Ratkovská Katarína
description
Transcript of Ratkovská Katarína
![Page 1: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/1.jpg)
UNIVERSITY OF WEST BOHEMIAFACULTY OF MECHANICAL ENGINEERING
DEPARTMENT OF POWER SYSTEM ENGINEERING
Ratkovská Katarína
![Page 2: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/2.jpg)
JET ENGINES
![Page 3: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/3.jpg)
HISTORY• 17.12.1903 Orvill Wright and Wilburom Wright
- first controlled flight
![Page 4: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/4.jpg)
• 1935 Frank Whitley- patented principle of jet engines
• 27.8.1939 Hans von Ohain- HeS – 3B jet engine
W - 1
![Page 5: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/5.jpg)
He - 178
![Page 6: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/6.jpg)
TYPICAL ENGINE CUTS
0 – 1 engine intake1 – 2 compressor2 – 3 main combustion chamber3 – 4 gas turbine4 – 5 exhaust system
![Page 7: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/7.jpg)
VK 1 engine with radial
compressor
![Page 8: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/8.jpg)
RD 33
![Page 9: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/9.jpg)
MiG-29
![Page 10: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/10.jpg)
BASIC PARAMETERS
• Engine thrust [N]- It's more important parameter, which is
characterized a jet engines with direct reaction
[N ]Where:- mass flow rate []- – output gas velocity []- – air speed []
![Page 11: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/11.jpg)
• Engine thrust [N]
mass flow rate - gas [] mass flow rate - air [] – output gas velocity [] – air speed []
![Page 12: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/12.jpg)
• Engine performance P[W] turbo-prop engines
- – propeller thrust [N]- – air speed- – propeller efficiency [1]
![Page 13: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/13.jpg)
Turboprop engine TP 100
![Page 14: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/14.jpg)
TS - 21
- Turboshaft engine with free gas turbine.- It is starter of R-27F2M-300 engines.
![Page 15: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/15.jpg)
Mig 23 - FLOGGER
![Page 16: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/16.jpg)
• Air mass flow rate[] - Quantity of air that flows through the engine
in second.
=
• m – air mass [kg]• t – time [s]
![Page 17: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/17.jpg)
• Specific engine thrust Fm []
• Hour fuel consumption [kg.]
- Fuel flow rate.
![Page 18: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/18.jpg)
• Total compressor pressure ratio - Define ratio between total pressure on compressor
output to total pressure on compressor input.
– total air pressure on compressor input [Pa] – total air pressure on compressor output [Pa]
![Page 19: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/19.jpg)
COMPRESSOR TYPESCentrifugal flow compressors
![Page 20: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/20.jpg)
AXIAL FLOW COMPRESSORS
![Page 21: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/21.jpg)
• Total absolute temperature before turbine stage [K]
- is the temperature value on combustion chamber output before turbine stage.
T3T = t3T+273,15 [K]
• Total absolute temperature behind turbine stage [K]
T4T = t4T+273,15 [K]
![Page 22: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/22.jpg)
THERMAL CYCLE
• Jet engines are reactive engines witch works with atmospheric air. Purpose of air in this case is:
- Basic component of working media in thermodynamic cycle- Oxygen included in air is used during chemical reaction of burning- Accelerated air (in case of engines with direct reaction) create trust
![Page 23: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/23.jpg)
SfJE - Ideal thermal cycle
![Page 24: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/24.jpg)
SfJE with afterburner – ideal thermal cycle
![Page 25: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/25.jpg)
WORK OF IDEAL THERMAL CYCLE
![Page 26: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/26.jpg)
• In p-V diagram
• In T-s diagram
1,,. . kgJWWW adkomadexid
121. . kgJqqWid
WORK OF IDEAL THERMAL CYCLE
![Page 27: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/27.jpg)
Ideal expansion work of gas:
1013
3
5353,
.11...11..
1..
kgJe
TcTc
TTTcTTcW
pp
ppadex
![Page 28: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/28.jpg)
EFFICIENCY OF IDEAL CYCLE - SfTJE
• Quality of transformation of input heat “” to work “” is described by thermodynamic efficiency “”
111111..
1.1..
10
0
1
ee
eeTce
eTc
qW
p
pi
t
![Page 29: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/29.jpg)
DEPENDENCE OF “” BY “”
![Page 30: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/30.jpg)
WORK OF IDEAL THERMAL CYCLE - SfTJE
0
3
.
1
. TTe
opt
opt
0dedWi
1.2
0
31.2.
TT
opt
![Page 31: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/31.jpg)
CONCLUSION
• Work of ideal cycle in thermodynamics is characterized by efficiency .
• Thermal efficiency of cycle depend by pressure ratio π and temperature ration /
![Page 32: Ratkovská Katarína](https://reader033.fdocuments.us/reader033/viewer/2022061511/56816394550346895dd48d45/html5/thumbnails/32.jpg)
DISCUSSION
QUESTIONS