CN202746019U - Fuel control system of gas turbine - Google Patents
Fuel control system of gas turbine Download PDFInfo
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- CN202746019U CN202746019U CN 201220348775 CN201220348775U CN202746019U CN 202746019 U CN202746019 U CN 202746019U CN 201220348775 CN201220348775 CN 201220348775 CN 201220348775 U CN201220348775 U CN 201220348775U CN 202746019 U CN202746019 U CN 202746019U
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- gas turbine
- fuel nozzle
- control system
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Abstract
The utility model discloses a fuel control system of a gas turbine. The fuel control system of the gas turbine mainly comprises a load determining unit and a fuel control unit; the load determining unit is used for determining load information of the gas turbine, and the fuel control system is used for receiving the determined load information and controlling fuel spray nozzles of the gas turbine to open or close selectively according to the received load information, so the sum of rated flow rates of the opened fuel spray nozzles is matched with the determined load information. No matter at a high load condition or a low load condition, the flow rate of each opened spray nozzle can be always kept under the rated flow rate during operation, so the combustion efficiency of each fuel spray nozzle can be kept at the maximum combustion efficiency, and the whole combustion system keeps at the maximum combustion efficiency.
Description
Technical field
The utility model relates to a kind of gas turbine, particularly relates to the fuel control mode of gas turbine.
Background technique
The fuel of gas turbine generally is to inject the firing chamber by a plurality of fuel nozzles to burn.When design, each fuel nozzle has the rated flow of a setting.This sets flow is to design for the motor maximum permissible load.For these fuel nozzles, only be operated in its rated flow and just can reach the design maximum combustion efficiency, and effectively control effulent, such as nitrogen oxide or carbon monoxide etc.But during gas turbine work, always have the situation of some variable working condition.As variable working condition appears, and for example, being operated under the sub load, current way is that the passing ratio valve is done throttling to each fuel nozzle at present.After throttling, the flow of fuel nozzle diminishes, so that be complementary by fuel flow rate summation and the actual load of these fuel nozzles injection firing chambers.Yet along with the fuel flow rate of fuel nozzle reduces, its combustion efficiency also decreases.At this moment, because incomplete combustion, the noxious emissions such as nitrogen oxide or carbon monoxide also can increase.
The model utility content
In view of this, this paper proposes the Fuel Control System that a kind of combustion efficiency that can make combustion system keeps its design maximum combustion efficiency basically.
Gas turbine fuel control system in this paper mainly comprises load determining unit and fuel control unit.Gas turbine comprises the firing chamber and is communicated with to inject a plurality of fuel nozzles of fuel to the firing chamber with the firing chamber.The load determining unit is used for determining the load information of gas turbine, and fuel control unit is used for receiving determined load information and optionally open or close according to the fuel nozzle of received load information control gas turbine, so that the summation of the rated flow of the fuel nozzle that is opened and determined load information are complementary.
In one embodiment, described a plurality of fuel nozzles can comprise first fuel nozzle and a plurality of the second fuel nozzle, and the rated flow of the rated flow of wherein said the first fuel nozzle and single the second fuel nozzle is unequal.In a particular embodiment, the rated flow of described the first fuel nozzle is greater than the rated flow of single the second fuel nozzle.
In one embodiment, the self-sustain speed that the rated flow of described the first fuel nozzle can corresponding gas turbine.
In one embodiment, described a plurality of the second fuel nozzle is around described the first fuel nozzle setting.
In one embodiment, the rated flow of each described fuel nozzle is identical.
In one embodiment, a part of fuel nozzle in described a plurality of fuel nozzle is designed to be controlled and cuts out simultaneously or open.In a specific embodiment, described a plurality of fuel nozzle comprises first lap fuel nozzle and the second circle fuel nozzle, each circle fuel nozzle includes a plurality of fuel nozzles, and a plurality of fuel nozzles of each circle fuel nozzle are designed to be controlled and cut out simultaneously or open.Certainly, described fuel nozzle also can comprise the more fuel nozzle of multi-turn.
In one embodiment, described load determining unit comprises the load detecting system, for detection of the load information of described gas turbine.In another embodiment, described load determining unit comprises the load information inputting interface, is used for receiving operator's load information input.
In one embodiment, described control system comprises the storage of store look-up tables, which fuel nozzle described fuel control unit determines to open by inquiring about described look-up table, and described look-up table comprises the contrast relationship of the fuel flow rate of the opening and closing state of the contrast relationship of the opening and closing state of each fuel nozzle and gas turbine load or each fuel nozzle and gas turbine.
In sum, fuel control mode in this paper optionally opens or closes by controlling each fuel nozzle, realizes the control of fuel flow rate, to mate the load of different gas turbines.In this manner, no matter be under high load or low-load situation, the flow of each fuel nozzle that is opened can always work under its rated flow, therefore the combustion efficiency of each fuel nozzle can remain on maximum combustion efficient, thereby so that whole combustion system remains essentially in maximum combustion efficient.
Description of drawings
Fig. 1 is a kind of schematic diagram of gas turbine fuel control system.
Fig. 2 is the table of comparisons that an embodiment fuel nozzle opens and closes state and fuel flow rate.
Fig. 3 is the table of comparisons that another embodiment's fuel nozzle opens and closes state and fuel flow rate.
Fig. 4 is the schematic diagram that an embodiment's fuel nozzle distributes.
Fig. 5 is the table of comparisons that the fuel nozzle of Fig. 4 opens and closes state and fuel flow rate.
Fig. 6 is the schematic diagram that another embodiment's fuel nozzle distributes.
Fig. 7 is a kind of schematic diagram of load information inputting interface.
Among the figure:
100 Fuel Control Systems; 102 load determining units; 104 fuel control units; 110 inputting interfaces; 112 controlling rods; 114 controlling rod positions; 116 storage unit.
Embodiment
Before describing embodiment in detail, it should be understood that the utility model is not limited among the application hereinafter or the detailed structure described in the accompanying drawing or arrangement of elements.The utility model can be the embodiment that alternate manner is realized.And, should be appreciated that the employed wording of this paper and term only as describing purposes, should not be construed as limiting interpretation.The similar wording such as this paper employed " comprising ", " comprising ", " having " mean and comprise listed thereafter item, its equivalent and other additional things.Particularly, when describing " certain element ", the quantity that the utility model does not limit this element is one, also can comprise a plurality of.
Fig. 1 is a kind of schematic diagram of gas turbine fuel control system.Gas turbine comprises the firing chamber and is communicated with to inject a plurality of fuel nozzle I N1, I N2, the I N3 of fuel to the firing chamber with the firing chamber ... I Nn.Fuel Control System 100 is used for injecting by these fuel nozzles according to the load control of gas turbine the flow of the fuel of firing chamber, makes it to be complementary with the load of gas turbine.Fuel Control System 100 mainly comprises load determining unit 102 and fuel control unit 104.Load determining unit 102 is used for determining or obtaining the load information of described combustion turbine, and fuel control unit 104 be used for receiving determined load information and according to received load information control these fuel nozzles I N1, IN2, IN3 ..., INn optionally opens or closes, so that the summation of the rated flow of the fuel nozzle that is opened and determined load information are complementary.
In brief, after determining a load, according to this load, fuel nozzle is controlled optionally to be opened or closed.If this load is not the design maximum load, be that gas turbine operation is under sub load, then only a part of fuel nozzle is opened to inject fuel to the firing chamber, and the remaining part fuel nozzle is closed, and the fuel flow rate of each fuel nozzle that is opened remains at its rated flow basically.If load reduction is then correspondingly closed one or more fuel nozzles again.On the contrary, if load increases, then open one or more fuel nozzles more and inject fuel to the firing chamber.Therefore, under this control mode, the quantity of the fuel nozzle that is opened or combination change along with the load variations of gas turbine.But, no matter be under high load or low-load situation, the flow of each fuel nozzle that is opened can always work under its rated flow, therefore the combustion efficiency of each fuel nozzle can remain on its maximum combustion efficient, thereby so that whole combustion system remains on the design maximum combustion efficiency.Simultaneously, because these fuel combustions that are injected into are complete, so that combustion system can effectively be controlled the effulents such as nitrogen oxide or carbon monoxide.
In addition, opening or closing of fuel nozzle can be realized by a switch that is attached thereto or valve.Two states only opened and close by this switch or valve and its state is subjected to fuel control unit 104 controls.For the way of the fuel flow rate of regulating each fuel nozzle by the usage ratio valve, fuel control mode in this paper also can significantly reduce controls cost.
The below illustrates above-mentioned control system by way of example.
In this n fuel nozzle, according to different designs, the rated flow of single fuel nozzle can be identical, also can be not identical.When the rated flow of each fuel nozzle is identical, suppose that the fuel flow rate summation when whole fuel nozzles are opened represents with 1, it is the design maximum flow, the maximum load of corresponding motor, and the flow of single fuel nozzle is the 1/n of peak rate of flow.
As shown in Figure 2, take 8 fuel nozzles as example, the setting flow of each fuel nozzle is 1/8 of total discharge.At this moment, according to the various combination that opens and closes state, the fuel flow rate that 8 fuel nozzles can provide is 1/8,2/8,3/8 ..., 1(" 1 " just represents peak rate of flow).At this moment, available fuel flow rate is 1/8 stepping with the maximum fuel flow.
Fig. 3 is take 12 fuel nozzles as example, and the rated flow of each fuel nozzle is 1/12 of total discharge.At this moment, open and close the various combination of state according to it, the fuel flow rate that these 12 fuel nozzles can provide is respectively 1/12,2/12,3/12 ..., 1(" 1 " just represents peak rate of flow).At this moment, available fuel flow rate is 1/12 stepping with the maximum fuel flow.
Will be appreciated that, along with the increase of the quantity (n) of fuel nozzle, available fuel flow rate can provide more fine-grained variation, the variation that therefore can mate more accurately engine loading.In specific design, the quantity of fuel nozzle can be determined according to the anticipated load situation of change of motor.Therefore, as long as can realize theory of the present utility model, the utility model is not done any restriction to the concrete quantity of fuel nozzle.
As previously mentioned, the rated flow of single fuel nozzle also can be different.Fig. 4 has provided an example with five fuel nozzles.These five fuel nozzles comprise the first fuel nozzle IN1 and four the second fuel nozzle IN2 to IN5.These four the second fuel nozzle IN2 to IN5 can arrange around fuel nozzle IN1 and have different flows from fuel nozzle IN1.In the concrete example of Fig. 4, the setting flow of the first fuel nozzle IN1 is 1/2 of total discharge, and the setting flow of other the second fuel nozzle IN2 to IN5 is identical, is 1/8.
Such as Fig. 5, according to the various combination that opens and closes state, these five available fuel flow rates of fuel nozzle be peak rate of flow 1/8,2/8,3/8 ..., 1(" 1 " just represents peak rate of flow).Equally, by more fuel nozzle is set, also can provide more fine-grained fuel flow rate to change.The utility model is the quantity of fuel limitation nozzle not.And the rated flow of each fuel nozzle also is not limited to the occurrence that the example of Fig. 4 and Fig. 5 provides.The rated flow of the first fuel nozzle can be greater than or less than the rated flow of single the second fuel nozzle.
In this fuel nozzle with different rated flows that Fig. 4 and Fig. 5 provide designs, the rated flow of one of them fuel nozzle can corresponding motor self-sustain speed or self-holding power, and remaining fuel nozzle is complementary with summation and the gas turbine load that realizes fuel flow rate according to the rising of gas turbine load or lower and optionally open or close.For example, self-sustain speed or the self-holding power of the corresponding gas turbine of the rated flow of the first fuel nozzle IN1, and the second fuel nozzle IN2 to IN5 optionally opens or closes according to the variation of gas turbine load.
In the above-mentioned example, each fuel nozzle is independent control, is about to single fuel nozzle and regards a controlled unit as.But also can be as a controlled unit with a plurality of fuel nozzles in other embodiments.At this moment, these a plurality of fuel nozzle IN1, IN2, IN3 ... part of fuel designs of nozzles one-tenth among the INn is controlled simultaneously to be opened or closed.For example, Fig. 6 illustration a kind of such embodiment.Gas turbine is provided with first lap fuel nozzle INR1 and the second circle fuel nozzle INR2.Each circle fuel nozzle all comprises a plurality of fuel nozzles.The fuel nozzle that fuel control unit 104 can be controlled each circle opens or closes simultaneously.For example, when control the second circle fuel nozzle INR2 closed or opens, all fuel nozzles of this second circle fuel nozzle INR2 all cut out simultaneously or open.
In the above-described embodiments, first lap fuel nozzle INR1 has 5 nozzles, and the second circle fuel nozzle INR2 has 8 nozzles.In other embodiments, each circle can have the fuel nozzle of other number.And, in this nozzle arranges, the more fuel nozzle of multi-turn can be set, so that each circle fuel nozzle can cut out or open simultaneously.It should be understood that only be a kind of example with a plurality of fuel nozzles as a controlled unit along being circular layout, the utility model does not repel these fuel nozzles that will be designed to close simultaneously or open with other arranged in form yet.
In one embodiment, load determining unit 102 comprises load detecting or tracing system, for detection of or follow the trail of the load information of gas turbine.Fuel control unit 104 optionally opens or closes based on the load information control fuel nozzle of the gas turbine that this load detecting system detects, so that the summation of the rated flow of the fuel nozzle that is opened and determined load information are complementary.Load detecting can realize with known method, such as utilizes one or more sensors, so the details of load detecting no longer discusses in detail again.In one embodiment, this load detecting is carried out in real time, so fuel control unit 104 can respond in real time the load variations of gas turbine and control fuel nozzle and optionally opens or closes.
In another embodiment, load determining unit 102 also can be controlled fuel nozzle according to the gas turbine load information of operator's input and optionally open or close.At this moment, load determining unit 102 can comprise the load information inputting interface, is used for receiving the load information of operator's input.Fig. 7 illustration a kind of such load information inputting interface 110.This inputting interface 110 comprises controlling rod 112 and a plurality of controlling rods position 114.In conjunction with the inputting interface 110 of Fig. 7, we suppose that gas turbine is that generator generates electricity (that is, generator is as the load of gas turbine) and its maximum generation ability is 100KW for driving.These controlling rod positions 114 are the different generated output of correspondence respectively, such as 100KW, 90KW, 80KW, 70KW, 60KW, 50KW etc.When needs send the electric power of 50KW, the operator can input the load information of corresponding 50KW generated output, for example, the operator can move to controlling rod 112 position of corresponding 50KW, and this fuel control unit 104 is controlled a part of fuel nozzle according to the information of this operator input and is opened, and closes the remaining fuel nozzle.When requiring to send the electric power of 80KW, the operator can move to controlling rod 112 position of corresponding 80KW to input the load information of corresponding 80KW generated energy, and this fuel control unit 104 is controlled more fuel nozzle according to the information of this operator input and is opened, to realize the output power of 80KW.Equally, when needs send the electric power of 100KW, the position of the removable controlling rod 112 to 100KW of operator, all fuel nozzles of fuel control unit 104 meeting controls this moment are all opened.It should be understood that, the above-mentioned load information inputting interface 110 that comprises controlling rod 112 only is a kind of example, the operator also can input by other inputting interface the load information of gas turbine, and for example, phonetic entry, button are selected or Direct Digital is inputted etc.Equally, generating also only is a kind of example of gas turbine application.
After determining engine loading, fuel control unit 104 can determine first should the needed fuel flow rate of load, then determines that based on this definite fuel flow rate which fuel nozzle opens, and which fuel nozzle cuts out.Determine fuel nozzle open or close can by the inquiry look-up table carry out.For example, this control system can comprise the storage unit 116 that is connected with fuel control unit 104, be used for store look-up tables, this look-up table comprises that predefined fuel nozzle opens and closes the contrast relationship (being similar to the table of comparisons of Fig. 2 and Fig. 3) of state and fuel flow rate.For example, if look-up table is similar to the table of comparisons of Fig. 2, when definite needed fuel flow rate of corresponding gas turbine load is 5/8 of peak rate of flow, then can know by question blank 2, fuel nozzle IN1 to IN5 should open, and remaining fuel nozzle IN6 to IN8 should close.Then fuel control unit 104 control fuel nozzle IN1 to IN5 open, and control fuel nozzle IN6 to IN8 closes.In other embodiments, this storage unit 116 also can be used as the part of fuel control unit 104.And storage unit 116 also can fuel-in-storage control unit 104 needs some data of storing in control procedure.
Subsequently, the load information that load determining unit 102 continues to detect the load information of gas turbine or receives operator's input.If load does not change, then fuel control unit 104 does not need to change the state that opens or closes of fuel nozzle.If load changes, then load determining unit 102 is sent to fuel control unit 104 with the load information that changes, so that controlling each fuel nozzle according to the load information that changes, fuel control unit 104 optionally opens or closes, so that the summation of the rated flow of the fuel nozzle that is opened is complementary with the gas turbine load that changes.
In another embodiment, after definite gas turbine load, can directly determine that by the mode of inquiry look-up table the fuel nozzle that meets determined load opens and closes state.For example, at this moment, the look-up table of storage comprises that predefined fuel nozzle opens and closes the contrast relationship of state and gas turbine load in the storage unit 116.
Although in above embodiment, the opening and closing state of determining fuel nozzle is to be undertaken by the mode of inquiry look-up table.But should be understood that, also can determine by the mode of calculating the opening and closing state of fuel nozzle.No matter be by inquiry or calculating, those skilled in the art need not to pay creationary effort and just can realize after reading this paper understands essence of the present utility model, therefore no longer discuss in detail at this.
In a word, this paper has proposed a kind of Fuel Control System that improves the combustion system combustion efficiency.By controlling the state that opens or closes of each fuel nozzle, realize the control of fuel flow rate, to mate different combustion gas loads.In this manner, the flow of each fuel nozzle that is opened can always work under its rated flow, therefore the combustion efficiency of combustion system can be remained at basically the maximum combustion efficient of its design.Simultaneously, because these fuel combustions that are injected into are complete, then combustion system can effectively be controlled the effulents such as nitrogen oxide or carbon monoxide.In addition, owing to not needing to adopt Proportional valve with high costs, can reduce the cost of material of gas turbine.And owing to just controlling the two states that opens or closes of each fuel nozzle, compared to the proportional control of Proportional valve, the control mode that this paper proposes is greatly simplified, and therefore controls cost and further reduces, and reliability also can improve.
Concept described herein in the situation that do not depart from its spirit and characteristic may be embodied to other form.Disclosed specific embodiment should be regarded as exemplary rather than restrictive.Therefore, scope of the present utility model is by appended claim, rather than determines according to these descriptions before.The scope that all should belong to these claims in letter and any change in the equivalency range of claim.
Claims (10)
1. gas turbine fuel control system, described gas turbine comprises the firing chamber and is communicated with to inject a plurality of fuel nozzles of fuel to described firing chamber with described firing chamber, it is characterized in that, described Fuel Control System comprises load determining unit and fuel control unit, described load determining unit is used for determining the load information of described gas turbine, described fuel control unit is used for receiving determined load information and controlling these fuel nozzles according to received load information optionally opening or closing, so that the summation of the rated flow of the fuel nozzle that is opened and determined load information are complementary.
2. gas turbine fuel control system as claimed in claim 1, it is characterized in that, described a plurality of fuel nozzle comprises first fuel nozzle and a plurality of the second fuel nozzle, and the rated flow of the rated flow of wherein said the first fuel nozzle and single the second fuel nozzle is unequal.
3. gas turbine fuel control system as claimed in claim 2 is characterized in that, the self-sustain speed of the corresponding described gas turbine of the rated flow of described the first fuel nozzle.
4. gas turbine fuel control system as claimed in claim 2 is characterized in that, the rated flow of described the first fuel nozzle is greater than the rated flow of single the second fuel nozzle.
5. gas turbine fuel control system as claimed in claim 1 is characterized in that, the rated flow of each described fuel nozzle is identical.
6. gas turbine fuel control system as claimed in claim 1 is characterized in that, a part of fuel nozzle in described a plurality of fuel nozzles is designed to be controlled and cuts out simultaneously or open.
7. gas turbine fuel control system as claimed in claim 6, it is characterized in that, described a plurality of fuel nozzle comprises first lap fuel nozzle and the second circle fuel nozzle, each circle fuel nozzle includes a plurality of fuel nozzles, and a plurality of fuel nozzles of each circle fuel nozzle are designed to be controlled and cut out simultaneously or open.
8. gas turbine fuel control system as claimed in claim 1 is characterized in that, described load determining unit comprises the load detecting system, for detection of the load information of described gas turbine.
9. gas turbine fuel control system as claimed in claim 1 is characterized in that, described load determining unit comprises the load information inputting interface, is used for receiving operator's load information input.
10. gas turbine fuel control system as claimed in claim 1, it is characterized in that, described control system comprises the storage unit of store look-up tables, which fuel nozzle described fuel control unit determines to open by inquiring about described look-up table, and described look-up table comprises the contrast relationship of the fuel flow rate of the opening and closing state of the contrast relationship of the opening and closing state of each fuel nozzle and gas turbine load or each fuel nozzle and gas turbine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220348775 CN202746019U (en) | 2012-07-18 | 2012-07-18 | Fuel control system of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220348775 CN202746019U (en) | 2012-07-18 | 2012-07-18 | Fuel control system of gas turbine |
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| Publication Number | Publication Date |
|---|---|
| CN202746019U true CN202746019U (en) | 2013-02-20 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN 201220348775 Expired - Fee Related CN202746019U (en) | 2012-07-18 | 2012-07-18 | Fuel control system of gas turbine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102748137A (en) * | 2012-07-18 | 2012-10-24 | 深圳智慧能源技术有限公司 | Fuel control system of gas turbine |
-
2012
- 2012-07-18 CN CN 201220348775 patent/CN202746019U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102748137A (en) * | 2012-07-18 | 2012-10-24 | 深圳智慧能源技术有限公司 | Fuel control system of gas turbine |
| CN102748137B (en) * | 2012-07-18 | 2015-06-17 | 深圳智慧能源技术有限公司 | Fuel control system of gas turbine |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130220 Termination date: 20150718 |
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