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MS 6001b Design features and performance characters
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MS 6001Heavy Duty Gas Turbine
2 /GE /
February 11, 2010
0
500
1,000
1,500
2,000
2,500
3,000
3,500
0 50,000 100,000 150,000 200,000 250,000
Fired Hours
Fire
dSt
arts
Cyclic Duty
Peaking Duty
Base Load
• 42 MW… 50/60 Hz
• Launched in 1978
• Over 1000 units
• Over 47 million operating hours
• Wide range of applications
• 99% reliability… 97% availability
• 12,000 hours of continuous operation
• Fuel flexible… from refinery gases tocrude oil
• Low NOx emissions 15ppm
6B… unmatched experience
3 /GE /
February 11, 2010
6B evolution… 30 % increase in output
30
32
34
36
38
40
42
44
19781978
19811983
19871995
19971999
MW
4 /GE /
February 11, 2010
6B evolution…
5 /GE /
February 11, 2010
6B Simple cycle performances
Output (MW): 42.1Efficiency (%): 32.1
Heat rate (kj/kwh): 11,230
Pressure ratio 11.8
Firing temperature (°C): 1,140
Shaft speed (rpm): 5,163
Exhaust flow (KG/sec): 141.1
Exhaust temperature (°C): 548
ISO conditions - natural gas
PG
6 /GE /
February 11, 2010
• Hot end drive• 2 bearings
Not to scale
• Axial flow exhaust• High performance
6B Design Features
• Axial compressor• 17 stages• IGV• Bolted construction
• 3 stage turbine• Bolted construction• Advanced materials• Enhanced cooling
• 10 can annular chambers• Dual fuel capability• 15 ppm NOx
(15% 02) with gas fuel
7 /GE /
February 11, 2010
Gas Turbine Position Orientation
8 /GE /
February 11, 2010
MS 6001 B DESCRIPTON
9 /GE /
February 11, 2010
6B Typical layout
Exhaust stack
Generator
Accessories
Gas turbine
Turbine controlcompartment
Inlet filter
10 /GE /
February 11, 2010
6B – Turbine support
The base that supports the gas turbine isa structural steel fabrication of welded
steel beams and plate
11 /GE /
February 11, 2010
INLET CASING
12 /GE /
February 11, 2010
6B – Inlet Casing
The inner bellmouth ispositioned to the outerbellmouth by seven airfoil-shaped radial struts andseven axial tiebars
13 /GE /
February 11, 2010
Axial Compressor IGV
14 /GE /
February 11, 2010
Axial Compressor IGV
15 /GE /
February 11, 2010
LVDT
MOOG
Axial Compressor IGV
16 /GE /
February 11, 2010
Magnetic Speed Pickups Control Speed
17 /GE /
February 11, 2010
Water Washing Manifold
18 /GE /
February 11, 2010
AXIAL COMPRESSOR
19 /GE /
February 11, 2010
Feature:
stages 17
stage of IGV (variable) 1
stages of EGV 2
Pressure Ratio: 11,8
AIR FLOW (KG/sec): 140
SPEED (rpm): 5163
Material:
Stub Shaft NiCrMoV
Compressor Disc NiCrMoV (stg. 1-15)CrMoV (stg. 16-17)
IGV GTD 450
Blade C 450 (stg. 1-8)AISI 403 (stg.9-17)
6B – Axial Compressor
20 /GE /
February 11, 2010
Axial Compressor assembly
21 /GE /
February 11, 2010
Axial Compressor assembly
22 /GE /
February 11, 2010
6B – Inlet, Compressor, Discharge Casing
23 /GE /
February 11, 2010
6B – Compressor Casing
The compressor statorblade are mounted intoring segments in the firstfour stages.
The remaining stages have a squarebase dovetail and are inserted directlyinto circumferential grooves in thecasing
24 /GE /
February 11, 2010
6B – Extraction pockets
• Compressor discharge casing… bleed belt incorporated into casting• Extraction system pipework• Turbine casing… bosses for pipe flange attachment• Second stage nozzle with radiation shield
Fifth stage
25 /GE /
February 11, 2010
COMBUSTION SYSTEM
26 /GE /
February 11, 2010
Feature:
N° chamber 10
Type reverse flow
Burner single, dual fuel
Firing Temperature (°C) + 1100
Water injection available
Steam injection available
DLN available
Material:
Liner Hastelloy X + HS188
with Thermal barrier coating
Cap Hastelloy X + HS188
Crossfire Tube AISI 304
Transition piece Nimonic 263
with Thermal barrier coating
6B – Combustion Section
27 /GE /
February 11, 2010
6B – C.C. Typical Layout
View looking downstream
Spark Plug
Flame Dectors
28 /GE /
February 11, 2010
6B – C.C. Sectional Drawing
29 /GE /
February 11, 2010
• Proven Dry Low NOx design and experience…
–Gas 15 ppm NOx (15%, O2)
–Distillate 42 ppm NOx (15%, O2) with water injection
DLN systems
30 /GE /
February 11, 2010
Reaction zoneWhere the fuel is burnedwith the combustion air
Dilution zoneWhere additional air is mixedwith the hot combustion gases
Liner CapMetering holes atenter of air
Louverprovide a film of airfor cooling the wallsof the liner and cap
6B – Liner
31 /GE /
February 11, 2010
6B – Liner
32 /GE /
February 11, 2010
Transition Piece
33 /GE /
February 11, 2010
6B – Spark Plug and Flame Detector
34 /GE /
February 11, 2010
Steam Inj. is available for Wet NOx Reduction
35 /GE /
February 11, 2010
TURBINE SECTION
36 /GE /
February 11, 2010
Feature:
stages 3
Ratation counterclockwise
Type axial flow
SPEED (rpm): 5163
Material:
Stub Shaft CrMoV
Turbine Disc CrMoV
Nozzle 1°stg FSX 414
Bucket 1°stg GTD111
Nozzle 2°stg GTD222
Bucket 2°stg IN 738
Nozzle 3°stg GTD222
Bucket 3°stg IN 738
6B – Turbine Rotor
37 /GE /
February 11, 2010
1° Wheel Turbine
Spacer
2° Wheel Turbine
Spacer
3° Wheel Turbine
6B – Turbine Rotor
38 /GE /
February 11, 2010
• Use existing GTD111DS material…Nickel base alloy material and coatingtechnology
• Turbine aerodynamic analysis…New engine operating conditions
• Optimised cooling configuration…16 cooling holes
6B – First Stage Bucket
39 /GE /
February 11, 2010
6B – Internal Path cooling
40 /GE /
February 11, 2010
• Nickel base alloy material• Enhanced cooling of airfoil• Contoured tip shroud for creep life improvement
6B – Second Stage Bucket
41 /GE /
February 11, 2010
6B – Spacer
42 /GE /
February 11, 2010
• Use existing FSX414 material (cobalt base alloy)• Enhanced cooling of platforms• Improved leakage control with introduction of chordal
hinge and additional line seal
6B – First Stage Nozzle
43 /GE /
February 11, 2010
Second Stage Nozzle
Third StageNozzle
Use existing GTD222…nickel base alloy materialand coating technology
6B – 2nd Stage nozzle and 3rd Stage nozzle
44 /GE /
February 11, 2010
6B – Second Stage Shroud Block
45 /GE /
February 11, 2010
EXHAUST SECTION
46 /GE /
February 11, 2010
6B – Exhaust Frame
47 /GE /
February 11, 2010
6B – Exhaust Frame
48 /GE /
February 11, 2010
TURBINE BEARINGS
49 /GE /
February 11, 2010
The gas turbine unit contains two main journal bearings used to support the gas turbinerotor. The unit also includes thrust bearings to maintain the rotor-to-stator axial position.These bearings and seals are incorporated in two housings: one at the inlet and one in theexhaust frame. These main bearings are pressure lubricated by fluid supplied from the mainlubricating system. The fluid flows through branch lines to an inlet in each bearing housing.
No. Class Type
1 Journal Elliptical
2 Journal Elliptical
1 Thrust Load (Equalizing)
1 Thrust Unloaded (Non-Equalizing)
Journal Thrust Load Thrust UnLoad
6B – Turbine Bearings
50 /GE /
February 11, 2010
6B – No. 1 Bearing
51 /GE /
February 11, 2010
6B – No. 1 Bearing
52 /GE /
February 11, 2010
6B – Thrust Bearing
53 /GE /
February 11, 2010
6B – No. 2 Bearing