Theory of aircraft engines II

Garant předmětu:

Lecturer:

Tutor:

Supervisor:

Department of Aerospace Engineering

Synopsis:

In the course, students are acquainted with the physical nature of the processes taking place in aircraft engines. The explanation is focused on clarifying the operation of single-stream, turboshaft and double-stream engines. An analysis of the equilibrium runs of these engines is performed, including the subsequent determination of speed, speed and altitude characteristics. Detailed knowledge of the parameters of vane engines will allow to analyze their behavior in air traffic in terms of diagnostics of the air gas tract.

Requirements:

Syllabus of lectures:

1. Basic parameters of single-stream engine (JPM). Circulation of JPM in p-v and T-s diagrams.

2. Analysis of the influence of compressor compression, temperature in front of the turbine and atmospheric temperature on the work of the circle, specific thrust and specific fuel consumption.

3. Efficinecy of JPM. Balanced operation of single-rotor JPM. Detailed analysis of the influence of JPM regulation (change of nozzle diameter, air discharge from the compressor, adjustment of stator blades) on the course of equilibrium operation.

4. Revolution, speed and altitude characteristics of JPM. Similarity parameters and reduced JPM parameters. JPM acceleration and deceleration.

5. Two-rotor JPM. Principle of solution of equilibrium operation of two-rotor JPM. Revolution, speed and height characteristics of a twin-rotor JPM.

6. Distribution of turboshaft engines (THM). THM circulation in p-v and T-s diagrams. Analysis of the influence of compressor compression, temperature before the turbine and atmospheric temperature on the work of THM circulation, specific power and specific fuel consumption.

7. THM efficiencies. Balanced operation of single-shaft THM. Balanced operation of two-shaft THM.

8. Revolution, speed and altitude characteristics of THM. Similarity parameters and reduced THM parameters. THM with heat recovery.

9. Classification of dual-stream engines (DPM). Main parameters of DPM. DPM thermal circulation analysis.

10. Influence of bypass ratio, energy distribution coefficient, temperature in front of the turbine, air compression in the first and second stream on specific thrust and specific fuel consumption. Principle of solution of equilibrium operation of two-shaft DPM.

11. Revolution, speed and altitude characteristics of DPM. DPM with mixing chamber.

12. Short-term increase in thrust (power) of jet and turboshaft engines. Short-term exceeding of the maximum permitted engine speed, injection of liquid into the compressor, injection of liquid into the combustion chamber. Use of additional fuel combustion behind the turbine. Influence of additional fuel combustion behind the turbine on the course of speed characteristics of single-stream and double-stream engines.

13. Perspectives of development of aircraft vane engines.

Syllabus of tutorials:

Study Objective:

Study materials:

Cohen, H., Rogers, G. F. C., Saravanamuttoo, H. I. H., Straznicky, P. V., Nix, A.C. : Gas Turbine Theory . 7th edition. Pearson 2017. IBSN 9781-292-09309-3.

Cumpsty, N. A. : Compressor Aerodynamics. Krieger Pub Co; 2nd edition 2004. IBSN -13 : 978-1575242477.

Note:

Further information:

No time-table has been prepared for this course

The course is a part of the following study plans: