Ms6001b operation description

MS 6001Heavy Duty Gas Turbine

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0

500

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1,500

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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

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6B evolution… 30 % increase in output

30

32

34

36

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19781978

19811983

19871995

19971999

MW

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6B evolution…

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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

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• 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

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Gas Turbine Position Orientation

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MS 6001 B DESCRIPTON

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6B Typical layout

Exhaust stack

Generator

Accessories

Gas turbine

Turbine controlcompartment

Inlet filter

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6B – Turbine support

The base that supports the gas turbine isa structural steel fabrication of welded

steel beams and plate

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INLET CASING

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6B – Inlet Casing

The inner bellmouth ispositioned to the outerbellmouth by seven airfoil-shaped radial struts andseven axial tiebars

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Axial Compressor IGV

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Axial Compressor IGV

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LVDT

MOOG

Axial Compressor IGV

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Magnetic Speed Pickups Control Speed

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Water Washing Manifold

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AXIAL COMPRESSOR

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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

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Axial Compressor assembly

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Axial Compressor assembly

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6B – Inlet, Compressor, Discharge Casing

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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

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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

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COMBUSTION SYSTEM

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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

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6B – C.C. Typical Layout

View looking downstream

Spark Plug

Flame Dectors

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6B – C.C. Sectional Drawing

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• Proven Dry Low NOx design and experience…

–Gas 15 ppm NOx (15%, O2)

–Distillate 42 ppm NOx (15%, O2) with water injection

DLN systems

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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

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6B – Liner

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Transition Piece

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6B – Spark Plug and Flame Detector

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Steam Inj. is available for Wet NOx Reduction

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TURBINE SECTION

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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

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1° Wheel Turbine

Spacer

2° Wheel Turbine

Spacer

3° Wheel Turbine

6B – Turbine Rotor

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• 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

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6B – Internal Path cooling

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• Nickel base alloy material• Enhanced cooling of airfoil• Contoured tip shroud for creep life improvement

6B – Second Stage Bucket

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6B – Spacer

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• 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

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Second Stage Nozzle

Third StageNozzle

Use existing GTD222…nickel base alloy materialand coating technology

6B – 2nd Stage nozzle and 3rd Stage nozzle

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6B – Second Stage Shroud Block

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EXHAUST SECTION

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6B – Exhaust Frame

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6B – Exhaust Frame

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TURBINE BEARINGS

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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

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6B – No. 1 Bearing

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6B – No. 1 Bearing

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6B – Thrust Bearing

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6B – No. 2 Bearing