Vibration Test Method of Aero-Engine 3D Printing Pre-Swirl Nozzle

2021 ◽  
Author(s):  
Yujie Zhao ◽  
Yeda Lian ◽  
Lei Li ◽  
Xu Gong ◽  
Xianghai Chai ◽  
...  
Keyword(s):  
3D Printing ◽  
Test Method ◽  
Vibration Test ◽  
Aero Engine

Experimental Research on Vibration Characteristics of Laminated Composite Cantilever Beam

2021 ◽  
Author(s):  
Rui Yang ◽  
Xiaobin Li ◽  
Hongxi Li
Keyword(s):  
Cantilever Beam ◽  
Optical Measurement ◽  
Laminated Composite ◽  
Experimental Methods ◽  
Test Methods ◽  
Vibration Characteristics ◽  
Test Method ◽  
Vibration Measurement ◽  
Vibration Test ◽  
Test Results

Abstract In this paper, the vibration characteristics of laminated composite cantilever beam is taken as the research object. Firstly, a vibration formula specific for laminated composite cantilever beam is derived, from which the low order natural frequency of laminated composite cantilever beam is calculated; Secondly, two experimental methods, electrical and optical measurement, are used to study the vibration characteristics of laminated composite cantilever beam, and the influence of different test methods, sensor types, number of measuring points and excitation methods on the test results are analyzed. Through the combination of theory and experiment, a test method that can be applied to the vibration test of composite material laminated structure cantilever beam is obtained. Based on the laser vibration measurement method in the optical method, the results show that the deviation between the experimental data and the theoretical solution is the smallest when the distance between the probe and the specimen is 0.5m and the sampling time is 5s by using the optical fiber vibrometer. The research content of this article can provide a reasonable reference for related vibration test research.

Swept Sine Vibration Test Conservatism

1995 ◽  
Vol 38 (6) ◽  
pp. 13-17
Author(s):  
M. Hine
Keyword(s):  
Response Spectrum ◽  
Three Dimensional ◽  
Test Method ◽  
Vibration Test ◽  
Transient Vibration ◽  
Mass Model ◽  
Dynamic Mass ◽  
Shock Response ◽  
Order Of Magnitude ◽  
Shock Response Spectrum

The excessive overtest associated with the swept sine vibration test method was measured quantitatively using the index of conservatism and the associated overtest factor for a dynamic mass model of a typical spacecraft component. The response to a fixed amplitude sine sweep test was compared with the flight transient vibration environment for sweep rates of 2, 4, and 6 octaves/min and 300 Hz/min. A response-limited test was also conducted at 6 octaves/min. The conservatism was measured using several characterizations; namely: number of peaks exceeding, ranked peaks, shock response spectrum, shock intensity, three-dimensional shock response spectrum, and ranked peaks. Overtest factors exceeding an order of magnitude were measured for the test response with the number of peaks exceeding and the three-dimensional shock response spectrum.

Research on Multi-Excitation Source United Controlling Test Method Based on Distributed Actuation

2011 ◽  
Vol 291-294 ◽  
pp. 2168-2174
Author(s):  
Jun Yao ◽  
Yan Fei Wu ◽  
Ming Ge Xu
Keyword(s):  
High Speed ◽  
Engineering Application ◽  
Piezoelectric Element ◽  
Test Method ◽  
Excitation Source ◽  
Vibration Test ◽  
Test Technique ◽  
Test Items ◽  
Application Potential ◽  
Vibrating Table

In view of the questions of high-speed aircraft withstanding complicated vibration environment, their vibration durability could not being plenary examined by existing vibration test technology, a vibration test technique integrating piezoelectric element, vibrating table, exciter is proposed. The vibration environment dimension of high-speed aircraft and its influence to the failures of high-speed aircraft are analysed. Based on the research on the material and actuation dimension of the piezoelectric element, the feasibility of piezoelectric element used as the distributed excitation source in vibration test is analysed. Last, a test demonstration system is constituted and a serials of test items are carried out. The rationality and the extensive engineering application potential of this technique are verified by the test results.

3D-printed polypropylene transtibial sockets: Mechanical behavior

2020 ◽  
pp. 095440622094392
Author(s):  
MacArthur L Stewart
Keyword(s):  
3D Printing ◽  
Yield Strength ◽  
Tensile Test ◽  
Tensile Properties ◽  
Material Properties ◽  
Standard Test ◽  
Test Method ◽  
Material Behavior ◽  
Cross Sectional ◽  
3D Printed

This paper defines the tensile properties of a successfully worn 3D-printed transtibial socket. The socket was printed from a proprietary polypropylene filament and FDM 3D-printing process. Fused disposition modeling involves producing successive cross-sectional layers on top of one another and welding them together. Because of this, a notch is formed between the printed layers. As part of this investigation, tensile test specimens were die-cut perpendicular to the material direction and tested according to ASTM D638—Standard Test Method for Tensile Properties of Plastics. From the measured load–elongation data, stress–strain curves and the corresponding material properties were determined, including modulus of elasticity E, Poisson’s ratio ν, yield strength Sy, and ultimate strength Su. The average values for each of these material properties were 955 MPa, 0.35, 11.4 MPa, and 16.3 MPa, respectively. In addition to defining tensile properties, this work demonstrated a viable methodology for characterizing the as-built material behavior of 3D-printed sockets.

Performance Simulation for the Supporting Structure of Aero-Engine Rotor in Wide Frequency Domain

2019 ◽  
Vol 11 (5) ◽  
Author(s):  
Baoxu Li
Keyword(s):  
Finite Element ◽  
Frequency Domain ◽  
Dynamic Characteristics ◽  
Stiffness Matrix ◽  
Structural Model ◽  
Test Method ◽  
Supporting Structure ◽  
Aero Engine ◽  
Rotor Support ◽  
Engine Rotor

The inertia load of aero-engine indeterminate rotor support is calculated by the finite element method coupled with plane stress element and Fourier ring element. Without considering the dynamic characteristics of rotor’s supporting structure, the test results are error-prone and inefficient. A new method for testing the supporting structure performance of aero-engine rotor in wide frequency domain is proposed. On this basis, the structural model of the casing-support and the structural model of aero-engine rotor are constructed by substructure modelling method. Combining the two sub-models, the semi-physical simulation model of the vibration of the engine rotor’s supporting structure is obtained. By superimposing the additional dynamic stiffness matrix of the casing-supporting structure at the designated DOF position in the overall stiffness matrix of the finite element model of the rotor structure, the overall stiffness matrix of the aero-engine rotor supporting structure is obtained. The effective stiffness matrix can be used to calculate the structural dynamic characteristics of aero-engine rotor supporting structure. Experiments show that the average error of the proposed method is 0.0023 and the number of units is 7.98 e4. The calculation time and storage space are reduced by 310 minutes and 166 GB respectively compared with the performance test method of rotor support based on finite element analysis, which shows that the proposed method is more efficient and accurate.

Sign in / Sign up

Export Citation Format

Share Document