CN101798959A - Gas turbine - Google Patents
Gas turbine Download PDFInfo
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- CN101798959A CN101798959A CN 201010115375 CN201010115375A CN101798959A CN 101798959 A CN101798959 A CN 101798959A CN 201010115375 CN201010115375 CN 201010115375 CN 201010115375 A CN201010115375 A CN 201010115375A CN 101798959 A CN101798959 A CN 101798959A
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- gas
- air distribution
- gas turbine
- distribution tube
- firing chamber
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Abstract
The invention provides a gas turbine, which comprises a compressor, a combustion chamber and a turbine. The gas turbine is characterized in that: a cavity is arranged on the side wall of an air distribution barrel of the combustion chamber, and is used for accommodating cooling fluid so as to protect the air distribution barrel through the cooling fluid; and all high-pressure air generated by the compressor enters the air distribution barrel and is used for mixing with fuels in the air distribution barrel and participating in the combustion. The gas turbine provided by the invention cools the air distribution barrel through the cooling fluid and reduces cooling gas supply of the compressor and the consumption of the compressor; and all the high-pressure air generated by the compressor enters the air distribution barrel of the combustion chamber to be combusted, so the efficiency of the gas turbine is improved.
Description
Technical field
The embodiment of the invention relates to field of mechanical technique, relates in particular to a kind of gas turbine.
Background technique
At present, the gas turbine that is used in power field is all inherited the employed gas turbine of jet in aviation field, this gas turbine generally comprises gas compressor, firing chamber and turbo machine and forms, wherein, the firing chamber comprises shell and air distribution tube, shell and air distribution tube are made by resistant to elevated temperatures alloy material, and shell wraps air distribution tube sealed packet.Is pressurized gas by gas compressor with air compression, and then pressurized gas participate in burning with fuel mix and form high-voltage high-speed gas in the air distribution tube of firing chamber, and last high-voltage high-speed gas will drive turbo machine and be rotated generating.
In the working procedure of gas turbine, will have a big chunk energy and be used for the firing chamber is lowered the temperature, cause in case make the alloy material Yin Gaowen of firing chamber damaging.The gas turbine that is 7MW with a gross output is an example, and wherein, driving the required power of generator is 2MW, and remaining 5MW is used for drive pressure mechanism of qi generation pressurized gas.And in the pressurized gas that gas compressor produces, will have the pressurized gas of 5%-40% will be used for the cooling combustion chamber, be unlikely to damage with the protection firing chamber.
In realizing process of the present invention, the inventor finds that there are the following problems at least in the prior art: the firing chamber in the prior art gas turbine, the pressurized gas that all need to utilize gas compressor to produce cool off the firing chamber, most energy of prior art gas turbine is consumed on the cooling combustion chamber, thereby causes the inefficiency of prior art gas turbine.
Summary of the invention
The embodiment of the invention provides a kind of gas turbine, in order to solve the low defective of gas turbine proficiency in the prior art, realizes improving the efficient of gas turbine.
The embodiment of the invention provides a kind of gas turbine, comprises gas compressor, firing chamber and turbo machine, and the sidewall of the air distribution tube of described firing chamber is provided with cavity; Described cavity is used for ccontaining cooling liquid, by described cooling liquid described air distribution tube is protected; The pressurized gas that described gas compressor produces all enter in the described air distribution tube, are used for mixing with fuel in the described air distribution tube participating in burning.
The gas turbine of the embodiment of the invention; be provided with cavity by sidewall at firing chamber air distribution tube; and by the ccontaining cooling liquid of cavity; the air distribution tube is carried out cooling protection by cooling liquid; can effectively reduce the air distribution tube temperature of firing chamber; thereby the pressurized gas that gas compressor is produced all enter in the air distribution tube and participate in burning with fuel mix, and need not to reserve the part pressurized gas air distribution tube of firing chamber are cooled off.Because the gas turbine that uses in the prior art is to develop by the gas turbine that uses on the aircraft, manufacture and design in the process at gas turbine, the technology prejudice that the pressurized gas that existence always must adopt gas compressor to produce are lowered the temperature to the firing chamber, thus cause the gas turbine that uses that is used to generate electricity still to adopt the pressurized gas of gas compressor generation to lower the temperature.The gas turbine of the embodiment of the invention has overcome technology prejudice of the prior art, the Environmental Conditions of the gas turbine that uses in conjunction with being used to generate electricity, employing is injected cooling liquid in the cavity of air distribution tube sidewall, by cooling liquid the air distribution tube is lowered the temperature, thereby improved air distribution tube cooling-down effect to the firing chamber, and need not the pressurized gas that the part gas compressor produces are used to cool off the air distribution tube, thereby improved the efficient of gas turbine significantly.
Aforesaid gas turbine, for the ease of in the cavity of air distribution tube, injecting cooling liquid, and the cooling liquid after will heating is discharged the cavity of air distribution tube, one end of described air distribution tube is provided with the import that is used to inject described cooling liquid, the other end of described air distribution tube is provided with the outlet that is used to discharge described cooling liquid, and described import and described outlet are communicated with described cavity respectively.
Aforesaid gas turbine in order to improve the pressure of the pressurized gas that gas compressor produces, and improves the efficient that gas compressor produces pressurized gas, and described gas compressor comprises a plurality of sub-gas compressors that link together.
Aforesaid gas turbine is provided with gas holder between the adjacent two described sub-gas compressors.
Aforesaid gas turbine, described sub-gas compressor is an axial-flow blower, or centrifugal blower, or flow-mixing blower fan.
Aforesaid gas turbine in order to protect the firing chamber, reduces being dispersed into outside energy from the firing chamber, and gas turbine also comprises: thermal insulation apparatus, described thermal insulation apparatus are arranged between described shell and the described air distribution tube.
Aforesaid gas turbine, described thermal insulation apparatus are the holding furnace that insulating brick assembles, and described holding furnace is installed on the described shell; One end of described holding furnace offers suction port, and described suction port is communicated with the air outlet of described gas compressor; The other end of described holding furnace offers the air outlet, and described air outlet is communicated with the suction port of described turbo machine.
Aforesaid gas turbine for the pressurized gas that pressure fan is produced are blown in the air distribution tube fast, offers at least one described suction port on the sidewall of an end of described holding furnace.
Aforesaid gas turbine, in order to make fuel fully burning in the firing chamber, the length of described firing chamber is 0.5 meter to 2 meters.
Description of drawings
In order to be illustrated more clearly in the embodiment of the invention or technological scheme of the prior art, to do one to the accompanying drawing of required use in embodiment or the description of the Prior Art below introduces simply, apparently, accompanying drawing in describing below is some embodiments of the present invention, for those of ordinary skills, under the prerequisite of not paying creative work, can also obtain other accompanying drawing according to these accompanying drawings.
Fig. 1 is the structural representation of the embodiment of the invention one gas turbine;
Fig. 2 is the structural representation of air distribution tube in the embodiment of the invention one gas turbine;
Fig. 3 is the deployed configuration schematic representation of air distribution tube in the embodiment of the invention one gas turbine;
Fig. 4 is the structural representation of gas compressor in the embodiment of the invention one gas turbine;
Fig. 5 is the structural representation of the embodiment of the invention two gas turbines.
Embodiment
For the purpose, technological scheme and the advantage that make the embodiment of the invention clearer, below in conjunction with the accompanying drawing in the embodiment of the invention, technological scheme in the embodiment of the invention is clearly and completely described, obviously, described embodiment is the present invention's part embodiment, rather than whole embodiments.Based on the embodiment among the present invention, those of ordinary skills belong to the scope of protection of the invention not making the every other embodiment who is obtained under the creative work prerequisite.
Embodiment one
Fig. 1 is the structural representation of the embodiment of the invention one gas turbine, Fig. 2 is the structural representation of air distribution tube in the embodiment of the invention one gas turbine, Fig. 3 is the deployed configuration schematic representation of air distribution tube in the embodiment of the invention one gas turbine, and Fig. 4 is the structural representation of gas compressor in the embodiment of the invention one gas turbine.As Fig. 1-shown in Figure 4, the present embodiment gas turbine comprises gas compressor 11, firing chamber 10 and turbo machine 13, and the sidewall of the air distribution tube 12 of firing chamber 10 is provided with cavity 121; Cavity 121 is used for ccontaining cooling liquid, by cooling liquid air distribution tube 12 is protected; The pressurized gas that gas compressor 11 produces all enter in the air distribution tube 12, are used for mixing with fuel in the air distribution tube 12 participating in burning.
Particularly, the sidewall of air distribution tube 12 is provided with cavity 121 in the firing chamber 10 in the present embodiment, cooling liquid can be injected in the cavity 121.In the process of present embodiment gas turbine work, can carry out potent cooling to air distribution tube 12 by the cooling liquid in the cavity 121, thereby need not air distribution tube 12 in the firing chamber 10 to be cooled off by the pressurized gas that gas compressor 11 produces, the pressurized gas that gas compressor 11 is produced all enter in the air distribution tube 12, be used for air distribution tube 12 in fuel mix participate in burning.Wherein, the air distribution tube 12 in the present embodiment is installed on the shell 14, and concrete means of fixation gas turbine embodiment of the present invention does not limit.In addition, be provided with coupling shaft (not shown) between gas compressor 11 and the turbo machine 13, this coupling shaft is used for gas compressor 11 and turbo machine 13 are linked together, and is in transmission connection between turbo machine 13 and the gas compressor 11 so that realize.
And the gas turbine that uses in the prior art is developed by the gas turbine that uses on the aircraft usually, and therefore, the structure of gas turbine and material are all identical with gas turbine on the aircraft.Because be subjected to the restriction of weight, the gas turbine of Shi Yonging can only cool off the firing chamber by air-cooled mode aboard, and can not adopt the mode of coolant jacket to cool off.Therefore, the pressurized gas that the firing chamber of the gas turbine that uses in the prior art all adopts gas compressor to produce cool, and cause the waste of gas compressor energy, make the inefficiency of gas turbine.Because the present embodiment gas turbine is used for placing generating on the ground, the present embodiment gas turbine can not be subjected to the restriction on the weight, therefore, the cooling liquid that employing in the present embodiment gas turbine is stored in air distribution tube 12 cavitys 121 is cooled off air distribution tube 12, has overcome the technology prejudice that exists in the prior art.In addition, air distribution tube 12 is cooled off by the cooling liquid in the cavity 121, can be with under the boiling temperature that maintains cooling liquid of air distribution tube 12 in the work.Thereby make the air distribution tube 12 in the present embodiment gas turbine promptly can adopt the more cheap metallic material manufacturing of price, also can adopt resistant to elevated temperatures nonmetallic material manufacturing.
Working procedure below in conjunction with 1 pair of present embodiment gas turbine of accompanying drawing describes.The concrete working procedure of present embodiment gas turbine is as follows:
One, the pressurized gas of gas compressor 11 generations are by pipeline 151, and the shell 14 that passes firing chamber 10 enters in the firing chamber 10, and enters into air distribution tube 12 by the suction port of offering on the air distribution tube 12 122.
Two, by the fuel entry port (not shown) on the air distribution tube 12 fuel is injected to air distribution tube 12 inside, fuel fully mixes after-combustion with pressurized gas, thereby will produce the gas of high temperature and high speed.At this moment, the cooling liquid in the cavity 121 of air distribution tube 12 will absorb the temperature of air distribution tube 12, thereby air distribution tube 12 is lowered the temperature.
Three, the gas of the high temperature and high speed that produces in the air distribution tube 12 blows to turbo machine 13 by air outlet 123, makes turbo machine 13 fast turn-arounds.Wherein, the high temperature and high speed gas that the air distribution tube 12 in the present embodiment produces can directly directly blow to turbo machine 13 by pipeline 152, makes turbo machine 13 fast turn-arounds thereby high temperature and high speed gas can be driven.
The gas turbine of the embodiment of the invention; be provided with cavity by sidewall at firing chamber air distribution tube; and by the ccontaining cooling liquid of cavity; the air distribution tube is carried out cooling protection by cooling liquid; can effectively reduce the air distribution tube temperature of firing chamber; thereby the pressurized gas that gas compressor is produced all enter in the air distribution tube and participate in burning with fuel mix, and need not to reserve the part pressurized gas air distribution tube of firing chamber are cooled off.Because the gas turbine that uses in the prior art is to develop by the gas turbine that uses on the aircraft, manufacture and design in the process at gas turbine, the technology prejudice that the pressurized gas that existence always must adopt gas compressor to produce are lowered the temperature to the firing chamber, thus cause the gas turbine that uses that is used to generate electricity still to adopt the pressurized gas of gas compressor generation to lower the temperature.The gas turbine of the embodiment of the invention has overcome technology prejudice of the prior art, the Environmental Conditions of the gas turbine that uses in conjunction with being used to generate electricity, employing is injected cooling liquid in the cavity of air distribution tube sidewall, by cooling liquid the air distribution tube is lowered the temperature, thereby improved air distribution tube cooling-down effect to the firing chamber, and need not the pressurized gas that the part gas compressor produces are used to cool off the air distribution tube, thereby improved the efficient of gas turbine significantly.
Based on technique scheme, optionally, for the ease of in the cavity 121 of air distribution tube 12, injecting cooling liquid, and the cooling liquid after will heating is discharged the cavity 121 of air distribution tube 12, one end of the air distribution tube 12 in the present embodiment is provided with the import 124 that is used to inject cooling liquid, the other end of air distribution tube 12 is provided with the outlet 125 that is used to discharge cooling liquid, and import 124 and outlet 125 are communicated with cavity 121 respectively.
Particularly, the cooling liquid that temperature is low can be injected in the cavity 121 of air distribution tube 12 by import 124, and heated cooling liquid can be discharged by outlet 125 in the cavity 121, thereby realizes that storing the lower cooling liquid of temperature all the time in the cavity 121 cools off air distribution tube 12.Wherein, in the present embodiment in cooling liquid can be water or wet goods liquid substance; And cooling liquid can be injected into cavity 121 by devices such as pumps.For example, the air distribution tube 12 in the present embodiment can be made by the two-layer pressed plate that fits together 120.Concrete, as shown in Figure 3,, and offering through hole 127 except that on the position of groove 126 on the pressed plate by the groove 126 that pressed plate 120 is carried out impact briquetting, make being formed for ccontaining cooling liquid on the pressed plate 120.Then, two pressed plate 120 correspondences are fit together and curl into air distribution tube 12, corresponding groove 126 forms cavitys 121, and corresponding through hole 127 forms suction ports 122.In addition, import 124 and outlet 125 are also corresponding to be formed, and is communicated with respectively at cavity 121.
Further, the length of the firing chamber in the present embodiment 10 can be 0.5 meter to 2 meters.Concrete, in order to make fuel fully burning in firing chamber 10, the length of the firing chamber 10 in the present embodiment can suitably increase, thereby makes fuel can have time enough fully to burn.
The present embodiment gas turbine by offer the import export that is communicated with cavity on the air distribution tube, makes the cooling liquid in the cavity remain low-temperature condition, thereby effectively the air distribution tube is lowered the temperature.In addition,, can make fuel can have time enough fully to burn, thereby can utilize fuel more efficiently, help saving the energy by increasing the length of firing chamber.
Based on technique scheme, optionally, in order to improve the pressure of the pressurized gas that gas compressor 11 produced, and improve the efficient that gas compressor 11 produces pressurized gas, the gas compressor 11 in the present embodiment comprises a plurality of sub-gas compressors 111 that link together.Further, can be provided with gas holder 112 between the adjacent two sub-gas compressors 111.Further, the sub-gas compressor 111 in the present embodiment can be axial-flow blower, or centrifugal blower, or flow-mixing blower fan.
Particularly, as depicted in figs. 1 and 2, can produce the more gas of high pressure in order to make gas compressor 11, the gas compressor 11 in the present embodiment can comprise a plurality of sub-gas compressors 111 that link together, and is provided with gas holder 112 between adjacent two sub-gas compressors 111.The sub-gas compressor 111 that is communicated with atmosphere can be stored into air compression in first gas holder 112, sub-gas compressor 111 behind first gas holder 112 is with the gas compression of first gas holder 112 outputs, finally, can be by last sub-gas compressor 111 with the supercharging and being transferred in the firing chamber 10 once more of the pressurized gas in the gas holder 112.At this moment, the pressure that enters into the pressurized gas of firing chamber 10 will significantly increase, and more help the abundant burning of fuel.Simultaneously, because the gas pressure that enters in the firing chamber 10 increases, this gas can form the gas that speed is faster, pressure is higher, thereby turbo machine can be turned round more fast after participating in burning with fuel mix.
The present embodiment gas turbine, by a plurality of sub-gas compressors and gas holder are joined together to form a total gas compressor, make gas compressor can export the more gas of high pressure, thereby the fuel in the firing chamber can be burnt more fully, realize that the firing chamber head pressure is bigger, speed faster gas more help improving the efficient of gas turbine to promote turbine operation.
Fig. 5 is the structural representation of the embodiment of the invention two gas turbines.As shown in Figure 5, the present embodiment gas turbine is based on the foregoing description one, and its difference is that the present embodiment gas turbine also comprises: thermal insulation apparatus 27, thermal insulation apparatus 27 are arranged between shell 24 and the air distribution tube 22.
Particularly, also be provided with a thermal insulation apparatus 27 between air distribution tube 22 in the present embodiment and the shell 24, this thermal insulation apparatus 27 can effectively reduce the heat that fuel combustion in the firing chamber 20 produces and be dispersed into the outside by shell 24, thereby more helps the efficient of saving energy and improving the present embodiment gas turbine.
Further, the holding furnace that the thermal insulation apparatus 27 in the present embodiment can assemble for insulating brick 272, holding furnace is installed on the shell 24; One end of holding furnace offers suction port 271, and this suction port 271 is communicated with the air outlet (not shown) of gas compressor 21; The other end of holding furnace offers air outlet (not shown), and this air outlet is communicated with the suction port (not shown) of turbo machine 23.Concrete, the thermal insulation apparatus 27 in the present embodiment can be the holding furnace that assembles by insulating brick 272, for example, insulating brick 272 can be fixed on the inwall of shell 24, thus the thermal insulation apparatus 27 in the formation present embodiment.Wherein, the pressurized gas of gas compressor 21 generations for convenience enter into air distribution tube 22, thermal insulation apparatus 27 in the present embodiment offers suction port 271 in the end near gas compressor 21, thereby the pressurized gas that gas compressor 21 produces enter into air distribution tube 22 by shell 24 and suction port 271 successively.Wherein, for the pressurized gas that pressure fan 21 is produced are blown in the air distribution tube 22 fast, can offer at least one suction port 271 on the sidewall of an end of the holding furnace in the present embodiment.By on the sidewall of thermal insulation apparatus 27, offering at least one suction port 271, the pressurized gas that gas compressor 21 is produced vertically blow to air distribution tube 22, thereby pressurized gas can be blown in the air distribution tube 22 fast, and the fuel in quickening and the air distribution tube 22 burns.
The present embodiment gas turbine can effectively reduce the energy that fuel combustion in the firing chamber produces and is dispersed into the outside by thermal insulation apparatus is set, and helps saving the efficient that can and improve the present embodiment gas turbine.In addition, by offering at least one suction port at the sidewall of thermal insulation apparatus, the pressurized gas that gas compressor is produced vertically blow to the air distribution tube, thereby pressurized gas can be blown in the air distribution tube fast, and the fuel in quickening and the air distribution tube burns.
It should be noted that at last: above embodiment only in order to technological scheme of the present invention to be described, is not intended to limit; Although with reference to previous embodiment the present invention is had been described in detail, those of ordinary skill in the art is to be understood that: it still can be made amendment to the technological scheme that aforementioned each embodiment put down in writing, and perhaps part technical characteristics wherein is equal to replacement; And these modifications or replacement do not make the essence of appropriate technical solution break away from the spirit and scope of various embodiments of the present invention technological scheme.
Claims (9)
1. a gas turbine comprises gas compressor, firing chamber and turbo machine, it is characterized in that, the sidewall of the air distribution tube of described firing chamber is provided with cavity; Described cavity is used for ccontaining cooling liquid, by described cooling liquid described air distribution tube is protected; The pressurized gas that described gas compressor produces all enter in the described air distribution tube, are used for mixing with fuel in the described air distribution tube participating in burning.
2. gas turbine according to claim 1, it is characterized in that, one end of described air distribution tube is provided with the import that is used to inject described cooling liquid, and the other end of described air distribution tube is provided with the outlet that is used to discharge described cooling liquid, and described import and described outlet are communicated with described cavity respectively.
3. gas turbine according to claim 1 and 2 is characterized in that, described gas compressor comprises a plurality of sub-gas compressors that link together.
4. gas turbine according to claim 3 is characterized in that, is provided with gas holder between the adjacent two described sub-gas compressors.
5. gas turbine according to claim 3 is characterized in that, described sub-gas compressor is an axial-flow blower, or centrifugal blower, or flow-mixing blower fan.
6. gas turbine according to claim 1 and 2 is characterized in that, also comprises: thermal insulation apparatus, described thermal insulation apparatus are arranged between described shell and the described air distribution tube.
7. gas turbine according to claim 6 is characterized in that, described thermal insulation apparatus is the holding furnace that insulating brick assembles, and described holding furnace is installed on the described shell; One end of described holding furnace offers suction port, and described suction port is communicated with the air outlet of described gas compressor; The other end of described holding furnace offers the air outlet, and described air outlet is communicated with the suction port of described turbo machine.
8. gas turbine according to claim 7 is characterized in that, offers at least one described suction port on the sidewall of an end of described holding furnace.
9. gas turbine according to claim 1 and 2 is characterized in that, the length of described firing chamber is 0.5 meter to 2 meters.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010115375 CN101798959A (en) | 2010-02-10 | 2010-02-10 | Gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010115375 CN101798959A (en) | 2010-02-10 | 2010-02-10 | Gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101798959A true CN101798959A (en) | 2010-08-11 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010115375 Pending CN101798959A (en) | 2010-02-10 | 2010-02-10 | Gas turbine |
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| CN (1) | CN101798959A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1112985A (en) * | 1994-03-21 | 1995-12-06 | Abb管理有限公司 | Cooling of hot unit of gas turbine |
| CN1580520A (en) * | 2003-08-08 | 2005-02-16 | 阿尔斯通技术有限公司 | Gas turbine and associated cooling method |
| CN2844491Y (en) * | 2005-07-11 | 2006-12-06 | 福建省泉州市力达机械有限公司 | Rear cooler of compressor |
| CN201650463U (en) * | 2010-02-10 | 2010-11-24 | 马鞍山科达洁能有限公司 | Combustion gas turbine |
-
2010
- 2010-02-10 CN CN 201010115375 patent/CN101798959A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1112985A (en) * | 1994-03-21 | 1995-12-06 | Abb管理有限公司 | Cooling of hot unit of gas turbine |
| CN1580520A (en) * | 2003-08-08 | 2005-02-16 | 阿尔斯通技术有限公司 | Gas turbine and associated cooling method |
| CN2844491Y (en) * | 2005-07-11 | 2006-12-06 | 福建省泉州市力达机械有限公司 | Rear cooler of compressor |
| CN201650463U (en) * | 2010-02-10 | 2010-11-24 | 马鞍山科达洁能有限公司 | Combustion gas turbine |
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Open date: 20100811 |