Optical Systems For Gas Turbine Engines

Mark Wrigley

doi:10.1117/12.938481

20 October 1986 Optical Systems For Gas Turbine Engines

Mark Wrigley

Proceedings Volume 0656, Contemporary Optical Instrument Design, Fabrication, and Testing; (1986) https://doi.org/10.1117/12.938481
Event: 1986 International Symposium/Innsbruck, 1986, Innsbruck, Austria

Abstract

The use of optical systems for data acquisition and transmission is becoming increasingly popular for aviation applications. Features such as weight and immunity to high levels of E.M.C. are distinct advantages over conventional electronic systems. In some cases optical transducers provide a means of measurememt which would otherwise be impossible. One such transducer is the Turbine Blade Pyrometer Transducer. This instrument determines gas turbine blade temperature by measuring emitted visible and near infrared radiation. The transducer is an engine mounted electro optical system which provides a voltage output proportional to turbine blade radiance. As such it must be designed to withstand the demanding environment of a gas turbine engine.

Citation Download Citation

Mark Wrigley "Optical Systems For Gas Turbine Engines", Proc. SPIE 0656, Contemporary Optical Instrument Design, Fabrication, and Testing, (20 October 1986); https://doi.org/10.1117/12.938481

ACCESS THE FULL ARTICLE

INSTITUTIONAL
Select your institution to access the SPIE Digital Library.

SELECT YOUR INSTITUTION

PERSONAL
Sign in with your SPIE account to access your personal subscriptions or to use specific features such as save to my library, sign up for alerts, save searches, etc.

PERSONAL SIGN IN

No SPIE Account? Create one

PURCHASE THIS CONTENT

SUBSCRIBE TO DIGITAL LIBRARY

50 downloads per 1-year subscription

Members: $195

Non-members: $335 ADD TO CART

25 downloads per 1 - year subscription

Members: $145

Non-members: $250 ADD TO CART

PURCHASE SINGLE ARTICLE

Includes PDF, HTML & Video, when available