CN1877101A - Gas turbine, method of controlling air supply and computer program product for controlling air supply - Google Patents
Gas turbine, method of controlling air supply and computer program product for controlling air supply Download PDFInfo
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- CN1877101A CN1877101A CNA2006100683013A CN200610068301A CN1877101A CN 1877101 A CN1877101 A CN 1877101A CN A2006100683013 A CNA2006100683013 A CN A2006100683013A CN 200610068301 A CN200610068301 A CN 200610068301A CN 1877101 A CN1877101 A CN 1877101A
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Abstract
The present invention provides a gas turbine capable of reducing energy consumption while suppressing a so-called cat back phenomenon. The gas turbine includes a combustor-accommodating chamber casing for accommodating therein a combustor which burns fuel and air compressed by a compressor to generate combustion gas and which injects the combustion gas to a turbine. The gas turbine also includes a first air supply passage and a second air supply passage on an upper portion of the combustor-accommodating chamber casing in the vertical direction. The first air supply passage discharges air toward the compressor in the combustor-accommodating chamber casing. The second air supply passage discharges air in a direction different from that of the first air supply passage.
Description
Present patent application is enjoyed the preference of number of patent application 2005-171454 of Japan that submitted on June 10th, 2005 and the patent application 2005-171455 of Japan that submits on the same day, quotes all the elements of above-mentioned Japan patent application in present patent application.
Technical field
The present invention relates to gas turbine, air feed controlling method and air feed control computer program product.
Background technique
Gas turbine is to turn round in turbo machine by the high temperature air jet that burner is produced.After gas turbine shut down, high-temperature gas was trapped in the unit room of accommodating burner, produced the temperature difference between upper half part of unit room and lower half portion.And because the high unit room upside of temperature expands, the unit room downside that temperature is low shrinks relatively and causes unit room to produce distortion, promptly produces the so-called cat back of the body (キ ヤ Star ト バ Star Network) phenomenon.In order to suppress this kind cat back of the body phenomenon, in for example special No. 0004 paragraph opening the 2004-218569 communique following technology is disclosed: in order to reduce the temperature difference of unit room 5, after gas turbine shuts down, by making the turbine blade rotation, make to produce air-flow in the unit room, make the temperature distribution in the unit room reduce (spin cooling hereinafter referred to as).
Yet, in the patent documentation 1 disclosed technology, after gas turbine shuts down, need the power that makes the turbine blade rotation, therefore there is the big problem of energy consumption.In addition, though after also disclosing gas turbine running end in the patent documentation 1, making purifies air continues to flow into the interior technology of unit room, in this technology, need to continue for a long time to flow into to purify air, thereby on this point that cuts down the consumption of energy, still leave some room for improvement.
Summary of the invention
The present invention In view of the foregoing proposes, and its purpose is to provide a kind of so-called cat back of the body phenomenon and the gas turbine that cuts down the consumption of energy, air feed controlling method and air feed control computer program product of suppressing.
In order to address the above problem, realize purpose, the gas turbine that the present invention relates to is provided with: accommodate the unit room of burner, the combustion gas that this burner is used for the air after combustion fuel and the compression of compressed machine is produced are ejected into turbo machine; The 1st air supply unit, it is arranged on the vertical top of above-mentioned unit room, towards the above-mentioned compressor one side discharged air of above-mentioned unit room inside; And the 2nd air supply unit, it is arranged on the vertical top of above-mentioned unit room, in the inside of above-mentioned unit room, towards the direction discharged air different with above-mentioned the 1st air supply unit.
The gas turbine that the present invention relates to is provided with: accommodate the unit room of burner, the combustion gas that this burner is used for the air after combustion fuel and the compression of compressed machine is produced are ejected into turbo machine; Form the unit with air layer, it is arranged on the inwall of vertical top one side of above-mentioned unit room, along the internal face discharged air of the vertical upside of above-mentioned unit room.
The air feed controlling method that the present invention relates to after shutting down at gas turbine, when the unit room of accommodating burner provides air, obtains the temperature of the vertical bottom of the temperature on vertical top of above-mentioned unit room and above-mentioned unit room; Obtain the temperature difference of temperature of the vertical bottom of the temperature on vertical top of above-mentioned unit room and above-mentioned unit room; Adjustment is to above-mentioned unit room air discharged amount, and with adjusted air quantity discharged air in above-mentioned unit room, so that the temperature difference of the temperature of the vertical bottom of the temperature on the vertical top of above-mentioned unit room and above-mentioned unit room reaches in the scope of predesignating.
The air feed control computer program product that the present invention relates to is after shutting down at gas turbine, when the unit room of accommodating burner provides air; Make computer-implemented following program: the temperature that obtains the vertical bottom of the temperature on vertical top of above-mentioned unit room and above-mentioned unit room; Obtain the temperature difference of temperature of the vertical bottom of the temperature on vertical top of above-mentioned unit room and above-mentioned unit room; Adjustment is to above-mentioned unit room air discharged amount, and with adjusted air quantity discharged air in above-mentioned unit room, so that the temperature difference of the temperature of the vertical bottom of the temperature on the vertical top of above-mentioned unit room and above-mentioned unit room reaches in the scope of predesignating.
Gas turbine that the present invention relates to and air feed controlling method and air feed control computer program product both can suppress so-called cat back of the body phenomenon, and be capable of reducing energy consumption again.
Description of drawings
Fig. 1 is the explanatory drawing of expression gas turbine.
Fig. 2 is the explanatory drawing of the so-called cat back of the body of expression phenomenon.
Fig. 3 is the part sectioned view of the unit room part of the gas turbine that relates to of expression mode of execution 1.
Fig. 4 observes explanatory drawing in the unit room from the arrow D direction of Fig. 3.
Fig. 5 is the part sectioned view of the unit room part of the gas turbine that relates to of expression mode of execution 2.
Fig. 6 observes explanatory drawing in the unit room from the arrow D direction of Fig. 5.
Fig. 7 A is the explanatory drawing that the set air layer of the gas turbine that relates to of expression mode of execution 2 forms the unit.
Fig. 7 B is the explanatory drawing that the set air layer of the gas turbine that relates to of expression mode of execution 2 forms the unit.
Fig. 8 observes the explanatory drawing that air layer forms the unit in the unit room of the gas turbine that relates to from mode of execution 2.
Fig. 9 is the overview diagram of the example of supply system.
Figure 10 is the overview diagram of another example of supply system.
Figure 11 is the flow chart of the order of the air feed controlling method that relates to of expression mode of execution 3.
Embodiment
Describe the present invention with reference to the accompanying drawings in detail.And the present invention is not limited to be used to implement best mode of the present invention (mode of execution hereinafter referred to as).In addition, comprise content that those skilled in the art expect easily or that essence is identical in the composed component in the following mode of execution.
Mode of execution 1
Present embodiment is characterised in that: by the 1st air supply unit on the unit room vertical top that is arranged on gas turbine compressor one side discharged air towards unit room inside, and by the 2nd air supply unit that is arranged on unit room vertical top equally towards the direction discharged air different with the 1st air supply unit.
Fig. 1 is the explanatory drawing of gas turbine.This gas turbine 1 is provided with in the horizontal mode of what is called.That is, in this gas turbine 1, the rotor shaft 9 of rotating disk and rotor blade being installed, basic and vertical, is that the action direction (direction of the arrow G among Fig. 1) of gravity disposes with intersecting vertically.Become the pressurized air of High Temperature High Pressure after compressed machine 3 compressions of air that import from air introducing port 2, be transported to the burner 4 that is configured in the unit room 5.In burner 4,, generate the combustion gas of High Temperature High Pressure by liquid fuels such as gaseous fuel such as rock gas or light oil being offered this pressurized air and making its burning.The combustion gas of this High Temperature High Pressure are directed being ejected in the turbo machine 7 after burner tail pipe 6.
Fig. 2 is the explanatory drawing of so-called cat back of the body phenomenon.The Zc of Fig. 2
1, Zc
2The central shaft of expression shell 1C, Zc
1Central shaft between 1 on-stream period of expression gas turbine, Zc
2Central shaft after the running of expression gas turbine 1 finishes.Between the on-stream period of gas turbine 1,, make the temperature distribution of shell (framework) 1C of gas turbine 1 less because of the rotation of compressor 3 and turbo machine 7.
In addition, gas turbine 1 running one finishes, and then the rotation of compressor 3 and turbo machine 7 promptly stops.Consequently, high-temperature gas concentrates on the vertical top U of gas turbine 1, and in contrast, the relatively low gas of temperature then concentrates on the bottom L of gas turbine 1.So, because the length of the vertical top U of shell 1C becomes longer to bottom L than plumbous double recipe, so turns on the vertical top U of shell 1C, form so-called cat antiform shape.This phenomenon is called cat back of the body phenomenon.
In case produce cat back of the body phenomenon, then the central shaft Zc of the shell 1C after gas turbine 1 running
2Central shaft Zc with respect to the shell 1C between gas turbine 1 on-stream period
1Produce crooked, dislocation.Because the central shaft Zc of the shell 1C between gas turbine 1 on-stream period
1Substantially parallel with the rotor shaft of gas turbine 1, thereby in a single day cat back of the body phenomenon takes place, the rotor blade that then is installed on the rotating disk might contact with shell 1C.Here, vertical is meant the action direction of gravity.And vertical top U refers to the opposite side of action of gravity direction G, and vertical bottom L refers to action of gravity direction one side.Hereinafter abbreviate vertical top as top as required, abbreviate the vertical bottom as bottom.
In order to suppress this kind cat back of the body phenomenon, in the gas turbine 1 that mode of execution 1 relates to, adopt following formation.Fig. 3 is the part sectioned view of the unit room part of the gas turbine that relates to of expression mode of execution 1.Fig. 4 observes explanatory drawing in the unit room from the arrow D direction of Fig. 3.As shown in Figure 3, Figure 4, this gas turbine 1 is provided with the 1st air supply unit (the 1st air feed path hereinafter referred to as) the 11 and the 2nd air supply unit (the 2nd air feed path hereinafter referred to as) 12 of discharged air in the unit room 5 in the top of unit room 5 U one side.
As shown in Figure 3, the path of the 1st air feed path 11 forms rotor shaft 9 run-off the straights of direction (channel axis to) with respect to gas turbine 1.And, the outside of slave chamber enclosure 5C towards inboard, form the 1st air feed path 11 towards compressor 3 one sides.In addition, form the 2nd air feed path 12, the rotor shaft 9 that its path forms direction (channel axis to) and gas turbine 1 intersects vertically substantially.As shown in Figure 4, form the 1st and the 2nd air feed path 11,12, its path forms direction (channel axis to) towards the rotary middle spindle Z of above-mentioned rotor shaft 9 (being the rotary middle spindle of turbo machine 7).
As shown in Figure 3, Figure 4, the 2nd air feed path 12 is towards bottom (being action of gravity direction one side) the L discharged air A of unit room.This air A is trapped in the high temperature air of unit room 5 top U one side by stirring, reduces the temperature departure that takes place in the unit room 5C.In the section that is provided with the 2nd air feed path 12, this action effect is especially good.
In addition, the 1st air feed path 11 is towards compressor 3 one sides, towards burner 4 discharged air A.Herein, as shown in Figure 4, in the section perpendicular to the rotary middle spindle Z of rotor shaft 9, the 1st air feed path 11 is configured to towards discharged air A between the burner 4.By adopting this kind configuration, be discharged into unit room inwall (the compressor one side unit room inwall) 5wc that unit room 5 interior air A pass between the burner 4 and arrive compressor 3 one sides of unit room 5 by the 1st air feed path 11.That is, the direction of the 1st air feed path 11 discharged air in unit room 5 is different with the direction of the 2nd air feed path 12 discharged air in unit room 5.
So, both can stir the high temperature air of the top U that is trapped in unit room 5, can stir near the air (the arrow J among Fig. 3) of unit room inwall 5wc of compressor one side again.And,, also can reduce the temperature departure that produces in the unit room shell 5C even on position away from the section that the 1st and the 2nd air feed path 11,12 is set.Consequently, owing to can fall the temperature departure of whole unit room shell 5C, thereby available seldom Energy Efficient suppresses cat back of the body phenomenon.
In the gas turbine 1 that this mode of execution 1 relates to, on the section (section shown in the arrow A of Fig. 3) of compressor 3 one sides of unit room 5, the top U of unit room 5 and the temperature difference (upper and lower temperature difference) between the L of bottom are compared with the spin cooling, have reduced about 15 ℃.In addition, near the section the flange of unit room 5 (section shown in the arrow B of Fig. 3), compare with the spin cooling, upper and lower temperature difference has reduced about 40 ℃.In addition, on the section (section shown in the arrow C of Fig. 3) of turbo machine one side of unit room 5, compare with the spin cooling, upper and lower temperature difference has reduced about 80 ℃.
More than, in this embodiment, the 2nd air supply unit that is provided with the 1st air supply unit that forms towards the compressor lopsidedness in the unit room of gas turbine and substantially forms with intersecting vertically with the rotor shaft of gas turbine.Can suppress the temperature departure on the whole unit room shell thus, thereby available seldom Energy Efficient suppresses cat back of the body phenomenon.In addition, though be in this embodiment from top one side of unit room towards unit room in discharged air, also can be from bottom one side of unit room, promptly from bottom one side of burner towards unit room in discharged air.
Mode of execution 2
Mode of execution 2 is characterised in that, is provided with to make air form the unit along unit room internal face flow air layer.In the following description, to the member mark identical label identical with mode of execution 1.Fig. 5 is the part sectioned view of the unit room part of the gas turbine that relates to of expression mode of execution 2.Fig. 6 observes explanatory drawing in the unit room from the arrow D direction of Fig. 5.
As Fig. 5, shown in Figure 6, this gas turbine 1a is provided with the 1st air supply unit (the 1st air feed path hereinafter referred to as) the 11 and the 2nd air supply unit (the 2nd air feed path hereinafter referred to as) 12 of discharged air in the unit room 5 in the top of unit room 5 U one side.As shown in Figure 5, the path of the 1st air feed path 11 forms rotor shaft 9 run-off the straights of direction (channel axis to) with respect to gas turbine 1.And, the outside of slave chamber enclosure 5C towards inboard, form the 1st air feed path 11 towards compressor 3 one sides.
In addition, form the 2nd air feed path 12, the rotor shaft 9 that its path forms direction (channel axis to) and gas turbine 1 intersects vertically substantially.As shown in Figure 4, form the 1st and the 2nd air feed path 11,12, its path forms the rotary middle spindle Z of direction (channel axis to) towards above-mentioned rotor shaft 9.
As Fig. 5, shown in Figure 6, on the part of unit room 5 inner openings, be provided with the 1st nozzle assembly (ノ ズ Le Block ロ Star Network) 13 that forms the unit as air layer at the 1st air feed path 11.In addition, on the part of unit room 5 inner openings, be provided with the 2nd nozzle assembly 14 that forms the unit as air layer at the 2nd air feed path 2.Here, compare to the part of unit room 5 inner openings with the 2nd air feed path 12, the 1st air feed path 1 is to more close compressor 3 one sides of the part of unit room 5 inner openings.Thus can be on the direction parallel with the rotor shaft 9 of gas turbine, configuration the 1st nozzle assembly 13 and the 2nd nozzle assembly 14 stagger.
Consequently, the air A (the arrow I Fig. 5) that the internal face of top U one side from the 1st, the 2nd nozzle assembly 13,14 along unit room 5 (top one side unit room internal face) 5wt gives off, top one side unit room internal face 5wt on a large scale in flow.Consequently, the temperature distribution of unit room shell 5C is further diminished, thereby suppress cat back of the body phenomenon more effectively.
Fig. 7 A, Fig. 7 B are the explanatory drawings that the air layer of the gas turbine configuration that relates to of expression mode of execution 2 forms the unit.Fig. 8 is the explanatory drawing when observing air layer in the unit room of the gas turbine that relates to from mode of execution 2 of expression and forming the unit.The paper upside of Fig. 8 is compressor 3 one sides.As Fig. 7 A, shown in Figure 8, the 1st nozzle assembly 13 is roughly cup-shaped tectosomes.On the peripheral part of the 1st nozzle assembly 13,13hc is towards compressor 3 one side openings for the discharging of compressor one side air, and turbo machine one side air discharge ports 13ht is towards turbo machine 7 one side openings.
The 1st nozzle assembly 13 changes the flow direction of flow air in the 1st air feed path 11, and one side unit room internal face 5wt is discharged into compressor 3 one sides and turbo machine 7 one sides along top.That is, along the direction discharged air A parallel with the rotary middle spindle of turbo machine 7.Because with respect to the bottom of unit room shell 5C, its top with the parallel direction of the rotary middle spindle of turbo machine 7 on relative elongated, so produce cat back of the body phenomenon.Because by along the direction discharged air A parallel with the rotary middle spindle of turbo machine 7, can effectively cool off with respect to the bottom of unit room shell 5C and elongated relatively part, carry on the back phenomenon so can effectively suppress cat with seldom energy.
As Fig. 7 B, shown in Figure 8, the 2nd nozzle assembly 14 is roughly cup-shaped tectosomes.The 2nd nozzle assembly 14 is provided with wall one side air discharge ports 14h.And, by changing the flow direction of flow air A in the 2nd air feed path 12, the one side unit room internal face 5wt discharging along top.
In addition, shown in Fig. 7 A, Fig. 7 B, on the 1st and the 2nd nozzle assembly 13,14, be provided with air discharge ports 13o, 14o in rotor shaft 9 one sides of unit room 5.In mode of execution 2, air discharge ports 13o, 14o can seal with stopper 13p, 14p.When pulling down stopper 13p, 14p, the rotor shaft 9 one sides discharging of the flow direction ground of the air A that is provided by the 1st and the 2nd air feed path 11,12 towards unit room 5 can also be provided the 1st and the 2nd nozzle assembly 13,14.
Adopt this kind formation, in the gas turbine 1a that mode of execution 2 relates to, utilize the 1st and the 2nd nozzle assembly 13,14, can make air A that the 1st and the 2nd air feed path 11,12 provided along top unit room internal face 5wt flow (the arrow I of Fig. 5, Fig. 7 A, Fig. 7 B).Can increase the heat conductivity on the one side unit room internal face 5wt of top thus, thereby compare, can more effectively cool off top one side unit room internal face 5wt with the gas turbine 1 (with reference to Fig. 3 etc.) that mode of execution 1 relates to.Use energy still less can suppress cat back of the body phenomenon like this.
That is, under the situation of the identical air quantity of the gas turbine that relates to mode of execution 11 of flowing, can be with top U one side of shorter time reduction unit room shell 5C and the temperature difference of bottom L one side.In addition,, compare, can further reduce by the 1st and the 2nd air quantity that provides for path 11,12 with the gas turbine 1 that mode of execution 1 relates to for the cooling effect of gas turbine 1 equal extent that obtains to relate to mode of execution 1.Consequently, use energy still less can suppress cat back of the body phenomenon.
In addition, also can be set at and remove stopper 13p at least, the air discharge ports 13o of open at least the 1st nozzle assembly 13 is by rotor shaft 9 one sides and the compressor 3 one side discharged air of the 1st nozzle assembly 13 towards unit room 5.And, can obtain the cooling effect of top one side unit room internal face 5wt and near these the two kinds of effects of air mixing effect the compressor one side unit room internal face 5wt by the air discharging ratio with air discharge ports 13o, 14o such as suitable setting compressor one side air discharge ports 13hc and wall one side air discharge ports 14h.In addition, also can be set at and not use the 1st nozzle assembly 13, and by the compressor 3 one side discharged air A in 5 stir near the compressor one side unit room inwall 5wc air from the 1st air feed path 11 towards unit room, and utilize the 2nd nozzle assembly 14 cooling top one side unit room internal face 5wt.So also can effectively reduce the temperature distribution of unit room 5.
The gas turbine 1a that this mode of execution relates to, on the section (section shown in the arrow A of Fig. 5) of compressor 3 one sides of unit room 5, the temperature difference (upper and lower temperature difference) of the top U of unit room 5 and bottom L is compared with the spin cooling, can make upper and lower temperature difference reduce about 80 ℃.In addition, on the section (section shown in the arrow C of Fig. 5) of turbo machine one side of unit room 5, compare, can make upper and lower temperature difference reduce about 100 ℃ with the spin cooling.
More than, in mode of execution 2, air is flowed along the top one side unit room internal face 5wt of unit room shell.Can increase the heat conductivity on the one side unit room internal face 5wt of top thus, effectively top one side of Coolers chamber enclosure.Consequently, owing to can more effectively suppress cat back of the body phenomenon, thereby can further reduce to unit room and provide air required energy.In addition, though be in this embodiment from top one side of unit room towards unit room in discharged air, also can be from bottom one side of unit room, promptly from bottom one side of burner towards unit room in discharged air.
Mode of execution 3
In mode of execution 3, the air feed control after gas turbine that mode of execution 1 and mode of execution 2 relate to shuts down is described.Fig. 9 is the overview diagram of an example of expression supply system.In this supply system, by adjusting the air quantity of air feed unit ejections such as blower, fan, compressor, adjust the air quantity in the unit room 5 of sending into gas turbine 1 and 1a.
Supply system shown in Figure 9 provides air A by the blower 25 that driven by motor 24 to the 1st and the 2nd air feed path 11,12.And air A is sent in the unit room 5 of gas turbine 1 or gas turbine 1a.Air filter 26 has been installed on the blower 25, and the air A that removes dust through air filter 26 sends from blower 25.
Air A from blower 25 is sent is sent to the 1st and the 2nd air feed path 11,12 after adjusting valve 27, stop valve 28.And be discharged in the unit room 5 from the 1st and the 2nd air feed path 11,12.The air supply controller 20 that is related to by present embodiment is via the motor 24 of transducer 23 controlling and driving blowers 25, thereby adjusts the air quantity of sending from blower 25.
Here, air supply controller 20 is made of processing division 21 and memory section 22.Processing division 21 is made of storage and CPU.Processing division 21, the computer program of the air supply method that relates to according to present embodiment and the data that obtain, processing division 21 reads in the laggard row operation of the storage that is assembled in the processing division 21 with aforementioned calculation machine program.At this moment, processing division 21 suitably deposits the numerical value in the computational process in memory section 22, again the numerical value that deposits in is extracted laggard row operation.And this processing division 21, also the hardware of available dedicated replaces aforementioned calculation machine program.
Stored computer program of the air supply method that this mode of execution relates to etc. in the memory section 22.Here, memory section 22 can make up and constitutes by nonvolatile storage such as hard disk unit, magneto-optical disc apparatus or flash memories (read-only storage medium such as CD-ROM) and RAM volatile storages such as (Random Access Memory) or to these.
In addition, aforementioned calculation machine program also can realize the air supply method that present embodiment relates to by making up with the computer program that is recorded in the computer system.In addition, the computer program recorded of function that also can be by will being used for realizing processing division 21 is to the recording medium that can be read by computer, the program on this recording medium of being recorded in is read in computer system and implement, carry out the air supply method that present embodiment relates to.In addition, said here " computer system " comprises hardware such as OS and peripheral unit.
The flow of the air A that provides to the 1st and the 2nd air feed path 11,12, available adjustment valve 27 controls.Stop valve 28 is open usually, closes when the 1st and the 2nd air feed path 11,12 provides air A stopping.In addition, by petcock 29 unwanted air A in the unit room 5 is discharged in the atmosphere.Adjust air supply controller 20 controls that valve 27, stop valve 28 and petcock 29 are related to by present embodiment.
The following describes other example of supply system.Figure 10 is the overview diagram of another example of supply system.In this supply system, be admitted to the air quantity in the unit room 5 of gas turbine 1 and 1a, send into the interior air quantity of unit room 5 of gas turbine 1 and 1a by being arranged on air feed unit such as blower and fan, compressor and the air regulating device adjustment between the unit room 5.Supply system shown in Figure 10 provides air A by the blower 25 that driven by motor 24 to the 1st and the 2nd supply system 11,12.And air A is sent in the unit room 5 of gas turbine 1 or 1a.
The air A that sends from blower 25 is sent to the 1st and the 2nd air feed path 11,12 after by flow rate regulating valve 31, stop valve 33.And in unit room 5, discharge from the 1st and the 2nd air feed path 11,12.Air supply controller 20 controls that can relate to by present embodiment are adjusted the air quantity of sending and offer unit room 5 from blower 25 as the aperture of the flow rate regulating valve 31 of air quantity regulation unit.
Flow rate regulating valve 31 is adjusted the pressure of the air A that offers the 1st and the 2nd air feed path 11,12.Stop valve 33 is open usually, closes when the 1st and the 2nd air feed path 11,12 provides air A stopping.In addition, by petcock 32 unwanted air A in the unit room 5 is discharged in the atmosphere.Processing division that above-mentioned air supply controller 20 disposed 21 is according to the information that is stored in the computer program in the memory section 22 and obtains from upper temp meter 40 etc., and control flow rate is adjusted the action of valve 31 grades.Because the formation of air supply controller 20 is same as described above, thereby omits its explanation.The air feed controlling method that mode of execution 3 is related to is illustrated below.
Figure 11 is the flow chart of the order of the air feed controlling method that relates to of expression mode of execution 3.Can be suitable in the gas turbine 1a that the gas turbine 1 that this air feed controlling method relates to for mode of execution 1, mode of execution 2 relate to, Fig. 9 of mode of execution 3, the supply system illustrated in fig. 10.Can be at gas turbine 1, carry out this air feed controlling method when 1a shuts down.
When gas turbine 1, when 1a shuts down, stop to gas turbine 1, when 1a provides fuel, then gas turbine 1,1a no longer produce output, air supply controller 20 comes into effect the air feed control of mode 3.The processing division 21 of air supply controller 20 is obtained the turbine rotational speed N E (step S101) of gas turbine 1,1a from tachometer 42.At this moment, though gas turbine 1,1a do not produce output, but by means of the inertia between on-stream period, rotor shaft 9 still continues to rotate.
Under the situation that adopts air supply system shown in Figure 9, if NE≤NEc, processing division 21 blower 25 etc. then, and open and adjust valve 27, stop valve 28, close petcock 29.Under the situation that adopts air supply system shown in Figure 10, if NE≤NEc, processing division 21 blower 30 etc. then, and open flow rate regulating valve 31, stop valve 33, close petcock 32.In addition, no matter be which kind of air supply system, in the 1st air feed path 11 or the 2nd air feed path 12, in a direction unit room 5, provide air to get final product at least.
In gas turbine, in case the rotating speed of rotor shaft descends, then the upper and lower temperature difference of shell sharply increases, but as mentioned above, if before the rotor shaft 9 of gas turbine 1,1a stops fully, provide air, then can be as early as possible be suppressed to the upper and lower temperature difference of shell very little to unit room 5.Can more effectively suppress the generation of cat back of the body phenomenon thus, thereby can further reduce to the required energy of unit room air feed.
Then, processing division 21 is obtained the temperature T on the top U of shell of gas turbine 1,1a from top and temperature of lower meter 40,41
UTemperature T on (upper temp) and the bottom L
L(temperature of lower) (step S104).Then, processing division 21 calculates upper temp T
UWith temperature of lower T
LPoor (upper and lower temperature difference) Δ T (=T
U-T
L), compare with the benchmark temperature difference Tc that predesignates.Predetermined benchmark temperature difference Tc for example can be set in about 10 ℃～20 ℃.
Under the situation of Δ T 〉=Δ Tc (step S105: be), processing division 21 increases the air quantity (step S106) that offers in the unit room 5.And before Δ T＜Δ Tc, processing division 21 makes the air quantity that offers in the unit room 5 change (increase).The air quantities that change (increase) at least one side from the 1st air feed path 11 or the 2nd air feed path 12 offers in the unit room 5 get final product.
So, owing to by feedback control upper and lower temperature difference Δ T is suppressed in the scope of predesignating (the benchmark temperature difference Tc that promptly predesignates), thereby can effectively suppress cat back of the body phenomenon.In addition, initial stage temperature when stopping along with running variation of environment and gas turbine or the air temperature reduction in the unit room etc. though required air demand changes, if adopt this controlling method, can be tackled and suppress the required air demand of cat back of the body phenomenon.
Consequently, by more effectively, more promptly suppressing cat back of the body phenomenon, also can reduce in order to provide air required energy consumption to unit room.In addition, suppress the required capacity air of cat back of the body phenomenon, avoided providing excess air, thereby also can reduce the required energy of air feed owing to can provide.
And make when offering unit room 5 air quantities and increasing, also can difference be set to the air demand of the 1st air feed path 11 and the 2nd air feed path 12.In addition, shown in the gas turbine 1a that enforcement mode 2 relates to, when near the unit room internal face, forming air layer, also can make the air demand difference according to the formation direction of air layer.At this moment, can obtain the temperature up and down of shell, air demand is provided with difference according to this measurement result in compressor 3 one sides (A of Fig. 3, Fig. 5) and unit room central authorities (B of Fig. 3, Fig. 5), turbo machine 7 one sides (C of Fig. 3, Fig. 5).If this method of employing then can more promptly make upper and lower temperature difference Δ T return in the benchmark temperature difference Tc by more effectively utilizing air.
Under the situation of Δ T＜Δ Tc (step S105: not), though the air quantity that offers unit room 5 than lacking before, upper and lower temperature difference Δ T also might converge in the predetermined benchmark temperature difference Tc.Therefore, processing division 21 reduces the air quantity (step 8107) that offers unit room 5 by adjusting transducer 23 (Fig. 9) or flow rate regulating valve 31 (Figure 10).Thus, can reduce the required energy of air feed.In addition, also step S107 can be set.
Then, the upper temp T that obtains of processing division 21 judgements
UWith temperature of lower T
LWhether all (step S108) below the temperature T m when stopping.Above-mentioned Tm can be set at room temperature+α ℃.At upper temp T
UOr temperature of lower T
LAt least one side be higher than under the situation of Tm (step S108: not), at upper temp T
UAnd temperature of lower T
LThe two all reach Tm following before, implementation step S104, step S105 repeatedly.
Upper temp T
UWith temperature of lower T
LThe two all reaches Tm when following (step S108: be), and processing division 21 is obtained the air temperature T in the unit room of top one side
WUAnd temperature T in the unit room of bottom one side
WL(step S109).And processing division 21 is judged T
WUAnd T
WLWhether in the unit room of predesignating (step S110) below the air temperature Tma.At T
WUOr T
WLAt least one side be higher than under the situation of Tma (step S110: not), at T
WUAnd T
WLThe two all reach Tm following before, implementation step S104, step S105 etc. repeatedly.Work as T
WUAnd T
WLThe two all reaches Tm when following (step S110: be), finishes this control.
More than, because in mode of execution 3, be set at by the temperature difference of feedback control and be suppressed in the predetermined range, thereby can effectively suppress cat back of the body phenomenon the upper and lower of the shell of gas turbine.In addition, even initial stage temperature when stopping because of turning round environmental change and gas turbine or the air temperature reduction in the unit room etc. make under the situation of required air demand change, still can be corresponding with required air demand.Consequently, can more effectively suppress cat back of the body phenomenon, in addition, owing to can avoid providing excess air, thereby also can reduce air feed institute energy requirement.And, owing to can suppress to provide excess air, thereby relative dwindling compared with the unit room bottom in unit room top.
As mentioned above, computer program product is used in the gas turbine that the present invention relates to, air feed controlling method and air feed control, and is useful when gas turbine is stopped, and especially is fit to suppress so-called cat back of the body phenomenon, cuts down the consumption of energy.
Gas turbine of the present invention be provided with in the unit room of gas turbine towards the 1st air supply unit of compressor one side discharged air with towards the 2nd air supply unit of different direction discharged air therewith.The temperature departure on the whole casing of unit room can be suppressed to constitute thus, thereby cat back of the body phenomenon can be effectively suppressed with energy seldom.
Above-mentioned the 2nd air supply unit is preferably towards the vertical bottom discharged air of above-mentioned unit room.So, the air in the agitator chamber more effectively, thereby can more effectively reduce the temperature distribution of the shell that constitutes the car chamber.Consequently, use energy seldom can effectively suppress cat back of the body phenomenon.
The gas turbine that the present invention relates to, in above-mentioned gas turbine, above-mentioned the 1st air supply unit is towards being provided with discharged air between a plurality of above-mentioned firing chambers.
If adopt the present invention, both can stir the high temperature air that is trapped in unit room top one side, also can stir near the air of unit room inwall of compressor one side.Consequently, owing to can reduce temperature departure on the whole casing that constitutes unit room, thereby can effectively suppress cat with seldom energy and carry on the back phenomenon.
The gas turbine that the present invention relates to, in above-mentioned gas turbine, after above-mentioned gas turbine shuts down, when the rotating speed of above-mentioned gas turbine is lower than the rotating speed of predesignating, has a side at least towards above-mentioned unit room discharged air in above-mentioned the 1st air supply unit or above-mentioned the 2nd air supply unit.
In gas turbine, in case the rotating speed of rotor shaft descends, then the upper and lower temperature difference of shell sharply increases, but if adopt the present invention, can be as early as possible is suppressed to the upper and lower temperature difference of shell very little.Thus, can more effectively suppress the generation of cat back of the body phenomenon, thereby also can further reduce to the required energy of unit room air feed.
The gas turbine that the present invention relates to, in above-mentioned gas turbine, at least one side in above-mentioned the 1st air supply unit or above-mentioned the 2nd air supply unit is towards above-mentioned unit room air discharged amount, changes according to the above-mentioned unit room temperature of the vertical bottom of the above-mentioned unit room temperature on the vertical top of above-mentioned car chamber and above-mentioned unit room.
Thus, can more effectively, promptly suppress cat back of the body phenomenon.In addition, suppress the required capacity air of cat back of the body phenomenon, avoid providing excess air, thereby also can reduce the required energy of air feed owing to can provide.
Because gas turbine is provided with air layer and forms the unit, thereby air is flowed along the unit room internal face of top one side of unit room shell.Thus, can increase the heat conductivity on the above-mentioned internal face, effectively cooling constitutes shell upper one side of unit room.Consequently, owing to can effectively suppress the cat back of the body, thereby can further reduce the required energy of air feed in unit room.
The gas turbine that the present invention relates to, in above-mentioned gas turbine, above-mentioned air layer forms the unit towards the direction discharged air parallel with the rotary middle spindle of above-mentioned turbo machine.
By towards the direction discharged air parallel, can effectively cool off the elongated relatively part in vertical bottom, thereby can effectively suppress cat back of the body phenomenon with energy seldom with respect to the shell that constitutes unit room with the rotary middle spindle of turbo machine.
The gas turbine that the present invention relates to, in above-mentioned gas turbine, after above-mentioned gas turbine shut down, when the rotating speed of above-mentioned gas turbine was lower than the rotating speed of predesignating, above-mentioned air layer formed the unit towards above-mentioned unit room discharged air.
In gas turbine, in case the rotating speed of rotor shaft descends, then the upper and lower temperature difference of shell sharply increases, but if adopt the present invention, can be as early as possible is suppressed to the upper and lower temperature difference of shell very little.Can more effectively suppress the generation of cat back of the body phenomenon thus, thereby also can further reduce to the required energy of unit room air feed.
The gas turbine that the present invention relates to, in above-mentioned gas turbine, form row of cells from above-mentioned air layer and be put into air quantity the above-mentioned unit room, change according to the temperature of the above-mentioned unit room of the vertical bottom of the above-mentioned unit room temperature on the vertical top of above-mentioned unit room and above-mentioned unit room.
Thus, can more effectively, promptly suppress cat back of the body phenomenon.In addition, suppress the required capacity air of cat back of the body phenomenon, avoid providing excess air, thereby can reduce the required energy of air feed owing to can provide.
In the air feed controlling method, owing to be discharged into air quantity in the unit room the hang down difference of temperature and the temperature of unit room vertical bottom on direction top of unit room is reached in the scope of predesignating, thereby can more effectively, promptly suppress cat and carry on the back phenomenon by adjustment.In addition, owing to can avoid providing excess air, thereby can reduce air feed institute energy requirement.
In above-mentioned air feed controlling method, after the rotating speed of above-mentioned gas turbine is less than the rotating speed of predesignating, towards above-mentioned unit room discharged air.
In gas turbine, in case the rotating speed of rotor shaft descends, then the upper and lower temperature difference of shell sharply increases, but if adopt the present invention, can be as early as possible is suppressed to the upper and lower temperature difference of shell very little.Can more effectively suppress the generation of cat back of the body phenomenon thus, thereby also can further reduce to the required energy of unit room air feed.
Above-mentioned air feed control computer program product has the recording medium that can be read by computer, and comprises the order of sequencing, the air feed controlling method that it can utilize computer realization the present invention relates to.
Claims (13)
1. a gas turbine (1,1a) is characterized in that, is provided with:
Accommodate the unit room (5) of burner (4), wherein said burner (4) after with the compression of combustion fuel and compressed machine (3) air and the combustion gas that produce are ejected in the turbo machine (7);
The 1st air supply unit (11), it is arranged on the vertical top of described unit room (5), towards inner described compressor (3) the one side discharged air of described unit room (5); With
The 2nd air supply unit (12), it is arranged on the vertical top of described unit room (5), and the inside in described unit room (5) is towards the direction discharged air different with described the 1st air supply unit (11).
2. gas turbine according to claim 1 is characterized in that: described the 2nd air supply unit (12) is towards the vertical bottom discharged air of described unit room (5).
3. gas turbine according to claim 1 and 2 is characterized in that: described the 1st air supply unit (11) is towards being provided with discharged air between a plurality of described burners (4).
4. according to each described gas turbine of claim 1 to 3, it is characterized in that: after described gas turbine (1,1a) shuts down, when the turbine rotating speed of described gas turbine (1,1a) becomes when being lower than the rotating speed of predesignating, at least one side in described the 1st air supply unit (11) or described the 2nd air supply unit (12) is towards described unit room (5) discharged air.
5. according to each described gas turbine of claim 1 to 4, it is characterized in that: at least one side from described the 1st air supply unit (11) or described the 2nd air supply unit (12) is towards described unit room (5) air discharged amount, changes according to the temperature of the described unit room (5) of the vertical bottom of the temperature of the described unit room (5) on the vertical top of described unit room (5) and described unit room (5).
6. a gas turbine (1,1a) is characterized in that, is provided with:
Accommodate the unit room (5) of burner (4), wherein said burner (4) after with the compression of combustion fuel and compressed machine (3) air and the combustion gas that produce are ejected in the turbo machine (7); With
Air layer forms unit (13,14), and it is arranged on the internal face of vertical top one side of described unit room (5), along the internal face discharged air of the vertical upside of described unit room (5).
7. gas turbine according to claim 6 is characterized in that: described air layer forms unit (13,14), towards the direction discharged air parallel with the rotary middle spindle of described turbo machine (7).
8. according to claim 6 or 7 described gas turbines, it is characterized in that: after described combustion turbo machine (1,1a) shuts down, when the turbine rotating speed of described gas turbine (1,1a) was lower than the rotating speed of predesignating, described air layer formed unit (13,14) towards described unit room (5) discharged air.
9. according to each described gas turbine of claim 6～8, it is characterized in that: form unit (13,14) towards described unit room (5) air discharged amount from described air layer, change according to the temperature of the described unit room (5) of the vertical bottom of the temperature of the described unit room (5) on the vertical top of described unit room (5) and described unit room (5).
10. air feed control gas method is used for providing air to the unit room of accommodating burner (4) (5) after gas turbine (1,1a) shuts down; It is characterized in that:
Obtain the temperature of the vertical bottom of the temperature on vertical top of described unit room (5) and described unit room (5);
Obtain temperature poor of the vertical bottom of the temperature on vertical top of described unit room (5) and described unit room (5);
Adjustment is to described unit room (5) air discharged amount, so that the difference of the temperature of the vertical bottom of the temperature on the vertical top of described unit room (5) and described unit room (5) reaches in the scope of predesignating;
With adjusted air quantity discharged air in described unit room (5).
11. air feed controlling method according to claim 10 is characterized in that: the turbine rotating speed of described gas turbine (1,1a) become be lower than the rotating speed of predesignating after, to described unit room (5) discharged air.
12. one kind after gas turbine (1,1a) shuts down, provide the air feed control computer program product of air to the unit room of accommodating burner (4) (5), it is characterized in that:
Obtain the temperature of the vertical bottom of the temperature on vertical top of described unit room (5) and described unit room (5);
Obtain temperature poor of the vertical bottom of the temperature on vertical top of described unit room (5) and described unit room (5);
Adjustment is to described unit room (5) air discharged amount, so that the difference of the temperature of the vertical bottom of the temperature on the vertical top of described unit room (5) and described unit room (5) reaches in the scope of predesignating;
With adjusted air quantity discharged air in described unit room (5);
Recording medium with embodied on computer readable comprises the order of sequencing, can be by computer-implemented.
13. air feed control computer program product according to claim 12 is characterized in that: the turbine rotating speed of described gas turbine (1,1a) become be lower than the rotating speed of predesignating after, to described unit room (5) discharged air.
Applications Claiming Priority (6)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2005-171454 | 2005-06-10 | ||
| JP2005171455 | 2005-06-10 | ||
| JP2005171454 | 2005-06-10 | ||
| JP2005171454A JP4523876B2 (en) | 2005-06-10 | 2005-06-10 | Gas turbine, air supply control method, and computer program for air supply control |
| JP2005-171455 | 2005-06-10 | ||
| JP2005171455A JP4523877B2 (en) | 2005-06-10 | 2005-06-10 | Gas turbine, air supply control method, and computer program for air supply control |
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| CN1877101A true CN1877101A (en) | 2006-12-13 |
| CN1877101B CN1877101B (en) | 2010-09-15 |
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| CN2006100683013A Active CN1877101B (en) | 2005-06-10 | 2006-03-28 | Gas turbine, method of controlling air supply and computer program product for controlling air supply |
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| JP (1) | JP4523876B2 (en) |
| CN (1) | CN1877101B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101769538B (en) * | 2008-12-31 | 2013-07-17 | 通用电气公司 | Methods and systems for controlling a combustor in turbine engines |
| CN103732992A (en) * | 2011-08-17 | 2014-04-16 | 西门子公司 | Combustion arrangement and turbine comprising a damping facility |
| CN104619957A (en) * | 2012-09-05 | 2015-05-13 | 西门子公司 | Combustor shell air recirculation system in a gas turbine engine |
| CN104884767A (en) * | 2012-12-19 | 2015-09-02 | 西门子公司 | Vane carrier temperature control system in a gas turbine engine |
| CN105121789A (en) * | 2013-04-26 | 2015-12-02 | 西门子股份公司 | Turbine engine shutdown temperature control system |
| CN109028141A (en) * | 2017-06-09 | 2018-12-18 | 安萨尔多能源瑞士股份公司 | Gas turbine including multiple tubular burners |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4523877B2 (en) * | 2005-06-10 | 2010-08-11 | 三菱重工業株式会社 | Gas turbine, air supply control method, and computer program for air supply control |
| JP5984447B2 (en) | 2012-03-26 | 2016-09-06 | 三菱重工業株式会社 | Method for preventing deformation of casing of gas turbine, purge device for executing the method, and gas turbine equipped with the device |
| US8893510B2 (en) * | 2012-11-07 | 2014-11-25 | Siemens Aktiengesellschaft | Air injection system in a gas turbine engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2003254010A (en) * | 2002-03-01 | 2003-09-10 | Mitsubishi Heavy Ind Ltd | Steam turbine casing |
| JP4015560B2 (en) * | 2003-01-16 | 2007-11-28 | 三菱重工業株式会社 | Operation method of dual-fired gas turbine |
| JP4523877B2 (en) * | 2005-06-10 | 2010-08-11 | 三菱重工業株式会社 | Gas turbine, air supply control method, and computer program for air supply control |
-
2005
- 2005-06-10 JP JP2005171454A patent/JP4523876B2/en active Active
-
2006
- 2006-03-28 CN CN2006100683013A patent/CN1877101B/en active Active
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101769538B (en) * | 2008-12-31 | 2013-07-17 | 通用电气公司 | Methods and systems for controlling a combustor in turbine engines |
| CN103732992A (en) * | 2011-08-17 | 2014-04-16 | 西门子公司 | Combustion arrangement and turbine comprising a damping facility |
| CN103732992B (en) * | 2011-08-17 | 2016-03-09 | 西门子公司 | Burner, with damping device turbine and run the method for burner |
| CN104619957A (en) * | 2012-09-05 | 2015-05-13 | 西门子公司 | Combustor shell air recirculation system in a gas turbine engine |
| CN104619957B (en) * | 2012-09-05 | 2016-09-28 | 西门子公司 | Burning chamber shell air recycle system in gas-turbine unit |
| CN104884767A (en) * | 2012-12-19 | 2015-09-02 | 西门子公司 | Vane carrier temperature control system in a gas turbine engine |
| US9562475B2 (en) | 2012-12-19 | 2017-02-07 | Siemens Aktiengesellschaft | Vane carrier temperature control system in a gas turbine engine |
| CN104884767B (en) * | 2012-12-19 | 2018-03-23 | 西门子公司 | Stator frame temperature control system in gas turbine |
| CN105121789A (en) * | 2013-04-26 | 2015-12-02 | 西门子股份公司 | Turbine engine shutdown temperature control system |
| CN109028141A (en) * | 2017-06-09 | 2018-12-18 | 安萨尔多能源瑞士股份公司 | Gas turbine including multiple tubular burners |
Also Published As
| Publication number | Publication date |
|---|---|
| JP4523876B2 (en) | 2010-08-11 |
| CN1877101B (en) | 2010-09-15 |
| JP2006342783A (en) | 2006-12-21 |
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