analysis of thrust equation for ideal turbo jet engine p m v subbarao professor mechanical...
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Analysis of Thrust Equation for Ideal Turbo Jet Engine
P M V Subbarao
Professor
Mechanical Engineering Department
Understanding the Features of A True Flying Machine Muscles
….
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Ideal Turbo Jet Cycle
T0
1,2
3
4
5,6
s
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p0
s
1,2
34
5,6
Ideal Turbo Jet Cycle
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Thrust
acjetairT VVfmF 1
pTVStation ac &,:1
fppfV jet &, 030
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pTVStation ac &,:1
002002 &, ppTTVci
0,0030,003 & prpTT comppcompp
0,0040,004 & prpTT comppcc
cc
p
comppcc
TcVH
f
00
,00
..
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Thrust
Isentropic Expansion in an Active Turbine
0,0,0,00405 TTT turbpccturbp
0,0,005 prrp comppturbp
turbppturbine TcfmW ,004 11
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Theory of Jet Propulsion : Jet Enough Work
The power input to the compressor = The power output of the turbine
turbinecompressor WW
turbppcomppp TcfmTcm ,004,00 111
turbpcompp TfT ,004,00 111
0,004 TT cc
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0,0,0,00 111 TfT ccturbpcompp
ccturbpcompp f ,0,0,0 111
cc
comppturbp f ,0
,0,0 1
11
cc
comppturbp f ,0
,0,0 1
11
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cc
comppccpturbine
fTcfmW
,0
,00,0 1
111
05041 TTcfmW pturbine
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Isentropic Expansion in a Passive Turbine(Nozzle)
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Thermodynamic SSSF model for Nozzle
0605 11 hfmhfm
06050605 & ppTT
2
26
605
VTcTc pp
605
26
2TTc
Vp
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1
0505
1
05
6056
p
pT
p
pTT
Limit of Utilization: Open Cycle Engine: Just to Ambient Pressure!!!
04,00504,005 & prpTT turbpturbp
1
04,004,06
pr
pTT
turbpturbp
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1
04
1
,004,06
1
p
p
rTT
turbpturbp
1
04046
p
pTT
0,00304 prpp compp
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1
0,0046
pr
pTT
compp
1
0,0
046
1
p
p
r
TT
compp
1
0,0
046
p
pTT
compp
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1
0,0
,006
p
pTT
compp
cc
605
26
2TTc
Vp
Maximum Obtainable Jet Kinetic Energy:
compp
ccTT,0
,06
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04,0
,005 1
11 T
fT
cc
compp
04,005 TT turbp
00
04
,0
,005 1
11 T
T
T
fT
cc
compp
0,0,0
,005 1
11 T
fT cc
cc
compp
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cc
p
comppcc
TcVH
f
00
,00
..
62 05
26 TTcV
p
compp
ccTT,0
,06
0,0,0
,005 1
11 T
fT cc
cc
compp
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62 05
26 TTcV
p
compp
cccc
cc
comppp TT
fc
V
,0
,00,0
,0
,02
6
1
11
2
cc
p
comppcc
TcVH
f
00
,00
..
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compp
cccc
cc
ccp
comppcc
comppp TT
TcVH
cV
,0
,00,0
,0
00
,00
,02
6
..1
11
2
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compp
cccc
cc
comppp T
T
fTc
V
,0
,00,0
,0
,02
6
1
11
2
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Generation of Thrust : The Capacity
acjetT VVfmF 1
ac
compp
cccc
cc
compppT V
T
T
fTcfmF
,0
,00,0
,0
,0
1
1121
compp
cccc
cc
compppjet T
T
fTcV
,0
,00,0
,0
,0
1
112
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Specific Thrust S
acjet VVfS 1
ac
compp
cccc
cc
comppp V
T
T
fTcfS
,0
,00,0
,0
,0
1
1121
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Propulsive Power or Thrust Power:
acjetacacTp VVfmVVFP 1
Thrust Specific Fuel Consumption TSFC
acjetacjet
fuel
T
fuel
VVf
f
VVfm
m
F
mTSFC
11
ac
compp
cccc
cc
comppp V
TT
fTcf
fTSFC
,0
,00,0
,0
,0
1
1121
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Aviation Appreciation
Propulsion Efficiency
Jet theofPower Kinetic Available
PowerThrustpropulsion
2212 acjet
acTpropulsion
VVfm
VF
22)1(
2
1
acjet
acacjetpropulsion
VVfm
VVVfm
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22)1(
12
acjet
acacjetpropulsion VVf
VVVf
compp
cccc
cc
compppjet T
T
fTcV
,0
,00,0
,0
,0
1
112
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Thermodynamic Appreciation
Thermodynamic Efficiency
InputPower Thermal
Jet theofPower Kinetic Availablethermal
..
12
22
VHm
VVfm
fuel
acjet
thermal
..
121 22
VHf
VVf acjet
thermal
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22)1(
12
acjet
acacjetpropulsion VVf
VVVf
thermalpropulsionoveral
..
121 22
VHf
VVf acjet
thermal
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22)1(
12
acjet
acacjetpropulsion VVf
VVVf
thermalpropulsionoveral
..
121 22
VHf
VVf acjet
thermal
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Jet engine Performance Parameters
ac
compp
cccc
cc
comppp V
TT
fTcf
fTSFC
,0
,00,0
,0
,0
1
1121
ac
compp
cccc
cc
comppp V
T
T
fTcfS
,0
,00,0
,0
,0
1
1121