parametric cycle analysis of turbofan engines
DESCRIPTION
Assignment of propulsion system lecturer about analysis of turbofan enginesTRANSCRIPT
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