Introduction to Gas Turbines - Värmeöverföring...Brequet equation dW fl h fl h T SFC dW SFC T dt fuel weight dt time T fuel weig t dt time fuel weig t dt dt dW 1 W dW D L SFC V

Introduction to Gas TurbinesLund UniversityLund University

Ideal Joule-Brayton Cycle TT

23

14

23

14

32

14,32

32

11TTTT

TTcTTc

qq

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


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)]


2 stage compressor turbine, rotor blade temp <900°C, COT-SOT = 70°C

Specific Power [kW/(kg/s)]

T,s-chart


The Early Days… DC8 (1958)


Courtesy of Boeing

Type of Propulsion Plant


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:


D, . . u g

fWDSFC

g

GE-404/RM12 – F18, JAS,…


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


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)]


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)


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


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


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


Aero-derivative (CF6-80C2 → LM6000)

CF6CF6--80C280C2

LM6000LM6000--PCPC


The world population and power usage I


The world population and power usage II


Gas turbine


Courtesy to Siemens

Combined cycle


Courtesy to Alstom

Combined cycle cont’d


Courtesy to Alstom

Combined cycles – desalination plant


Steam turbine


Courtesy to Siemens

Turbine cooling



Turbine cooling cont’d

Multi-passThermal BarrierThermal Barrier

Coating



Global warming


Naturvårdsverket

Wind power


Courtesy to Siemens

Wind power – the challenge


Row diffusion – How to get static pressurecos SA 11 cos SA

11 cos SA 11 cos SA

Θopt: 6…11°

022

222

1101 21

21 pWpWpp

22 cos SA


D. C. Wisler: Axial-Flow and Fan Aerodynamics

Documents

Introduction to Gas Turbines - Värmeöverföring...Brequet equation dW fl h fl h T SFC dW SFC T dt fuel weight dt time T fuel weig t dt time fuel weig t dt dt dW 1 W dW D L SFC V