The present invention relates to dual fuel delivery system for a gas turbine. A dual fuel delivery system for a gas turbine includes a main fuel line having a main fuel oil conduit and a main fuel gas conduit, wherein the main fuel gas conduit encloses, at least partially, the main fuel oil conduit; and a first fuel divider having a first fuel oil divider connected to the main fuel oil conduit and a first fuel gas divider connected to the main fuel gas conduit, wherein the first fuel gas divider encloses, at least partially, the first fuel oil divider.
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1. A dual fuel delivery system for a gas turbine, comprising:
a main fuel line having a main fuel oil conduit and a main fuel gas conduit, wherein the main fuel gas conduit encloses, at least partially, the main fuel oil conduit; and
a first fuel divider having a first fuel oil divider connected to the main fuel oil conduit and a first fuel gas divider connected to the main fuel gas conduit, wherein the first fuel gas divider encloses, at least partially, the first fuel oil divider; and
at least one second fuel divider that includes at least one of a second fuel oil divider and a second fuel gas divider, wherein the second fuel gas divider encloses the second fuel oil divider.
2. The dual fuel delivery system of
3. The dual fuel delivery system of
4. The dual fuel delivery system of
two second fuel dividers, wherein each of two second fuel dividers are connected to different outlets of the first fuel divider.
5. The dual fuel delivery system of
6. The dual fuel delivery system of
8. The dual fuel delivery system of
9. The dual fuel delivery system of
10. The dual fuel delivery system of
11. The dual fuel delivery system of
12. The dual fuel delivery system of
14. The gas turbine of
15. A Method for delivering dual fuel to the burner of the gas turbine of
supplying the fuel oil and/or the fuel gas to the main fuel line;
dividing the fuel oil and/or the fuel gas in the first fuel divider; and
guiding the fuel oil and/or the fuel gas to the burner.
16. The dual fuel delivery system of
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The present invention relates to a fuel delivery system, and more particularly the invention relates to dual fuel delivery system for a gas turbine engine.
Modern gas turbines may operate on a number of different fuels, such as various kinds of liquid and gaseous fuels. For this reason, power plants may have gas turbine engines that can operate with dual fuel capability, for example, natural gas and diesel fuel. In general, the choice of the operational fuel depends on the price, availability and operational parameters.
Gas turbines comprise various types of combustors configured to produce a hot gas by burning a fuel in a compressed air. The fuel is introduced in the combustor using one or more fuel nozzles. To provide an operational flexibility, the nozzles usually have capabilities to inject a dual fuel.
Dual fuel has to be delivered to the fuel nozzles from the fuel source. Design of such dual fuel delivery systems has various challenges such as: space constrains, vibrational instabilities and thermal expansions.
What is desired, therefore, is dual fuel delivery system that is simpler and more efficient than the systems from the prior art.
In view of the above mentioned problems, it is primary object of the present invention to provide an improved dual fuel delivery system for a gas turbine engine.
One object of the present invention is to provide improved dual fuel delivery system in terms of the complexity and space saving.
Another object of the present invention is to provide improved dual fuel delivery system in terms of thermal and vibrational stability.
Yet another object of the present invention is to provide improved dual fuel system particularly adapted to substantially rectangular shaped burners.
The above and other objects of the invention are achieved by a dual fuel delivery system for a gas turbine, comprising: a main fuel line having a main fuel oil conduit and a main fuel gas conduit, wherein the main fuel gas conduit encloses, at least partially, the main fuel oil conduit, and a first fuel divider having a first fuel oil divider connected to the main fuel oil conduit and a first fuel gas divider connected to the main fuel gas conduit, wherein the first fuel gas divider encloses, at least partially, the first fuel oil divider.
According to one embodiment, the dual fuel delivery system further comprises at least one second fuel divider having a second fuel oil divider and a second fuel gas divider, wherein one outlet of the first fuel divider is connected to an inlet of the second fuel divider. In one preferred embodiment, the dual fuel delivery system comprises two second fuel dividers.
According to yet another embodiment, the first fuel divider is positioned in a first plane and the second fuel divider is positioned in a second plane, and the first plane is different from the second plane . . . . In one preferred embodiment these two planes are substantially at degrees angle. This configuration is particularly advantageous regarding space saving inside a gas turbine.
According to another embodiment, both the first fuel oil divider and the first fuel gas divider, have one inlet and two outlets.
According to yet another embodiment, the main fuel gas conduit comprises an extension means, preferably metallic bellows. This configuration is particularly advantageous regarding problem of thermal expansions.
According to another embodiment, the first fuel oil divider comprises at least one extension means, such as a metallic hose or an extension joint.
According to yet another embodiment, a connection between the main fuel oil conduit and the first fuel oil divider comprises a horizontal sliding guide, and/or a connection between the first fuel oil divider and the second fuel oil divider comprises a vertical sliding guide.
According to another embodiment, the dual fuel delivery system further comprises an injection head, which comprises at least one injection nozzle adapted to inject fuel oil and/or fuel gas, wherein the injection head is connected to the first fuel divider or the second fuel divider. In one preferred embodiment, the injection head comprises plurality of injection sections, wherein every injection section is connected to one outlet of the first fuel divider or the second fuel divider.
According to yet another embodiment, the dual fuel delivery system comprises fuel manifold connected to the inlet of the main fuel line, and adapted to supply fuel gas and fuel oil to the main fuel line.
The present application also relates to a gas turbine comprising dual fuel delivery system. In one preferred embodiment, a gas turbine comprises a can combustor, a cooling air housing, and a burner adapted to receive the injection head, wherein the inlet of the main fuel line is positioned outside the can housing, the outlet of the main fuel line and the inlet to the first fuel divider are positioned between the can housing and the cooling air housing.
In addition, the present application also provides for a method for delivering dual fuel to the injection head inside the burner of the gas turbine comprising the dual fuel delivery system. The method comprises following steps: supplying fuel oil and/or fuel gas to the main fuel line, dividing the fuel oil and/or the fuel gas in the first fuel divider, and guiding fuel oil and/or fuel gas to the injection head.
Additional advantages and features of the present invention will be set forth in part in a description which follows, and in part will become apparent to those skilled in the art upon examination of the following, or may be learned from practice of the invention. The instant invention will now be described with particular reference to the accompanying drawings.
Preferred embodiments of the invention are described in the following with reference to the drawings, which are for the purpose of illustrating the present preferred embodiments of the invention and not for the purpose of limiting the same. In the drawings,
Referring now to the drawings, in which like numerals refer to like elements throughout the several views, figure shows a schematic view of gas turbine engine 100 according to one embodiment of the invention. The gas turbine 100 is comprised of a compressor 102, which compresses a flow of air 116. The compressed air 118 is directed to a combustor 106 which may comprise several combustor cans and burners. In the combustor 106, the compressed air 118 is mixed with fuel oil 112 or fuel gas 114, and the mixture of air and fuel is ignited to create a flow of hot combustion gases 120, which are directed to drive a turbine 104. The mechanical work produced in the turbine 104 drives the compressor 102 and load 110 via a shaft 122. Fuels 112 and 114 are delivered to the combustor 106 via a dual fuel delivery system 400 according to the invention.
The dual fuel delivery system 400 comprises also a first fuel divider 408, having a first fuel oil divider 412 connected to the main fuel oil conduit 406 and a first fuel gas divider 410 connected to the main fuel gas conduit 404. In general, a fuel divider is a device for dividing a fuel flow, and it has one inlet and two or more outlets. The number of branches of the divider is equal to the number of the outlets. The fuel flow may be divided equally or non-equally among the branches. The first fuel gas divider 410 encloses, at least partially, the first fuel oil divider 412. In the preferred embodiment, shown in
The dual fuel delivery system 400 may have a second fuel divider 414. In one preferred embodiment shown in
Additional advantageous features which contribute to avoid thermal expansions and negative vibrational effects are also show in
In addition, as shown in
The present invention also discloses a gas turbine engine 100 adapted to be used with the dual fuel delivery system 400 according to the invention.
It should be apparent that the foregoing relates only to the preferred embodiments of the present application and that numerous changes and modifications may be made herein by one of ordinary skill in the art without departing from the scope of the invention as defined by the following claims.
100 Gas turbine engine
102 Compressor
104 Turbine
106 Combustor
110 Load
112 Fuel oil
114 Fuel gas
116 Inlet air
118 Compressed air
120 Combustion gas
122 Shaft
200 Fuel delivery system
202 Fuel ring pipe
204 Fuel ring pipe
206 Fuel feed
300 Dual fuel supply system
302 Fuel
304 Fuel
306 Fuel line
308 Fuel line
310 Nozzle
312 Burner
400 Dual fuel delivery system
402 Main fuel line
404 Main fuel gas conduit
406 Main fuel oil conduit
408 First fuel divider
410 First fuel gas divider
412 First fuel oil divider
414 Second fuel divider
416 Second divider outlet
418 Main fuel line inlet
420 Second fuel oil divider
422 Second fuel gas divider
424 Bellow
426 Metallic hose
506 Fuel manifold
508 Fuel oil inlet
510 Fuel gas inlet
602 Injection head
604 Injection nozzles
606 Fuel injection section
800 Burner
902 Can combustor
904 Cooling air housing
Heynen, Fridolin, Maiztegui, Inaki
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