1 / 32

Ratkovská Katarína

UNIVERSITY OF WEST BOHEMIA FACULTY OF MECHANICAL ENGINEERING DEPARTMENT OF POWER SYSTEM ENGINEERING. Ratkovská Katarína. JET ENGINES. HISTORY. 17.12.1903 Orvill Wright and Wilburom Wright - first controlled flight. 1935 Frank Whitley - patented principle of jet engines

mimi
Download Presentation

Ratkovská Katarína

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript

  1. UNIVERSITY OF WESTBOHEMIAFACULTY OF MECHANICALENGINEERINGDEPARTMENT OF POWER SYSTEM ENGINEERING Ratkovská Katarína

  2. JET ENGINES

  3. HISTORY • 17.12.1903OrvillWright and WilburomWright - firstcontrolledflight

  4. 1935 Frank Whitley - patentedprincipleofjetengines • 27.8.1939Hans von Ohain - HeS – 3B jetengine W - 1

  5. He - 178

  6. TYPICAL ENGINE CUTS 0 – 1 engineintake 1 – 2 compressor 2 – 3 maincombustionchamber 3 – 4 gasturbine 4 – 5 exhaustsystem

  7. VK 1 enginewithradialcompressor

  8. RD 33

  9. MiG-29

  10. BASIC PARAMETERS • Enginethrust[N] • It's more important parameter, which ischaracterized a jet engines with direct reaction [N ] Where: - mass flow rate [] - – output gas velocity [] - – airspeed []

  11. Enginethrust[N] mass flow rate - gas[] mass flow rate - air[] – output gas velocity [] – airspeed []

  12. Engineperformance P[W] turbo-propengines - – propellerthrust [N] - – airspeed - – propellerefficiency [1]

  13. Turbopropengine TP 100

  14. TS - 21 - Turboshaftenginewithfreegasturbine. - ItisstarterofR-27F2M-300 engines.

  15. Mig 23 - FLOGGER

  16. Air mass flow rate[] • Quantity of air that flows through the engine insecond. = • m – airmass [kg] • t – time [s]

  17. Specific engine thrust Fm [] • Hour fuel consumption [kg.] - Fuelflowrate.

  18. Totalcompressorpressureratio • Define ratio between total pressure on compressoroutput to total pressure oncompressor input. – total air pressure on compressor input [Pa] – totalairpressure on compressoroutput [Pa]

  19. COMPRESSOR TYPESCentrifugalflowcompressors

  20. AXIAL FLOW COMPRESSORS

  21. Total absolute temperature before turbine stage[K] • is the temperature value on combustionchamber output before turbine stage. T3T = t3T+273,15 [K] • Total absolute temperature behind turbine stage [K] T4T = t4T+273,15 [K]

  22. THERMAL CYCLE • Jet engines are reactive engines witch works with atmospheric air. Purpose of air in this case is: -Basic component of working media inthermodynamic cycle - Oxygen included in air is used during chemicalreaction of burning - Accelerated air (in case of engines with direct reaction) create trust

  23. SfJE - Idealthermalcycle

  24. SfJE with afterburner – ideal thermal cycle

  25. WORK OF IDEAL THERMAL CYCLE

  26. WORK OF IDEAL THERMAL CYCLE • In p-V diagram • In T-s diagram

  27. Ideal expansion work of gas:

  28. EFFICIENCY OF IDEAL CYCLE -SfTJE • Quality of transformation of input heat “” to work “” is described by thermodynamic efficiency “”

  29. DEPENDENCE OF “” BY “”

  30. WORK OF IDEAL THERMAL CYCLE - SfTJE

  31. CONCLUSION • Work of ideal cycle in thermodynamics is characterized by efficiency. • Thermal efficiency of cycle depend by pressure ratio π and temperature ration /

  32. DISCUSSION QUESTIONS

More Related