Hypergravity Material Testing System for Multi-Field Coupling
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current material testing systems fail to effectively simulate and measure the dynamic performance of materials under volume force-surface force-temperature coupling effects, particularly in high-speed rotation states, which are critical for advanced aviation and aerospace components.
Innovation Solution
A material performance testing system is developed, comprising a hoisted sealed cabin, a bearing frame, a high-temperature furnace, and a mechanical test device, capable of operating in a hypergravity environment (1 g to 2500 g) from room temperature to 1600°C, simulating the complex stress conditions of centrifugal, thermal, and surface forces on samples.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If material testing is conducted under uniaxial stress in laboratory conditions, then the testing setup is simple and easy to control, but the testing results do not reflect the actual complex multi-field coupling effects experienced by turbine working blades during service
Solution Approach 1:
The patent combines multiple testing fields (thermal field, centrifugal force field, and mechanical load field) into a single integrated testing system. The turbine working blade is simultaneously subjected to high temperature, centrifugal force, and mechanical loading in the hypergravity environment, replicating the actual service conditions where all these fields act together on the blade components.
Solution Approach 2:
The testing system dynamically generates centrifugal force by rotating the sample in a hypergravity environment (up to 2500g), creating dynamic coupling effects between thermal stress and centrifugal stress. This dynamic approach allows the testing of material behavior under time-varying multi-field coupling conditions that match actual service environments.
2Power
If the front gas inlet temperature of the turbine is increased to 2000 K to 2200 K to achieve higher thrust-to-weight ratio, then the engine performance is improved, but the performance requirements on core hot end components become significantly higher and more difficult to meet
Solution Approach 1:
The testing system enables parameter studies by independently controlling temperature (up to 1600°C), centrifugal acceleration (up to 2500g), and mechanical load levels. This allows systematic investigation of material behavior across the full range of extreme parameters that correspond to next-generation high-temperature turbine operating conditions.
3Power
If the turbine working blade operates under coupled loading conditions of high temperature, high pressure, high rotation speed, and alternating load, then the engine achieves high power output, but the material damage mechanism becomes significantly different from simple surface force effects
Solution Approach 1:
The testing system segments the complex service loading into controllable components: centrifugal force (simulating rotation), thermal load (from heating furnace), and mechanical load (from testing machine). Each component can be independently controlled and adjusted, allowing systematic study of their coupling effects while maintaining overall system manageability.
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 real-time measurement of mechanical performance data under volume force-surface force-temperature coupling conditions, accurately simulating the service environment of high-speed rotating parts like aero engines, thereby assessing material performance under complex stress states.
Implementation Method 1
The centrifugal stress generated by the centrifugal load belongs to volume force
Implementation Method 2
The thermal stress generated by the thermal load is closely related to geometric constraints
Implementation Method 3
The aerodynamic force generated by the aerodynamic load is a surface distributed pressure, which is an area force
Implementation Method 4
the maximum surface force provided is 300 kN
Data Source
AI summary
Provided is a material performance testing system under a fixed multi-field coupling effect in a hypergravity environment, including a hoisted sealed cabin, a bearing frame, a high-temperature furnace, a mechanical test device, and a buffer device. The bearing frame and the high-temperature furnace are fixedly mounted inside the hoisted sealed cabin. The bearing frame is covered on the high-temperature furnace. The buffer device is mounted at a bottom of the high-temperature furnace. Upper and lower ends of the mechanical test device are connected in a top of the bearing frame and the bottom of the high-temperature furnace. A sample is connected and mounted at an end of the mechanical test device.