CN104421003B - Gas turbine combustion system - Google Patents
Gas turbine combustion system Download PDFInfo
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- CN104421003B CN104421003B CN201410412682.7A CN201410412682A CN104421003B CN 104421003 B CN104421003 B CN 104421003B CN 201410412682 A CN201410412682 A CN 201410412682A CN 104421003 B CN104421003 B CN 104421003B
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 114
- 239000000446 fuel Substances 0.000 claims abstract description 248
- 238000011068 load Methods 0.000 claims abstract description 55
- 239000004615 ingredient Substances 0.000 claims abstract description 36
- 210000000214 Mouth Anatomy 0.000 claims abstract description 33
- 239000007789 gas Substances 0.000 claims description 155
- 239000007788 liquid Substances 0.000 claims description 22
- 230000001629 suppression Effects 0.000 claims description 13
- 239000000203 mixture Substances 0.000 claims description 6
- 206010018987 Haemorrhage Diseases 0.000 claims description 5
- 230000000740 bleeding Effects 0.000 claims description 5
- 231100000319 bleeding Toxicity 0.000 claims description 5
- 238000005259 measurement Methods 0.000 claims description 5
- 230000000875 corresponding Effects 0.000 claims description 4
- 238000002347 injection Methods 0.000 claims description 4
- 239000007924 injection Substances 0.000 claims description 4
- 239000000567 combustion gas Substances 0.000 claims description 2
- 230000003134 recirculating Effects 0.000 claims description 2
- 238000007906 compression Methods 0.000 claims 2
- 230000001052 transient Effects 0.000 claims 1
- 238000007792 addition Methods 0.000 description 17
- OKTJSMMVPCPJKN-UHFFFAOYSA-N carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 12
- UGFAIRIUMAVXCW-UHFFFAOYSA-N carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 11
- 229910002091 carbon monoxide Inorganic materials 0.000 description 11
- 239000001257 hydrogen Substances 0.000 description 11
- 229910052739 hydrogen Inorganic materials 0.000 description 11
- 239000003245 coal Substances 0.000 description 9
- 238000002309 gasification Methods 0.000 description 9
- 241000196324 Embryophyta Species 0.000 description 8
- 230000001276 controlling effect Effects 0.000 description 7
- 230000000694 effects Effects 0.000 description 7
- UFHFLCQGNIYNRP-UHFFFAOYSA-N hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 7
- CURLTUGMZLYLDI-UHFFFAOYSA-N carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 5
- 230000000630 rising Effects 0.000 description 5
- 229960004424 Carbon Dioxide Drugs 0.000 description 4
- 239000001569 carbon dioxide Substances 0.000 description 4
- 229910002092 carbon dioxide Inorganic materials 0.000 description 4
- 230000005611 electricity Effects 0.000 description 4
- 239000012530 fluid Substances 0.000 description 4
- 150000002431 hydrogen Chemical class 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 239000003345 natural gas Substances 0.000 description 4
- IJGRMHOSHXDMSA-UHFFFAOYSA-N nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 4
- 239000003921 oil Substances 0.000 description 4
- 239000007921 spray Substances 0.000 description 4
- 229940103846 Unburn Drugs 0.000 description 3
- 229910052799 carbon Inorganic materials 0.000 description 3
- 239000003034 coal gas Substances 0.000 description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000002093 peripheral Effects 0.000 description 3
- 239000004215 Carbon black (E152) Substances 0.000 description 2
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- 235000003140 Panax quinquefolius Nutrition 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 229910002090 carbon oxide Inorganic materials 0.000 description 1
- 239000000571 coke Substances 0.000 description 1
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- 239000000470 constituent Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 201000008286 diarrhea Diseases 0.000 description 1
- 201000010099 disease Diseases 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 239000003502 gasoline Substances 0.000 description 1
- 235000005035 ginseng Nutrition 0.000 description 1
- 235000008434 ginseng Nutrition 0.000 description 1
- XEEYBQQBJWHFJM-UHFFFAOYSA-N iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- ATUOYWHBWRKTHZ-UHFFFAOYSA-N propane Chemical compound CCC ATUOYWHBWRKTHZ-UHFFFAOYSA-N 0.000 description 1
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Abstract
The present invention provides a kind of gas turbine combustion system, it is possible to suppress the unburnt ingredient of gaseous fuel to discharge under the full load condition till from fractional load to nominal load.Above-mentioned gas turbine combustion system is characterised by possessing: multiple gas fuel combustion mouths (32,33)；IGV (9), it adjusts the flow of the air mixed with gaseous fuel；And control device (500), it in time being made the partial burn mode of gas fuel combustion be switched to the full-burn mode being made gas fuel combustion by all gas fuel combustion mouth (32,33) by a part for multiple gas fuel combustion mouths (32,33), makes air mass flow temporarily from standard flow to drop to set flow to IGV (9) output signal in combustion mode.
Description
Technical field
The present invention relates to gas turbine combustion system.
Background technology
In recent years, from cost of electricity-generating reduction, utilization of resources, prevent global warming angularly, research
Secondary to the coke-stove gas given birth to by steel plant's pair or the waste gas given birth to by oil plant pair etc. angry body is acted effectively as fuel.
It addition, study following scheme, by rich in natural resources i.e. Coal Gasification the Coal Gasification compound power-generating that generates electricity
In equipment (IGCC:Integrated coal Gasification Combined Cycle), by being fed to
System (the CCS:Carbon Capture and that carbon in the gaseous fuel of gas turbine reclaims, accumulates
Storage), the carbon of coal is converted into hydrogen (H2) and reduce carbon dioxide (CO2) output (ginseng
According to patent documentation 1 etc.).
Prior art literature
Patent documentation 1: Japanese Unexamined Patent Publication 2013-139975 publication
Secondary angry body or coal gas etc. are containing hydrogen.In the case of using this gaseous fuel, if loss of ignition,
Gaseous fuel unburned is directly discharged from burner and is caused hydrogen to immerse turbine.Therefore exist and use the side of operation as follows
The situation of method, with the most hydrogeneous starting fuel (oil fuel) igniting, by fuel under partial load conditions
After starting fuel replaces with gaseous fuel, increase quantity the frontad of the burner making gas fuel combustion
Fixed load conditional jump.In IGCC plant, due to gasification furnace utilize by turbine give up thermogenetic steam come
Generate coal gasification gas, therefore with the starting fuel starting turbine beyond coal gasification gas, and use above-mentioned
Operation method.
But, (below, combustion mode is made the pattern of gas fuel combustion from a part of burner of use
Partial burn mode) it is switched to use whole burners to make the pattern of gas fuel combustion (below, completely
Combustion mode) after, owing to the expansion of the increase ratio combustion zone relative to fuel flow rate is relatively big, therefore
Fuel concentration temporarily reduces.During fuel concentration reduces, flame temperature reduction causes gaseous fuel not
Burning completely, the output of the unburnt ingredients such as CO or unburned hydrocarbon, increases.In this case,
The output that there is unburnt ingredient, exceedes the trouble of the inconvenience such as environment limits value and then generating output reduction.
Summary of the invention
It is an object of the invention to provide a kind of gas turbine combustion system, it is possible to from fractional load to specified
The discharge of the unburnt ingredient of gaseous fuel is suppressed under the full load condition of load.
For achieving the above object, the present invention by combustion mode from the part by multiple gas fuel combustion mouths
The partial burn mode making gas fuel combustion switches to the burner by whole multiple gaseous fuels to make gas
During the full-burn mode of fuel combustion, burner inlet air flow rate is made temporarily to drop to from standard flow set
Constant flow.
The effect of the present invention is as follows.
According to the present invention, under the full load condition from fractional load to nominal load, suppress gaseous fuel not
The discharge of combusting component.Therefore, even if using containing H2Or the gaseous fuel of CO also is able to suppress CO
Or the output of unburned hydrocarbon etc..
Accompanying drawing explanation
Fig. 1 is the turbine device of the gas turbine combustion system of the first embodiment representing and possessing the present invention
The figure of a configuration example.
Fig. 2 is to represent from the IGV divergence started to normal loading conditions of gas turbine, burner
The figure of the change of inlet air flow rate, fuel flow rate, fuel air ratio and burning gas temperature.
Fig. 3 is to represent the control possessed by the gas turbine combustion system of first embodiment of the present invention
The control block exporting order to the command signal of air mass flow adjusting apparatus that device is carried out.
Fig. 4 is the pass of local flame temperature and the unburnt ingredient output representing main burner outer region
The figure of anchor line (string).
Fig. 5 is to represent outside main burner required below setting for the suppression of unburnt ingredient output
The figure of the relation that all flame temperatures form with gaseous fuel.
Fig. 6 is the figure of the change representing that all amounts such as unburnt ingredient output load relative to gas turbine.
Fig. 7 is the turbine device representing the gas turbine combustion system possessing second embodiment of the present invention
The figure of a configuration example.
Fig. 8 is the turbine device representing the gas turbine combustion system possessing third embodiment of the present invention
The figure of a configuration example.
In figure: 2 compressors, 3 burners, 4 turbines, 6 electromotors, 9 IGV (air stream
Amount adjusting apparatus), 11 bleed adjusts valve (air mass flow adjusting apparatus), and 14 bleed adjusts valve (air
Flow adjuster), 20 air orifice plates, 21 airports, 22 fuel nozzles, 32 pilot-operated type combustions
Burner (gas fuel combustion mouth, double-combustion mouth), 72 gas fuel systems, 400 gasmetry devices,
500 control device, 601 gas temperature measuring devices.
Detailed description of the invention
Embodiments of the present invention are illustrated by accompanying drawing used below.
The gas turbine burner of the present invention, in addition to common gaseous fuel, is also applied for making as forming into
Gaseous fuel (hereinafter referred to as the hydrogen-containing fuel) burning that subpackage is hydrogeneous.Specifically, the combustion gas of the present invention
Turbine combustion device can be preferably applied to such as, except using the coal gas of hydrogen-containing fuel obtained by Coal Gasification
Change outside combined cycle plant, the secondary angry body i.e. coke-stove gas (COG:Coke that will obtain from ferrum equipment processed
Oven Gas), blast furnace gas (BFG:Blast Furnace Gas), coal gas of converter (LDC:Linzer
Donawitz Gas) or their mixed gas is used as the gas turbine of fuel or uses from raw gasoline
The secondary angry body etc. that decomposer etc. obtain comprises the gaseous fuel (hydrogen-containing fuel) with hydrogen as constituent
Gas turbine.
(the first embodiment)
1. gas-turbine plant
Fig. 1 is the turbine device of the gas turbine combustion system of the first embodiment representing and possessing the present invention
The figure of a configuration example.
Gas-turbine plant 1 shown in this figure possesses gas turbine and by gas turbine powered electromotor
6.Gas turbine possesses compressor 2, gas turbine combustion system and turbine 4.Compressor 2, turbine 4
And each rotor of electromotor 6 is attached on coaxial.Carrying out following to gas turbine combustion system, it possesses
Burner 3 is as main element.
The action of this gas-turbine plant 1 is as described below.I.e., the air 101 sucked from air is by air
Compressor 2 compresses, and compressed air 102 supplies to burner 3.Gaseous fuel and pressure is made in burner 3
Contracting air 102 together burns and generates burning gases 110.Turbine 4 is by the burning generated by burner 3
Gas 110 drives.Electromotor 6 is driven by the rotary power of turbine 4 and generates electricity.
2. gas turbine combustion system
Gas turbine combustion system possess burner 3, liquid fuel system 71, gas fuel system 72,
IGV9 and control device 500.The most successively these elements are illustrated.
Burner
Burner 3 possesses urceolus 10, liner 12, tail pipe (not illustrating) and burner 8.Urceolus 10
It is disposed on the cylinder-like part of turbine case (not shown) peripheral part.Urceolus 10 with turbine 4 opposition side
End (head) closed by end shield 13.Liner 12 is to be internally formed the cylindric burning of combustor 5
Device inner core, is arranged at the inner side of urceolus 10 and is formed with ring-type air flow channel between urceolus 10.?
It is equipped with multiple airport on this liner 12.Combustor 5 be by liner 12 between burner 8 and tail pipe
The space formed, together burns at this with air 102a from the fuel of burner 8 ejection.Tail pipe is and whirlpool
The parts that the air flue entrance (primary stator blade entrance) of wheel 4 and liner 12 connect swimmingly.It addition,
Oriented burner 8 is set on end shield 13 and distributes the fuel distributor 23 of fuel.Although it addition, the most especially
Diagram, but in burner 3, it is also equipped with the ignition of mixed gas to the fuel in combustor 5 and air
Igniter.In gas-turbine plant 1, turbine case (not shown) peripheral part along the circumferential direction with
Certain is arranged at intervals with multiple such burner 9.
Burner 8 is arranged on end shield 13 between combustor 5.This burner 8 is containing multiple
Unit burner, the central part at burner 3 configures a pilot-operated type burner 32, burns at pilot-operated type
In the way of surrounding pilot-operated type burner 32, it is configured with multiple main burner 33 outside the direction, footpath of mouth 32.
Each main burner 33 is gas fuel combustion mouth, possesses air orifice plate 20 and multiple fuel nozzle
22.But, air orifice plate 20 is that the air orifice plate of multiple main burner 33 is connected to each other.This airport
Plate 20 is configured to interarea (area maximum one side) towards combustor 5, and has multiple edge from end shield 13
The airport 21 extended towards the direction of combustor 5.Air is sprayed to combustor 5 from these airports 21
102a.There is the airport 21 the most paired with each fuel nozzle 22, each fuel nozzle 22 is with corresponding
Airport 21 be in coaxial mode and extend from fuel distributor 23, it addition, there is also each fuel nozzle
The situation of airport 21 (being positioned at airport 21) is inserted in the front end of 22, but constitutes in the present embodiment
For front end relative with the entrance of airport 21 (than air orifice plate 20 closer to end shield 13 side).Spray from fuel
The gaseous fuel of mouth 22 injection is by having the airport 21 of corresponding relation, and by this airport 21
Air 121a mono-combustor 5 in the same direction sprays.It addition, in multiple main burners 33, airport 21 is also
It is listed on the multiple row centered by each burner axle (being 3 row in this example) concentric circular.By these airports
Row be denoted as successively outside the direction, centrally directed footpath of each main burner 33, first row airport 51,
Two row airport 52 and the 3rd row airports 53.Additionally, in the following description, it is being referred to as " main combustion
Burner inner circumferential " in the case of refer to the first row airport 51 of each burner 33, be referred to as " main burner
Periphery " in the case of refer to secondary series airport 52 and the 3rd row airport 53.
Pilot-operated type burner 32 is to make gaseous fuel and the double-combustion mouth of liquid fuel both sides burning, position
Center in multiple main burners 33.Specifically, it is configured to possess gas fuel combustion mouth and liquid
Fuel combustion mouth.The structure of gas fuel combustion mouth is similar with main burner 33, has air orifice plate
With multiple fuel nozzles, air orifice plate is provided with the multiple airports paired with each fuel nozzle.This gas
The difference of fluid fuel burning mouth and main burner 33 be airport be classified as two row and airport towards
Combustor 5 also rolls tiltedly to the central shaft of burner 3.Liquid fuel combustion mouth is by liquid fuel nozzle (example
Such as atomizer) 40 compositions, it is positioned at central authorities' (airport row of gas fuel nozzle in gas fuel nozzle portion
Center).
Liquid fuel system
Liquid fuel system 71 is that the liquid fuel nozzle 40 to pilot-operated type burner 32 supplies liquid fuel
Fuel system, possess liquid fuel source 210, fuel cutoff valve 65 and fuel control valve 66.From liquid
Fluid fuel source 210 supplies the oil fuels such as the light oil as starting fuel, kerosene or A heavy oil.This liquid
Fluid fuel source 210 is connected with liquid fuel nozzle 40 by pipeline 204.Pipeline 204 is provided with
State fuel cutoff valve 65 and fuel control valve 66.Fuel cutoff valve 65 and fuel control valve 66 origin
The signal of self-control device 500 drives, and each carries out either on or off or changes divergence.
Gas fuel system
Gas fuel system 72 is the gas fuel combustion mouth to pilot-operated type burner 32 and each main burning
The fuel system of mouth 33 gaseous fuelled, possesses gas fuel source 200, fuel cutoff valve 60 and combustion
Material control valve 61-63.Coke-stove gas, refinery flares or Coal Gasification is supplied from gas fuel source 200
Gas etc. are containing hydrogen or the fuel of carbon monoxide.The pipeline that the gaseous fuel of this gas fuel source 200 is passed through
Fork is the pipeline 201-203 of three systems, pipeline 201 and the gas fuel combustion mouth of pilot-operated type burner 32
The fuel distributor 23 in portion connects, and pipeline 202 is connected with the fuel distributor 23 of each main burner inner circumferential,
Pipeline 203 is connected with the fuel distributor 23 of each main burner periphery.Fuel cutoff valve 60 is arranged at fork
Front pipeline, fuel control valve 61-63 is respectively arranged at pipeline 201-203.Fuel cutoff valve 60 and combustion
The signal of material control valve 61-63 origin self-control device 500 drives, and each carries out either on or off or changes scattered
Degree.Either on or off and divergence by fuel control valve 61-63 adjust, and are configured to pilot-operated type burner
32, the variable-scale of the gaseous fuel of each main burner inner circumferential and the supply of each burner periphery.
It addition, pipeline between gas fuel source 200 and fuel cutoff valve 60 is provided with gasmetry
Device 400 and gas temperature measuring device 601.Gasmetry device 400 is to measure to supply from gas fuel source 200
The composition of the gaseous fuel given or the measuring device of caloric value, in this case, measure hydrogen, one
Carbonoxide, methane, carbon dioxide, the concentration of nitrogen, and measure caloric value based on these measured values.Gas
Temperature meter 601 is the measuring devices such as the thermocouple of the temperature measuring gaseous fuel, sets in the present embodiment
Put from the pipeline between gas fuel source 200 and fuel cutoff valve 60 to the pipeline of gasmetry device 400
In Tu.
·IGV
IGV (Inlet Guide Vane) 9 is disposed on the inlet guide vane of compressor 2 entrance.At this
In embodiment, IGV9 plays the sky of the flow adjusting the air mixed in burner 3 with gaseous fuel
The effect of throughput adjusting apparatus, regulates, by the divergence of regulation IGV9, the air 101 that compressor 2 sucks
Flow, its result can regulate to burner 3 supply air mass flow.
Control device
Control device 500 and there is following function, electrically-based measuring device 602, air themperature measuring device 603,
The measurement result of air-flow measurement device 604, gas temperature measuring device 601 and gasmetry device 400 is come
Control fuel cutoff valve 60,65, fuel control valve 61-63,66 and IGV9.Controlling device 500
In comprise collection have fuel cutoff valve 60,65, the control institute of fuel control valve 61-63,66 and IGV9
Necessary program or the storage part of data or storage have fuel cutoff valve 60,65, fuel control valve 61-63,
The storage part of the control record (divergence record) of 66 and IGV9.Specifically, device 500 is controlled
By combustion mode from being made the part of gas fuel combustion burn by a part for multiple gas fuel combustion mouths
When pattern switches to the full-burn mode being made gas fuel combustion by whole multiple gas fuel combustion mouths, to
IGV9 output signal makes air mass flow temporarily drop to set flow from standard flow.
So-called " partial burn mode " refers to when at least one system in closing pipeline 201-203
Make the combustion mode of gas fuel combustion, such as close pipeline 202,203 and only to pilot-operated type burner 32
Distribution gaseous fuel state, close pipeline 203 and only to pilot-operated type burner 32 and each main burner
The state of inner circumferential distribution gaseous fuel.So-called " full-burn mode " is referred to complete for pipeline 201-203
Portion opens, from pilot-operated type burner 32, whole main burner inner circumferentials and whole main burner peripheries
The combustion mode of injection gaseous fuel.It addition, so-called " standard flow " refers to consider suppression fractional load
Under the conditions of the generation agitated and freeze of compressor 2 and the value set.So-called " setting flow " refer to
Suppression is local fuel air ratio near burner end face when partial burn mode shifts to full-burn mode
Deviation is objective, based on the gas measured by gasmetry device 400 and gas temperature measuring device 601 respectively
Composition and the temperature of fuel and by controlling the value that device 500 calculates.
3. action
Fig. 2 is to represent from the IGV divergence started to normal loading conditions of gas turbine, burner
The figure of the change of inlet air flow rate, fuel flow rate, fuel air ratio and burning gas temperature.At this figure
Higher level, by combustion mode signalization, represents at the burner burnt in operation with blacking.
Following (a)～(f) can be substantially divided into from the process started till transferring to normal loading conditions
6 processes.
A () gas turbine starts
B () is non-loaded rated revolution (FSNL:Full Speed No Load)
(c) Fuel switching (liquid fuel → gaseous fuel)
(d) gas burn down mode switching (partial burn mode → full-burn mode)
E () controls, because of delivery temperature, the IGV divergence increase that setting causes
(f) normal loading conditions
Hereinafter each process is illustrated.
(a)～(b): gas turbine starts～non-loaded rated revolution
Control device 500 to rise employ motor (not illustrating) output signal, by rise employ motor start combustion
Gas-turbine.Thereafter, device 500 can be controlled after the value of ignition condition when gas turbine revolution rises to meet
To fuel cutoff valve 65 and fuel control valve 66 output signal, to liquid fuel nozzle 40 for liquid
Fuel also makes burner 3 light a fire.Start to starting to obtain load (starting generating) from gas turbine
Operation area is referred to as accelerating region.In accelerating region, control device 500 to IGV9 and fuel control valve 66
Output signal, keeps the divergence of IGV9, on one side till turbine rpm reaches regulation revolution consistently
Promote the divergence of fuel control valve 66.Thus together increase fuel air ratio with fuel flow rate, make burner outlet
Gas temperature rise.
After turbine rpm reaches regulation revolution, control device 500, to IGV9 output signal, makes IGV9
Divergence increase to benchmark divergence.Thereafter, along with the increase of fuel flow rate, gas turbine revolution reaches without negative
Carry rated revolution (FSNL).It addition, (IGV divergence reaches benchmark after air mass flow reaches standard flow
After divergence), control device 500, to electromotor 6 output signal, starts to obtain load (starting generating).
Here, " benchmark divergence " is the IGV divergence for realizing said reference flow, it is with negative in part
Compressor 2 will not be made under the conditions of load to produce the divergence that the mode agitated or freeze specifies.What is called is agitated and is referred to
When increasing the pressure ratio of compressor 2, produce under any pressure ratio with sound effect the most significantly
Pressure oscillation, the big ups and downs of air stream and mechanical vibration and make unstable the showing of action of compressor 2
As.So-called accumulated ice refers to, in the case of reducing the divergence of IGV9 under conditions of temperature is relatively low, along with IGV9
The increase fluid temperature (F.T.) of muzzle velocity (Mach number) decline and the phenomenon that makes in air contained moisture freeze.
Freeze if producing, then the moisture (ice cube) solidified and the blade collision of compressor 2, there is damaged blade
Hidden danger.
(b)～(c): non-loaded rated revolution～Fuel switching
After reaching non-loaded rated revolution, control device 500 and start to obtain load, Operational Zone from electromotor 6
Territory is load rising area.In this region, IGV9 is kept with controlling device 500 constant (benchmark divergence)
Divergence, and constant (standard flow) keep burner inlet air mass flow.Therebetween, due to load
Together increasing fuel flow rate and make fuel air ratio increase, therefore burner outlet gas temperature rises.Make in load
Rise, arrive by fuel from employ liquid fuel switch to gaseous fuel regulation partial load conditions (figure
(c) in 2).
(c)～(d): Fuel switching～the switching of gas burn down mode
After arriving the partial load conditions of regulation, control device 500 to fuel cutoff valve 60,65 and combustion
Material control valve 61,62,66 output signal, makes the flow of liquid fuel reduce and makes for guide
The flow of the gaseous fuel of formula burner 32 and main burner inner circumferential increases, and is cut from liquid fuel by fuel
It is changed to gaseous fuel.Combustion mode after Fuel switching is only to use pilot-operated type burner 32 and main burning
The partial burn mode of mouth inner circumferential.In the operation area of partial burn mode, control device 500 by IGV
Divergence maintains benchmark divergence, and burner inlet air mass flow is maintained at standard flow.Fire in fractional load
In the operation of burning pattern, control device 500 and coordinate load rising to make the flow of gaseous fuel increase, by increasing
Adding fuel air ratio, burner outlet gas temperature also rises.
(d)～(e): the switching of gas burn down mode～IGV divergence increase
After the partial load conditions (d) of the regulation arriving switching combustion mode, control device 500 to fuel
Control valve 61-63 output signal, also to main burning in addition to pilot-operated type burner 32 and main burner inner circumferential
Mouth periphery distribution gaseous fuel, is switched to full-burn mode by combustion mode from partial burn mode.To
When combustion mode switches to full-burn mode, control device 500, to IGV9 output signal, makes IGV dissipate
Spend from benchmark divergence decline (only Δ IGV) to setting divergence, temporarily make burner inlet air mass flow subtract
Few.Thereafter, make IGV divergence gradually return to benchmark divergence from setting divergence, and make burner inlet air
Flow returns standard flow.Therebetween, controlling device 500 coordinates load rising to make the flow of gaseous fuel increase.
(e)～(f): IGV divergence increases～normal loading conditions
Thereafter, burner outlet gas temperature rises along with load and rises, and the delivery temperature arriving turbine surpasses
Cross the condition (e) of limit value.After arriving this condition (e), control device 500 and make the divergence of IGV9
Increase further from benchmark divergence, control burner outlet gas temperature by delivery temperature suppression limit value with
Under.By load arrival 100%, service condition transfers to normal loading conditions.Additionally, rise in load
Qu Zhong, the region in addition to normal loading conditions (load 100%) is referred to as fractional load region.
Here, Fig. 3 is to represent to utilize the command signal to air mass flow adjusting apparatus controlling device 500 defeated
Go out the control block of order.
By combustion mode after partial burn mode is switched to full-burn mode, need to dissipate IGV
Spend and narrow down to setting divergence IGV from benchmark divergence IGV0 '.The switching of this combustion mode is born by gas turbine
It is downloaded to reach above-mentioned condition (d) and trigger.Therefore, the electrically-based measuring device of device 500 602 is being controlled
After measurement result judges gas turbine load reaching condition (d), start the change instruction of IGV divergence
Control.
After starting the control of change instruction of IGV divergence, control device 500 and input by gasmetry device 400
The concentration of unburnt ingredient and the gas measured by gas temperature measuring device 601 in the gaseous fuel measured
The temperature of fuel.The unburnt ingredient concentration of the most so-called input, refers to suppress unburned and direct
Concentration from the gaseous fuel of the object component of burner 3 discharge, refers to hydrogen or carbon monoxide specifically
Concentration, additionally, also comprise the concentration of methane, carbon dioxide, nitrogen.Receive in advance in controlling device 500
Keep the local flame temperature of main burner outer region and the relation line of unburnt ingredient output (with reference to figure
4), and according to this relation input value based on unburnt ingredient concentration calculate and meet unburnt ingredient output
The main burner periphery local flame temperature Tr of fixed value Unburn (r).Now, strictly speaking, rule
Determine flame temperature Tr not only along with the concentration change of the unburnt ingredient being contained in gaseous fuel, also as combustion
Material temperature degree and change.Fig. 5 is to represent the master by required below setting for the suppression of unburnt ingredient output
The figure of the relation that burner periphery flame temperature forms with gaseous fuel.As shown in the drawing, in gaseous fuel
Unburnt ingredient concentration is the highest or fuel temperature Tf (Tf1 < Tf2 < Tf3) is the lowest, then meet unburned burning till
The Tr of divider definite value Unburn (r) is the highest.Therefore, collect the most in advance at control device 500
The local flame temperature of main burner outer region and the pass of unburnt ingredient output under each ignition temperature
System, in controlling device 500, it is desirable to input value based on unburnt ingredient concentration with fuel temperature calculates
Main burner periphery local flame temperature Tr.
It follows that control device 500 based on from gasmetry device 400, gas temperature measuring device 601 and
The present fuel composition of air themperature measuring device 603 input, fuel temperature, air themperature and calculate
Main burner periphery local flame temperature Tr, calculates for realizing main burner periphery local flame temperature
Local fuel air ratio (F/A) r of the main burner peripheral end face near zone of Tr.Then from (F/A) r and
The divergence of present gas fuel flow rate (fuel control valve 61-63) calculates and realizes local, main burner periphery
Air mass flow Ar required for flame temperature Tr.
Finally, control device 500 and compare Ar and present air mass flow, and divergence based on IGV is with empty
The relation of throughput, calculates variation delta IGV of IGV divergence.Now, in order to avoid because of IGV divergence
Extremely reducing and produce and agitate or freeze, Δ IGV is limited divergence (minimum decrement) by IGV and limits.
Then, control device 500, based on the Δ IGV calculated, calculates and makes IGV divergence become setting divergence IGV '
The command value of (=IGV0-Δ IGV), and to IGV9 output instruction signal.So, IGV9
Divergence reduces to setting divergence IGV ', air mass flow is contracted to set flow.Control device 500 subsequently also
It is repeatedly carried out the order of Fig. 3.In the order being repeatedly carried out Fig. 3, the fuel air ratio of main burner outer region
Rise, setting divergence IGV of calculation ' move closer to benchmark divergence IGV0.I.e., divergence IGV is set ' and
Non-constant.The result of the control of this IGV divergence, after making IGV divergence reply benchmark divergence IGV0, control
Device 500 processed terminates the order of Fig. 3, IGV divergence is maintained at benchmark divergence IGV0 and increases fuel stream
Amount, increases IGV divergence through condition (c) as above, thus is transferred to normal loading conditions.
4. action effect
Fig. 6 is the figure of the change representing that all amounts such as unburnt ingredient output load relative to gas turbine.?
In this figure, burner inlet air mass flow will be kept in the feelings of standard flow when shifting to full-burn mode
Condition represents in the lump as comparison other.The actuating wire that comparison other shares with present embodiment is illustrated by the broken lines,
Actuating wire specific to the present embodiment differently changed with comparison other is represented with solid line difference.At this
Figure represents and starts to the IGV divergence arrived normal loading conditions, unburnt ingredient from gas turbine
The change of the local flame temperature in each region of output, fuel flow rate, fuel air ratio and burner.
First, it is conceived to when full-burn mode shifts burner inlet air mass flow is maintained at reference flow
Amount situation, it can be seen that gas burn combustion mode from partial burn mode to full-burn mode
During switching (d), unburnt ingredient output, increases sharply.Thereafter, although along with load rises unburnt ingredient row
Output slowly reduces, but unburnt ingredient output more state temporarily continues, and exists and exceedes environment limit
The probability of value processed.Thereafter further up when load, under the conditions of a certain, unburnt ingredient output, starts
Reduce, arrive normal loading conditions with keeping thereafter less unburnt ingredient output.
The reason that unburnt ingredient output increases to standard flow when full-burn mode shifts is constant
Consider as follows.I.e., after combustion mode switches to full-burn mode, fuel flow rate is shown greatly shown in Fig. 3
Ratio distribute to each burner.As shown in the drawing, the most main burner outer region after being initially supplied fuel
Fuel air ratio less than pilot-operated type burner or main burner inner circumferential, at the local flame temperature of main burner periphery
In the state lower than other.Its result, from the gaseous fuel of main burner periphery ejection the most completely
It is discharged as a part of unburnt ingredient under the state of burning.Further, since gaseous fuel contains CO,
Therefore compared to the fuel such as the natural gas typically used have unburnt ingredient output be prone to increase become
Gesture.Load rises post fuel flow and increases, and (is somebody's turn to do when the flame temperature of main burner periphery rises to a certain temperature
T0 in figure) after, also begin to burn completely at main burner outer region gaseous fuel, unburnt ingredient
Output, reduces.
To this, in the present embodiment, by adjusting as shown by the solid line when shifting to full-burn mode
IGV divergence also reduces air mass flow, it is possible to be maintained at by the local flame temperature of main burner outer region
More than Tr also suppresses unburnt ingredient output.Therefore, even if using containing H2Or the gaseous fuel of CO,
Also be able to from fractional load to fix load full load condition suppress the unburned of gaseous fuel to burn till
The discharge divided.Thereby, it is possible to suppression unburnt ingredient output exceedes environment limits value, more can suppress to send out
Electricity output reduces.
It addition, the gaseous fuel of present embodiment contains hydrogen (H2) or carbon monoxide (CO) conduct is mainly
Composition, very fast compared to natural gas (the being mainly composed of methane) burning velocity that gas turbine is typically used.
Therefore, the burner end face in combustor 5 is formed about the flame of high temperature.To this, in present embodiment
The burner structure that middle employing is following, is arranged in pairs multipair fuel nozzle 22 and airport 21, by multiple
Airport 21 sprays the fuel stream around being covered state by air stream in combustor 5, and by runner
Expand rapidly and make fuel and air mixing sharp.Accordingly, because can be while improving the dispersibility of fuel
While making fuel combustion in combustor equably, it is possible to suppression forms the flame of high temperature, and can press down
The metal temperature of burner processed rises.It addition, additionally aid reduction NOXOutput.
It addition, calculate unburned burning till by measured value based on gasmetry device 400 or temperature meter 601
Point output, is suppressed in setting divergence IGV of Unburn (r) ', it is possible to reasonably suppress unburnt ingredient
Output.
Further, since the ratio supplying the gaseous fuel to each burner district can be changed by fuel control valve 61-63
Become, therefore, effectively make main burner periphery by making the fuel flow rate of main burner outer region increase
The local flame temperature in region rises such that it is able to suppression unburnt ingredient output effectively.It addition, also
Contribute to suppressing fuel irregular.
As being positioned at the pilot-operated type burner 32 at main burner 33 center, by possess make gaseous fuel and
The double-combustion mouth of liquid fuel both sides burning, it is possible to after Fuel switching is gaseous fuel also from burner
Injection fuel near the heart such that it is able to maintain the uniformity of burning.
(the second embodiment)
Fig. 7 is the turbine device representing the gas turbine combustion system possessing second embodiment of the present invention
The figure of a configuration example.Identical with foregoing figures to portion markings as the first embodiment in this figure
Reference also omits the description.
The present embodiment difference from the first embodiment is, makes the compressed air compressed by compressor 2
The air-breathing recirculating system (IBH system: Inlet Bleed Heat) of 102 entrances returning this compressor 2
Adjustment valve 11 of bleeding be air mass flow adjusting apparatus.So-called IBH system refers to by making compressed air 102
A part return compressor 2 air-breathing make the temperature of compressed air 102 rise and reduce air mass flow
System.IBH system has the effect identical with IGV system, returns the flow of suction port of compressor by bleeding
Adjust valve 11 to adjust.Present embodiment is configured to be controlled to bleed by control device 500 adjust the divergence of valve 11
Replace IGV9, bled by control and adjust the divergence of valve 11, adjust burner inlet as illustrated in fig. 2 empty
Throughput.Other points are identical with the first embodiment.
Even if in the present embodiment, because can be bled tune by raising when shifting to full-burn mode
The divergence of whole valve 11 makes the flow of compressed air 102 reduce, so also being able to obtain and the first embodiment
Identical effect.
(the 3rd embodiment)
Fig. 8 is the turbine device representing the gas turbine combustion system possessing third embodiment of the present invention
The figure of a configuration example.Identical with foregoing figures to portion markings as the first embodiment in this figure
Reference also omits the description.
The present embodiment difference from the most each embodiment is, with the air that will aspirate from compressor 2
To the adjustment valve 14 of bleeding of the separate system of turbine 4 shunting for air mass flow adjusting apparatus.Separate system is
Using a compressed-air actuated part as turbine 4 high-temperature component cooling air suction system, it is possible to pass through
Bleed and adjust the divergence adjustment of valve 14, control burner inlet air mass flow as illustrated in fig. 2.Additionally,
Although illustrating the most especially, but IGV9 or IBH can be set in the gas turbine of present embodiment.
In this case, in partial load run, in partial burn mode and the Operational Zone of full-burn mode
Time maintain IGV9 or extraction flow to adjust the divergence of valve 11 with benchmark divergence, the adjustment valve 14 that controls to bleed is made
For burner inlet air mass flow to be narrowed down to the method setting flow IGV ' from standard flow IGV0.Its
His structure is identical with the first or second embodiment.
Even if also being able in the present embodiment obtain the effect identical with the first or second embodiment.Separately
Outward, because when shifting to full-burn mode, reducing in burner inlet air mass flow and make each burner
The local flame temperature in region increases the cooling air delivery of turbine when rising, it is possible to relax Metal Temperature
The rising of degree.
(other)
In the respective embodiments described above, although the present invention to be suitable for use with coke-stove gas, refinery flares
Or coal gasification gas etc. is with hydrogen (H2) or the combustion of gaseous fuel that carbon monoxide (CO) is main component
Illustrate in case of gas-turbine combustion system, but can certainly use as gaseous fuel main
Other gaseous fuels including natural gas.Although it addition, to use liquid fuel as the feelings of starting fuel
Illustrate as a example by condition, but also be able to use the gaseous fuel such as natural gas or propane as starting fuel.
In this case, pilot-operated type burner needs not be double-combustion mouth.
Although it addition, to be applicable to the present invention be arranged in pairs multipair fuel nozzle 22 and airport 21 and lead to
Cross multiple airport 21 in combustor 5, spray the combustion of the multiple fuel streams around being covered state by air stream
Illustrate in case of the gas turbine combustion system of nozzle structure, but the present invention also is able to be applicable to
The gas turbine of the main burner of other combustion systems such as the burner possessing general premixed combustion mode
Combustion system.
It addition, calculate setting flow with the input signal based on gasmetry device 400 or temperature meter 601,
And burner inlet air mass flow is illustrated as a example by standard flow is contracted to the structure of setting flow.
However, it is also possible to control to set flow along actuating wire set in advance, it means that in combustion mode to completely
Gasmetry device 400 or the input of gas temperature measuring device 601 is need be not necessarily based on during combustion mode switching
Signal calculates setting flow.Even if it addition, select to calculate mensuration flow, it is also possible to based on gasmetry device
400 and the measured value of gas temperature measuring device 601 calculate, by set flow calculate based on not
Certain needs uses such as electricity meter 602, air themperature measuring device 603, air-flow measurement device 604
Deng input value.
Although it addition, saying in case of the present invention is applicable to single axle single cycle gas turbine
Bright, but the present invention also is able to be applicable to twin-shaft turbine or association circulating power generation system, high humility sky
Diarrhea due to disorder of QI gas turbine (AHAT:Advanced Humid Air Turbine) and being heated by turbine exhaust
The gas turbine of other modes such as the regeneration cycle gas turbine of compressor outlet air.
Claims (11)
1. a gas turbine combustion system, it is characterised in that possess:
Multiple gas fuel combustion mouths；
Air mass flow adjusting apparatus, this air mass flow adjusting apparatus adjusts the stream of the air mixed with gaseous fuel
Amount；
The gasmetry device of the concentration of the unburnt ingredient in measurement above-mentioned gas fuel；
Measure the gas temperature measuring device of the temperature of above-mentioned gas fuel；And control device, this control device
The part of gas fuel combustion is made to fire in combustion mode from by a part for above-mentioned multiple gas fuel combustion mouths
Burning pattern is switched to be made the mould of burning completely of gas fuel combustion by whole above-mentioned multiple gas fuel combustion mouths
During formula, according to the concentration of the unburnt ingredient in the above-mentioned gas fuel measured by above-mentioned gas measuring device and
The temperature of the above-mentioned gas fuel measured by above-mentioned gas temperature meter, calculates and adjusts for above-mentioned air mass flow
The command value of engagement positions output signal make air mass flow temporarily drop to set flow from standard flow, and
And, therebetween, coordinate load to rise and make the flow of above-mentioned gas fuel increase.
Gas turbine combustion system the most according to claim 1, it is characterised in that
Said reference flow be consider suppression compressor produce under partial load conditions agitate and freeze and
The value set.
Gas turbine combustion system the most according to claim 1, it is characterised in that
Above-mentioned air mass flow adjusting apparatus is the inlet guide vane of compressor.
Gas turbine combustion system the most according to claim 1, it is characterised in that
Above-mentioned air mass flow adjusting apparatus is to make to be returned the entrance of this compressor by the air of compressor compresses
The adjustment valve of bleeding of air-breathing recirculating system.
Gas turbine combustion system the most according to claim 1, it is characterised in that
Above-mentioned air mass flow adjusting apparatus be by from the air of compressor suction to the separate system of turbine bypass
Adjustment valve of bleeding.
Gas turbine combustion system the most according to claim 1, it is characterised in that
Above-mentioned gas fuel combustion mouth possesses air orifice plate and multiple fuel nozzle, described air orifice plate towards
Combustor and have multiple airport, the plurality of fuel nozzle has the most corresponding with above-mentioned multiple airports
Relation, and the gaseous fuel of injection is supplied to above-mentioned combustor by corresponding airport.
Gas turbine combustion system the most according to claim 1, it is characterised in that
Possessing gas fuel system, this gas fuel system makes supply to above-mentioned multiple gas fuel combustion mouths
The variable-scale of gaseous fuel.
Gas turbine combustion system the most according to claim 1, it is characterised in that
Possess at the center of above-mentioned multiple gas fuel combustion mouths and make gaseous fuel and liquid fuel both sides combustion
The double-combustion mouth burnt.
9. a gas-turbine plant, it is characterised in that possess:
Compressor, this compressor compresses air；
Gas turbine combustion system described in claim 1, this gas turbine combustion system makes by above-mentioned compression
The air of machine compression movement together burns with fuel；
Turbine, this turbine is by the combustion gases drive from above-mentioned gas turbine combustion system；And
Electromotor, this electromotor is driven by the rotary power of above-mentioned turbine.
10. an operation method for gas turbine combustion system, this gas turbine combustion system possesses: multiple
The air mass flow adjusting apparatus of the air mass flow that gas fuel combustion mouth and adjustment mix with gaseous fuel；Measure
The gasmetry device of the concentration of the unburnt ingredient in above-mentioned gas fuel；And measure above-mentioned gas fuel
The gas temperature measuring device of temperature, the operation method of above-mentioned gas turbine combustion system is characterised by,
In combustion mode from the portion being made gas fuel combustion by a part for above-mentioned multiple gas fuel combustion mouths
Divided combustion pattern is switched to be made the combustion completely of gas fuel combustion by whole above-mentioned multiple gas fuel combustion mouths
During burning pattern, according to the concentration of the unburnt ingredient in the above-mentioned gas fuel measured by above-mentioned gas measuring device
And the temperature of the above-mentioned gas fuel measured by above-mentioned gas temperature meter, calculate for above-mentioned air stream
The command value of amount adjusting apparatus output signal, operate above-mentioned air mass flow adjusting apparatus and make air mass flow temporary transient
Drop to set flow from standard flow, and, therebetween, coordinate load to rise the stream making above-mentioned gas fuel
Amount increases.
The operation method of 11. gas turbine combustion systems according to claim 10, it is characterised in that
Consider that suppression compressor produces to agitate and freeze under partial load conditions and set said reference stream
Amount.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2013180189A JP6190670B2 (en) | 2013-08-30 | 2013-08-30 | Gas turbine combustion system |
| JP2013-180189 | 2013-08-30 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104421003A CN104421003A (en) | 2015-03-18 |
| CN104421003B true CN104421003B (en) | 2017-01-04 |
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|---|---|---|---|---|
| US4683715A (en) * | 1984-12-14 | 1987-08-04 | Hitachi, Ltd. | Method of starting gas turbine plant |
| EP1816327A2 (en) * | 2006-02-01 | 2007-08-08 | Hitachi, Ltd. | Control method and control system of gas turbine |
| CN101999037A (en) * | 2008-11-28 | 2011-03-30 | 三菱重工业株式会社 | Gas turbine controller |
| EP2423600A2 (en) * | 2010-08-27 | 2012-02-29 | Hitachi Ltd. | Gas turbine combustor |
| CN102713209A (en) * | 2009-11-27 | 2012-10-03 | 诺沃皮尼奥内有限公司 | Exhaust temperature versus turbine pressure ratio based turbine control method and device |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4683715A (en) * | 1984-12-14 | 1987-08-04 | Hitachi, Ltd. | Method of starting gas turbine plant |
| EP1816327A2 (en) * | 2006-02-01 | 2007-08-08 | Hitachi, Ltd. | Control method and control system of gas turbine |
| CN101999037A (en) * | 2008-11-28 | 2011-03-30 | 三菱重工业株式会社 | Gas turbine controller |
| CN102713209A (en) * | 2009-11-27 | 2012-10-03 | 诺沃皮尼奥内有限公司 | Exhaust temperature versus turbine pressure ratio based turbine control method and device |
| EP2423600A2 (en) * | 2010-08-27 | 2012-02-29 | Hitachi Ltd. | Gas turbine combustor |
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Address after: Kanagawa Prefecture, Japan Patentee after: Mitsubishi Power Co., Ltd Address before: Kanagawa Prefecture, Japan Patentee before: MITSUBISHI HITACHI POWER SYSTEMS, Ltd. |