Adapter Interface – Turbine Engine Blade Moment Weighing Scale

2021 ◽  
Author(s):  
Keyword(s):  
Turbine Engine ◽  
Engine Blade

scholarly journals Study of surface quality using quasi-optimal correlation algorithms

2018 ◽  
Vol 224 ◽  
pp. 01077
Author(s):  
Nicolay V. Nosov
Keyword(s):  
Surface Roughness ◽  
Turbine Blades ◽  
Variable Component ◽  
Electronic Unit ◽  
Average Amplitude ◽  
New Approach ◽  
Turbine Engine ◽  
Computer Methods ◽  
Engine Blade ◽  
Electronic Method

The article proposes a new approach for evaluating roughness of the profile surface of gas turbine engine blade airfoils after vibratory polishing. An optical electronic unit was used to study microgeometry of blade suction and pressure sides: video imagery of the surface was processed using computer methods to obtain the average amplitude of the autocorrelation function variable component. The applied optical electronic method of evaluating microgeometry of compressor/turbine blades allows obtaining fields of surface roughness and tension concentration coefficients as well as analyzing the finish machining technology to a greater depth.

Very high cycle fatigue behaviors of a turbine engine blade alloy at various stress ratios

2017 ◽  
Vol 99 ◽  
pp. 35-43 ◽  
Author(s):  
Kun Yang ◽  
Chao He ◽  
Qi Huang ◽  
Zhi Yong Huang ◽  
Cong Wang ◽  
...  
Keyword(s):  
High Cycle Fatigue ◽  
Cycle Fatigue ◽  
Turbine Engine ◽  
Very High Cycle Fatigue ◽  
Engine Blade ◽  
Stress Ratios ◽  
Blade Alloy ◽  
Very High

Vibrations of Twisted Cantilevered Plates—Experimental Investigation

1985 ◽  
Vol 107 (1) ◽  
pp. 187-196 ◽  
Author(s):  
J. C. MacBain ◽  
R. E. Kielb ◽  
A. W. Leissa
Keyword(s):  
Research Study ◽  
Natural Frequencies ◽  
Vibration Mode ◽  
Mode Shapes ◽  
Turbine Engine ◽  
Aspect Ratios ◽  
Engine Blade ◽  
Vibrational Characteristics ◽  
Cantilevered Plates ◽  
Effect Of Support

The experimental portion of a joint government/industry/university research study on the vibrational characteristics of twisted cantilevered plates is presented. The overall purpose of the research study was to assess the capabilities and limitations of existing analytical methods in predicting the vibratory characteristics of twisted plates. Thirty cantilevered plates were precision machined at the Air Force’s Aero Propulsion Laboratory. These plates, having five different degrees of twist, two thicknesses, and three aspect ratios representative of turbine engine blade geometries, were tested for their vibration mode shapes and frequencies. The resulting nondimensional frequencies and selected mode shapes are presented as a function of plate tip twist. The trends of the plate natural frequencies as a function of the governing geometric parameters are discussed. The effect of support compliance on the plate natural frequency and its impact on numerically modeling twisted plates is also presented.

Modeling of the Superficial Laser Shock Peening Treatment Process: Application on a Titanium Aircraft Turbine Engine Blade

2011 ◽  
Vol 62 ◽  
pp. 85-94
Author(s):  
Mounir Frija ◽  
Raouf Fathallah ◽  
Lasaad Ben Fkih
Keyword(s):  
Operating Conditions ◽  
Laser Shock Peening ◽  
Fatigue Properties ◽  
Laser Shock ◽  
Turbine Engine ◽  
Foreign Object Damage ◽  
Proposed Model ◽  
Engine Blade ◽  
Shock Peening ◽  
Blade Failure

This paper presents a numerical simulation of the Laser Shock Peening (LSP) process using Finite Element Method (FEM). The majority of the controlling parameters of the process have been taken into account. The LSP loading has been characterized by using a repetitive time Gaussian increment pressure applied uniformly at the impacted zone. The used behavior law of the treated material is supposed Johnson Cook elastic-viscous-plastic coupled with damage. The proposed model leads to obtain the surface modifications (i) the in-depth residual stresses profile, (ii) the induced plastic strains profile, (iii) the geometrical surface modification of the impacted zone and (iv) the superficial damage which can be induced in few cases, where the operating conditions are not well chosen and optimized. An aeronautical application of LSP has been carried out on aircraft turbine engine blade made by Ti-6Al-4V super alloy. This mechanical treatment is applied in order to increase the durability of titanium fan blades and decrease their sensitivity to foreign object damage (FOD). The resulting surface compressive residual stress significantly improves the high-cycle-fatigue properties of the component and greatly increases resistance to blade failure. Finally, we studied the feasibility of the influence of LSP treatment on the phenomenon of crack propagation by introducing a superficial crack defect on the edge of the studied blade structure. This is physically consistent and leads to optimize the operating conditions in order to limit the damage risks.

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