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Assignment of propulsion system lecturer about analysis of turbofan engines
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PARAMETRIC CYCLE ANALYSIS OF TURBOFAN ENGINES
PROPULSI PESAWAT TERBANG
AE 3212
AGUSTINUS DIMAS 13608039
FAKULTAS TEKNIK MESIN DAN DIRGANTARA
JURUSAN AERONOTIKA & ASTRONOTIKA
INSTITUT TEKNOLOGI BANDUNG
2011
INPUTS : M0, T0, γ, CP, hPR, Tt4, πc, πf, α
OUTPUTS : F/ṁ0, f, S, ηT, ηP, ηO, FR
EQUATIONS :
R= γ−1γ
Cp
a0=√γR gc T 0
τ r=1+γ−12
M 02
τ λ=T t 4
T 0
τ c=( πc )(γ−1)
γ
τ f=( π f )( γ−1 )
γ
V 9
a0=√ 2
γ−1 {τ λ−τ r [τc−1+α (τ f−1 ) ]−τ λ
τ r τ c}
V 19
a0=√ 2
γ−1( τ λ τ f −1 )
Specific Thrust
Fm0
=a0gc
11+α [ V 9
a0−M 0+α(V 19
a0−M 0)]
Fuel/air Ratio
f =Cp T 0
hPR(τ λ−τ r τ c )
Thrust Specific Fuel Consumption
S= f
(1+α )( Fm0
)Thermal Efficiency
ηT=1−1
τ r τ c
Propulsive Efficiency
ηP=2M 0
V 9
a0−M 0+α(V 19
a0−M 0)
V 92
a02−M 0
2+α(V 192
a02 −M 0
2)Overall Efficiency
ηo=ηT ηP
Thrust Ratio
FR=
V 9
a0−M 0
V 19
a0−M 0
0 5 10 15 20 25 30100
200
300
400
500
600
700
specific thrust
0.511.52345812
πc
F/ṁ0
[N/(k
g/se
c)]
Gambar 1 Ideal turbofan performance versus πc, for πf =2 and M0=0.9: specific thrust
0 5 10 15 20 25 3012
14
16
18
20
22
24
26
28
thrust specific fuel consumption
0.511.52345812
πc
S[mg/
(N.se
c)]
Gambar 2 Ideal turbofan performance versus πc, for πf =2 and M0=0.9: thrust specific fuel consumption
0 5 10 15 20 25 300.022
0.024
0.026
0.028
0.030
0.032
fuel/air ratio
f
πc
f
Gambar 3 Ideal turbofan performance versus πc, for πf =2 and M0=0.9: fuel/air ratio
0 5 10 15 20 25 3020
30
40
50
60
70
thermal efficiency
ηT
πc
ηT
Gambar 4 Ideal turbofan performance versus πc, for πf =2 and M0=0.9: thermal efficiency
0 5 10 15 20 25 3020
30
40
50
60
70
80
propulsive and overall efficiencies
0.5 11.5 23 45 812 0.51 1.52 34 58 12
πc
ηP(%)η0
Gambar 5 Ideal turbofan performance versus πc, for πf =2 and M0=0.9: propulsive and overall efficiencies
0 5 10 15 20 25 300
1
2
3
4
5
6
specific thrust
0.511.52345812
πc
FR
Gambar 6 Ideal turbofan performance versus πc, for πf =2 and M0=0.9: thrust ratio
0 5 10 15 20 25 30160.00
180.00
200.00
220.00
240.00
260.00
280.00
300.00
specific thrust
1.21.5233.544.5
πc
F/ṁ0
[N/(k
g/se
c)]
Gambar 7 Ideal turbofan performance versus πc, for α=5 and M0=0.9: specific thrust
0 5 10 15 20 25 3012
14
16
18
20
22
24
26
28
thrust specific fuel consumption
1.21.5233.544.5
πc
S[mg/
(N.se
c)]
Gambar 8 Ideal turbofan performance versus πc, for α=5 and M0=0.9: thrust specific fuel consumption
0 5 10 15 20 25 3045
50
55
60
65
70
75
propulsive efficiency
1.5233.544.5
πc
ηP(%)
Gambar 9 Ideal turbofan performance versus πc, for α=5 and M0=0.9: propulsive efficiency
0 5 10 15 20 25 3015
20
25
30
35
40
45
overall efficiency
1.21.5233.544.5
πc
η0(%)
Gambar 10 Ideal turbofan performance versus πc, for α=5 and M0=0.9: overall efficiency
0 5 10 15 20 25 300
2
4
6
8
10
thrust ratio
1.21.5233.544.5
πc
FR
Gambar 11 Ideal turbofan performance versus πc, for α=5 and M0=0.9: thrust ratio
1 2 3 4 5 650
100
150
200
250
300
350
400
specific thrust
3456781012
πc
F/ṁ0
[N/(k
g/se
c)]
Gambar 12 Ideal turbofan performance versus πf, for πc =24 and M0=0.9: specific thrust
1 2 3 4 5 610
12
14
16
18
20
22
24
26
thrust specific fuel consumption
3456781012
πc
S[mg/
(N.se
c)]
Gambar 13 Ideal turbofan performance versus πf, for πc =24 and M0=0.9: thrust specific fuel consumption
1 2 3 4 5 640
45
50
55
60
65
70
75
80
propulsive efficiency
3456781012
πc
ηP(%)
Gambar 14 Ideal turbofan performance versus πf, for πc =24 and M0=0.9: propulsive efficiency
1 2 3 4 5 60
1
2
3
4
5
thrust ratio
3456781012
πc
FR
Gambar 15 Ideal turbofan performance versus πf, for πc =24 and M0=0.9: thrust ratio
0 2 4 6 8 10 12100.00
200.00
300.00
400.00
500.00
600.00
specific thrust
1.522.533.544.5
πc
F/ṁ0
[N/(k
g/se
c)]
Gambar 16 Ideal turbofan performance versus α, for πc =24 and M0=0.9: specific thrust
0 2 4 6 8 10 1212.00
14.00
16.00
18.00
20.00
22.00
thrust specific fuel consumption
1.522.533.544.5
πc
S[mg/
(N.se
c)]
Gambar 17 Ideal turbofan performance versus α, for πc =24 and M0=0.9: thrust specific fuel consumption
0 2 4 6 8 10 1230
40
50
60
70
80
propulsive efficiency
1.522.533.544.5
πc
ηP(%)
Gambar 18 Ideal turbofan performance versus α, for πc =24 and M0=0.9: propulsive efficiency
0 2 4 6 8 10 120
1
2
3
4
5
thrust ratio
1.522.533.544.5
πc
FR
Gambar 19 Ideal turbofan performance versus α, for πc =24 and M0=0.9: thrust ratio
0 0.5 1 1.5 2 2.5 30.00
100.00
200.00
300.00
400.00
500.00
600.00
700.00
800.00
specific thrust
0.5125810
M0
F/ṁ0
[N/(k
g/se
c)]
Gambar 20 Ideal turbofan performance versus M0, for πc =24 and πf =2: specific thrust
0 0.5 1 1.5 2 2.5 35.00
10.00
15.00
20.00
25.00
30.00
thrust specific fuel consumption
0.5125810
M0
S[mg/
(N.se
c)]
Gambar 21 Ideal turbofan performance versus M0, for πc =24 and πf =2: thrust specific fuel consumption
0 0.5 1 1.5 2 2.5 30
20
40
60
80
100
propulsive efficiencies
0.5125810ηT
M0
ηP(%)
Gambar 22 Ideal turbofan performance versus M0, for πc =24 and πf =2: propulsive efficiency
0 0.5 1 1.5 2 2.5 30
10
20
30
40
50
60
70
80
overall efficiency
0.5125810
M0
η0(%)
Gambar 23 Ideal turbofan performance versus M0, for πc =24 and πf =2: overall efficiency
0 0.5 1 1.5 2 2.5 30
1
2
3
4
5
6
thrust ratio
0.5125810
M0
FR
Gambar 24 Ideal turbofan performance versus M0, for πc =24 and πf =2: thrust ratio
0 0.5 1 1.5 2 2.5 30.00
200.00
400.00
600.00
800.00
1000.00
1200.00
specific thrust
00.20.5125
M0
F/ṁ0
[N/(k
g/se
c)]
Gambar 25 Ideal turbofan performance versus M0, for πc =24 and πf =3: specific thrust
0 0.5 1 1.5 2 2.5 35.00
10.00
15.00
20.00
25.00
30.00
thrust specific fuel consumption
00.20.5125
M0
S[mg/
(N.se
c)]
Gambar 26 Ideal turbofan performance versus M0, for πc =24 and πf =3: thrust specific fuel consumption
0 0.5 1 1.5 2 2.5 30
20
40
60
80
100
propulsive efficiencies
00.20.5125ηT
M0
ηP(%)
Gambar 27 Ideal turbofan performance versus M0, for πc =24 and πf =3: propulsive efficiency
0 0.5 1 1.5 2 2.5 30
10
20
30
40
50
60
70
80
overall efficiency
00.20.5125
M0
η0(%)
Gambar 28 Ideal turbofan performance versus M0, for πc =24 and πf =3: overall efficiency
0 0.5 1 1.5 2 2.5 30
0.5
1
1.5
2
2.5
3
3.5
thrust ratio
00.20.5125
M0
FR
Gambar 29 Ideal turbofan performance versus M0, for πc =24 and πf =3: thrust ratio
