Title of Invention	A REDUNDANT LIQUID FUEL SYSTEM FOR GAS TURBINE
Abstract	Accordingly, there is provided a redundant liquid fuel system adaptable to gas turbines for pumping, metering and supplying pressurizes fuel via fuel nozzles to the combustors of the gas turbines, the system comprising a skid base for accommodating the devices of the system. A solenoid operated fuel stop valve is provided being operably connected to a protection means for shutting of fuel supply to the turbine during shutdown of the plant. A three-screw fuel pump and motor assembly is provided for pumping the fuel including metering and delivery of the pressurized and measured fuel. A hydraulic operated bypass valve is arranged for modulating high pressure fuel flow from the pump. A liquid fuel flow divider for equally distributing input fuel flow to the gas turbine is disposed. The redundant liquid fuel system of the invention attains significance on two fronts viz. availability and maintainability of the gas turbine. The Redundant liquid fuel system supplements the on-base system under normal conditions and assumes the role of a substitute system in the event of a failure of the on-base system. This ensures a continuous availability of the gas turbine. Since at any given point of time, only one of the systems will be operational, maintenance can be carried out on the other one even while the gas turbine is running. This is particularly valid if the downtime required of replacements of components like pump and flow divider due to failure of any of these is constituted. Thus the maintainability of the gas turbine is also improved 3. Figure 03 is a schematic diagram of the redundant liquid fuel system according to the invention. 4. Figure 04 is the General arrangement of the redundant liquid fuel system according to the invention.

Title of Invention

A REDUNDANT LIQUID FUEL SYSTEM FOR GAS TURBINE

Abstract

Accordingly, there is provided a redundant liquid fuel system adaptable to gas turbines for pumping, metering and supplying pressurizes fuel via fuel nozzles to the combustors of the gas turbines, the system comprising a skid base for accommodating the devices of the system. A solenoid operated fuel stop valve is provided being operably connected to a protection means for shutting of fuel supply to the turbine during shutdown of the plant. A three-screw fuel pump and motor assembly is provided for pumping the fuel including metering and delivery of the pressurized and measured fuel. A hydraulic operated bypass valve is arranged for modulating high pressure fuel flow from the pump. A liquid fuel flow divider for equally distributing input fuel flow to the gas turbine is disposed. The redundant liquid fuel system of the invention attains significance on two fronts viz. availability and maintainability of the gas turbine. The Redundant liquid fuel system supplements the on-base system under normal conditions and assumes the role of a substitute system in the event of a failure of the on-base system. This ensures a continuous availability of the gas turbine. Since at any given point of time, only one of the systems will be operational, maintenance can be carried out on the other one even while the gas turbine is running. This is particularly valid if the downtime required of replacements of components like pump and flow divider due to failure of any of these is constituted. Thus the maintainability of the gas turbine is also improved 3. Figure 03 is a schematic diagram of the redundant liquid fuel system according to the invention. 4. Figure 04 is the General arrangement of the redundant liquid fuel system according to the invention.

Full Text	3 A typical fuel oil system generally consist of: - a Fuel Oil Stop Valve; - a fuel Oil Pump driven by Accessory Gear Box of the Gas Turbine; - a Bypass Valve; - a Servo Valve; - a Trip Valve; - a Duplex Filter; - a How Divider; - a Selector Valve; - Piping circuit having the necessary instrumentation, and - a Control Panel In a typical liquid fuel system mounted on an accessory base, fuel is received from a forwarding system at a predetermined point. The fuel flows through the stop valve, the accessory gear box driven by the main fuel pump, a high- pressure filter and free wheeling flow divider. The flow divider meters essentially equal fuel to each combustor. The total fuel flow is controlled by a bypass valve around the main fuel pump which is modulated by the gas turbine control system. Objects of the Invention: It is therefore an object of the present invention to propose a redundant liquid fuel system which eliminates the disadvantages of the prior art. Another object of the present invention is to propose a redundant liquid fuel system which achieves the dual role of normal operation as an on-base system and substitute operation in the case of failure of the on-base system, thereby maintaining a continuous operation of the gas turbine. An yet another object of the present invention is to propose a redundant liquid fuel system which eliminates the requirement of a forced feed lub oil system. A further object of the present invention is to propose a redundant liquid fuel system which is simple in construction and cheaper in manufacturing. 4 Summary of the Invention: Accordingly, there is provided a redundant liquid fuel system adaptable to gas turbines for pumping, metering and supplying pressurizes fuel via fuel nozzles to the combustors of the gas turbines, the system comprising a skid base for accommodating the devices of the system. A solenoid operated fuel stop valve is provided being operably connected to a protection means for shutting of fuel supply to the turbine during shutdown of the plant. A three-screw fuel pump and motor assembly is provided for pumping the fuel including metering and delivery of the pressurized and measured fuel. A hydraulic operated bypass valve is arranged for modulating high pressure fuel flow from the pump . A liquid fuel flow divider for equally distributing input fuel flow to the gas turbine is disposed. The redundant liquid fuel system of the invention attains significance on two fronts viz. availability and maintainability of the gas turbine. The Redundant liquid fuel system supplements the on-base system under normal conditions and assumes the role of a substitute system in the event of e failure of the on-base system. This ensures a continuous availability of the gas turbine. Since at any given point of time, only one of the systems will be operational, maintenance can be carried out on the other one even while the gas turbine is running. This is particularly valid if the downtime required of replacements of components like pump and flow divider due to failure of any of these is constituted. Thus the maintainability of the gas turbine is also improved XXX 2 FIELD OF THE INVENTION: The mention relates to a redundant liquid fuel system for gas turbine application. BACKGROUND OF THE INVENTION 5 3. Figure D3 is a schematic diagram of the redundant liquid fuel system according to the invention. 4. Figure D4 is the General arrangement of the redundant liquid fuel system according to the invention. DETAILED DESCRIPTION OF A PREFERRED EMBODIMENT OF THE INVENTlON: Figure 2 presents a schematic diagram of a packaged Redundant liquid fuel system adapted to an Industrial/Utility gas turbine. following are the design parameters of the invention. - Desiring of a Skid Base flow mounting liquid fuel system components. - Selection of the liquid fuel system - Designing of a piping circuit - Selecting a logic for fuel oil change over standard to Redundancy and Redundant to standard fuel system. - Adding a control logic for a redundant liquid fuel system into gas turbine control system. - Selecting a test procedure - Design of an enclosure for outdoor installation - Finalising the steps for erection and commissionig. A Redundant liquid fuel oil system as shown in figures 03 & 04, according to the invention comprises:- - a skid base assembly (1) - a solenoid operated fuel stop valve (2) - a hydraulic operated fuel stop valve (3) - a three screw fuel pump and motor assembly (5) - a hydraulic operated bypass valve (6) - a high pressure duplex filter fuel filter (7) 6 - a liquid fuel flow divider (8) - a selector valve (9) - a plurality of check valves - skid enclosure assembly with ventilation/cooling fans, fire protection devices, naphtha sensors, AC/DC lighting and power outlets. - a piping circuit having checks valves and manual isolation bail valves. - a plurality of liquid fuel pressure and temperature gauges. - a plurality of etectrical junction boxes, conduit and wining. - a three-way valve (4) connected to the hydraulic operated stop valve (3), the fuel pump (5), and to the standard fuel system. The base assembly (1) incorporates the following features: a. Welded Structure made From low Carbon steel material. b. Foundation anchor bolt attachment holes,foundation hardware (bolts,nuts washers etc.) and mounting pads. c. Lifting lugs to allow uniform lift of the entire skid by means of cables and spreader bars. d. The base provides rigid support for the pump-motor assemble, filters,vaIves, flow divider, piping and other skid quipment. e. The floor plate is constructed with a durable, rigid, slip-resistant material (e.g. checkered carbon steel ptate painted with sand bearing epoxy of galvanized grating). 2. A Solenoid Operated Fuel Stop Valve (2) The solenoid-operated fuel oil stop valve (2) is an emergency valve, operated from a protection system (not shown),which shuts off the supply of the fuel to the turbine(10) during normal or emergency shutdowns. 3. A Hydraulic Operated Fuel Stop Valve (3) The fuel oil stop valve (3) is an emergency valve, operated from the protected system, which shuts off the supply of the fuel to the turbine (10) during normal or emergency shutdowns. 7 When an etectric trip occurs, the solenoid valve (2), causes dump valve (13) to operate in the same manner as above, dumping the high-pressure hydraulic oil from a stop valve cylinder, allowing a spring to close the stop valve (3). 4. A three Screw Fuel Pump and Motor Assembly (5) The fuef pump (5) is a positive-displacement, continuous-output,screw pump with three sets of opposing screws. The screws are so profiled that they form a liquid tight seal between the thread. As the screws rotate, pockets. Cavities are formed where liquid gets trapped and conveyed from one end of the screws to the other end. 5. A Hydraulic Operated Bypass (Re-circulation) Valve (6). The servo-controlled bypass valve (6) modulates high-pressure flow from the pump 6. A High pressure Duplex Filter Fuel Filter (7) Fuel oil at high pressure, from the fuel oil pump (5) is filtered by the High pressure Duplex Fitter fuel Fitter (7) before passing through a flow divider (8) and entering into the combustion chambers of the Gas Turbine (10). 7. A Liquid Fuel Flow Dividder(B). The flow divider (8) equally distributes input fuel flow to the combustion nozzles of the Gas Turbine (10). 8. A Selector Valve (5). A selector valve (9) with pressure gauges is provided at the output of the flow divider (9) to allow monitoring of selected fuel oil pressure in a nozzle inlet line. 8 9. A plurality of Check Valves: A plurality of check valves is mounted one each in each flow divider discharge line correcting each fuel nozzle- in each of a fuel train. 10. Skid Enclosure Assembly with Ventilation/Cooling Fans, Fire Protection Devices, Naphtha Sensors, AC/DC Lighting and Power Outlets. 11. A piping circuit having Checks Valves and manual isolation Ball Valves. 12. A plurality of Liquid Fuel Pressure and Temperature Gauges. 13. A plurality of Electrical Junction Boxes, Conduit and Wiring. 14. A three-way valve (4) connected to the hydrometic operated stop valve(3), the fuel pump (5) and to the standard fuel system. 9 We Claim: 1. A redundant liquid fuel system adaptable to gas turbines for pumping,metering and supplying pressurizes fuel via fuel nozzles to the combustors of the gas turbines, the system comprising; -a skid base (1) for accommodating the devices of the system; -a solenoid operated fuel stop valve (2) operably connected to a protection means for shutting of fuel supply to the turbine doing shutdown of the plant; -a three screw fuel pump and motor assembly (5) for pumping the fuel including metering and delivery of the pressurized and measured fuel ; -a hydrantic operated bypass valve (6) for modulating high pressure fuel flow from the pump (5), and -a liquid fuel flow divider (8) for equally distributing input fuel flow to the gas turbine. 2. The system as claimed in claim I, comprising a hydraulic operated fuel stop valve (3) for need-based shotting of the fuei supply in case of an electric trip, the valve (3) being controlled and actuated by the solenoid operated stop valve (2) . 3. The system as claimed in claim 1, comprising a selector valve (9) disposed at the output of the flow divider (8) to allow monitoring of fuel oil pressure in an inlet line of the fuel nozzle. 4. A redundant liquid fact system adaptable to gas turbines for pumping/metering and supplying pressurizes fuel via fuel nozzles to the combustors of the gas turbines as substantially described and illustrated herein with reference to the accompanying drawings.

Full Text

3
A typical fuel oil system generally consist of:
- a Fuel Oil Stop Valve;
- a fuel Oil Pump driven by Accessory Gear Box of the Gas Turbine;
- a Bypass Valve;
- a Servo Valve;
- a Trip Valve;
- a Duplex Filter;
- a How Divider;
- a Selector Valve;
- Piping circuit having the necessary instrumentation, and
- a Control Panel
In a typical liquid fuel system mounted on an accessory base, fuel is received
from a forwarding system at a predetermined point. The fuel flows through the
stop valve, the accessory gear box driven by the main fuel pump, a high-
pressure filter and free wheeling flow divider. The flow divider meters essentially
equal fuel to each combustor. The total fuel flow is controlled by a bypass valve
around the main fuel pump which is modulated by the gas turbine control
system.
Objects of the Invention:
It is therefore an object of the present invention to propose a redundant liquid
fuel system which eliminates the disadvantages of the prior art.
Another object of the present invention is to propose a redundant liquid fuel
system which achieves the dual role of normal operation as an on-base system
and substitute operation in the case of failure of the on-base system, thereby
maintaining a continuous operation of the gas turbine.
An yet another object of the present invention is to propose a redundant liquid
fuel system which eliminates the requirement of a forced feed lub oil system.
A further object of the present invention is to propose a redundant liquid fuel
system which is simple in construction and cheaper in manufacturing.

4
Summary of the Invention:
Accordingly, there is provided a redundant liquid fuel system adaptable to gas
turbines for pumping, metering and supplying pressurizes fuel via fuel nozzles to
the combustors of the gas turbines, the system comprising a skid base for
accommodating the devices of the system. A solenoid operated fuel stop valve is
provided being operably connected to a protection means for shutting of fuel
supply to the turbine during shutdown of the plant. A three-screw fuel pump and
motor assembly is provided for pumping the fuel including metering and delivery
of the pressurized and measured fuel. A hydraulic operated bypass valve is
arranged for modulating high pressure fuel flow from the pump . A liquid fuel
flow divider for equally distributing input fuel flow to the gas turbine is disposed.
The redundant liquid fuel system of the invention attains significance on two
fronts viz. availability and maintainability of the gas turbine. The Redundant
liquid fuel system supplements the on-base system under normal conditions and
assumes the role of a substitute system in the event of e failure of the on-base
system. This ensures a continuous availability of the gas turbine.
Since at any given point of time, only one of the systems will be operational,
maintenance can be carried out on the other one even while the gas turbine is
running. This is particularly valid if the downtime required of replacements of
components like pump and flow divider due to failure of any of these is
constituted. Thus the maintainability of the gas turbine is also improved
XXX
2
FIELD OF THE INVENTION:
The mention relates to a redundant liquid fuel system for gas turbine
application.
BACKGROUND OF THE INVENTION

5
3. Figure D3 is a schematic diagram of the redundant liquid fuel system
according to the invention.
4. Figure D4 is the General arrangement of the redundant liquid fuel system
according to the invention.
DETAILED DESCRIPTION OF A PREFERRED EMBODIMENT OF THE
INVENTlON:
Figure 2 presents a schematic diagram of a packaged Redundant liquid fuel
system adapted to an Industrial/Utility gas turbine.
following are the design parameters of the invention.
- Desiring of a Skid Base flow mounting liquid fuel system components.
- Selection of the liquid fuel system
- Designing of a piping circuit
- Selecting a logic for fuel oil change over standard to Redundancy and
Redundant to standard fuel system.
- Adding a control logic for a redundant liquid fuel system into gas turbine
control system.
- Selecting a test procedure
- Design of an enclosure for outdoor installation
- Finalising the steps for erection and commissionig.
A Redundant liquid fuel oil system as shown in figures 03 & 04, according to the
invention comprises:-
- a skid base assembly (1)
- a solenoid operated fuel stop valve (2)
- a hydraulic operated fuel stop valve (3)
- a three screw fuel pump and motor assembly (5)
- a hydraulic operated bypass valve (6)
- a high pressure duplex filter fuel filter (7)

6
- a liquid fuel flow divider (8)
- a selector valve (9)
- a plurality of check valves
- skid enclosure assembly with ventilation/cooling fans, fire protection
devices, naphtha sensors, AC/DC lighting and power outlets.
- a piping circuit having checks valves and manual isolation bail valves.
- a plurality of liquid fuel pressure and temperature gauges.
- a plurality of etectrical junction boxes, conduit and wining.
- a three-way valve (4) connected to the hydraulic operated stop valve (3),
the fuel pump (5), and to the standard fuel system.
The base assembly (1) incorporates the following features:
a. Welded Structure made From low Carbon steel material.
b. Foundation anchor bolt attachment holes,foundation hardware (bolts,nuts
washers etc.) and mounting pads.
c. Lifting lugs to allow uniform lift of the entire skid by means of cables and
spreader bars.
d. The base provides rigid support for the pump-motor
assemble, filters,vaIves, flow divider, piping and other skid quipment.
e. The floor plate is constructed with a durable, rigid, slip-resistant material
(e.g. checkered carbon steel ptate painted with sand bearing epoxy of
galvanized grating).
2. A Solenoid Operated Fuel Stop Valve (2)
The solenoid-operated fuel oil stop valve (2) is an emergency valve,
operated from a protection system (not shown),which shuts off the supply
of the fuel to the turbine(10) during normal or emergency shutdowns.
3. A Hydraulic Operated Fuel Stop Valve (3)
The fuel oil stop valve (3) is an emergency valve, operated from the
protected system, which shuts off the supply of the fuel to the turbine
(10) during normal or emergency shutdowns.

7
When an etectric trip occurs, the solenoid valve (2), causes dump valve
(13) to operate in the same manner as above, dumping the high-pressure
hydraulic oil from a stop valve cylinder, allowing a spring to close the stop
valve (3).
4. A three Screw Fuel Pump and Motor Assembly (5)
The fuef pump (5) is a positive-displacement, continuous-output,screw
pump with three sets of opposing screws. The screws are so profiled that
they form a liquid tight seal between the thread. As the screws rotate,
pockets. Cavities are formed where liquid gets trapped and conveyed from
one end of the screws to the other end.
5. A Hydraulic Operated Bypass (Re-circulation) Valve (6).
The servo-controlled bypass valve (6) modulates high-pressure flow from
the pump
6. A High pressure Duplex Filter Fuel Filter (7)
Fuel oil at high pressure, from the fuel oil pump (5) is filtered by the High
pressure Duplex Fitter fuel Fitter (7) before passing through a flow divider
(8) and entering into the combustion chambers of the Gas Turbine (10).
7. A Liquid Fuel Flow Dividder(B).
The flow divider (8) equally distributes input fuel flow to the combustion
nozzles of the Gas Turbine (10).
8. A Selector Valve (5).
A selector valve (9) with pressure gauges is provided at the output of the
flow divider (9) to allow monitoring of selected fuel oil pressure in a nozzle
inlet line.

8
9. A plurality of Check Valves:
A plurality of check valves is mounted one each in each flow divider
discharge line correcting each fuel nozzle- in each of a fuel train.
10. Skid Enclosure Assembly with Ventilation/Cooling Fans, Fire Protection
Devices, Naphtha Sensors, AC/DC Lighting and Power Outlets.
11. A piping circuit having Checks Valves and manual isolation Ball Valves.
12. A plurality of Liquid Fuel Pressure and Temperature Gauges.
13. A plurality of Electrical Junction Boxes, Conduit and Wiring.
14. A three-way valve (4) connected to the hydrometic operated stop
valve(3), the fuel pump (5) and to the standard fuel system.

9
We Claim:
1. A redundant liquid fuel system adaptable to gas turbines for
pumping,metering and supplying pressurizes fuel via fuel nozzles to the
combustors of the gas turbines, the system comprising;
-a skid base (1) for accommodating the devices of the system;
-a solenoid operated fuel stop valve (2) operably connected to a protection
means for shutting of fuel supply to the turbine doing shutdown of the plant;
-a three screw fuel pump and motor assembly (5) for pumping the fuel including
metering and delivery of the pressurized and measured fuel ;
-a hydrantic operated bypass valve (6) for modulating high pressure fuel flow
from the pump (5), and
-a liquid fuel flow divider (8) for equally distributing input fuel flow to the gas
turbine.
2. The system as claimed in claim I, comprising a hydraulic operated fuel stop
valve (3) for need-based shotting of the fuei supply in case of an electric trip, the
valve (3) being controlled and actuated by the solenoid operated stop valve (2) .
3. The system as claimed in claim 1, comprising a selector valve (9) disposed at
the output of the flow divider (8) to allow monitoring of fuel oil pressure in an
inlet line of the fuel nozzle.
4. A redundant liquid fact system adaptable to gas turbines for
pumping/metering and supplying pressurizes fuel via fuel nozzles to the
combustors of the gas turbines as substantially described and illustrated herein
with reference to the accompanying drawings.

Documents:

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Patent Number

271729

Indian Patent Application Number

199/KOL/2006

PG Journal Number

10/2016

Publication Date

04-Mar-2016

Grant Date

02-Mar-2016

Date of Filing

09-Mar-2006

Name of Patentee

BHARAT HEAVY ELECTRICALS LIMITED

Applicant Address

REGIONAL OPERATIONS DIVISION (ROD), PLOT NO : 9/1, DJBLOCK 3RD FLOOR, KARUNAMOYEE, SALT LAKE CITY, KOLKATA-700091, HAVING ITS REGISTERED OFFICE AT BHEL HOUSE, SIRI FORT, NEW DELHI-110049, INDIA.

Inventors:

#	Inventor's Name	Inventor's Address
1	ABBA JAMESH	GAS TURBINE ENGINEERING, ENGINEERING BUILDING, BHEL RAMACHANDRAPURAM, HYDERABAD, 502 032 ANDHRA PRADESH
2	YELLUMBALASE PARAMESWARA GIRISH	GAS TURBINE ENGINEERING, ENGINEERING BUILDING, BHEL RAMACHANDRAPURAM, HYDERABAD, 502 032 ANDHRA PRADESH

PCT International Classification Number

F02C9/26

PCT International Application Number

N/A

PCT International Filing date

PCT Conventions:

#	PCT Application Number	Date of Convention	Priority Country
1			NA