Next Article in Journal
A Digital Lock-In Amplifier for Use at Temperatures of up to 200 °C
Next Article in Special Issue
Probabilistic Model Updating for Sizing of Hole-Edge Crack Using Fiber Bragg Grating Sensors and the High-Order Extended Finite Element Method
Previous Article in Journal
Tunnel Magnetoresistance Sensors with Magnetostrictive Electrodes: Strain Sensors
Previous Article in Special Issue
Strain Measurement in Aluminium Alloy during the Solidification Process Using Embedded Fibre Bragg Gratings
Article Menu

Export Article

Open AccessArticle
Sensors 2016, 16(11), 1897; doi:10.3390/s16111897

Tip-Clearance Measurement in the First Stage of the Compressor of an Aircraft Engine

1
Department of Communications Engineering, Engineering School of Bilbao, University of the Basque Country UPV/EHU, Alda. Urquijo s/n E-48013 Bilbao, Spain
2
Air Force Institute of Technology (Instytut Techniczny Wojsk Lotniczych), ul. Ksiecia Boleslawa 6 01-494 Warszawa, Poland
*
Author to whom correspondence should be addressed.
Academic Editor: Jose Miguel López Higuera
Received: 30 September 2016 / Revised: 2 November 2016 / Accepted: 4 November 2016 / Published: 11 November 2016
(This article belongs to the Special Issue Optical Fiber Sensors 2016)
View Full-Text   |   Download PDF [6810 KB, uploaded 15 November 2016]   |  

Abstract

In this article, we report the design of a reflective intensity-modulated optical fiber sensor for blade tip-clearance measurement, and the experimental results for the first stage of a compressor of an aircraft engine operating in real conditions. The tests were performed in a ground test cell, where the engine completed four cycles from idling state to takeoff and back to idling state. During these tests, the rotational speed of the compressor ranged between 7000 and 15,600 rpm. The main component of the sensor is a tetrafurcated bundle of optical fibers, with which the resulting precision of the experimental measurements was 12 µm for a measurement range from 2 to 4 mm. To get this precision the effect of temperature on the optoelectronic components of the sensor was compensated by calibrating the sensor in a climate chamber. A custom-designed MATLAB program was employed to simulate the behavior of the sensor prior to its manufacture. View Full-Text
Keywords: tip clearance; optical fiber sensor; aircraft engine; optical fiber bundle; compressor tip clearance; optical fiber sensor; aircraft engine; optical fiber bundle; compressor
Figures

Figure 1

This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited. (CC BY 4.0).

Scifeed alert for new publications

Never miss any articles matching your research from any publisher
  • Get alerts for new papers matching your research
  • Find out the new papers from selected authors
  • Updated daily for 49'000+ journals and 6000+ publishers
  • Define your Scifeed now

SciFeed Share & Cite This Article

MDPI and ACS Style

García, I.; Przysowa, R.; Amorebieta, J.; Zubia, J. Tip-Clearance Measurement in the First Stage of the Compressor of an Aircraft Engine. Sensors 2016, 16, 1897.

Show more citation formats Show less citations formats

Note that from the first issue of 2016, MDPI journals use article numbers instead of page numbers. See further details here.

Related Articles

Article Metrics

Article Access Statistics

1

Comments

[Return to top]
Sensors EISSN 1424-8220 Published by MDPI AG, Basel, Switzerland RSS E-Mail Table of Contents Alert
Back to Top