introduction to gas turbines - värmeöverföring...brequet equation dw fl h fl h t sfc dw sfc t dt...
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Ideal Joule-Brayton Cycle TT
23
14
23
14
32
14,32
32
11TTTT
TTcTTc
qw
p
pNTH
T
2
3
4
Tq2-3
wn
4
31
1
2
TTPR
TT
s
1
C q4-1
1
12
1
43
PRTTPRTT
1 TTTT
12 3
4
1
14
114
1
1
4
114 1111
PRTTPR
TT
TPRTPR
TTTH
1-2: Isentropic compression
2-3: Const pressure heat addition
1
11 PR
TH
3-4: Isentropic expansion
4-1: Const pressure heat rejection
Lund University /LTH/Energy Sciences/TPE/Magnus Genrup
PR
Ideal Joule-Brayton Cycle cont’d
12432143 TTcTTcwww ppN
11
1
21
3
43 T
TTcTTTcw ppN
tTTPR
PRTT
Tcwp
N
1
31
11
3
1
111
PR
C.R.S
1111
11
PR
PRt
Tcwp
N
Lund University /LTH/Energy Sciences/TPE/Magnus Genrup
PR
Cycle design parametersOpt pressure ratio’sOpt pressure ratio’s
COT=1643K
• S/C : 25.06.4
Pressure Ratio = 10 ... 26 Burner Exit Temperature = 1473 ... 1773 [K]
22 24 26 WCLTq2 iterated for T_m_T=1173
ZW2Rstd iterated for W2=100
• C/C : 18:08
• Spec. work: 14.36.38
0.51 0.52
0.56 16
18
20 22
WCLNq2 iterated for cp_val1=70
34
.36
mal
Effi
cien
cy
0.54
0.55
12
14
E l !.32
.34
Ther
m
147
3
152
3
157
3
162
3
167
3
172
3
177
3
0.53
10 Example!
.3300 350 400 450 500
Specific Power [kW/(kg/s)]
Dotted Lines = (PWSD*0.985*0.985+cp_val7)/(WF* [g/(kN*s)]
Lund University /LTH/Energy Sciences/TPE/Magnus Genrup
2 stage compressor turbine, rotor blade temp <900°C, COT-SOT = 70°C
Specific Power [kW/(kg/s)]
The Early Days… DC8 (1958)
Lund University /LTH/Energy Sciences/TPE/Magnus Genrup
Courtesy of Boeing
Type of Propulsion Plant
Lund University /LTH/Energy Sciences/TPE/Magnus Genrup
Rolls-Royce, The Jet Engine
Brequet equationThf lhf ldW
dtTSFCdWSFCweightfuel
dtTT
timeweightfueldt
timeweightfueldt
dtdWdW
1
WdW
DL
SFCVdW
TSFCVRange
dtTSFCdWSFCTtime
ff WW
1
i
i
WWtt
f
f
WW
tt
ft
VdR
WDSFCTSFCii WW
ff WW
WdW
DL
SFCV
WdW
DL
SFCVRange
it
VdtRange ii WW WDSFCWDSFC
Steady flight condition:W = L, i.e weight = liftT = D, i.e. trust = drag
iWLVRange ln
Brequet range equation:
Lund University /LTH/Energy Sciences/TPE/Magnus Genrup
D, . . u g
fWDSFC
g
GE and Pratt & Whitney GP7000
Parameter 7270 7277
Trust (lbs) 70,000 77,000
Trust (kN) 311 343
OPR (-) 43.9 45.6
BPR (-) 8.7 8.7
Lund University /LTH/Energy Sciences/TPE/Magnus Genrup
F/LPC/HPC 1/5/19 1/5/9
HPT/LPT 2/6 2/6
Turbofan or Bypass Engine
1750
2000
441
182 1613
1250
1500
]
42434445
464 7 48
182
3
5 6 8
22 31
16
43
13
24 4
414847
452521
500
750
1000
Tem
pera
ture
[K]
1000 kPa 2000 kPa 3000 kPa 4000 kPa 5000 kPa
24 25
3
5 8
s8NGVCool.
HPT cooling
handling bleed
hp leak to bypass
HP leak to LPT exit recirculating
2 0 2 4 6 8 1 1 20
250
500
Pso (ambient) = 101 kPa
0 2
21 2213 18
s18overboard bleeds
leakage from bypassIPT cooling
IPT NGV cooling
g
LPT cooling
-.2 0 .2 .4 .6 .8 1 1.2
Entropy [kJ/(kg K)]
Lund University /LTH/Energy Sciences/TPE/Magnus Genrup
Produced with GasTurb 11
TP4000 D6 10 690 h f Ai b A400MTP4000 D6 – 10,690 shp for Airbus A400MMTU, Rolls-Royce, SNECMA, ITP (3-shaft, 25 PR, 1500 K SOT)
Lund University /LTH/Energy Sciences/TPE/Magnus Genrup
The Future?
1813 14212 24 25 16
3 4143
455
314 47 48
8
76
HP leak to LPT exit
LPT cooling
a b ced
Handling Bleed
overboard bleedsleakage from bypass
a HP leakage to bypassb HPT NGV coolingc HPT coolingd IPT NGV coolinge IPT cooling
e
35
Lund University /LTH/Energy Sciences/TPE/Magnus Genrup
Produced with GasTurb 11
e IPT cooling
The Future?
1600
1800
441400
500
600
700
100 kPa
200 k Pa
300 kPa
400 k Pa
3
1200
140042
434445
4647 48
0
100
200
300
400
Tem
pera
ture
[K] 100 kP
0 221
24
25
13 18
s18
800
1000
1200
atur
e [K
]
35
495
6
0 .04 .08 .12 .16 .2 .24 .28 .32 .36
Entropy [kJ/(kg K)]
0
400
600
800
Tem
pera
100 kPa 200 kPa 300 kPa 400 kPa
24
3
7 8
s8
0
200
400 100 kP
Pso (ambient) = 19.3 kPa
0 221
2425
13 18
s18
Lund University /LTH/Energy Sciences/TPE/Magnus Genrup
Produced with GasTurb 110 .2 .4 .6 .8 1 1.2 1.4 1.6 1.8
Entropy [kJ/(kg K)]
0
GE UDF/UHB j t iGE UDF/UHB jet engine35:1 BPR
Lund University /LTH/Energy Sciences/TPE/Magnus Genrup
Aero-derivative (CF6-80C2 → LM6000)
CF6CF6--80C280C2
LM6000LM6000--PCPC
Lund University /LTH/Energy Sciences/TPE/Magnus Genrup
Turbine cooling cont’d
Multi-passThermal BarrierThermal Barrier
Coating
Lund University /LTH/Energy Sciences/TPE/Magnus Genrup
Rolls-Royce, The Jet Engine