6B9E Uprates

GE Energy

6B & 9E Extendor & Performance Uprates Maximize Productivity with Advanced Technology

Contents 1. What is Extendor? 2. Benefits of Extendor 3. How Extendor Works? 4. Extendor Features 5. Applicability 6. Extendor Experience 7. 2011 NPI – 9E Advanced Extendor Copyright 2008 General Electric Company. All Rights Reserved. FOR GE INTERNAL USE ONLY. This material may not be copied or distributed in whole or in part, without prior written permission of the copyright owner.

2

What is Extendor? Advanced design Combustion hardware that allows you to EXTEND HOURS Between Combustion Inspections

Starts have different wear mechanisms so Extendor does not extend starts intervals for CI Copyright 2008 General Electric Company. All Rights Reserved. FOR GE INTERNAL USE ONLY. This material may not be copied or distributed in whole or in part, without prior written permission of the copyright owner.

3

Sample Inspection Intervals Year

1

2

3

4

5

6

6B / 9E Standard Combustion System

CI

CI

HGPI

CI

CI

MI

6B Extendor Combustion System 9E Extendor Combustion System 9E Advanced Extendor Combustion System

HGPI

CI

HGPI

MI

CI

HGPI

MI

MI

Eliminate Combustion Inspections ! Copyright 2008 General Electric Company. All Rights Reserved. FOR GE INTERNAL USE ONLY. This material may not be copied or distributed in whole or in part, without prior written permission of the copyright owner.

4

Extendor Benefits Availability- Eliminate 4 CI in 6 years – extra 20 days availability Generation- Extra MWHr each year. Extra Steam each year. Penalty Savings- Avoid penalties in Gas Take or Pay Contracts Repair Cost Savings- Reduce CI repair costs by up to 66% Services Cost Savings- Reduce CI craft labor & TA costs by 66% Repair Shipping Savings– Reduce CI repair shipping by 66% Reliability Improvement- Less restart problems and less time off site for CI parts. Also less testing such as overspeed. Copyright 2008 General Electric Company. All Rights Reserved. FOR GE INTERNAL USE ONLY. This material may not be copied or distributed in whole or in part, without prior written permission of the copyright owner.

5

Technical modifications Focus on combustion system wear • Reduce vibratory motion in the system • Reduce wear rate on – – – – – –

Fuel nozzle tips Combustion liner stops Combustion liner hula seal/transition piece Transition piece forward support and bracket Transition piece seal slots Transition piece material change

Liner hula seal to transition forward sleeve

Transition piece seal frame

Fuel nozzle tip to liner collar Liner stop Transition piece forward support Copyright 2008 General Electric Company. All Rights Reserved. FOR GE INTERNAL USE ONLY. This material may not be copied or distributed in whole or in part, without prior written permission of the copyright owner.

Transition piece modifications 6

Fuel nozzle tips Extendor fuel nozzle tip to combustion liner collar sub-system • Wear-couple material • Sacrificial material applied to fuel nozzle tip • New liner collar applied to each Collar

• Critical clearance control between nozzle tip and liner collar

CL-Extendor: fuel nozzle tip and liner collar pictures from 8000 hour inspection Copyright 2008 General Electric Company. All Rights Reserved. FOR GE INTERNAL USE ONLY. This material may not be copied or distributed in whole or in part, without prior written permission of the copyright owner.

7

Liner stop system • 3-position liner stop modification applied to each liner and flow sleeve • Critical clearance control between liner and flow sleeve stops • Wear material with sacrificial slow-sleeve liner stop covers • Verification that modified liner achieves design fit with modified flow sleeve liner stop

Sacrificial material on liner stop Copyright 2008 General Electric Company. All Rights Reserved. FOR GE INTERNAL USE ONLY. This material may not be copied or distributed in whole or in part, without prior written permission of the copyright owner.

8

Liner hula seal to transition piece • Hula seals with sacrificial wear-resistant material • Transition piece forward sleeve with sacrificial wear-resistant material • Wear coatings added by HVOF High Velocity Oxy Fuel spray • Tightened critical clearance control between liner hula seal and transition piece forward sleeve Hula seals

Transition piece forward sleeve

Combustion liner

Liner with Extendor hula seals from 8000 hour inspection

Copyright 2008 General Electric Company. All Rights Reserved. FOR GE INTERNAL USE ONLY. This material may not be copied or distributed in whole or in part, without prior written permission of the copyright owner.

9

Transition piece forward support • New sacrificial wear cover applied to each transition piece forward bracket • “Wear couple” material applied to support bracket to significantly reduce wear Transition Piece Bull-Horn Bracket H-Block (Guide) Bull-Horn/Wear Cover


10

Transition piece seal frame • Sacrificial “slot-protectors” installed in the transition piece end frames • Redesigned side seals • Modified inner and outer floating seals (without slots) Transition piece aft frame Wear resistant insert

Transition piece


Floating seals

11

Transition piece modifications Nimonic 263* aft “picture frame” • Replaces hastelloy-X aft frame • Provides greater creep strength

Class C thermal barrier coating • Reduces bulk metal temperature • Reduces creep deformation

Liner

Class C TBC

Nimonic end frame * Trademark of Udimet Corp, which is not affiliated with GE


12

Applicability Applicable to Frame 5, 6B, 9E Units Available as new parts or existing parts can be modified in our GE Service Shop in Bandung, Indonesia


13

Extendor experience Customers like Extendor combustion system • More than 60% of new 6B and 9E gas turbine shipped with CLExtendor since 2002 • Numerous retrofits on operating fleet performed Frame

Applied as retrofit*

6000B Std combustion 6000B DLN1 combustion

122 21

7001E/EA Std combustion 7001E/EA MNQC comb. 7001E/EA DLN1 combustion

43 4 40

9001E Std combustion 9001E DLN1 combustion

37 32

Total

299


14

Reducing wear and creep Understanding wear and creep root causes • Thermal cycle causing cracks and distortion • Dynamic pressure creating mechanical vibration and erosion • Heat causing creep • Experience shows that wear is a leading contributor to combustion system repair cost

Advanced Extendor leverages GE’s extensive fleet experience and technology improvements from DLN1+ and F-class • Enhanced thermal barrier coatings (TBC) • Material changes • Wear coatings • Hardening of surface in contact • Clearance reduction

Copyright 2011 General Electric Company. All Rights Reserved. This material may not be copied or distributed in whole or in part, without prior written permission of the copyright owner.

15 5/11/2012

From Extendor to Advanced Extendor Components

9E Standard combustor

Primary fuel nozzle

Fully machined nozzle tip with wear coating

Liner

Thicker liner body, double leaf hula seal, spring loaded liner stops

Flow sleeve

Spring loaded liner stop

Transition piece

Integral mount, full length class-C TBC, cloth seals

Casing

No change

Crossfire tubes

Material change, wear coating

Spark plugs

No change

Flame detector

No change

Existing parts cannot be modified. ®

Nimonic is a trademark of Udimet Corp.


16 5/11/2012

Liner and flow sleeve • Double leaf hula seal provides tighter air control and reduced seal temperatures • Spring loaded stops for uniform loading, reduced wear and wear variation, improved installation (from F-class) • Thicker liner body reduces risks of bulging and crack initiation

Spring loaded stops Double leaf hula seal


17 5/11/2012

Transition piece • Nimonic 263 has better creep and strength characteristics than Hastelloy-X • Class C TBC for reduced metal temperatures • Integral mount reduces the aft frame deformation and improves its durability (from DLN1+) • Cloth seals for tighter air control (from F-class)

Integral mount TP

Current TP with tractor mount design

Nimonic 263 and full length class-C TBC


18 5/11/2012

Cross-fire tubes • Inner male and female cross-fire tube material changed from stainless steel to alloy to provide better heat resistance • Wear coating applied on collars Wear coating on collars

Inner male cross-fire tube

Inner female cross-fire tube


19 5/11/2012

MS6001B Performance History

Current New Unit Production *

ISO with distillate fuel, STD combustor, no inlet or exhaust losses ** Available as retrofit only 20

Copyright 2008 General Electric Company. GE Proprietary Information.. All rights reserved. This material may Paul Gilmurray - Indonesia SOA 5/11/2012 not be copied or distributed in whole or in part, without prior written permission of the copyright owner.

MS9001E continuous improvement 150

125 PG9141E Tf = 1955°F 17 Units 105 MW

PG9151E Tf = 2000°F 46 Units

PG9161E Tf = 2020°F 57 Units

PG9171E Tf = 2055°F 264 Units

9E Latest Evolution PG9171E Tf = 2055°F >200 units 126 MW

123 MW 116 MW

111 MW

100 40 1978

1983

1988

1993

2003

21 Copyright 2008 General Electric Company. GE Proprietary Information.. All rights reserved. This material may Paul Gilmurray - Indonesia SOA 5/11/2012 not be copied or distributed in whole or in part, without prior written permission of the copyright owner.

CM&U Philosophy – Providing Customer Value Improved Performance

Advanced Technology

New and Improved Designs Materials, Coatings Improved Cooling, Sealing Leveraging Aircraft Engine Technology

Increased Reliability & Availability Improved Output & Heat Rate Reduced Emission Levels Reduced Maintenance Costs 22


Contents 1. Firing temperature uprate 2. Compressor uprates 3. Sealing uprates 4. 2008 NPI – Advanced Aero 5. 2011 NPI – 9E Performance Advantage

Copyright 2008 General Electric Company. GE Proprietary Information. FOR GE INTERNAL USE ONLY. All rights reserved. This material may not be copied or distributed in whole or in part, without prior written permission of the copyright owner.

23

6B Value proposition As a result of increasing the firing temperature of your MS6001B with the GE firing temperature uprates, you have the ability to reposition your unit for future growth and compliance to regulatory changes, resulting in ... • gas turbine output increased up to about 5.25%* • gas turbine heat rate improvement up to about 1.05%*

* Based on PG6541B model and uprate from 2042°F/1116°C to 2084°F/1140°C with required components only. 24 Copyright 2008 General Electric Company. GE Proprietary Information.. All rights reserved. This material may Paul Gilmurray - Indonesia SOA 5/11/2012 not be copied or distributed in whole or in part, without prior written permission of the copyright owner.

9E Value proposition As a result of increasing the firing temperature of your MS9001 with the GE Firing temperature uprates, you have the ability to reposition your unit for future growth and compliance to regulatory changes, resulting in ... • Gas turbine output increased up to about 5.6%* • Gas turbine heat rate improvement up to about 1.6%*

* Based on 9E model and uprate from 2020°F to 2055°F with required components only 25 Copyright 2008 General Electric Company. GE Proprietary Information.. All rights reserved. This material may Paul Gilmurray - Indonesia SOA 5/11/2012 not be copied or distributed in whole or in part, without prior written permission of the copyright owner.

6B Technical modifications • Improved heat rate and increased output due to increase in firing temperature and reduction in cooling flows • Advanced technology combustion and hot gas path parts TBC coated combustion liners

Improved cooling stage 1 nozzle

HR-120* 1st stage shrouds

GTD-111 DS* stage 1 buckets

Improved cooling stage 2 buckets Brush Seal (optional)

IN-738* stage 3 buckets

Nimonic263* transition piece

GTD-222+* stage 2 nozzle

GTD-222+ stage 3 nozzle

* GTD-111 DS, GTD-222+ are trademarks of the General Electric Company. HR-120 is a trademark of Haynes International, Inc., which is not affiliated with General Electric. Nimonic263 and IN738 are trademarks of the Special Metals Corporate group of companies, which is not affiliated with General Electric. 26 Copyright 2008 General Electric Company. GE Proprietary Information.. All rights reserved. This material may Paul Gilmurray - Indonesia SOA 5/11/2012 not be copied or distributed in whole or in part, without prior written permission of the copyright owner.

Firing temperature uprates for 6B Several firing temperature uprates are available to match your specific configuration and needs

Expected output and heat rate improvement (in %) Model

PG6541

PG6551B

PG6561B

Original Tf (°F/°C)

2042 / 1116

2042 / 1116

2042 / 1116

Max Uprate Tf (°F/°C)

2084 / 1140

2084 / 1140

2084 / 1140

Output improvement, minimal configuration

5.25%

4.25%

4.25%

Heat rate improvement, minimal configuration

-1.05%

-0.65%

-0.65%

Expected performances when combined with other uprate offerings Output improvement with other uprates

10.70%

8.70%

8.10%

Heat rate improvement with other uprates

-4.12%

-3.32%

-3.25%


9E Technical modifications • Improved heat rate and increased output due to increase in firing temperature and reduction in cooling flows • Advanced technology combustion and hot gas path parts TBC coated combustion liners

Improved cooling stage 1 nozzle

HR-120*** stage 1 shrouds

BLE/DS GTS-111* stage1 buckets Improved cooling stage 2 buckets IN-738** stage 3 buckets

Brush seal (optional)

Nimonic-263** transition pieces

GTD-222+* Stage 2 nozzle

GTD-222+* stage3 nozzle

*GTD-111, GTD-222+ are trademarks of the General Electric Company. ** Nimonic-263 and In-738 are a trademarks of the Special Metals Corporate group of companies, which is not affiliated with General Electric. ***HR-120 is a trademark of Haynes International, Inc., which is not affiliated with General Electric. 28 Copyright 2008 General Electric Company. GE Proprietary Information.. All rights reserved. This material may Paul Gilmurray - Indonesia SOA 5/11/2012 not be copied or distributed in whole or in part, without prior written permission of the copyright owner.

Firing temperature uprates for 9B/9E Several firing temperature uprates are available to match your specific configuration and needs

Expected output and heat rate improvement Model

9B

9E

9E

9E

Original Tf (°F/°C)

1840 / 1004

1955 / 1068

2000 / 1093

2020 / 1104

Max Uprate Tf (°F/°C)

2020 / 1104

2020 / 1104

2055 / 1124

2055 / 1124

Output improvement, minimal configuration

24.78%

8.80%

9.30%

5.60%

Heat rate improvement, minimal configuration

-5.20%

-1.30%

-2.05%

-1.60%

Expected performances when combined with other uprate offerings Output improvement with other uprates

28.38%

13.40%

12.90%

9.20%

Heat rate improvement with other uprates

-7.50%

-4.00%

-4.35%

-3.9°%


6B Firing temp increase 2084°F Required Components

Optional Components

• Nimonic*-263 transition pieces with TBC coating & aft frame cooling holes • Slot-cooled combustion liners with TBC coating • Improved cooling stage 1 nozzle • GTD**-111 DS perimeter cooled stage 1 buckets • HR-120 stage-1 shroud blocks with improved spline sealing • GTD-222+ stage 2 nozzle • Stage 2 buckets with improved cooling • GTD-222+ stage 3 nozzle • IN-738 Stage 3 buckets • Inner barrel counter bore covers • GTD-450 reduced camber high flow IGV’s (pre-1987 units)

• Stage 1 shroud abradable coating • Stage 2 & stage 3 honeycomb shroud blocks • Brush seals (high pressure packing, stage 2 nozzle interstage) • Increase IGV angle to 86 degrees (for units with GTD-450 IGV’s) • Extendor* combustion system • Shrouded stage 17 and exit guide vanes • 5163 RPM speed increase • Advanced Aero stage 3 buckets and nozzles

* Nimonic is a trademark of the Special Metals Corporate group of companies, which is not affiliated with General Electric. ** GTD, Extendor are trademarks of the General Electric Company. 30


9E Firing temp increase to 2055oF Required Components

Optional Components

• Nimonic-263** transition pieces with TBC coating & aft frame cooling holes • Slot-cooled combustion liners with TBC coating • Improved cooling stage 1 nozzle • GTD*-111 DS/BLE stage 1 buckets • HR-120*** stage 1 shroud blocks with improved spline sealing • GTD-222+ stage 2 nozzle • Stage 2 buckets with improved cooling • GTD-222+ stage 3 nozzle • IN-738* stage 3 buckets • Exhaust frame blowers • Inner barrel bore plugs • Stage 3 shroud cooling air modification • GTD-450* reduced camber high flow IGV’s

• Stage 1 shroud abradable coating • Stage 2 & stage 3 honeycomb shroud blocks • Brush seals (hpp, #2 bearing, interstage) • Increase IGV angle to 86 degrees (for units with GTD-450 IGV’s) • Extendor* combustion system • Shrouded stage 17 and exit guide vanes • 1100°F of exhaust isotherm limit • Advanced aero stage 3 buckets and stage 3 nozzles *GTD and Extendor are trademarks of the General Electric Company. ** Nimonic 263 and In-738 are a trademarks of the Special Metals Corporate group of companies, which is not affiliated with General Electric. ***HR-120 is a trademark of Haynes International, Inc., which is not affiliated with General Electric.


Shrouded stator 17, EGV1, EGV2 • •

FS2B

Stage 17 stator and EGVs 1 & 2 have been shrouded to reduce the sensitivity of the structure and help prevent blade failure Applicable to sites with low ambient conditions, steam or water injection, or modulating IGVs (i.e. for heat recovery applications)

Compressor Discharge Casing S17

Detail A Stage 17, EGV-1, EGV2

EGV-1

EGV-2

Thicker Shroud

Increased Clearance

Inner Barrel Casing Detail A


FT6B

• Airfoil design for higher flow • Variable airfoil thickness to maintain reliability • GTD-450 for higher tensile strength and superior corrosion resistance • Provides : • Output up to +4.4% for 9B and 1.5% for 9E • Efficiency up to –0.7% for 9B and –0.38% in heat rate for 9E • Option to open inlet guide vanes to 86 degrees • 1% increase in airflow, loss in compressor efficiency • Output up to +0.4%, heat rate increased by +0.2% • Modification includes IGV stops and control card

Alternating Stress Amplitude (Ratio to AISI403)

GTD-450 high flow IGV 1.8 1.6 1.4 1.2 1.0

GTD 450

.8

AISI 403SS

.6 .4 .2 0

10

20 30 40 50 60

70

Mean Stress (KSI)

Higher performance airfoil design Variable thickness airfoil


No. 2 Bearing Brush Seals for 9E • Reduces air leakage to bearing cavity • Reduces oil mist • More durable than labyrinth seals

FS2X

Air Seal

Compressor extraction flow

Cross-Section Bearing Housing


High pressure packing (HPP) with brush seal

FS2V

Reduces air leakage Tolerant of misalignments More durable than labyrinth seals Inner barrel Inner barrel

Aft stub shaft Aft stub shaft

Labyrinth arrangement

Brush seal arrangement 35


Stage 2 honeycomb shroud block

FS2T

• Honeycomb material brazed between casing shroud teeth • Tighter clearance with buckets improves performance • improved output (up to 0.35%) • increased efficiency (up to 0.35%) • Reduced bucket damage, less potential for rubs • Requires buckets with cutter teeth

Honeycomb material


FS2Z

Stage 2 Interstage brush seal

First aft wheelspace

Second forward wheelspace

Brush seal element

1-2 Turbine wheelspacer

Current stage 2 nozzle design

New stage 2 nozzle design 37


6B Experience Firing temperature uprates performed as of 2Q ‘08 • 7 conversions to PG6571B (2077°F) • 16 conversions of PG6581B (2084°F) All components are integrated in current production of 6B turbine All components have been applied as part of retrofits Components

Reference code Applied as retrofit

Stage 1 buckets GTD-111 DS perimeter cooled

FS4A

59

Improved cooling stage 2 buckets

FS4B

76

Improved cooling Stage 1 nozzles with chordal hinge

FS2J

60

GTD-222 stage 2 nozzles

FS1P

176

GTD-222 stage 3 nozzles

FS1R

67

HR120 stage 1 shrouds with cloth seals

FS2Y

130

Stage 2 honeycomb shroud blocks

FS2T

124

Stage 3 honeycomb shroud blocks

FS2U

96

Slot cooled combustion liners with TBC

FR1G

6

Combustion liner Extendor kit

FR1V/FR1W

201

Brush seals (HPP, Interstage)

FS2V/FS2Z

208

FR2B

40

Nimonic transition pieces w/TBC


9E Experience Firing temperature uprates performed as of 1Q ’08 : • 1 conversions from 9B (1840°F) to 9E (2020°F), and 5 9B uprate 1840°F to 1965°F • 8 conversions of 9E to 2055°F Proven components: All components are integrated in current production of 9E turbine and have been applied as part of retrofits Components Stage 1 buckets GTD-111 BLE-DS Improved cooling stage 2 buckets IN-738 stage 3 buckets Improved cooling stage 1 nozzles with chordal hinge GTD-222 stage 2 nozzles GTD-222 stage 3 nozzles HR-120 stage 1 shrouds with cloth seals Stage 2 honeycomb shroud blocks Stage 3 honeycomb shroud blocks Slot cooled combustion liners with TBC Nimonic transition pieces w/TBC

Reference code Applied as retrofit FT6J 21 FS2F 19 FS2K 18 FS2J 42 FS1P 43 FS1R 26 FS2Y 57 FS2T 37 FS2U 46 FR1G 10 FR1D 17 39


Firing temperature uprate Benefits • Increases output, improving revenues • Improves efficiency (heat rate), reducing fuel costs • Reduces maintenance costs with extended maintenance intervals

GE advantage • • • • • •

Largest installed fleet and experience Patented and proven technology Extensive testing, validation and monitoring Component design and system integration OEM commitment and longevity Worldwide service and repair network


6B Tech requirements & effect on heat rate Reference Code

Required for 2084°F

Original Tf Uprated Tf

PG6541 (*)

PG6551 (*)

PG6561 (**)

2042°F / 1116°C 2084°F / 1140°C

2042°F / 1116°C 2084°F / 1140°C

2042°F / 1116°C 2084°F / 1140°C

% -0.20 0.00 0.00 -0.40 0.00 -0.45 0.00 0.00 0.00 0.00 0.00

% -0.20 0.00 0.00 0.00 0.00 -0.45 0.00 0.00 0.00 0.00 0.00

% -0.20 0.00 0.00 0.00 0.00 -0.45 0.00 0.00 0.00 0.00 0.00

-1.05

-0.65

-0.65

0.20 -0.50 -0.07 -0.70 -0.50 -0.35 -0.25 -0.90

-0.50 -0.07 -0.70 -0.50 -0.90

-0.50 -0.70 -0.50 -0.90

-4.12

-3.32

-3.25

Required hardware and software Increase in Tf to 2084 & Control Mod GTD-111 DS Perimeter cooled Stage 1 bucket Improved Cooling Stage 1 nozzle with chordal Hinge GTD-222+ Stage 2 Nozzle GTD-222+ Stage 3 Nozzle HR-120 Stage 1 Shrouds with Cloth Seals Improved cooling 6 holes Stage 2 bucket IN-738 Stage 3 bucket Nimonic Transition Pieces w/TBC Slot Cooled Combustion Liners w/TBC S17 protection (Inner barrel counterbore covers + Shrouded EGV)

FT4P FS4A FS2J FS1P FS1R FS2Y FS4B FS2K FR2B FR1G FS2B

Total expected Tfire heat rate improvement (%) Additional 2° IGV (86°) HPP Brush Seals 5163 RPM load gear S1S Abradable Coating Stage 2 nozzle Interstage Brush Seal Stage 2 Shrouds w. Honeycomb Seals Stage 3 Shrouds w. Honeycomb Seals Advanced Aero Stage 3 bucket/nozzle

FT4M FS2V FP4E FS6A FS2Z FS2T FS2U FS4L/S4K

Total expected heat rate (%) improvement with further options

X X X X X X X X X X X

Total effect are compounding effect of all the performance improvements above. All performance estimates apply at ISO conditions (59°F/15°C, 14.7psia/1.013 bar) (*) Assumes current GT speed is 5100 RPM (**) Assumes current GT speed is 5133 RPM

41


6B Tech requirements & effect on output Reference Code

Required for 2084°F


PG6541 (*)

PG6551 (*)

PG6561 (**)

2042°F / 1116°C 2084°F / 1140°C

2042°F / 1116°C 2084°F / 1140°C

2042°F / 1116°C 2084°F / 1140°C

% 3.20 0.00 0.00 1.00 0.00 1.05 0.00 0.00 0.00 0.00 0.00

% 3.20 0.00 0.00 0.00 0.00 1.05 0.00 0.00 0.00 0.00 0.00

% 3.20 0.00 0.00 0.00 0.00 1.05 0.00 0.00 0.00 0.00 0.00

5.25

4.25

4.25

0.40 0.75 1.10 0.70 1.00 0.35 0.25 0.90

0.75 1.10 0.70 1.00 0.90

0.75 0.50 0.70 1.00 0.90

10.70

8.70

8.10

Required hardware and software Increase Tf to 2084°F & controls modifications GTD-111 DS perimeter cooled Stage 1 bucket Improved Cooling Stage 1 nozzle with chordal Hinge GTD-222+ Stage 2 Nozzle GTD-222+Stage 3 Nozzle HR-120 Stage 1 Shrouds with Cloth Seals Improved cooling 6 holes Stage 2 bucket IN-738 Stage 3 bucket Nimonic Transition Pieces w/TBC Slot Cooled Combustion Liners w/TBC S17 protection (Inner barrel counterbore covers + Shrouded EGV)

FT4P FS4A FS2J FS1P FS1R FS2Y FS4B FS2K FR2B FR1G FS2B

Total expected Tfire output improvement (%) Additional 2° IGV (86°) HPP Brush Seals 5163 RPM load gear S1S Abradable Coating Interstage Brush Seal Stage 2 Shrouds w. Honeycomb Seals Stage 3 Shrouds w. Honeycomb Seals Adavnced aero Stage 3 buckets/Nozzles

FT4M FS2V FP4E FS6A FS2Z FS2T FS2U FS4L/FS4K

Total expected output(%) improvement with further options

X X X X X X X X X X X

Total effect are compounding effect of all the performance improvements above. All performance estimates apply at ISO conditions (59°F/15°C, 14.7psia/1.013 bar) (*) Assumes current GT speed is 5100 RPM (**) Assumes current GT speed is 5133 RPM

42


9E Tech requirements & effect on heat rate Required Reference 9B to 9E Required Required Code 2020°F for 2020°F for 2055°F

MS9001B 1840°F 1004°C 1905°F 1041°C


MS9001E

MS9001E

1840°F 1840°F 1955°F 1985°F 2000°F 1955°F 1985°F 2000°F 2020°F 1004°C 1004°C 1068°C 1085°C 1093°C 1068°C 1085°C 1093°C 1104°C 1965°F 2020°F 2020°F 2020°F 2020°F 2055°F 2055°F 2055°F 2055°F 1074°C 1104°C 1104°C 1104°C 1104°C 1124°C 1124°C 1124°C 1124°C

Required hardware and software Increase Tf to 9E Increase in Tf to 2020 & Control Mod Increase in Tf to 2055 & Control Mod GTD-111 BLE-DS Stage 1 bucket Improved Cooling Stage 1 nozzle with chordal Hinge GTD-222+ Stage 2 Nozzle with reduced cooling flow GTD-222+ Stage 3 Nozzle HR120 Stage 1 Shrouds with Cloth Seals Air-Cooled Stage 2 bucket GTD-450 camber IGV's (84°) IN-738 Stage 3 bucket Nimonic Transition Pieces w/TBC Slot Cooled Combustion Liners w/TBC Exh. Frm. Motor Blowers/ Isotherm temp. Upgrade Inner barrel bore plug

FT6X FT6C FT6Y FT6J FS2J FS1P FS1R FS2Y FS2F FT6B FS2K FR1D FR1G FS1W FS2S

X X X X X X X X X X X X X X

X O O X X O X O X X X X

X X X X X X X X X X X X X

O O O O X O O O O

O O O O O O O O O

O O O O X O O O O

Total expected Tfire heat rate improvement (%) Additional 2° IGV (86°) HPP Brush Seals #2 Bearing Brush Seals S1S Abradable Coating GTD-222+ Stage 2 Nozzle with reduced cooling flow Interstage Brush Seal Stage 2 Shrouds w. Honeycomb Seals Stage 3 Shrouds w. Honeycomb Seals Advanced Aero Stage 3 bucket/nozzle

FT5H FS2V FS2X FS6A FS1P FS2Z FS2T FS2U FS4L/S4K

% -1.10 0.00 -1.90 0.20 0.00 -0.20 -0.90 -0.60 0.00 0.00 0.00 -0.20

-4.70

Maximum expected heat rate(%) improvement with further options

% -2.00 0.00 -1.90 0.20 0.00 -0.20 1.10 -0.90 -0.60 0.00 0.00 0.00 -0.20

% -2.60 0.00 -1.90 0.20 0.00 -0.20 1.10 -0.90 -0.60 0.00 0.00 -0.10 -0.20

% -0.60 0.00 0.00 -0.20 -0.30 0.00 0.00 0.00 -0.20

% -0.27 0.00 0.00 -0.20 -0.30 0.00 0.00 0.00 -0.20

% -0.15 0.00 0.00 -0.20 -0.30 0.00 0.00 0.00 -0.20

% -0.77 0.00 -0.25 -0.40 0.00 -0.20 0.00 -0.30 -0.28 0.00 0.00 0.00 -0.20

% -0.54 0.00 -0.25 -0.40 0.00 -0.20 0.00 -0.30 -0.28 0.00 0.00 0.00 -0.20

% -0.42 0.00 -0.25 -0.40 0.00 -0.20 0.00 -0.30 -0.28 0.00 0.00 0.00 -0.20

% -0.27 0.00 -0.25 -0.40 0.00 -0.20 0.00 0.00 -0.28 0.00 0.00 0.00 -0.20

-4.50 -5.20 -1.30 -0.97 -0.85 -2.40 -2.17 -2.05 -1.60

0.20 -0.20 -0.20 -0.40 -0.20 -0.35 -0.15 -1.00

0.20 -0.20 -0.20 -0.40 -0.20 -0.35 -0.15 -1.00

0.20 -0.20 -0.20 -0.40 -0.20 -0.35 -0.15 -1.00

0.20 -0.20 -0.20 -0.40 -0.40 -0.20 -0.35 -0.15 -1.00

0.20 -0.20 -0.20 -0.40 -0.40 -0.20 -0.35 -0.15 -1.00

0.20 -0.20 -0.20 -0.40 -0.40 -0.20 -0.35 -0.15 -1.00

0.20 -0.20 -0.20 -0.40 -0.20 -0.35 -0.15 -1.00

0.20 -0.20 -0.20 -0.40 -0.20 -0.35 -0.15 -1.00

0.20 -0.20 -0.20 -0.40 -0.20 -0.35 -0.15 -1.00

0.20 -0.20 -0.20 -0.40 -0.20 -0.35 -0.15 -1.00

-7.00

-6.80

-7.50

-4.00

-3.67

-3.55

-4.70

-4.47

-4.35

-3.90

Total effect are compounding effect of all the performance improvements above. All performance estimates apply at ISO conditions (59°F/15°C, 14.7psia/1.013 bar) 43 Copyright 2008 General Electric Company. GE Proprietary Information.. All rights reserved. This material may Paul Gilmurray - Indonesia SOA 5/11/2012 not be copied or distributed in whole or in part, without prior written permission of the copyright owner.

9E Tech requirements & effect on output Required Required Required Reference 9B to 9E for for Code 2020°F 2020°F 2055°F

MS9001B

MS9001E

MS9001E

1840°F 1840°F 1840°F 1955°F 1985°F 2000°F 1955°F 1985°F 2000°F 2020°F 1004°C 1004°C 1004°C 1068°C 1085°C 1093°C 1068°C 1085°C 1093°C 1104°C 1905°F 1965°F 2020°F 2020°F 2020°F 2020°F 2055°F 2055°F 2055°F 2055°F 1041°C 1074°C 1104°C 1104°C 1104°C 1104°C 1124°C 1124°C 1124°C 1124°C


Required hardware and software Increase Tf to 9E Increase in Tf to 2020 & Control Mod Increase in Tf to 2055 & Control Mod GTD-111 BLE-DS Stage 1 bucket Improved Cooling Stage 1 nozzle with chordal Hinge GTD-222+ Stage 2 Nozzle w/ reduced cooling flow GTD-222+Stage 3 Nozzle HR120 Stage 1 Shrouds with Cloth Seals Air-Cooled Stage 2 bucket GTD-450 camber IGV's (84°) IN-738 Stage 3 bucket Nimonic Transition Pieces w/TBC Slot Cooled Combustion Liners w/TBC Exh. Frm. Motor Blowers/ Isotherm temp. Upgrade Inner barrel bore plug

FT6X FT6C FT6Y FT6J FS2J FS1P FS1R FS2Y FS2F FT6B FS2K FR1D FR1G FS1W FS2S

X X X X X X X X X X X X X X

X O O X X O X O X X X X

X X X X X X X X X X X X X

O O O O X O O O O

O O O O O O O O O

O O O O X O O O O

Total expected Tfire output improvement (%) Additional 2° IGV (86°) HPP Brush Seals #2 Bearing Brush Seals S1S Abradable Coating GTD-222+ Stage 2 Nozzle w/ reduced cooling flow Interstage Brush Seal Stage 2 Shrouds w. Honeycomb Seals Stage 3 Shrouds w. Honeycomb Seals Adavnced aero Stage 3 buckets/Nozzles

FT5H FS2V FS2X FS6A FS1P FS2Z FS2T FS2U FS4L/FS4K

% 6.70 0.00 0.00 -1.00 0.00 0.40 4.40 0.00 0.00 0.00 0.33

% 12.80 0.00 0.00 -1.00 0.00 0.40 1.65 4.40 0.60 0.00 0.00 0.00 0.33

% 18.20 0.00 0.00 -1.00 0.00 0.40 1.65 4.40 0.60 0.00 0.00 0.20 0.33

% 6.50 0.00 0.00 0.40 1.50 0.00 0.00 0.00 0.40

% 4.00 0.00 0.00 0.40 1.50 0.00 0.00 0.00 0.40

% 2.70 0.00 0.00 0.40 1.50 0.00 0.00 0.00 0.40

% 9.50 0.00 0.00 1.00 0.00 0.40 0.00 1.50 0.30 0.00 0.00 0.00 0.40

% 7.00 0.00 0.00 1.00 0.00 0.40 0.00 1.50 0.30 0.00 0.00 0.00 0.40

% 5.70 0.00 0.00 1.00 0.00 0.40 0.00 1.50 0.30 0.00 0.00 0.00 0.40

% 3.50 0.00 0.00 1.00 0.00 0.40 0.00 0.00 0.30 0.00 0.00 0.00 0.40

10.83 19.18 24.78 8.80 6.30 5.00 13.10 10.60 9.30 5.60

Maximum expected output(%) improvement with further options

0.40 0.50 0.30 0.40 0.50 0.35 0.15 1.00

0.40 0.50 0.30 0.40 0.50 0.35 0.15 1.00

0.40 0.50 0.30 0.40 0.50 0.35 0.15 1.00

0.40 0.50 0.30 0.40 1.00 0.50 0.35 0.15 1.00

0.40 0.50 0.30 0.40 1.00 0.50 0.35 0.15 1.00

14.43 22.78 28.38 13.40 10.90

0.40 0.50 0.30 0.40 1.00 0.50 0.35 0.15 1.00

9.60

0.40 0.50 0.30 0.40 0.50 0.35 0.15 1.00

0.40 0.50 0.30 0.40 0.50 0.35 0.15 1.00

0.40 0.50 0.30 0.40 0.50 0.35 0.15 1.00

16.70 14.20 12.90

0.40 0.50 0.30 0.40 0.50 0.35 0.15 1.00

9.20

Total effect are compounding effect of all the performance improvements above. All performance estimates apply at ISO conditions (59°F/15°C, 14.7psia/1.013 bar) 44 Copyright 2008 General Electric Company. GE Proprietary Information.. All rights reserved. This material may Paul Gilmurray - Indonesia SOA 5/11/2012 not be copied or distributed in whole or in part, without prior written permission of the copyright owner.

New S3B consists of a higher-efficiency, 3-D aerodynamic design Tip Shroud – Improved stage efficiency and durability Airfoil – Higher efficiency Bucket Stack – Reduced stresses Platform – Better bucket balance Shank Pocket – Reduces stress concentrations 45 Copyright 2008 General Electric Company. All Rights Reserved. This material may not be copied or distributed in whole or in part, without prior written permission of the copyright owner.

New S3N design provides significant efficiency improvement New aerodynamic nozzle configuration • Improved output and heat rate • Optimized airflow distribution • Improved airflow exit angle

View Looking Upstream • Improved mechanical design features complement this new design Red-Uprate

Green-Baseline

46 Copyright 2008 General Electric Company. All Rights Reserved. This material may not be copied or distributed in whole or in part, without prior written permission of the copyright owner.

6B - Benefits Provides Significant Improvement in Output and Heat Rate Ambient temperature New S3B/New S3N, Hot Day, 100F/38C, Reference only New S3B/New S3N, ISO Day, 59F/15C, Guarantee pt New S3B/New S3N, Cold Day, 0F/-18C, Reference Only

S/C Output

S/C Heat Rate

+0.6%

-0.6%

+0.9%

-0.9%

+1.1%

-1.1%

Efficiency improvement results in exhaust temperature and exhaust energy decrease. Combined cycle analysis can be provided to estimate over-all plant impact.


9E - Benefits Provides Significant Improvement in Output and Heat Rate Ambient temperature New S3B/New S3N, Hot Day, 100F/38C, Reference only New S3B/New S3N, ISO Day, 59F/15C, Guarantee pt New S3B/New S3N, Cold Day, 0F/-18C, Reference Only

S/C Output

S/C Heat Rate

+0.7%

-0.7%

+1.0%

-1.0%

+1.2%

-1.2%

Efficiency improvement results in exhaust temperature and exhaust energy decrease. Combined cycle analysis can be provided to estimate over-all plant impact.


Experience • More than 30 S3B/S3N installed* as retrofit ValPak • 14 7E/7EA • 12 9E • 8 6B

• 7EA Fleet leader reached 24,000 hrs in March 2008 • Introduced as an option into new units as part of Performance Improvement Pack • 7EA in 2007 • 9E in 2007 • 6B in 2008 *As of April 2008 Copyright 2008 General Electric Company. All Rights Reserved. This material may not be copied or distributed in whole or in part, without prior written permission of the copyright owner.

49

New advanced features Hot Gas Path (HGP) cooling and clearance closure S1B cooling S1S abradable coating thickness S1N cooling S2B cooling and sealing S2S aluminized honeycomb S2N material and cloth seal S3B Advanced aero sealing S3S aluminized honeycomb S3N Advanced aero sealing

Reduced leakage and improved cooling Copyright 2011 General Electric Company. All Rights Reserved. This material may not be copied or distributed in whole or in part, without prior permission of the copyright owner.

50

Increased performance • In combined cycle, approximately: Combined cycle 9E PIP – 1x1

Output

Heat rate

Exhaust energy

+1.95%*

-0.66%*

+0.75%*

9E non PIP

Site specific evaluation

• In simple cycle, approximately: Simple cycle

Rating

Ship

Output

Heat rate

Exhaust energy

9E PIP

128MW

Since 2010

+1.29%

-0.66%

+0.49%

9E PIP

127MW

2008-2009

+1.95%

-0.79%

+0.75%

9E non PIP

126MW

2003-2007

+4.18%

-2.50%

+0.34%

9E non PIP

<126MW

Before 2003

Unit specific evaluation

• Design retains all current parts life and rotor life estimates * ISO conditions, 1 GT + 1 steam turbine, 2 pressure reheat cycle, HRSG sized for higher exhaust energy, site specific evaluation required to determine actual performance benefits. Copyright 2011 General Electric Company. All Rights Reserved. This material may not be copied or distributed in whole or in part, without prior permission of the copyright owner.

51

HGP sub-package #1 Benefit: Improved cooling & sealing Scope and design changes Stage 1 nozzle

• Stage 1 nozzle – Reduced leakage on cloth seals – Film cooling hole improvement – Re-designed retaining ring with improved cooling and anti-rotation pin slot

• Stage 1 bucket – Improved cooling technology (turbulators) – Enhanced dovetail sealing

Stage 1 bucket

• Stage 1 shroud – Enhanced cloth seal – Thicker GE proprietary gen3 abradable coating Stage 1 shroud Copyright 2011 General Electric Company. All Rights Reserved. This material may not be copied or distributed in whole or in part, without prior permission of the copyright owner.

52

HGP sub-package #2 Benefit • Improved cooling & sealing • Improved component life

Scope and design changes

Stage 2 nozzle

• Stage 2 Nozzle – Material change to GTD*262 alloy with improved creep improved creep, low cycle fatigue and oxidation compared to GTD*241 – Enhanced sealing

Improved design 8 holes advanced Cooling

• Stage 2 Bucket – Cooling design change reducing creep – Dovetail sealing

Stage 2 bucket

• Stage 2 shroud – Thicker abradable honeycomb for improved operating clearance – Cloth and solid seals replacing pumpkin teeth * Trademark of General Electric Company

Stage 2 shroud

Copyright 2011 General Electric Company. All Rights Reserved. This material may not be copied or distributed in whole or in part, without prior permission of the copyright owner.

53

HGP sub-package #3 Benefit • Improved cooling & sealing • Reduced performance degradation

Scope and design changes

Advanced Aero stage 3 nozzle dovetail sealing

• Stage 3 Nozzle – Advanced Aero with cloth seals instead of solid seals

• Stage 3 Bucket – Advanced Aero with improved dovetail sealing

• Stage 3 shroud

Advanced Aero stage 3 bucket

– Cloth and solid seals replacing pumpkin teeth – Abradable honeycomb for improved operating clearance Stage 3 shroud * Trademark of General Electric Company Copyright 2011 General Electric Company. All Rights Reserved. This material may not be copied or distributed in whole or in part, without prior permission of the copyright owner.

54

Fuel Gas Re-Commissioning Gas change leads to design changes • Fuel nozzle – Sized for nominal gas composition – Nozzles are capable of handling +/- 5% Modified Wobbe Index variation from nom – Wrong sized nozzles lead to combustion dynamics and hardware damage

• Gas Valves – –

Sized for supply pressure and composition Incorrect valve sizing can limit load

• Gas Piping – Sized for nominal gas composition – Increases in inert % such as N2, CO2 may require piping redesign – Incorrect piping sizing can limit load


Fuel Gas Skid Re-Commissioning Extended Layup Requires Preservation • Fuel gas skid – – – – –

Servos Solenoids Instrumentation Wiring Hydraulics

• Gas Valves – –

Corrosion Contamination

• Extensive Protection Systems

B

A

H

• Many trip sources

• Replace better than Repair 56 Copyright 2008 General Electric Company. GE Proprietary Information.. All rights reserved. This material may Paul Gilmurray - Indonesia SOA 5/11/2012 not be copied or distributed in whole or in part, without prior written permission of the copyright owner.

Combined cycle - value proposition Fuel savings

Fuel savings – 5 year NPV

$3 000 000

– Improved heat rate of 0.66%*, resulting in significant fuel cost reduction – $345k* yearly – $1.4MM NPV* over 5 years

Incremental output – 1.95%* output increase generates gross revenue – $525k* yearly – 2.1MM* NPV over 5 years

$2 500 000

$2 000 000

$1 500 000

$1 000 000

$500 000

$0 0

1

2

3 4 5 6 7 First year Fuel price ($MMBtu)

8

9

10

Incremental income – 5 year NPV

Same or better maintenance intervals * Net Present Value & Conditions • 9E with PIP •Combined cycle, Natural gas – ISO conditions • 109E CC output baseline : 190 MW • 9E Heat rate baseline : 7,030 kJ/kWh • Utilization : 6,000 hours/year • Electricity price : $70 MWhr • Fuel costs : $7/Mbtu • Discount rate : 8% 57 Copyright 2008 General Electric Company. GE Proprietary Information.. All rights reserved. This material may Paul Gilmurray - Indonesia SOA 5/11/2012 not be copied or distributed in whole or in part, without prior written permission of the copyright owner.

Simple cycle - value proposition Fuel savings – 5 year NPV

Fuel savings – Improved heat rate of 0.61%*, resulting in significant fuel cost reduction – $125k* yearly – $500k NPV* over 5 years

Incremental output – 1.29%* output increase generates gross revenue – $199k* yearly – $796k* NPV over 5 years Incremental income – 5 year NPV

Same or better maintenance intervals * Net Present Value & Conditions •9E PIP output baseline: •9E PIP Heat rate baseline : • Utilization : • Electricity price : • Fuel costs : • Discount rate :

128.1MW 10,570 KJ/kWh 4,000 hours/year $70 MWhr $4/Mbtu 8%


6B9E Uprates

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