CN104595927A - Low-heat value fuel gas combustion chamber of gas turbine - Google Patents
Low-heat value fuel gas combustion chamber of gas turbine Download PDFInfo
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- CN104595927A CN104595927A CN201510035910.8A CN201510035910A CN104595927A CN 104595927 A CN104595927 A CN 104595927A CN 201510035910 A CN201510035910 A CN 201510035910A CN 104595927 A CN104595927 A CN 104595927A
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- fuel
- combustion chamber
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- calorie fuels
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Abstract
The invention relates to the technical field of a gas turbine, and specifically discloses a low-heat value fuel gas combustion chamber of the gas turbine. The low-heat value fuel gas combustion chamber comprises a casing, an end cover arranged at the front end of the casing, a head fuel spray nozzle arranged on the end cover, a flow guiding bush arranged in the casing, a flame tube arranged in the flow guiding bush and a transition section connected with the rear end of the flame tube, wherein the front end of the flame tube is connected with the head fuel spray nozzle; a plurality of rows of main combustion holes are distributed in the flame tube along the axial direction; low-heat value fuel spray nozzles are arranged among the main combustion holes in each row of the flame tube. According to the low-heat value fuel gas combustion chamber disclosed by the invention, lower pollutant emission level can be achieved, and the thermo-acoustic oscillation risk is lower.
Description
Technical field
The present invention relates to gas turbine technology field, particularly relate to a kind of low heat value of gas turbine fuel gas combustion chamber.
Background technology
For the low calorie fuels such as synthesis gas from coal gasification, blast furnace gas, coke-stove gas, chemical industry periodic off-gases, town gas, its complicated component, volume calorific value is low, if directly can cause larger pollution to flare system discharge.Gas turbine combustion is adopted to be a more excellent and Application way for environmental protection, can such low calorie fuels gas of flexible utilization, be converted into electric energy or heat energy.
Usually for gas-turbine combustion chamber, its lower heat of combustion fuel gas uses nozzle to transform for adopting ripe fuel gas nozzle, and reforming mode is fuel metering hole thus the volume flow of coupling fuel.In this kind of situation, it is narrower that combustion chamber adapts to fuel range, and usually allow Wobbe index excursion to be +/-5%, indivedual new combustion chamber is by being optimized control and regulation, and Wobbe index accommodation is +/-10%.
As shown in Figure 1, for conventional gas turbine combustion chamber of the prior art, comprise: casing 1, end cap 2, head fuel nozzle 3, burner inner liner 4, water conservancy diversion lining 5 and changeover portion 6, on burner inner liner 4, first half section arranges many row's primary holes 42, second half section arranges blending hole 47, and flame tube wall equally also arranges many row's Cooling Holes 48.
This kind of typical operation principle in combustion chamber is: enter fuel gas and a certain proportion of air by nozzle 3, and fuel gas and air enter combustion chamber by the mode of eddy flow, and concrete eddy flow comprises: axial swirler, radial swirler or mixing cyclone.Burner inner liner 4 leading portion has some mix aperture, and air radially enters burner inner liner 4, and the fuel gas entered with eddy flow and air carry out blending, complete combustion process.Simultaneously, unnecessary air is entered by the blending hole 47 of burner inner liner 4 rear end, be ensure that the air of burner inner liner front end and fuel burn with appropriate proportioning on the one hand, the outlet air section of this portion of air to combustion chamber also can be utilized to regulate on the one hand in addition.
However, for variety classes low calorie fuels gas, fuel nozzle often needs to redesign, and except calorific value, in fuel, hydrogen content is also the major reason redesigning nozzle for the impact of nozzle.
Summary of the invention
(1) technical problem that will solve
The object of this invention is to provide a kind of low heat value of gas turbine fuel gas combustion chamber, to reach lower pollutant emission level, and have lower thermal acoustic oscillation risk.
(2) technical scheme
In order to solve the problems of the technologies described above, the invention provides a kind of low heat value of gas turbine fuel gas combustion chamber, comprise casing, be located at the end cap of described casing front end, the head fuel nozzle be located on described end cap, be located at described casing inside water conservancy diversion lining, be located in described water conservancy diversion lining and the burner inner liner that is connected with described head fuel nozzle of front end and the changeover portion that is connected with the rear end of described burner inner liner; Described burner inner liner is provided with the primary holes that many rows distribute vertically, and described burner inner liner is provided with low calorie fuels nozzle between each row's primary holes.
Preferably, described burner inner liner is circumferentially provided with equally distributed multiple low calorie fuels nozzle at same axial location.
Preferably, the outside of described casing is provided with low calorie fuels ring cavity, and described low calorie fuels ring cavity is connected with the outer end being positioned at same multiple low calorie fuels nozzles circumferentially respectively, for being multiple low calorie fuels nozzle supply fuel.
Preferably, described low calorie fuels nozzle is 1 ~ 4 row, and the quantity of described low calorie fuels ring cavity is corresponding with the row of described low calorie fuels nozzle.
Preferably, described low calorie fuels nozzle is cartridge, and the inner of described cartridge is provided with fuel orifice, and the axis of described fuel orifice is perpendicular to the sidewall of described burner inner liner.
Preferably, the fuel jet speed of described low calorie fuels nozzle is 100m/s ~ 150m/s.
Preferably, the fuel entered from described head fuel nozzle is natural gas, and the load of the maximum stream flow band of natural gas meets 5% ~ 10% of gas turbine base load, and the air capacity entered from described head fuel nozzle accounts for 7% ~ 15% of combustion air amount.
Preferably, the fuel flow channel of described head fuel nozzle and the eddy flow angular region of air flow channel are 10 ° ~ 25 °.
Preferably, during removal of load, directly interdict the supply of low calorie fuels gas, adjustment center gas discharge, when regulating load, by regulating the fuel supply of low calorie fuels ring cavity classification carried out to low calorie fuels thus meet different load demand.
Preferably, often arrange primary holes to be uniformly distributed circumferentially.
(3) beneficial effect
A traditional natural gas swirl flame is set up at burner inner liner head in low heat value of gas turbine fuel gas combustion chamber of the present invention, in downstream, low calorie fuels gas is introduced at a high speed at axially different position in combustion chamber, enter Swirl flame combustion, the longer weak swirl flame in center is used for lighting and maintains low calorie fuels gas, therefore low calorie fuels gas itself does not need self steady flame mechanism, poor blowoff limit can be widened, fuel characteristic also becomes insensitive, therefore, same chamber structure can be scalable low calorie fuels, without the need to carrying out special design for the Wobbe index of often kind of fuel or hydrogen content, this burning concept can be applicable to the requirement of multiple different range Wobbe index, the low calorie fuels gas of hydrogen content, simultaneously, this chamber structure also can complete sufficient blending before combustion, form distributed flame, thus burner inner liner internal flame Thermal release is even, reach lower pollutant emission level, and there is lower thermal acoustic oscillation risk, present invention also offers the scheme of removal of load and Load Regulation, Adjusted Option is simple, also the effect of low stain thing discharge is more easily realized.
Accompanying drawing explanation
Fig. 1 is the structural representation of conventional gas turbine combustion chamber in prior art;
Fig. 2 is the structural representation of the low heat value of gas turbine fuel gas combustion chamber of the embodiment of the present invention;
Fig. 3 is the partial structurtes schematic diagram at the low calorie fuels nozzle place of the low heat value of gas turbine fuel gas combustion chamber of the embodiment of the present invention;
Fig. 4 is the circumferentially figure of the low calorie fuels nozzle of the low heat value of gas turbine fuel gas combustion chamber of the embodiment of the present invention.
In figure, 1: casing; 2: end cap; 3: head fuel nozzle; 4: burner inner liner; 5: water conservancy diversion lining; 6: changeover portion; 41: low calorie fuels nozzle; 42: primary holes; 43: low calorie fuels ring cavity; 44: cartridge; 45: fuel orifice; 46: fuel manifold; 47: blending hole, 48: Cooling Holes; 49: primary holes axis.
Detailed description of the invention
Below in conjunction with drawings and Examples, embodiments of the present invention are described in further detail.Following examples for illustration of the present invention, but can not be used for limiting the scope of the invention.
In describing the invention, it should be noted that, term " " center ", " longitudinal direction ", " transverse direction ", " on ", D score, " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end ", " interior ", orientation or the position relationship of the instruction such as " outward " are based on orientation shown in the drawings or position relationship, only the present invention for convenience of description and simplified characterization, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore limitation of the present invention can not be interpreted as.Non-separately have clear and definite regulation and restriction, and term " installation ", " being connected ", " connection " should be interpreted broadly, and such as, can be fixedly connected with, also can be removably connect, or connect integratedly; Can be mechanical connection, also can be electrical connection; Can be directly be connected, also indirectly can be connected by intermediary, can be the connection of two element internals.For the ordinary skill in the art, concrete condition above-mentioned term concrete meaning in the present invention can be understood.In addition, in describing the invention, except as otherwise noted, the implication of " multiple " is two or more.
As in Figure 2-4, the low heat value of gas turbine fuel gas combustion chamber of the present embodiment comprises: machine 1 casket, the end cap 2 being located at casing 1 front end, the head fuel nozzle 3 be located on end cap 2, be located at casing 1 inside water conservancy diversion lining 5, be located in water conservancy diversion lining 5 and the burner inner liner 4 that is connected with head fuel nozzle 3 of front end and the changeover portion 6 that is connected with the rear end of burner inner liner 4.
Burner inner liner 4 is provided with the primary holes 42 that many rows distribute vertically, often row can comprise multiple primary holes 42 be uniformly distributed circumferentially, burner inner liner 4 is provided with low calorie fuels nozzle 41 between each row's primary holes 42, preferably, burner inner liner 4 is circumferentially provided with equally distributed multiple low calorie fuels nozzle 41 at same axial location.Low calorie fuels nozzle 41 can be cartridge 44, and the inner (being namely in one end of burner inner liner 4 inside) of cartridge 44 is provided with fuel orifice 45, and the axis of fuel orifice 45 is perpendicular to the sidewall of burner inner liner 4.The fuel jet speed of low calorie fuels nozzle 41 is 100m/s ~ 150m/s.Head fuel nozzle 3 introduces exotic fuels gas (as natural gas) and partial air, sets up traditional swirl flame at burner inner liner 4 head, and low calorie fuels nozzle 41 introduces height jet low calorie fuels in downstream.Height jet low calorie fuels is introduced in downstream by low calorie fuels nozzle 41, then in burner inner liner 4 center, burning forms distributed flame to the first blending of fuel, pollutant is low, and flameholding, not easily there is combustion oscillation, simultaneously because low calorie fuels gas is by Swirl flame ignition, without the need to having steady flame mechanism, therefore fuel tolerance is strong.
The outside of casing 1 is provided with low calorie fuels ring cavity 43, low calorie fuels ring cavity 43 is connected with the outer end being positioned at same multiple low calorie fuels nozzles 41 circumferentially respectively, for being multiple low calorie fuels 41 nozzle supply fuel, the uniformity of fuel jet can be ensured.Each low calorie fuels ring cavity 43 can arrange fuel manifold 46, and fuel manifold 46 is for introducing low calorie fuels gas to low calorie fuels ring cavity 43.
Low calorie fuels nozzle 41 can be 1 ~ 4 row, often arrange low calorie fuels nozzle 41 to stagger the axial location of primary holes 42, be arranged between primary holes 42 axial location, in like manner, the quantity of low calorie fuels ring cavity 43 should be corresponding with the row of low calorie fuels nozzle 41.Like this, before low calorie fuels jet enters into high temperature reaction zone, with the abundant blending of jet air in primary holes 42.After low calorie fuels enters into high temperature reaction zone, owing to possessing higher effluxvelocity, and can not react at once, but after mixing with high-temperature flue gas, react after self-ignition time delay, now combustion chamber there is no clear and definite Flame of Natural Gas and low calorie fuels gas flame face is distinguished, but becomes as a whole, can reduce pollutant emission.
The fuel entered from head fuel nozzle 3 is natural gas, and the load of the maximum stream flow band of natural gas meets 5% ~ 10% of gas turbine base load, and the air capacity entered from head fuel nozzle 3 accounts for 7% ~ 15% of combustion air amount.The fuel flow channel of head fuel nozzle 3 and the eddy flow angular region of air flow channel are 10 ° ~ 25 °.Eddy flow angle is less, and while maintenance head swirl flame, the length of flame is longer, and the low calorie fuels air lift that can be downstream, for high temperature dot burning things which may cause a fire disaster, has comparatively uniform heat release result simultaneously.
During removal of load, direct blocking low calorie fuels gas supply, adjustment center gas discharge, when regulating load, carries out classification to low calorie fuels by regulating the fuel supply of low calorie fuels ring cavity 43 (fuel manifold 46) thus meets different load demand.
A traditional natural gas swirl flame is set up at burner inner liner head in low heat value of gas turbine fuel gas combustion chamber of the present invention, in downstream, low calorie fuels gas is introduced at a high speed at axially different position in combustion chamber, enter Swirl flame combustion, the longer weak swirl flame in center is used for lighting and maintains low calorie fuels gas, therefore low calorie fuels gas itself does not need self steady flame mechanism, poor blowoff limit can be widened, fuel characteristic also becomes insensitive, therefore, same chamber structure can be scalable low calorie fuels, without the need to carrying out special design for the Wobbe index of often kind of fuel or hydrogen content, this burning concept can be applicable to the requirement of multiple different range Wobbe index, the low calorie fuels gas of hydrogen content, simultaneously, this chamber structure also can complete sufficient blending before combustion, form distributed flame, thus burner inner liner internal flame Thermal release is even, reach lower pollutant emission level, and there is lower thermal acoustic oscillation risk, present invention also offers the scheme of removal of load and Load Regulation, Adjusted Option is simple, also the effect of low stain thing discharge is more easily realized.
Embodiments of the invention provide in order to example with for the purpose of describing, and are not exhaustively or limit the invention to disclosed form.Many modifications and variations are apparent for the ordinary skill in the art.Selecting and describing embodiment is in order to principle of the present invention and practical application are better described, and enables those of ordinary skill in the art understand the present invention thus design the various embodiments with various amendment being suitable for special-purpose.
Claims (10)
1. a low heat value of gas turbine fuel gas combustion chamber, it is characterized in that, comprise casing, be located at the end cap of described casing front end, the head fuel nozzle be located on described end cap, be located at described casing inside water conservancy diversion lining, be located in described water conservancy diversion lining and the burner inner liner that is connected with described head fuel nozzle of front end and the changeover portion that is connected with the rear end of described burner inner liner; Described burner inner liner is provided with the primary holes that many rows distribute vertically, and described burner inner liner is provided with low calorie fuels nozzle between each row's primary holes.
2. low heat value of gas turbine fuel gas combustion chamber according to claim 1, is characterized in that, described burner inner liner is circumferentially provided with equally distributed multiple low calorie fuels nozzle at same axial location.
3. low heat value of gas turbine fuel gas combustion chamber according to claim 2, it is characterized in that, the outside of described casing is provided with low calorie fuels ring cavity, described low calorie fuels ring cavity is connected with the outer end being positioned at same multiple low calorie fuels nozzles circumferentially respectively, for being multiple low calorie fuels nozzle supply fuel.
4. low heat value of gas turbine fuel gas combustion chamber according to claim 3, is characterized in that, described low calorie fuels nozzle is 1 ~ 4 row, and the quantity of described low calorie fuels ring cavity is corresponding with the row of described low calorie fuels nozzle.
5. low heat value of gas turbine fuel gas combustion chamber according to claim 3, it is characterized in that, described low calorie fuels nozzle is cartridge, and the inner of described cartridge is provided with fuel orifice, and the axis of described fuel orifice is perpendicular to the sidewall of described burner inner liner.
6. low heat value of gas turbine fuel gas combustion chamber according to claim 5, is characterized in that, the fuel jet speed of described low calorie fuels nozzle is 100m/s ~ 150m/s.
7. low heat value of gas turbine fuel gas combustion chamber according to claim 1, it is characterized in that, the fuel entered from described head fuel nozzle is natural gas, the load of the maximum stream flow band of natural gas meets 5% ~ 10% of gas turbine base load, and the air capacity entered from described head fuel nozzle accounts for 7% ~ 15% of combustion air amount.
8. low heat value of gas turbine fuel gas combustion chamber according to claim 7, is characterized in that, the fuel flow channel of described head fuel nozzle and the eddy flow angular region of air flow channel are 10 ° ~ 25 °.
9. low heat value of gas turbine fuel gas combustion chamber according to claim 3, it is characterized in that, during removal of load, direct blocking low calorie fuels gas supply, adjustment center gas discharge, when regulating load, by regulating the fuel supply of low calorie fuels ring cavity classification carried out to low calorie fuels thus meet different load demand.
10. low heat value of gas turbine fuel gas combustion chamber according to claim 1, is characterized in that, often arranges primary holes and is uniformly distributed circumferentially.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510035910.8A CN104595927B (en) | 2015-01-23 | 2015-01-23 | Low heat value of gas turbine fuel combustion chamber |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510035910.8A CN104595927B (en) | 2015-01-23 | 2015-01-23 | Low heat value of gas turbine fuel combustion chamber |
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| CN104595927A true CN104595927A (en) | 2015-05-06 |
| CN104595927B CN104595927B (en) | 2019-10-01 |
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| CN201510035910.8A Active CN104595927B (en) | 2015-01-23 | 2015-01-23 | Low heat value of gas turbine fuel combustion chamber |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108458366A (en) * | 2018-01-23 | 2018-08-28 | 中科合肥微小型燃气轮机研究院有限责任公司 | A kind of bush assembly of adjustable combustion area air mass flow |
| CN111594874A (en) * | 2020-05-29 | 2020-08-28 | 杭州汽轮动力集团有限公司 | Low-emission combustion chamber capable of adjusting flame temperature |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030150216A1 (en) * | 2001-07-03 | 2003-08-14 | O'beck John Timothy | Gas turbine |
| CN101373075A (en) * | 2007-08-21 | 2009-02-25 | 通用电气公司 | Turbine fuel delivery apparatus and system |
| CN101713546A (en) * | 2008-10-08 | 2010-05-26 | 中国航空工业第一集团公司沈阳发动机设计研究所 | Low-pollution combustor for various fuels |
| CN204593456U (en) * | 2015-01-23 | 2015-08-26 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Low heat value of gas turbine fuel gas combustion chamber |
-
2015
- 2015-01-23 CN CN201510035910.8A patent/CN104595927B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030150216A1 (en) * | 2001-07-03 | 2003-08-14 | O'beck John Timothy | Gas turbine |
| CN101373075A (en) * | 2007-08-21 | 2009-02-25 | 通用电气公司 | Turbine fuel delivery apparatus and system |
| CN101713546A (en) * | 2008-10-08 | 2010-05-26 | 中国航空工业第一集团公司沈阳发动机设计研究所 | Low-pollution combustor for various fuels |
| CN204593456U (en) * | 2015-01-23 | 2015-08-26 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Low heat value of gas turbine fuel gas combustion chamber |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108458366A (en) * | 2018-01-23 | 2018-08-28 | 中科合肥微小型燃气轮机研究院有限责任公司 | A kind of bush assembly of adjustable combustion area air mass flow |
| CN108458366B (en) * | 2018-01-23 | 2020-06-19 | 中科合肥微小型燃气轮机研究院有限责任公司 | Bush subassembly of adjustable combustion zone air mass flow |
| CN111594874A (en) * | 2020-05-29 | 2020-08-28 | 杭州汽轮动力集团有限公司 | Low-emission combustion chamber capable of adjusting flame temperature |
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| CN104595927B (en) | 2019-10-01 |
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