Principal resonance bifurcation of bending–torsion coupling of aero-engine compressor blade with assembled clearance under lateral displacement excitation of rotor shaft

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.

Download Full-text

Thermal Contact Resistance between Aero Engine Compressor Blade and Flexible Fixture

Journal of Thermal Science ◽

10.1007/s11630-020-1316-0 ◽

2020 ◽

Author(s):

Shijie Dai ◽

Dong Wang ◽

Huibo Zhang ◽

Shibo Li ◽

Zhiping Wang

Keyword(s):

Contact Resistance ◽

Thermal Contact Resistance ◽

Thermal Contact ◽

Compressor Blade ◽

Aero Engine ◽

Engine Compressor

Download Full-text

Vibration Analysis of an Aero-Engine Compressor Blade

Proceedings of the 1st International Conference on Mechanical Engineering and Material Science ◽

10.2991/mems.2012.46 ◽

2012 ◽

Author(s):

Zhang Kai ◽

Qu Wenhao ◽

Wang Wanshan

Keyword(s):

Vibration Analysis ◽

Compressor Blade ◽

Aero Engine ◽

Engine Compressor

Download Full-text

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

Key Engineering Materials ◽

10.4028/www.scientific.net/kem.684.497 ◽

2016 ◽

Vol 684 ◽

pp. 497-506 ◽

Cited By ~ 1

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.

Download Full-text

Oxidation-Resistance of (Ti,Al,Cr,Y)N Coatings Prepared by Arc Ion Plating

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.177.338 ◽

2010 ◽

Vol 177 ◽

pp. 338-341

Author(s):

Ming Sheng Li ◽

Yong Zhong Fan ◽

Shu Juan Zhang

Keyword(s):

Oxidation Resistance ◽

Crystal Size ◽

Substrate Bias ◽

Compressor Blades ◽

Arc Ion Plating ◽

Ion Plating ◽

Cr Content ◽

Heat Treated ◽

Aero Engine ◽

Engine Compressor

In this study, composite metastable (Ti0.49Al0.49Y0.02)N, (Ti0.44Al0.44Cr0.1Y0.02)N and (Ti0.34Al0.34Cr0.3Y0.02)N coatings were respectively deposited on a wrought martensite steel 1Cr11Ni2W2MoV for aero-engine compressor blades by arc ion plating technique with a pulse substrate bias. All the coatings have B1NaCl phase structure with a (220) preferred orientation and dense structures. The introduction of chromium into the coatings gave rise to a minute shrinkage of crystal lattice and a decrease of crystal size. Annealed at 800°C, Oxidation-resistance of the coatings improved with increased Cr content. But heat-treated at 900°C, the incorporation of Cr gave rise to obvious decrease of oxidation-resistance.

Download Full-text