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8/10/2019 Engines en1 v1
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0. 0.543330 -4.--01,5-
C*ose &r/&t 0.3 0.2-,55342 1,1.13521-,30.22124-14-4 1,2
1 2
t 21.502-0-1- m/s
1t 31.-20 m/s
a 333.4-5441 m/s
r 140.-513535
61t 0.5,44--04, transoni( speed
*ub radius 0.132-4,-1 mmean radius 0.20-41200, m
02 1.5,55 bar
T02 330.,04303 K
T2 31.020131 K
2 1.3--,54- bar
densti)2 1.51214125 kg/m3
A2 0.154305,5 m2
7lade8*eig*t8e9it 0.1140051 m&t8e9it 0.2,,,14,05 m
&r8e9it 0.142140 m
0.1
umber of stage design
Temperature rise t*roug* fan 42.,04302 K
mean blade speed 211.12-0303 m/s
71 54.,0-24401, deg
1 25.-,1 m/s
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tan b1 ; tanb2
Ca 150 m/s
1,2 &$
&t 0.2-,55342 0.2-,55342
&m 0.20-41200, 0.20-41200,
&r 0.132-4,-1 0.132-4,-1
roperties 1st 2nd stage
01 1.01
t !m/s# 21.502-0-1- 21.502-0-1-02
m !m/s# 211.12-0303 211.12-0303---
r !m/s# 140.-513535 140.-51353551
T!K# 2 30.4
work done fa(tor 0. 0.3
dT !K# 21.4 20.4
delta w*irl +elo(i) dCw !m/s# 103.4,511, 104.41,5-44-13
Cw1 !m/s# 0 11.1221---Cw2 !m/s# 103.4,511, 115.54,3,34
tan71;tan72 2.303221 1.-051502
tan71"tan72 1.44304,5 0.,,1104,5
71 !deg# 54.,0-24401, 53.12-141
72 !deg# 35.54-202251 32.5054545,4
a1 !deg# 0 4.243502-1
a2 !deg# 34.-21051, 3-.,0-351,,5
a3!deg# 4.243502-1 0
71"72 !deg# 1.0,0041-,5 20.,24250355
2/1 !de
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C=6&>$$=& ???
0
211.12-
0
32.
0.5
25
140.004
",.,,4352133.340,
1.-051
0.333,,
55.44355
2-.4101
"2.54322
41.,350
2.0333,
0.,351
0.-4-31
1.2545
1 5212
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Known
T*rust 13000
Cruise speed 21.44444444 m/s
&ange 355 km
&ate of (limb 124., m/min
Ceiling 13-1, m
@eig*t!empt)# 4004 kg
ma9 takeoff -200 kg
@ing span 15. m
engt* 14. m@ing area 31. m2
T)pi(al passenger people $eparate (old and *ot
fan dri+en b) turbin
umber of spools 2
=+erall pressure rat 1
7) pass ratio 1. 11.,1203225
an pressure ratio 1.55
Turbine inlet Temp 1235 K Area of intake 0.104-,an'(omp'turb pol) 0. &ad intake 0.24,233 m
:sen eff of noBBle 0.5
me(*ani(al eff 0.
Combus press loss 1.5 bar
Total air mass flow 35 kg/s --.1,1-1--
o 1 bar
T0 2 K
gamma'(omp 1.4000-
gamma' e9p 1.333 55
Cpa 1.005 densit) 1
Cpg 1.14 densit) 2
(ompression e9pansion ,-,
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$pe(ifi( T*rust 352.12 s/kg
densit) 1.1520-44 Total t*urst 1235.21-
A 0.0,,341442 Total t*urst 2-23.1 lb
0.14-0-05 35.212
f/a 0.015 oBBle
mf 0.12,3113 kg/s Area 0.11
mf ,5.30-21003 kg/*r &adius 0.1-121
$C 0.00004232 kg/s
$C 0.1530050- kg/*
Total T*rust 12352.1-
$pe(ifi( T*rust 352.12 s/kgf/a t*eor) 0.015
f/a a(tual 0.015152
mf 0.12,3 kg/s
mf ,5.30-2 kg/*r
$C 0.15301 kg/*
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noBBles are used
e and (ompressor b)
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Compressor design
known
Compressure pressure ratio 1.55 4.15
Air mass flow 35 kg/s
Turbine inlet Temp 1235 K
Cpa 1.005
amma 1.4
amma/!amma"1# 3.5
$teps%
1" &otational speed' annulus dimensions
2" number of stages' assumed effi(ien()
3" air angles for ea(* stage' mean radius
4" +ariation of air angles from root to tip
5" (ompressabilit) effe(ts
," (ompresssor blading
-" (*e(k on effi(ien()
" off design performan(e" rig testing
Assumption
t 20 m/s
Ca 150 m/s
*ub"tip ratio 0.4"0.,
T01 2 K
01 1.01 bar !n"1#/n 0.31-5
fan eff 0.
Cal(ulated
C1 150 m/s
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0. 0.543330 -4.--01,5-
C*ose &r/&t 0.3 0.2-,55342 1,1.13521-,3
0.22124-14-4 1,2
1 2
t 21.502-0-1- m/s
1t 31.-20 m/s
a 333.4-5441 m/s
r 140.-513535
61t 0.5,44--04, transoni( speed
*ub radius 0.132-4,-1 mmean radius 0.20-41200, m
02 1.5,55 bar
T02 330.,04303 K
T2 31.020131 K
2 1.3--,54- bar
densti)2 1.51214125 kg/m3
A2 0.154305,5 m2
7lade8*eig*t8e9it 0.1140051 m&t8e9it 0.2,,,14,05 m
&r8e9it 0.142140 m
0.1
umber of stage design
Temperature rise t*roug* fan 42.,04302 K
mean blade speed 211.12-0303 m/s
71 54.,0-24401, deg
1 25.-,1 m/s
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a2t 2-.4-511333 2.3113545
E=& &==T 0.-5400-,-2 0.-1,-03032
C3 150.41234303 150.14--23124
T3 2.1443412 31.53-33,1
3 1.112-32253, 1.3-324,124
dens3 1.300415-122 1.5010,21
A3 0.1-4201- 0.15535---25
* 0.13-,-31- 0.1120-,55
entr)
&t $TAT
&r $TAT&t &=T 0.2-,55342 0.2,,,14,05
&r &=T 0.132-4,-1 0.142140
>9it
&t $TAT 0.3453125 0.32,223203
&r $TAT 0.20--1-434 0.20-015,30
&t &=T 0.2-,40,,2 0.2,,212455
&r &=T 0.20-5,4-2 0.20-21-415-t rot 21.34-45, 2-1.504-313
r rot 211.2-- 210.21,3334
Cw2t -.0022,-2 0.05043-041
Cw2r 103.-1250, 104.04--332-31
Cw1t 0 .,5553102
Cw1r 0 15.5-5140021
widt* 0.0452-3 0.03-35,5 0.05,2
0.0114-315 0.0033-1, 0.02140-
0.10-03,
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0.11401
C=6&>$$=& ???
120.51-
211.12-
0
32.
0.5
25
140.004
",.,,4352133.340,
1.-051
0.333,,
55.44355
2-.4101
"2.54322
41.,350
2.0333,
0.,351
0.-4-31
1.2545
1 5212
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30 m/s
mass flow 12.0,- kg/s
inlet radius 0.1223 m
inlet *ub 0.100,
:nlet area 0.01001 m2
outlet radius *ub 0.114112outlet radius Tip 0.15114, 0.03-034
=utlet area 0.030,1 m2
0.0
rimrar) (ombustor +olume 0.01 0.01
(omb
densit) 1 .2----- kg/m3
densit) 2 4.,551,5 kg/m4
a+erage densit) ,.,,4-1 kg/m5
Area 0.05--4 m2
*ub radius middle 0.114112 m
tip radius middle 0.1--21 m 0.0,30
engt* 0.0,-5 m
2.5"3F=E
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Compressor design
knownCompressure pressure ratio 11.,1 4.15
Air mass flow 12.0,,551-2 kg/s
Turbine inlet Temp 1235 K
Cpa 1.005
amma 1.4
amma/!amma"1# 3.5
$teps%
1" &otational speed' annulus dimensions
2" number of stages' assumed effi(ien()
3" air angles for ea(* stage' mean radius
4" +ariation of air angles from root to tip
5" (ompressabilit) effe(ts
," (ompresssor blading
-" (*e(k on effi(ien()
" off design performan(e
" rig testing
Assumption &eason
t 350 m/s re+iousl) s*own t*at t*is will lead to a((ept
Ca 150 m/s 6odest' no :Gs' no w*irl +elo(it) at entran(
*ub"tip ratio 0.4"0.,
T01 32. K
01 1.4-254002, bar o loss in intake
!n"1#/n 0.31-5
isen eff 0.
Cal(ulated
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*ub radius 0.0--3450415 m
mean radius 0.11,01-5,22 m
02 1-.0,1-323 bar T02 -1.34-02- K
T2 -0-.153,042 K
2 1,.11--53-04 bar
densti)2 -.-315,5-5 kg/m3
A2 0.01001332 m2 e9it annulus area
7lade8*eig*t8e9it 0.013434,-, m
&t8e9it 0.12232, m
&r8e9it 0.100524 m
umber of stage design
Temperature rise t*roug* (om 3.54-02- K
mean blade speed 2,2.425543204 m/s
Ca1Ca2Ca
71 ,0.2411,421 deg
1 302.2-002121 m/s
de
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T!K# 32. 351.5, 3-,.0, 400.0, 423.0, 445.0,
work done fa(tor 0. 0.3 0. 0.3 0.3 0.3
dT !K# 21.-, 24.5 24 23 22 22
delta w*irl +elo(i) dCw !m/s# 5.03403200-- 100. 104.4452 10,.123 101.50 101.50
Cw1 !m/s# ",.,,43521455 2.2325 -.01- -.15125 0.452- 0.452-
Cw2 !m/s# -.3,,-,21 12.1-21 13.4354 14.2-43 11.,-3 11.,-3
tan71 ; Tan72 2.,1531 2.44305 1.-4504 1.-4504 1.-4504 1.-4504
tan71 " Tan73 1.1-5-455 0.,-252 0.,,301 0.-0-4- 0.,-,-2- 0.,-,-2-
71 !deg# ,2.-2035323 5-.3541 50.-2,22 50.542 50.50042 50.50042
1 32.0,5544555
2 0
72 !deg# 50.210000,,1 41.,1,4 2-.--134 2-.51 2.20, 2.20,
a1 !deg# "2.543220402 10.,-04 2-.--134 2-.51 2.20, 2.20,
a2 !deg# 2-.554-131 40.-332 50.-2,22 50.542 50.50042 50.50042
a3!deg# 10.,-03-1-0- 2-.--134 2-.51 2.20, 2.20, 2.20,
71"72 !deg# 11.-1034,,2 15.-342 22.54 23.3343 22.212 22.212
2/1 !de
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&t &=T 0.1521553- 0.1413- 0.14,21 0.1434 0.141- 0.13-34
&r &=T 0.0---3,5 0.02 0.05-54 0.01, 0.00335 0.02301
t rot 344.1,-3-1213 33-.3402 330.04 325.3-4 320.51 31,.0-12
r rot 10.,3-0-25, 1-.510 13.-0- 1.4-2- 204.3323 20.--
Cw2t 5.-5,40,444 ,0.,5-- ,2.15,02 ,3.20-04 ,4.1,53- ,5.0,2
Cw2r 113.243514,4 10.,01 10,.02-4 103.102 100.,50 .50,,3
Cw1t "4.2,4102 "5.0535 "5.1214- "5.1,112 "5.25105 "5.313
Cw1r ".,52213 ".-,02 ".535- ".3212-1 ".11,011 ".15,
widt* 0.0224020-1 0.01,23 0.01-0, 0.0150,2 0.013443 0.0120,,
0.005,00521 0.0040, 0.0042,5 0.003-,, 0.0033,1 0.00301-
rotor 9 0.0224020-1
stator 9 0.02002,0 0.02452 0.021325 0.012 0.01,03 0.01503
dor m 0.5
Eor r 0.1,1
& 0.--1-,
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ble stresses
e' donGt want to in(rease 6a rel to blade
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4,-.0, 4.0, 511.0, 533.0, 555.0, 5--.0, 5.0, ,21.0, ,43.0,
0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3
22 22 22 22 22 22 22 22 22
101.50 101.50 101.50 101.50 101.50 101.50 101.50 101.50 101.50
0.452- 0.452- 0.452- 0.452- 0.452- 0.452- 0.452- 0.452- 0.452-
11.,-3 11.,-3 11.,-3 11.,-3 11.,-3 11.,-3 11.,-3 11.,-3 11.,-3
1.-4504 1.-4504 1.-4504 1.-4504 1.-4504 1.-4504 1.-4504 1.-4504 1.-4504
0.,-,-2- 0.,-,-2- 0.,-,-2- 0.,-,-2- 0.,-,-2- 0.,-,-2- 0.,-,-2- 0.,-,-2- 0.,-,-2-
50.50042 50.50042 50.50042 50.50042 50.50042 50.50042 50.50042 50.50042 50.50042
2.20, 2.20, 2.20, 2.20, 2.20, 2.20, 2.20, 2.20, 2.20,
2.20, 2.20, 2.20, 2.20, 2.20, 2.20, 2.20, 2.20, 2.20,
50.50042 50.50042 50.50042 50.50042 50.50042 50.50042 50.50042 50.50042 50.50042
2.20, 2.20, 2.20, 2.20, 2.20, 2.20, 2.20, 2.20, 2.20,
22.212 22.212 22.212 22.212 22.212 22.212 22.212 22.212 22.212
0.-21- 0.-21- 0.-21- 0.-21- 0.-21- 0.-21- 0.-21- 0.-21- 0.-21-
0.-21- 0.-21- 0.-21- 0.-21- 0.-21- 0.-21- 0.-21- 0.-21- 0.-21-
1.15,405 1.1401- 1.14225 1.13,153 1.13051 1.125331 1.12054 1.11,101 1.111-
5.111, 5.-3-, ,.-05, -.,230, .,104 .,15- 10.,-1- 12.12, 13.4-034.0, 511.0, 533.0, 555.0, 5--.0, 5.0, ,21.0, ,43.0, ,,5.0,
0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.5
53.1-105 53.-4313 54.30003 54.422- 55.3-032 55.4,4 5,.35, 5,.-3 5-.34,,
50.50042 50.50042 50.50042 50.50042 50.50042 50.50042 50.50042 50.50042 50.50042
,5.144 ,4.0--4 ,4.,143, ,4.31451 ,4.00- ,3.,4, ,3.3-411 ,3.04,3 ,2.-10534.,5,03 3,.1,1- 3-.5-42 3.0,,- 40.1,,5, 41.3,20- 42.43- 43.535 44.,10
2.20, 2.20, 2.20, 2.20, 2.20, 2.20, 2.20, 2.20, 2.20,
5.,5 5.3451 5.045 5.3-3-- 5-.435- 5-.2 5,.-31 5,.1,32, 55.5-035
3 331415 3 2,2-52 3 1,5 3 1335-2 3 0-2-4 3 014222 2 5- 2 03,23 2 5131
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0.13-1, 0.13,21 0.134,21 0.13310 0.131,,4 0.13021 0.124- 0.12-,5- 0.12,405
0.0411 0.051- 0.0-414 0.02- 0.1003-1 0.101-55 0.1030 0.1043- 0.105,3
311.5- 30.11, 304.50, 301.025 2-.1- 24.,-- 21.,-2 2.-545 25.215
212.32 21,.-325 220.345 223.-,, 22-.0332 230.1,34 233.1-1 23,.0,, 23.2,
,5.2,23 ,,.-4-, ,-.535, ,.30-54 ,.05,32 ,.-5 -0.51142 -1.223, -1.255
,.,033 4.214 3.33,3- 1.03- 0.5,-, .354- .11 -.102- ,.0-,43
"5.3,31 "5.45, "5.532,,5 "5.,0-,0 "5.,4,11 "5.-,3-5 "5.4513 "5.251 ",.014,
".-314,- ".55111 ".3-053 ".211,1 ".052135 "-.504 "-.-50,25 "-.,012 "-.4-0
0.010- 0.00, 0.004 0.00211 0.00-532 0.00,32 0.00,4 0.00525 0.0055
0.002-22 0.0024,- 0.00224, 0.002053 0.0013 0.001-33 0.001, 0.00141 0.0013-5
0.013,0 0.01233, 0.01123 0.0102,4 0.00415 0.00,,5 0.00- 0.00-40, 0.00,-5
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,,5.0, ,-.0, -0.0,
0.3 0.3 0.3
22 22 22.01 401.2- 3.54
101.50 101.50 101.5,-
0.452- 0.452- 0.41444
11.,-3 11.,-3 12.0111
1.-4504 1.-4504 1.-4504
0.,-,-2- 0.,-,-2- 0.,--311
50.50042 50.50042 50.50-1
2.20, 2.20, 2.155
2.20, 2.20, 2.155
50.50042 50.50042 50.50-1
2.20, 2.20, 2.155
22.212 22.212 22.311,
0.-21- 0.-21- 0.-21,0-
0.-21- 0.-21- 0.-21,0-
1.1013- 1.104551 1.10125 1.10122 13.5,4
14.454- 1,.5003 1.1004 (*e(k 0,-.0, -0.0, -31.0- 3.344334
0.5 0.5 0.5 1.1
5-.1342 5.2,554 5.-0,42
50.50042 50.50042 50.50-1
,2.3,-1 ,2.01,,4 ,1.,5-145.,05- 4,.553 4-.4,1,
2.20, 2.20, 2.155
54.55- 54.33001 53.,0-3
2 004- 2 -5213- 2 -0502
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0.12515 0.1233 0.1222,
0.10,5 0.10042 0.1020
23.1,1 20.4,5 2--.25
241.,3 244.353 24-.02,
-2.,305 -3.32-4 -4.025-4
5.035- 4.1545 3.25521
",.103,1 ",.15021 ",.2135
"-.3344, "-.210,25 "-.0-11
0.00511 0.004--4 0.0044,3 0.14251
0.0012 0.00114 0.00111, 0.04,0,3
engt* 0.230314
0.00,3 0.005, 0.0055- 0.230314
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0 0.005 0.01 0.015 0.02 0.025 0.03 0.035 0.04 0.045 0.05
0
0.02
0.04
0.0,
0.0
0.1
0.12
0.14
0.1,
rr
&otor8t
&otor8r
$tator8t
$tator8r
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0 0.1 0.2 0.3 0.4 0.5 0., 0.- 0. 0. 1
"10
0
10
20
30
40
50
,0
-0
0
angles_stage1
a1
a2
b1
b2
r/rm
degrees
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0 0.1 0.2 0.3 0.4 0.5 0., 0.- 0. 0. 1
"10
0
10
20
30
40
50
,0
-0
angles_stage17
a1
a2
b1
b2
r/rm
degrees
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0. 1 1.2 1.4 1., 1. 2 2.2
0
0.05
0.1
0.15
0.2
0.25
0.3
0.35
0.4
0.45
0.5
fan size
&t
&r
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Cpg 1.14 kI/kgK
gamma 1.333
g/!g"1# 4
isen effi(ien() 0.
Assumption
Jn 0.05 Con+ergant noBBles are emplo)ed' t*e) are op
s 0.
(riti(al pressure ratio 1.515,5
=+erallTemp drop 34,.33-3
mass flow 11.1, kg/s
:nlet temp 1235 K
3 stages
ressure ratio 01/03 4.31-,225
:nlet pressure 1,.5
ressure reLuired 3.2154-,ressure : got 3.2154-,
3,0 &e+/s fi9ed b) t*e (ompressor' t*e design
300 m/s e9perien(e w*i(* stressing diffi(ulti
M 2.45150,
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T1 1223.021 T02"T2 -5.0-5111-3
1 15.14,3 T02T01 1235
densit)1 4.530-3 T2 115.10242-
A1 0.015430- T2"T2G 3.-544-555*1 0.0151, T2G 115,.155-,132,
&r/&t1 1.15000, 01/2 1.301-433
satisfa(tD1 )es 2 12.,-30,03,
satisfa(tD2 no 01/( 1.515,5041,
(*o(kedD no
densit)2 3.0,32
A2 0.0154321-
A2n !t*roa 0.010433,43*2 0.01252,03-1
&r/&t2 1.0124-2
satisfa(tD1 )es
satisfa(tD2 no
* 0.0204-,
7lade *eig*t/widt* 3 needs to be (*anged w*en t*e blade stresses
widt* 0.00,42 0.25 is rat*er low' be(ause we want to redu(e
$pa(e b/w stator and rotor blades 0.001-3-3 suall) b/w 0.2 and 0.5
2(*o(ked ,,,.14415
T( .11302
3,0 &e+/s fi9ed b) t*e (ompressor' t*e design
300 m/s e9perien(e w*i(* stressing diffi(ulti
M 2.45150,
N 0.
a3 12 deg tr) to a+oid negati+e +alues at t*e r
tan a3 0.21255,,
tanb3 1 4,255,,
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A1 0.014,,5 01/2 1.4322-4-,34
*1 0.01-5 2 -.0-4-22022
&r/&t1 1.14524- 01/( 1.515,5041,
satisfa(tD1 )es (*o(kedD nosatisfa(tD2 no densit)2 2.3003-2
A2 0.0131121
A2n !t*roa 0.010145113
*2 0.0232,355
&r/&t2 1.1231-5531
satisfa(tD1 )es
satisfa(tD2 no
* 0.025-1-7lade *eig*t/widt* 3 needs to be (*anged w*en t*e blade stresses
widt* 0.005-23 0.25 is rat*er low' be(ause we want to redu(e
$pa(e b/w stator and rotor blades 0.0021431 suall) b/w 0.2 and 0.5
3,0 &e+/s fi9ed b) t*e (ompressor' t*e design
300 m/s e9perien(e w*i(* stressing diffi(ulti
M 2.45150,
N 0.
a3 2 deg tr) to a+oid negati+e +alues at t*e r
tan a3 0.531-04
tanb3 1.-1-04
E=& 0.,0-
73 ,0.,,3 degtan b2 0.0500- stage pressure ratio
tan a2 1.3000-
b2 3.3--02
a2 52 ,224--
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A2n !t*roa 0.01,3-40,
*2 0.0323,-11-3
&r/&t2 1.2--52211
satisfa(tD1 )essatisfa(tD2 )es
* 0.03,5542
7lade *eig*t/widt* 3 needs to be (*anged w*en t*e blade stresses
widt* 0.01214- 0.25 is rat*er low' be(ause we want to redu(e
$pa(e b/w stator and rotor blades 0.00304,2 suall) b/w 0.2 and 0.5
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erating wit* a pressure ratio !p01/p2# less t*an (rit pressure ratio
no of stages 3
$tage Temp drop 115.445 K
1 115.445
2 115.445
3 115.445
of t*e (ompressor is more (riti(al t*an turbine be(ause of de(elerating flow
es will be se+ere.
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3 .-3-0 E=& 0.525,-
densit)3 3.0,0-5 73 ,.44,4- deg
A3 0.02430 b2 22.4,221 deg
*3 0.021, a2 ,-.4352 deg03 10.1325 a1 0 deg
63 0.230343
T3O 105.54
3 35.01,
32/2F(p ,4.5,35
&r/&t2 1.24-104
satisfa(tD1 )essatisfa(tD2 )es
Jr 0.34531
JrPJn )es
are being e+aluated
*e a9ial lengt* and weig*t of t*e turbine. ibrational stresses indu(ed in rotor blades as t*e) pass t*roug* wa
of t*e (ompressor is more (riti(al t*an turbine be(ause of de(elerating flow
es will be se+ere.
ot' t*erefore aim for a E=& of abo+e 0.4
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63 0.3224
T3O ,-.34,2
3 425.21232/2F(p -.-5023
&r/&t2 1.23-53
satisfa(tD1 )es
satisfa(tD2 )es
Jr 0.10,053
JrPJn )es
are being e+aluated
*e a9ial lengt* and weig*t of t*e turbine. ibrational stresses indu(ed in rotor blades as t*e) pass t*roug* wa
of t*e (ompressor is more (riti(al t*an turbine be(ause of de(elerating flow
es will be se+ere.
ot' t*erefore aim for a E=& of abo+e 0.4
$tage Temp drop K
2 115.4451.,2351-45,
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satisfa(tD1 )es
satisfa(tD2 )es
Jr "0.03205JrPJn no
are being e+aluated
*e a9ial lengt* and weig*t of t*e turbine. ibrational stresses indu(ed in rotor blades as t*e) pass t*roug* wa
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E=& 0.,0
73 ,0.,,3 deg
b2 3.3--0 deg
a2 52.,224 dega1 2 deg
kes of t*e noBBle blades' and t*e) in(rease s*arpl) wit* de(rease in a9ial spa(e b/w t*e blade rows#
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kes of t*e noBBle blades' and t*e) in(rease s*arpl) wit* de(rease in a9ial spa(e b/w t*e blade rows#
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kes of t*e noBBle blades' and t*e) in(rease s*arpl) wit* de(rease in a9ial spa(e b/w t*e blade rows#
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&epeating stage design multistage design
work done fa(tor is unne(essar) be(ause of t*e a((elerating flow t*e effe(t of t*e growt* of t*e boundar) l
de(elerating flow wit* an ad+erse pressure gradient.
low psi !temp drop (oeff# and low p*i !flow (oeff# )ield best stage effi(ien(ies.
low psi !temp drop (oeff# and low p*i !flow (oeff# impl) low gas +elo(ities and *en(e redu(ed fri(tion losses
low pis means more stages for a gi+en o+erall turbine output and a low p*i means a larger turbine annulus$in(e weig*t and frontal area are desirable to be low' *ig*er +alues of psi and p*i must be used.
=pt +alues for psi range from 3 to 5' and p*i range from 0. to 1. A low swirl angle !a3 H 20 deg# is desirabl
pipe and propelling noBBle.
mean diameter design is (*osen
Con+ergant"di+ergant noBBles are not used sin(e t*e) tend to be ineffi(ient at pressure ratios ot*er t*an t*
*ig* C2 usuall) impl) *ig* +alues of 2. :f 6a relati+e to t*e mo+ing blades at inlet' 6+2' e9(eeds 0.-5' ad
wa+es in rotor blade passages
gamma 1.333
g/!g"1# 4
Assumption
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tan a3 0.21255-
tanb3 2.21255-
E=& 0.4030,
73 ,5.,-,, degtan b2 0.,0022
tan a2 2.,0022
b2 30.-5,4
a2 ,.,45-
a1 2
&m 0.24-31
$tage 1 stage 2 stage 3Ca1 C1 C3 1,.55 Ca2 150 T03
C12/2(p 12.5-01, C2 41-.12 T3
T1 -,.024 T02"T2 -,.05, 3
1 3.,0, T02T01 .,,2, densit)3
densit)1 1.435,, T2 12.,02 A3
A1 0.045-5, T2"T2G 3.024 *3
*1 0.024-0 T2G 0.- 63
&r/&t1 1.0-501 01/2 1.45-415 T3O
satisfa(tD1 )es 2 2.,22141 3satisfa(tD2 no 01/( 1.515,5 32/2F(p
(*o(kedD no &r/&t2
densit)2 1.124335 satisfa(tD1
A2 0.0,,1-2 satisfa(tD2
A2n !t*roa 0.023-52
*2 0.0122,
&r/&t2 1.0444,
satisfa(tD1 )es Jr satisfa(tD2 no JrPJn
* 0.02-23
7lade *eig*t/widt* 3 needs to be (*anged w*en t*e blade stresses are being e+
widt* 0.000-- 0.25 is rat*er low' be(ause we want to redu(e t*e a9ial len
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a)er along t*e annulus walls is mu(* less t*an w*en t*ere is a
area for a gi+en mass fllow
e be(ause swirl in(reases losses in Iet
design +alue !i.e. at part load#. And partl) be(ause
itional loss ma) be in(urred b) formation of s*o(k
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--.4032
-,5.331
2.120
0.,43
0.0--0
0.041,33
0.2--12
--0.,3,3
3,4.20,5-.--23
1.1514
)es
no
"0.0313 tip leakage loss in rotor blades makes t*is )esno
aluated
t* and weig*t of t*e turbine. ibrational stresses indu(ed in rotor blades as t*e) pass t*roug* wakes of t*e noBBl
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blades' and t*e) in(rease s*arpl) wit* de(rease in a9ial spa(e b/w t*e blade rows#
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0 0.01 0.02 0.03 0.04 0.05 0.0, 0.0- 0.0 0.0 0.1
0
2
4
,
10
12
2nd stage
a1a2
b1
b2