Turbomachine Rotor Blade Centrifugal Acceleration Simulation Device
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Solution Overview
Problem
Existing methods for simulating centrifugal acceleration in aeronautical turbomachine rotor blades are impractical due to the risk of damaging real blades, complex tensioning structures, and the need for large-scale installations, which hinder accurate permeability measurements.
Innovation Solution
A simulation device featuring a test piece with a false blade and a screw-spacer mechanism that simulates centrifugal acceleration by screwing into a rotor disk cell, allowing for simple and precise displacement of the blade to mimic operational conditions without using real blades or large tensioning structures.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If real blades are used in the simulation device, then the measurement represents actual operating conditions, but the blades risk being damaged particularly at their roots
Solution Approach 1:
The patent uses false blades (copies) that replicate the geometric and functional characteristics of real turbine blades without using actual blade material. These false blades are equipped with sensors and designed to withstand the simulation forces, thereby eliminating the risk of damaging expensive real blades while maintaining measurement representativeness
Solution Approach 2:
The false blades are designed as inexpensive, replaceable components that can be easily manufactured and discarded if needed. This allows multiple simulation tests to be performed without concern for damaging valuable real blades, as the false blades serve as sacrificial or reusable proxies
2Reliability
If a tension structure is used to simulate centrifugal acceleration, then the blade loading is represented, but the structure becomes complex and risks non-uniform deformation
Solution Approach 1:
The patent extracts the essential function of centrifugal acceleration simulation from a complex global tension structure and implements it through localized force application. Instead of tensioning the entire blade assembly, the invention applies forces directly at the blade root attachment point, eliminating the need for a bicycle wheel-like tension structure
Solution Approach 2:
The simulation device divides the centrifugal acceleration simulation into independent, manageable components. Each false blade is tensioned independently through its own attachment mechanism to the rotor disk, allowing precise control of individual blade loading without affecting other blades, thus avoiding the non-uniform deformation problems of global tension structures
3Productivity
If a large-scale installation is used to tension multiple blades simultaneously, then all blade stages can be tested, but the device dimensions become very large
Solution Approach 1:
The rotor disk structure serves multiple functions simultaneously: it provides the mounting platform for multiple false blades, acts as the reaction mass for generating centrifugal forces, and serves as the reference frame for measurement. This multi-functionality eliminates the need for separate large-scale tensioning structures for each blade stage
Solution Approach 2:
The patent merges the tensioning mechanisms for multiple blades into a single integrated rotor disk assembly. All false blades are attached to and tensioned through the same rotor disk structure, allowing simultaneous testing of multiple blade stages in a compact configuration rather than requiring separate large-scale installations for each blade
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
Enables accurate permeability measurements under representative centrifugal acceleration conditions, avoiding blade damage and complex installations, while allowing for simultaneous simulation of multiple blade stages and fine adjustment of tension.
Implementation Method 1
the screw comes into abutment against said spacer and presses it against the two lateral teeth situated on either side of said rotor disk cell and this causes the displacement of the false blade toward the outside of the disk, so as to simulate a centrifugal acceleration applied to said false blade
Data Source
AI summary
The invention relates to a device for simulating the centrifugal acceleration applied to at least one aeronautical turbomachine rotor blade. This device is notable in that it comprises at least one rotor disc (2) comprising a rim in which there are formed a plurality of pockets (23) delimited by two lateral teeth (24) and at least one simulation test (3) which comprises a screw (32), a spacer (33) and a dummy blade (31), in the dummy blade comprises a bore (347), which is tapped over at least part of its length and in that the dummy blade, the screw and the spacer are configured and arranged in such a way that when the screw is screwed into the tapped bore, the root (35) of the dummy blade is engaged in the pocket in the disc, the screw comes into abutment against the spacer and presses same against the two lateral teeth situated one on each side of the pocket in the rotor disc and that this causes the dummy blade to move towards the outside of the disc.