Holography as a Routine Method of Vibration Analysis

1970 ◽  
Vol 12 (1) ◽  
pp. 37-47 ◽  
Author(s):  
B. S. Hockley ◽  
J. N. Butters
Keyword(s):  
Vibration Analysis ◽  
Turbine Blades ◽  
Compressor Blade ◽  
Routine Method ◽  
Contact Probe ◽  
Turbine Disc ◽  
Aero Engine ◽  
Engine Compressor ◽  
Compressor And Turbine Blades ◽  
Crystal Contact

The application of holography as a routine method of analysing the vibrations in aero-engine compressor and turbine blades and discs is studied to overcome the disadvantages of the usual sand pattern and piezo-electric crystal contact probe methods. The Stetson-Powell time average fringe hologram technique of vibration analysis is used to investigate the nodal patterns of a 3-in and 6-in compressor blade together with those of a 10-in diameter turbine disc and the disc with a full set of blades. Two real time holographic methods of vibration analysis are also studied. The hologram system and apparatus are simplified to enable the normal methods of clamping the vibrating components to be utilized. A completely self-contained unit that is capable of both taking the hologram and photographing the reconstructed image has been developed. The unit is a box-like structure which is simple to operate and can be used in a normal inspection bay environment for objects up to 2 ft diameter.

Analysis on nonlinear dynamics of the aero-engine compressor blade

2013 ◽  
Vol 43 (4) ◽  
pp. 345-362 ◽  
Author(s):  
Wei ZHANG ◽  
XiangYing GUO ◽  
ZhiQing FENG
Keyword(s):  
Nonlinear Dynamics ◽  
Compressor Blade ◽  
Aero Engine ◽  
Engine Compressor

Effect of Periodic Wake Passing on Film Effectiveness of Discrete Cooling Holes Around the Leading Edge of a Blunt Body

1997 ◽  
Vol 119 (2) ◽  
pp. 292-301 ◽  
Author(s):  
K. Funazaki ◽  
M. Yokota ◽  
S. Yamawaki
Keyword(s):  
Blunt Body ◽  
Free Stream ◽  
Turbine Blades ◽  
Density Ratio ◽  
Leading Edge ◽  
Test Model ◽  
Free Stream Turbulence ◽  
Aero Engine ◽  
Secondary Air ◽  
Wake Passing

Detailed studies are conducted on film effectiveness of discrete cooling holes around the leading edge of a blunt body that is subjected to periodically incoming wakes as well as free-stream turbulence with various levels of intensity. The cooling holes have a configuration similar to that of typical turbine blades except for the spanwise inclination angle. Secondary air is heated so that the temperature difference between the mainstream and secondary air is about 20 K. In this case, the air density ratio of the mainstream and secondary air becomes less than unity, therefore the flow condition encountered in an actual aero-engine cannot be simulated in terms of the density ratio. A spoke-wheel type wake generator is used in this study. In addition, three types of turbulence grids are used to elevate the free-stream turbulence intensity. We adopt three blowing ratios of the secondary air to the mainstream. For each of the blowing ratios, wall temperatures around the surface of the test model are measured by thermocouples situated inside the model. The temperature is visualized using liquid crystals in order to obtain qualitative information of film effectiveness distribution.

Designing Forging and Die Tooling for the Manufacture of Turbine Engine Compressor Blades in Siemens NX

2016 ◽  
Vol 684 ◽  
pp. 497-506 ◽  
Author(s):  
D.S. Goryainov ◽  
V.V. Anokhin ◽  
Aleksey Shlyapugin
Keyword(s):  
Point Cloud ◽  
Compressor Blade ◽  
Compressor Blades ◽  
Turbine Engine ◽  
Direct Modeling ◽  
Engine Compressor ◽  
Data Source ◽  
Theoretical Contour ◽  
Gas Turbine Compressor ◽  
Complex Parts

For designing forging and die tooling for bulk forging a necessity in using the data of the geometry of the part produced arises. Obviously, the use as a data source for designing drawings of commonly applied in “manual alternate design” (without a computer) especially such complex parts as compressor blades is not perspective because of the complexity of developing theoretical contour specified by a point cloud. In this case the use of special tooling of direct modeling that provides changing the original model of the part developed by the designers is a perspective one. It should be taken into account during the process of forging and die tooling designing that it is necessary to register the special features of the technology, upon that, the technologist should be highly proficient in using the software. The work given describes the designing technique of gas turbine compressor blade with the account of using the potential of NX Siemens program.

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