CN203671658U - Combustion chamber of combustion gas turbine and combustion gas turbine with same - Google Patents
Combustion chamber of combustion gas turbine and combustion gas turbine with same Download PDFInfo
- Publication number
- CN203671658U CN203671658U CN201320817118.4U CN201320817118U CN203671658U CN 203671658 U CN203671658 U CN 203671658U CN 201320817118 U CN201320817118 U CN 201320817118U CN 203671658 U CN203671658 U CN 203671658U
- Authority
- CN
- China
- Prior art keywords
- combustion chamber
- head construction
- gas turbine
- combustion
- head
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 134
- 239000000567 combustion gas Substances 0.000 title claims abstract description 8
- 238000010276 construction Methods 0.000 claims description 102
- 239000007789 gas Substances 0.000 claims description 47
- 230000001788 irregular Effects 0.000 claims description 4
- 238000005516 engineering process Methods 0.000 description 12
- 239000000295 fuel oil Substances 0.000 description 12
- 230000010349 pulsation Effects 0.000 description 9
- 238000000889 atomisation Methods 0.000 description 4
- 230000005764 inhibitory process Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 239000003921 oil Substances 0.000 description 3
- 238000011144 upstream manufacturing Methods 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 206010020843 Hyperthermia Diseases 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000008030 elimination Effects 0.000 description 1
- 238000003379 elimination reaction Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000036031 hyperthermia Effects 0.000 description 1
- 230000008676 import Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000035484 reaction time Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
Images
Abstract
The utility model relates to a combustion chamber of a combustion gas turbine and the combustion gas turbine with the combustion chamber. The combustion chamber is an annular combustion chamber and comprises a plurality of head structures, the head structures are circumferentially arranged along the combustion chamber, and each head structure comprises an outer cylinder and a combustion chamber nozzle arranged in the outer cylinder. At least two sets of head structures are included, and each set of head structures in the at least two sets of head structures is provided with sizes different from those of the other set of head structures. According to the structural arrangement of the combustion chamber, the unstable combustion in the combustion chamber can be restrained.
Description
Technical field
The utility model relates to a kind of combustion chamber of gas turbine and has the gas turbine of this combustion chamber, is specifically related to the layout of head construction in the combustion chamber of this gas turbine.Gas turbine of the present utility model can be used for the applications such as aero-engine.
Background technology
Current, gas turbine, especially what generally adopt as the gas turbine of aero-engine is the layout structure of toroidal combustion chamber.In addition,, along with day by day harsh to NOx discharge standard, developed lean premixed preevaporated (LPP) combustion system, to substitute traditional diffusion combustion mode.
In LPP combustion system, fuel-steam and air are pre-mixed, and so that fuel oil is carried out to atomization, the oil gas equivalent of the fuel oil after atomization is than being conventionally less than 1.Then, after fuel oil is atomized, then carry out the combustion reaction of fuel oil and air.Like this, because fuel oil is by atomization in advance, therefore can accelerate combustion reaction time, and can control combustion temperature, reduce or avoid the generation of localized hyperthermia, thereby reduce the growing amount of NOx.
Although LPP combustion system can reduce the discharge capacity of NOx, also there is the problem of combustion instability, that is, can produce hugging.Specifically, along with the development of flame mechanism, in combustion chamber, oil-gas ratio can reduce, and along with the reduction of oil-gas ratio, the local inhomogeneous situation of burning that can occur in combustion zone in combustion chamber, and the inhomogeneous pulsation that can produce heat release rate of such burning.Meanwhile, in combustion process, also there is the situation of pulsation in the parameter such as pressure in combustion chamber, temperature, incoming flow oil-gas ratio.When the pulsation of heat release rate and the pulsation of these parameters are to coupling, can produce self-oscillation resonance in other words conj.or perhaps, thereby cause the generation of combustion instability phenomenon.
Combustion instability phenomenon can cause the efficiency of combustion of gas turbine to reduce, the serious chamber structure that also can destroy.In addition, combustion instability can cause reappearing hot-spot region in combustion chamber, increases the growing amount of NOx.Thus, offset the effect of the reduction NOx discharge capacity of LPP.Therefore, need to take combustion instability inhibition technology to the combustion chamber of gas turbine.
The combustion instability inhibition technology adopting at present mainly contains three kinds: first combustion instability inducement inhibition technology, this technology is mainly by the design of the oil circuit of improvement combustion chamber, gas circuit, premix section, head construction etc., eliminates the disturbance of external factor to burning; It two is Passive Control technology, and this technology is mainly the resonant frequency that changes each structure, or increases damping to suppress vibration, controls thus vibration; It three is active control technologies, and this technology is mainly that sensing device and the fuel flow control system such as unstable state pressure sensor is installed in gas turbine, thereby in real time combustion instability phenomenon is controlled.
Above-mentioned three kinds of technology have application in various degree in the gas turbine of prior art, and it respectively has pluses and minuses.Such as, above-mentioned three kinds of methods all need the structure of gas turbine to change to some extent.For example need to change oil circuit, gas circuit etc.; Or extra device need to be set, as sensor, flow control system etc.And the ripple frequency of heat release rate, chamber pressure, temperature etc. is not what fix, can be different under different combustion conditions, therefore the effect of above-mentioned inhibition technology is limited.
Utility model content
The utility model is made in order to solve the problems of the technologies described above, its objective is the chamber structure that a kind of gas turbine is provided, it can simply and effectively suppress the combustion instability in combustion chamber, reduces and the adverse effect of elimination combustion instability to chamber structure and combustion process.
According to an aspect of the present utility model, a kind of combustion chamber of gas turbine is toroidal combustion chamber, and comprise multiple head constructions, head construction is along the circumferential array of combustion chamber, head construction comprises outside cylindrical shell and is arranged on the combustion chamber burner in outside cylindrical shell, wherein, head construction comprises at least two group head constructions, and each the group head construction in this at least two groups head construction has the size different from the head construction of other groups.
By the head construction that size is different is set in combustion chamber, makes in each head construction because the oil-gas ratio frequency of oscillation causing of pulsing interferes with each other and offsets, thereby generally speaking can suppress the combustion instability in combustion chamber with regard to combustion chamber.
Preferably, the combustion chamber burner being arranged in head construction comprises the pre-combustion grade nozzle that is positioned at central main combustion stage nozzle and arranges round main combustion stage nozzle.
In a kind of preferred embodiments, head construction can comprise first group of head construction with first size and second group of head construction with the second size, and wherein first size is greater than the second size.
In the above-mentioned situation with two groups of head constructions, the each head construction in first group of head construction can with second group of head construction in each head construction be arranged alternately each other.
In another kind of preferred embodiments, head construction comprise have first size first group of head construction, there is second group of head construction of the second size and there is the 3rd group of head construction of the 3rd size, wherein first size is greater than the 3rd size, and the second size occupy between first size and the 3rd size.
In this case, the spread pattern of each head construction can be as follows: the each head construction in each head construction and the 3rd group of head construction in first group of head construction is alternately set between the each adjacent head construction in second group of head construction.
Except regularly arranged, this at least two groups head construction in the utility model can irregular order along the circumferential array of combustion chamber.
The utility model also relates to a kind of gas turbine, wherein, the flow direction in this gas turbine along air and combustion gas, this gas turbine comprises compressor, combustion chamber, turbine and jet pipe successively, wherein, this combustion chamber is above-described combustion chamber.
Brief description of the drawings
Fig. 1 shows a kind of longitudinal section of exemplary gas turbine engine.
Fig. 2 shows the cross-sectional view of gas turbine of the present utility model at combustion chamber place, and the first that wherein shows the head construction in combustion chamber is arranged.
Fig. 3 shows the cross-sectional view of gas turbine of the present utility model at combustion chamber place, and the second that wherein shows the head construction in combustion chamber is arranged.
Fig. 4 shows the cross-sectional view of gas turbine of the present utility model at combustion chamber place, wherein shows the third layout of the head construction in combustion chamber.
Detailed description of the invention
Below in conjunction with accompanying drawing, detailed description of the invention of the present utility model is elaborated.Should understand, shown in the drawings is only preferred embodiment of the present utility model, and it does not form the restriction to scope of the present utility model.Those skilled in the art can carry out various apparent amendments, modification, equivalence replacement to the utility model on the basis of embodiment shown in the drawings, within these all drop on protection domain of the present utility model.
Fig. 1 shows a kind of longitudinal section with gas turbine with circular combustion chamber.As example, this gas turbine is turbojet, comprise combustion chamber 10, be positioned at the upstream of combustion chamber 10 compressor 20, be positioned at combustion chamber 10 downstream turbine 40 and be positioned at the jet pipe 30 in the downstream of turbine 40.Herein, so-called " upstream " and " downstream " are that flow direction taking air or combustion gas is as benchmark.
Be provided with head construction 11 in the import department of combustion chamber 10, as shown in Figure 1, head construction 11 is cylindric, comprises outside cylindrical shell 13 and is arranged on the combustion chamber burner 12 in outside cylindrical shell 13.Except combustion chamber burner 12, this head construction 11 also can additionally arrange the device such as blender, cyclone, to realize the mixing to fuel oil and air and to make incoming flow air deflection to form the function of whirlpool shape fluidal texture.Preferably, head cooling device also can be set on head construction.
In the course of the work, air is through compressor 20 and compressed, mixes with the fuel oil spraying in combustion chamber burner 12 in combustion chamber 10, makes fuel-oil atmozation.Fuel oil through atomization burns in combustion chamber.Fuel oil and air reaction and the expansion combustion gas that produces is discharged from jet pipe through turbine, thus power produced.
Gas turbine of the present utility model adopts LPP combustion system, and in order to overcome the problem of the existing combustion instability of LPP combustion system, the utility model improves the layout of combustion chamber 10.Specifically, size and the arrangement form of head construction 11 are wherein improved.Lower mask body discloses several detailed description of the invention of the present utility model.
< the first embodiment >
Fig. 1 is the cross-sectional view through the combustion chamber 10 of gas turbine, wherein shows the first arrangement form of the head construction 11 of combustion chamber 10.
As shown in Figure 1, the combustion chamber 10 of the gas turbine form of combustion chamber in the form of a ring, has multiple head constructions along the circumferential arrangement of combustion chamber 10.Head construction shown in Fig. 2 mainly comprises two kinds of different sizes (for example diameter), and wherein head construction 11a has first size, and head construction 11b has second size less than first size.
In addition, still as shown in Figure 2, head construction of the present utility model comprises combustion chamber burner 12a, 12b.Taking the combustion chamber burner 12a in head construction 11a as example, this combustion chamber burner 12a comprises the main combustion stage nozzle 122a that is positioned at central pre-combustion grade nozzle 121a and arranges round pre-combustion grade nozzle 121a.Similarly, the combustion chamber burner 12b of head construction 11b also comprises pre-combustion grade nozzle 121b and main combustion stage nozzle 122b.Preferably, because the size of head construction 11a is greater than the size of head construction 11b, corresponding, the size of combustion chamber burner 12a is also greater than the size of combustion chamber burner 12b.
Preferably, in the first arrangement form of the head construction shown in Fig. 2, the first head construction 11a and the second head construction 11b arrange alternately with each other.
In running, from the air of 10 upstreams, combustion chamber of for example compressor 20 through head construction 11 and enter in annular combustion chamber 10.Meanwhile, fuel oil is injected in combustion chamber 10 by combustion chamber burner 12, and mixes mutually with the air through head construction 11, and is atomized.In this process, the disturbance meeting that incoming flow air, fuel oil etc. produce is pulsed and is transmitted in the combustion zone of toroidal combustion chamber 10 by oil-gas ratio.This pulsation of oil-gas ratio causes the heat release rate pulsation in combustion zone, thereby causes the pulsation of chamber pressure and fuel gas flow speed.
Now, owing to being furnished with head construction 11a and the head construction 11b that size is different in combustion chamber, thereby between different head constructions, their oil-gas ratio pulsation is also different.Like this, the frequency of the chamber pressure being associated from different head constructions and the pulsation of fuel gas flow speed is different, interferes with each other, and widens the frequency domain width of vibration.Like this, with regard to toroidal combustion chamber generally speaking, combustion instability is suppressed.
< the second embodiment >
Fig. 3 shows the second arrangement form of the head construction 11 of combustion chamber 10.In Fig. 3, the technical characterictic identical with Fig. 2 uses identical Reference numeral, and for for simplicity, no longer does the description of repetition for identical structure.
In Fig. 3, identical with shown in Fig. 2, also comprises multiple head constructions in combustion chamber 10.And, except the head construction 11a with first size shown in Fig. 2 and having the head construction 11b of the second size, in the embodiment shown in Fig. 3, also comprise the head construction 11c with the 3rd size.From Fig. 3, can be clear that, the 3rd size is all less than first size and the second size.
In the arrangement form shown in Fig. 3, taking the head construction 11b with the second size as benchmark, between two adjacent head construction 11b, alternately arrange the head construction 11a with first size and the head construction 11c with the 3rd size.
< the 3rd embodiment >
Fig. 4 shows the third arrangement form of the head construction 11 of combustion chamber 10.Similar with the second arrangement form shown in Fig. 3, in toroidal combustion chamber 10 shown in Fig. 4, be also furnished with three kinds of head construction 11a, 11b and 11c, they have respectively first size, than the second little size of first size and than the second size little the 3rd size.
The difference of the second arrangement form shown in the third arrangement form shown in Fig. 4 and Fig. 3 is, the head construction of three kinds of sizes of the combustion chamber 10 in layout drawing 4 is arranged in irregular mode, in other words these three kinds of head constructions with random order the circumferential arrangement along combustion chamber 10.
Above detailed description of the invention of the present utility model is described.As mentioned before, on the basis of above-mentioned detailed description of the invention, those skilled in the art can carry out various conversion, and these convert all within scope of the present utility model.For example:
In detailed description of the invention shown in the drawings, head construction 11 is cylindric.But, it should be known that head construction also can be other various shapes, for example cross section is square, regular polygon, oval etc.
In above-described three embodiments, the head construction with two kinds and three kinds different sizes is disclosed respectively.Should be appreciated that the head construction that also can arrange other any amount of size category in combustion chamber, as four kinds of sizes, five kinds of sizes etc.And these head constructions can also be rule or the irregular alignment of other any-modes except above three kinds of embodiments along circumferential the putting in order in combustion chamber.
Claims (8)
1. the combustion chamber of a gas turbine, described combustion chamber is toroidal combustion chamber, and comprise multiple head constructions, described head construction is along the circumferential array of described combustion chamber, each described head construction comprises outside cylindrical shell and is arranged on the combustion chamber burner in described outside cylindrical shell, it is characterized in that, described head construction comprises at least two group head constructions, and each the group head construction in described at least two group head constructions has the size different from the head construction of other groups.
2. the combustion chamber of gas turbine as claimed in claim 1, is characterized in that, described combustion chamber burner comprises the pre-combustion grade nozzle that is positioned at central main combustion stage nozzle and arranges round described main combustion stage nozzle.
3. the combustion chamber of gas turbine as claimed in claim 1 or 2, is characterized in that, described head construction comprises first group of head construction with first size and second group of head construction with the second size, and described first size is greater than described the second size.
4. the combustion chamber of gas turbine as claimed in claim 3, is characterized in that, the each head construction in the each head construction in described first group of head construction and described second group of head construction is arranged alternately each other.
5. the combustion chamber of gas turbine as claimed in claim 3, is characterized in that, described head construction also comprises the 3rd group of head construction with the 3rd size, and wherein said the 3rd size is less than described the second size.
6. the combustion chamber of gas turbine as claimed in claim 5, it is characterized in that, the each head construction in each head construction and described the 3rd group of head construction in described first group of head construction is alternately set between the each adjacent head construction in described second group of head construction.
7. the combustion chamber of gas turbine as claimed in claim 1 or 2, is characterized in that, described at least two group head constructions are the circumferential array along described combustion chamber with irregular order.
8. a gas turbine, the flow direction in described gas turbine along air and combustion gas, described gas turbine comprises compressor, combustion chamber, turbine and jet pipe successively, it is characterized in that, described combustion chamber is the combustion chamber as described in any one in claim 1-7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320817118.4U CN203671658U (en) | 2013-12-11 | 2013-12-11 | Combustion chamber of combustion gas turbine and combustion gas turbine with same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320817118.4U CN203671658U (en) | 2013-12-11 | 2013-12-11 | Combustion chamber of combustion gas turbine and combustion gas turbine with same |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203671658U true CN203671658U (en) | 2014-06-25 |
Family
ID=50967947
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320817118.4U Expired - Lifetime CN203671658U (en) | 2013-12-11 | 2013-12-11 | Combustion chamber of combustion gas turbine and combustion gas turbine with same |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203671658U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104534515A (en) * | 2014-12-03 | 2015-04-22 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Combustion chamber head structure of gas turbine |
| CN104566476A (en) * | 2014-12-03 | 2015-04-29 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Combustion gas turbine combustion chamber head structure and combustion organization method of combustion gas turbine combustion chamber |
| CN106439914A (en) * | 2016-11-21 | 2017-02-22 | 深圳智慧能源技术有限公司 | Combustion chamber of combustion gas turbine |
| CN106996579A (en) * | 2017-05-16 | 2017-08-01 | 西北工业大学 | A kind of oil-poor direct jetstream whirl nozzle mould of low-pollution burning chamber of gas turbine |
-
2013
- 2013-12-11 CN CN201320817118.4U patent/CN203671658U/en not_active Expired - Lifetime
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104534515A (en) * | 2014-12-03 | 2015-04-22 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Combustion chamber head structure of gas turbine |
| CN104566476A (en) * | 2014-12-03 | 2015-04-29 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Combustion gas turbine combustion chamber head structure and combustion organization method of combustion gas turbine combustion chamber |
| CN104566476B (en) * | 2014-12-03 | 2018-03-23 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas-turbine combustion chamber head construction and its burning tissues method |
| CN104534515B (en) * | 2014-12-03 | 2018-04-20 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas-turbine combustion chamber head construction |
| CN106439914A (en) * | 2016-11-21 | 2017-02-22 | 深圳智慧能源技术有限公司 | Combustion chamber of combustion gas turbine |
| CN106996579A (en) * | 2017-05-16 | 2017-08-01 | 西北工业大学 | A kind of oil-poor direct jetstream whirl nozzle mould of low-pollution burning chamber of gas turbine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP5984770B2 (en) | Gas turbine combustor and gas turbine engine equipped with the same | |
| CN102954492B (en) | For reducing the system and method for combustion dynamics in the burner | |
| CN103629670A (en) | System and method for reducing combustion dynamics | |
| CN105716116B (en) | Axial staged mixer for injecting dilution air | |
| CN103629698A (en) | System and method for reducing modal coupling of combustion dynamics | |
| CN203671658U (en) | Combustion chamber of combustion gas turbine and combustion gas turbine with same | |
| JP2010223577A (en) | Swirler, method of preventing flashback in burner equipped with at least one swirler, and burner | |
| US10125992B2 (en) | Gas turbine combustor with annular flow sleeves for dividing airflow upstream of premixing passages | |
| JP2010223577A6 (en) | Swirl, method for preventing backfire in burner equipped with at least one swirler, and burner | |
| CN105715378B (en) | Separate supply of cooling and dilution air | |
| KR20140052874A (en) | Damper arrangement for reducing combustion-chamber pulsation | |
| JP2011033331A (en) | Fuel nozzle for turbine combustor, and method for forming the same | |
| JP2008528932A (en) | Damping of thermoacoustic vibrations in a gas turbine combustor with an annular plenum. | |
| US20160032842A1 (en) | Combustor and gas turbine | |
| JP2015075314A (en) | Gas turbine fuel injection device | |
| US9416975B2 (en) | Dual fuel combustor for a gas turbine engine including a toroidal injection manifold with inner and outer sleeves | |
| WO2017034435A1 (en) | Systems and methods for a multi-fuel premixing nozzle with integral liquid injectors/evaporators | |
| KR20120078636A (en) | Sculpted trailing edge swirler combustion premixer and method | |
| JP2015511698A (en) | Mixing device for mixing fuel into a flow of oxygen-containing gas | |
| JP4727548B2 (en) | Combustor | |
| WO2011163289A2 (en) | Secondary water injection for diffusion combustion systems | |
| US20210172606A1 (en) | Mixer | |
| KR20140101825A (en) | Burner | |
| JP2020521907A (en) | Burner with acoustic damper | |
| JP5203290B2 (en) | Method for reducing combustor emissions |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: AECC COMMERCIAL AIRCRAFT ENGINE Co.,Ltd. Address before: 201108 Shanghai city Minhang District Lotus Road No. 3998 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |
|
| CP03 | Change of name, title or address | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140625 |
|
| CX01 | Expiry of patent term |