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Information system and model for analyzing blade geometry and solving problems on ensuring quality of aircraft gas-turbine engines

  • Experimental Mechanics, Diagnostics, and Testing
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Abstract

A procedure is presented to improve the technology for producing turbocompressors that makes it possible to increase an aircraft engine’s quality indices by preassembling compressor blades based on the closeness of the geometric characteristics. Preassmbly uses an intelligence system, the essence of which is a model for analyzing and classifying the geometry of a blade’s complicated surface. The paper describes the mathematical model for analyzing and preassembling the blade geometry according to the closeness of the geometric characteristics using clusterization. The model and its software system are tested on a series of profiles of the concave parts of gas-turbine engine compressor blades as a result of measurement with a coordinate-measuring machine.

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Authors and Affiliations

  1. Samara State Aerospace University (National Research University), ul. Molodogvardeiskaya 151, Samara, 443001, Russia

    V. A. Pechenin, M. A. Bolotov & N. V. Ruzanov

  2. JSC Kuznetzov, sh. Zavodskoye 29, Samara, 443009, Russia

    V. A. Kondovin

Authors
  1. V. A. Pechenin
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  2. M. A. Bolotov
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  3. N. V. Ruzanov
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  4. V. A. Kondovin
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Corresponding author

Correspondence to V. A. Pechenin.

Additional information

Original Russian Text © V.A. Pechenin, M.A. Bolotov, N.V. Ruzanov, V.A. Kondovin, 2016, published in Problemy Mashinostroeniya i Nadezhnosti Mashin, 2016, No. 2, pp. 105–111.

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Pechenin, V.A., Bolotov, M.A., Ruzanov, N.V. et al. Information system and model for analyzing blade geometry and solving problems on ensuring quality of aircraft gas-turbine engines. J. Mach. Manuf. Reliab. 45, 185–190 (2016). https://doi.org/10.3103/S1052618816020102

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  • DOI: https://doi.org/10.3103/S1052618816020102

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