing gas turbine engine compressor stator assembly design suffers from misalignment and wear issues due to the separation of inner ring halves, leading to efficiency losses, air leaks, and reduced operating life, caused by the blind assembly and excess clearances between the inner ring halves and labyrinth teeth.
Innovation Solution
The introduction of an inner bushing assembly with a biasing element, comprising a first and second bushing and a biasing element, such as a spring washer, which centers and clamps the inner ring halves together, reducing misalignment and wear by providing a radial force to maintain proper alignment and reduce clearance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If the inner ring halves are assembled without a biasing element, then the assembly process is simpler, but misalignment and wear between the inner ring halves and labyrinth teeth increase
Solution Approach 1:
The biasing element transforms the static inner ring half assembly into a dynamic system where the inner ring halves can self-adjust and self-center under the continuous radial force applied by the biasing element, ensuring consistent alignment precision without complex assembly procedures
Solution Approach 2:
The biasing element enables the inner ring halves to self-center and self-align within the compressor stator assembly by continuously applying radial force, eliminating the need for complex external alignment tools or procedures during assembly and maintenance
2Device complexity
If the inner ring halves are assembled without a biasing element, then the device structure is simpler, but wear and operating life are reduced
Solution Approach 1:
The biasing element pre-applies radial force to maintain optimal clearance and alignment between the inner ring halves and labyrinth teeth before wear occurs, preventing excessive wear and extending operating life through continuous protective contact pressure
Solution Approach 2:
The biasing element acts as an intermediary component that mediates the interaction between the inner ring halves and the compressor stator assembly, ensuring consistent radial force application and alignment maintenance throughout the operating cycle
3Length of stationary object
If the inner ring halves are assembled without a biasing element, then the clearance is larger, but air leaks increase and efficiency decreases
Solution Approach 1:
The biasing element dynamically maintains optimal clearance parameters between the inner ring halves and labyrinth teeth by applying continuous radial force, preventing excessive clearance that would lead to air leaks and efficiency losses while avoiding excessive tightness
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
The solution effectively centers and clamps the inner ring halves, preventing air leaks, reducing lockup issues, and extending the operating life of the compressor components by minimizing misalignment and wear, thereby enhancing the overall efficiency and reliability of the gas turbine engine.
Implementation Method 1
An inner bushing assembly to a biasing force between a guide vane and an inner ring half of a gas turbine engine compressor is disclosed
Implementation Method 2
an elastomeric material being inserted between the inner bushing and the outer bushing to allow the vane to pivot about its axis and absorb at least some of the flexing of the pivot at right angles to the axis
Data Source
AI summary
An inner bushing assembly (280) to provide a biasing force between a guide vane (260) and an inner ring half (261) of a gas turbine engine compressor (200) is disclosed. The inner bushing assembly (280) includes a first bushing (281), a second bushing (282), and a biasing element (283). The first bushing (281) is configured to be installed about an inner vane shaft (267) of the guide vane (260) adjacent to an airfoil (265) of the guide vane (260). The second bushing (282) is configured to be installed about the inner vane shaft (267) distal to the airfoil (265). The biasing element (283) is configured to be installed about the inner vane shaft (267) between the first bushing (281) and the second bushing (282).