Abstract
Gas turbine engines are very important in aviation. Pressure is one of the key thermodynamic parameters which, first of all, suffers radical change within the flow passage of a gas turbine, on the other hand, there are several accessories like fuel and oil supply, in which the pressure of the working medium is essential. The measurement of this variable is therefore inevitable in data acquisition or engine control systems. The author shows the process of development of an advanced pressure signal acquisition card that fits into a modular electronic control system of a turbojet engine. The unit incorporates numerous experiences gathered with the previous generation of this module regarding power supply and integrated sensors as well. Furthermore, there are several innovations that enable a more efficient installation, data acquisition and built-in test possibilities. The most important difference is the 32-bit ARM Cortex-M0+ microcontroller which allows faster operation which allows the acquisition of more signals, including additional functions as thrust measurement, digital input/output handling and many others. The unit operation was thoroughly assessed using simulated and real operating conditions as well.
Highlights
Gas turbine engines are very widely used in various fields of industry; their safe and economical operation is rather important
The data obtained on a turbojet engine can be used on larger, more complex engine types, due to the similar basic operating principle [5,6]
After creating a software for the single pressure module which was able to read the communication from the RS232 channel, another program was realized in order to monitor all the messages sent through the controller area network (CAN) bus
Summary
Gas turbine engines are very widely used in various fields of industry; their safe and economical operation is rather important. There are some cases where their simplicity overcomes the previously mentioned drawbacks These special roles include military drones [1], hobby radio-controlled aircraft [2]; they can be used as test bed for different research purposes [3,4]. At the Department of Aeronautics and Naval Architecture, there is a single stream, single-spool turbojet engine with variable area exhaust nozzle, type TKT-1. This unit serves already for more than ten years for research and education purposes. It features a modular, full authority digital electronic control (FADEC) system, which was previously presented by the author [7].
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
