Compressor Blade Intermediate Part Elastic Deformation
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Solution Overview
Problem
High pressure axial compressors in gas turbines face issues with plastic deformation of intermediate parts between adjacent blades during start-up, leading to large circumferential gaps and potential damage, as existing solutions either allow plastic deformation or are complex and expensive.
Innovation Solution
An intermediate part with elastic deformation properties, pre-bended to act like a spring, absorbs compressive forces during start-up without plastic deformation, maintaining consistent blade gap dimensions and preventing escape.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If intermediate parts are made of softer material than compressor blades, then they can absorb compressive forces during start-up, but plastic deformation occurs leading to large circumferential gaps and potential escape
Solution Approach 1:
The patent changes the material parameters by selecting a material with optimized elastic properties and appropriate elastic modulus. The material is designed to deform elastically rather than plastically, maintaining structural integrity while absorbing compressive forces during start-up. This parameter optimization prevents both excessive rigidity and permanent deformation.
Solution Approach 2:
The intermediate part is designed with dynamic deformation characteristics, allowing it to flex elastically during start-up when compressive forces are applied. The part returns to its original shape after the forces are removed, maintaining consistent blade gap dimensions throughout operation cycles.
2Stability of the object's composition
If intermediate parts are made rigid to prevent deformation, then blade gap dimensions are maintained, but high stresses occur during start-up that can damage the compressor structure
Solution Approach 1:
The patent optimizes the elastic modulus and geometric parameters of the intermediate part to achieve a balance between rigidity and flexibility. The material and design are selected so that the part deforms elastically within acceptable limits, maintaining blade gap consistency while reducing peak stresses during start-up conditions.
3Reliability
If distance pieces are made rigid to follow the shape of the intermediate gap, then sealability is ensured, but very high stresses occur that can damage the pieces and compressor blades
Solution Approach 1:
The patent employs an intermediate part with flexible elastic properties that can deform to maintain contact and sealability between adjacent compressor blades. The elastic material allows the part to conform to the intermediate gap shape while accommodating thermal expansion and mechanical stresses without generating damaging force concentrations.
4Ease of manufacture
If intermediate parts are made from softer material, then they can be manufactured easily, but they deform plastically to a significant degree during start-up
Solution Approach 1:
The patent selects materials and designs parameters that enable elastic deformation behavior instead of plastic deformation. The material properties are chosen so that the intermediate part can be manufactured with standard processes while maintaining dimensional stability through reversible elastic deformation, preventing permanent shape changes during operation.
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 avoids plastic deformation, maintaining consistent blade gap dimensions and preventing intermediate part escape, thus reducing the risk of compressor damage and forced outages while being less complex and expensive.
Implementation Method 1
the deformation of this intermediate part is effected by the elastic deformation of the whole intermediate part material acting as an elastic element, typically acting as a spring, without any plastic deformation in the intermediate part
Data Source
AI summary
Intermediate part (1) located in a circumferential groove (4) of a drum (6) where blades (2) are inserted, the intermediate part (1) being located between two adjacent compressor blades (2, 20) in a high pressure axial compressor, presenting in its rest position certain degree of pre-bending (A) provided by the elastic properties of the material of which the cited intermediate part (1) is made. The invention also refers to a gas turbine (100) with a high pressure axial compressor, such that an intermediate part (1) as cited above is located between each two adjacent compressor blades (2, 20).