CN104534514B - A kind of gas-turbine combustion chamber blade bleed swirl nozzle - Google Patents
A kind of gas-turbine combustion chamber blade bleed swirl nozzle Download PDFInfo
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- CN104534514B CN104534514B CN201410699685.3A CN201410699685A CN104534514B CN 104534514 B CN104534514 B CN 104534514B CN 201410699685 A CN201410699685 A CN 201410699685A CN 104534514 B CN104534514 B CN 104534514B
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- housing
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Abstract
The present invention relates to gas turbine technology field, disclosing a kind of gas-turbine combustion chamber blade bleed swirl nozzle includes housing, and one end is arranged at the conical inner body in housing, multiple first swirl vanes and second swirl vane circumferentially disposed along conical inner body lateral wall；The peripheral air passage of annular is formed between the conical inner body and housing, is provided with the conical inner body on fuel channel and air duct, first swirl vane and the fuel passage, first swirl vane and is provided with multiple fuel orifices；Second swirl vane and the first swirl vane are correspondingly arranged, housing through-hole is provided with the housing, the housing through-hole is connected by second swirl vane with the air duct, and the one end being located on the conical inner body in the housing is provided with airport.The gas-turbine combustion chamber blade bleed swirl nozzle that the present invention is provided has mixing effect good, the advantage of Reasonable Combustion.
Description
Technical field
Sprayed the present invention relates to gas turbine technology field, more particularly to a kind of gas-turbine combustion chamber blade bleed eddy flow
Mouth, particularly a kind of more rationally gas-turbine combustion chamber blade bleed of effective tissue burning and control pollutant emission
Swirl nozzle.
Background technology
In the current energy resource structure of China, most shares are occupied using the thermal power generation of traditional coal combustion technology.
But to there is generating efficiency low for this traditional generation technology, pollutant emission is high, especially NOx emission, expends freshwater resources
Many the shortcomings of.Gas turbine power generation technology by fuel of natural gas can generate electricity as one of clean energy technology meeting
While burden requirement, the discharge of pollutant is effectively reduced, the design of gas-turbine combustion chamber nozzle is for tissue among these
Burning, reduction pollutant emission are particularly important.
In gas-turbine combustion chamber, fuel gas and air realize premixing and the change of velocity profile by nozzle, in nozzle
Outlet reaches rational VELOCITY DISTRIBUTION, and matches rational fuel-air mixture example, organizes to burn into combustion chamber, forms steady
Fixed flow field and combustion field.Currently, to the design form of gas-turbine combustion chamber nozzle, such as patent CN100567823C is adopted
With the notched air swirling vanes in bottom, the speed of air duct inner circumferential side, matching nozzle exit velocity type and fuel are improved
Air mixture ratio.
But, because air swirling vanes bottom has breach, the flow-deviation angle degree of passage inner circumferential side is small, swirl strength
It is weak, cause the mixing effect of this side fuel and air to be deteriorated；Fuel gas is in the STH spray of hollow blade two, fuel gas simultaneously
Blending distance with air is shorter, and adds the difficulty of blade processing, influences the generation of the tissue and pollutant of burning.Cause
This, it is still desirable to more rationally effective gas-turbine combustion chamber form of nozzle comes tissue burning and control pollutant emission.
In view of the defect of above-mentioned prior art, it is desirable to provide a kind of more rationally effective tissue burns and control pollutant
The gas-turbine combustion chamber blade bleed swirl nozzle of discharge.
The content of the invention
(1) technical problem to be solved
The technical problem to be solved in the present invention is that existing air swirling vanes bottom has breach, the gas of passage inner circumferential side
Stream deflection angle is small, and swirl strength is weak, causes the mixing effect of this side fuel and air to be deteriorated；Fuel gas is in hollow leaf simultaneously
The STH spray of piece two, the blending distance of fuel gas and air is shorter, and adds the difficulty of blade processing, influences the group of burning
Knit the generation with pollutant.Therefore, there is still a need for more rationally effective gas-turbine combustion chamber form of nozzle carrys out tissue burning
The problem of with control pollutant emission.
(2) technical scheme
In order to solve the above-mentioned technical problem, the invention provides a kind of gas-turbine combustion chamber blade bleed swirl nozzle.
The gas-turbine combustion chamber blade bleed swirl nozzle includes：Housing, one end is arranged at the conical inner body in housing, multiple in
Heart cone lateral wall circumferentially disposed the first swirl vane and the second swirl vane；It is formed between the conical inner body and housing
The peripheral air passage of annular, is provided with fuel channel and air duct in the conical inner body, first swirl vane with
Multiple fuel orifices are provided with the fuel passage, first swirl vane；Second swirl vane and
One swirl vane is correspondingly arranged, and housing through-hole is provided with the housing, and the housing through-hole passes through second swirl vane
Connected with the air duct, the one end being located on the conical inner body in the housing is provided with airport.
Wherein, one end that the conical inner body is arranged in the housing is conical end, and the airport is arranged at described
In conical end, and setting is at an angle of with the axial direction of the conical inner body.
Wherein, the angle of the airport and the axis of the conical inner body is 0-45 °.
Wherein, the aperture of the airport is 0.5-2mm.
Wherein, contraction section is provided with the housing, the conical end of the conical inner body is located in the contraction section.
Wherein, the number of first swirl vane is 4-6, and the number of second swirl vane is 4-6.
Wherein, the 2-5 spray-holes are provided with first swirl vane.
Wherein, the aperture of the fuel orifice is 0.1-0.5mm.
(3) beneficial effect
The above-mentioned technical proposal of the present invention has the following advantages that：The gas-turbine combustion chamber blade bleed rotation that the present invention is provided
It is formed between conical inner body and housing in flow nozzle in the peripheral air passage of annular, conical inner body and is provided with fuel channel
And air duct, the first swirl vane and fuel passage, multiple fuel orifices are provided with the first swirl vane；Second
Swirl vane and the first swirl vane are correspondingly arranged, and housing through-hole is provided with housing, and housing through-hole passes through the second swirl vane
Connected with air duct, the one end being located on conical inner body in housing is provided with airport.The gas turbine that the present invention is provided
Connected in the blade bleed swirl nozzle of combustion chamber using two swirl vanes with two passages, realize fuel supply and center bleed
Dual-use function, the advantage of Reasonable Combustion good with mixing effect.
Brief description of the drawings
Fig. 1 is the structural representation of gas-turbine combustion chamber blade bleed swirl nozzle of the embodiment of the present invention；
Fig. 2 is the schematic perspective view of gas-turbine combustion chamber blade bleed swirl nozzle of the embodiment of the present invention.
In figure：1：Conical inner body；2：Peripheral air passage；3：Fuel channel；4：Air duct；5：First swirl vane；
6：Fuel orifice；7：Second swirl vane；8：Housing；9：Airport；10：Contraction section.
Embodiment
In the description of the invention, unless otherwise indicated, " multiple " are meant that two or more；Term " on ",
" under ", "left", "right", " interior ", the orientation of the instruction such as " outer " or position relationship be based on orientation shown in the drawings or position relationship,
The description present invention and simplified description are for only for ease of, rather than indicates or imply that the machine or element of meaning must be with specific
Orientation, with specific azimuth configuration and operation, therefore be not considered as limiting the invention.
In the description of the invention, it is necessary to illustrate, unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " should be interpreted broadly, for example, it may be being fixedly connected or being detachably connected, or be integrally connected；Can
To be mechanical connection or electrical connection；Can be joined directly together, can also be indirectly connected to by intermediary.For this
For the those of ordinary skill in field, the concrete meaning of above-mentioned term in the present invention can be understood with concrete condition.
The embodiment to the present invention is described in further detail with reference to the accompanying drawings and examples.Following examples
For illustrating the present invention, but it is not limited to the scope of the present invention.
As depicted in figs. 1 and 2, gas-turbine combustion chamber blade bleed swirl nozzle provided in an embodiment of the present invention includes：
Housing 8, one end is arranged at the conical inner body 1 in housing 8, multiple along the circumferentially disposed in the outside of conical inner body 1 of conical inner body 1
The first swirl vane 5 and the second swirl vane 7 on wall；The number of first swirl vane 5 and the second swirl vane 7 is 4-6
It is individual.The peripheral air passage 2 of annular is formed between conical inner body 1 and housing 8, be provided with conical inner body 1 fuel channel 3 and
Be provided with air duct 4, conical inner body 1 in cavity, conical inner body 1 and be provided with partition, by cavity be divided into fuel channel 3 and
Air duct 4.First swirl vane 5 is connected with fuel channel 3, and multiple fuel orifices 6 are provided with the first swirl vane 5,
The aperture of fuel orifice 6 is 0.1-0.5mm.2-5 spray-hole 6 is provided with the present embodiment on first swirl vane 5.Second
Swirl vane 7 is correspondingly arranged with the first swirl vane 5, i.e. the second swirl vane 7 and the first swirl vane 5 are oppositely arranged, and wrong
Row arrangement.Housing through-hole is provided with housing 8, housing through-hole is connected with air duct 4 by the second swirl vane 7, is arranged at
Airport 9 is provided with one end of conical inner body 1 in housing 8.
The present invention provides a kind of gas-turbine combustion chamber blade bleed swirl nozzle, real by two hollow swirl vanes
Existing fuel injection, the blending of fuel gas air, the purpose from the outside of housing 8 introducing air.Realize fuel supply and center bleed
Dual-use function, while nozzle difficulty of processing is not increased, solve nozzle center body wall and downstream have low regime
Problem, Reasonable adjustment flow field velocity is distributed the technology difficulty for reducing center bleed, and can guarantee that good mixed effect and stream
Field distribution.Air is blown clearly the boundary-layer of conical inner body 1, reduces the low regime in the downstream of conical inner body 1, it is ensured that burning
Reliability.It can ensure the air-flow axial velocity of air duct inner circumferential side by adjusting air mass flow size and airflow direction, from
And ensure that nozzle exit velocity is reasonably distributed, fuel-air blends uniform and good Exit temperature distribution.
In gas-turbine combustion chamber blade bleed swirl nozzle provided in an embodiment of the present invention, conical inner body 1 is arranged at shell
One end in body 8 is conical end, and airport 9 is arranged in conical end, and is at an angle of setting with the axial direction of conical inner body 1.Air
The angle of the axis of hole 9 and conical inner body 1 is 0-45 °, when for 0 ° when airport 9 be located at the top of conical inner body 1.Airport 9
Aperture be 0.5-2mm, in the present embodiment the axial direction of airport 9 and conical inner body 1 be at an angle of setting can be preferably by air
The inner circumferential of air duct 2 is introduced, prevents the downstream of conical inner body 1 from forming low regime, strengthens inner circumferential side air axial velocity.Adjustment is empty
The exit angle of stomata 9 can adjust mixing effect of the fuel in inner circumferential side, be distributed beneficial to rational fuel is formed.
In order to ensure that the fuel of housing 10 fully burns, contraction section 10, conical inner body are provided with the present embodiment on housing 8
1 conical end is located in contraction section 10.Volume is diminished so that fuel and air are more fully mixed.
When gas-turbine combustion chamber blade bleed swirl nozzle of the present invention is used：Gas fuel enters from fuel channel 3
Nozzle, the fuel gas playpipe entered by the wall perforate of conical inner body 1 in the first swirl vane 5, the fuel injection from both sides
Hole 6 sprays.Air point two-stage enters nozzle, most of to be directly entered by peripheral air passage 2, before the first swirl vane 5
Hold the fuel gas blending sprayed with fuel orifice 6.Gaseous mixture is after the generation deflection of the first swirl vane 5 again through the second eddy flow leaf
Piece 7 is reversely rotated and blended, and is accelerated through nozzle contraction 10 gaseous mixtures of section.Another fraction air passes through the perforate of housing 8, warp
The hollow pipeline air inlet passage 4 of second swirl vane 7, sprays from the airport 9 in conical end, with main flow gaseous mixture
Blending, to jet expansion.The axial velocity in the surface of conical inner body 1 and tail area is improved, the nozzle exit velocity point of matching is formed
Cloth and fuel-air mixing effect, it is ensured that the stability of burning and good Exit temperature distribution.
In summary, the present invention has advantages below：The gas-turbine combustion chamber blade bleed eddy flow spray that the present invention is provided
It is formed between conical inner body and housing in mouth in the peripheral air passage of annular, conical inner body and is provided with fuel channel and sky
Multiple fuel orifices are provided with gas passage, the first swirl vane and fuel passage, the first swirl vane；Second eddy flow
Blade and the first swirl vane are correspondingly arranged, and housing through-hole is provided with housing, and housing through-hole passes through the second swirl vane and sky
Gas passage is connected, and the one end being located on conical inner body in housing is provided with airport.The gas turbine combustion that the present invention is provided
Connected in the blade bleed swirl nozzle of room using two swirl vanes with two passages, realize pair of fuel supply and center bleed
Weight function, the advantage of Reasonable Combustion good with mixing effect.
Further, the axial direction of airport and conical inner body, which is at an angle of setting, can preferably introduce air into air duct
Inner circumferential side, prevents the downstream of conical inner body from forming low regime, strengthens inner circumferential side air axial velocity.
The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations；Although with reference to the foregoing embodiments
The present invention is described in detail, it will be understood by those within the art that：It still can be to foregoing each implementation
Technical scheme described in example is modified, or carries out equivalent substitution to which part technical characteristic；And these modification or
Replace, the essence of appropriate technical solution is departed from the spirit and scope of various embodiments of the present invention technical scheme.
Claims (8)
1. a kind of gas-turbine combustion chamber blade bleed swirl nozzle, it is characterised in that including：Housing (8), one end is arranged at shell
Conical inner body (1) in body (8), multiple first swirl vanes (5) circumferentially disposed along conical inner body (1) lateral wall and the second rotation
Flow blade (7)；The peripheral air passage (2) of annular, the center cone are formed between the conical inner body (1) and housing (8)
Fuel channel (3) and air duct (4), first swirl vane (5) and the fuel channel are respectively arranged with body (1)
(3) connect, multiple fuel orifices (6) are provided with first swirl vane (5)；Second swirl vane (7) and
One swirl vane (5) is correspondingly arranged, and housing through-hole is provided with the housing (8), and the housing through-hole is revolved by described second
Stream blade (7) is connected with the air duct (4), and the one end being located on the conical inner body (1) in the housing (8) is set
There is airport (9).
2. gas-turbine combustion chamber blade bleed swirl nozzle according to claim 1, it is characterised in that：The center cone
It is conical end that body (1), which is arranged at one end in the housing (8), and the airport (9) is arranged in the conical end, and with institute
State the angled setting in axial direction of conical inner body (1).
3. gas-turbine combustion chamber blade bleed swirl nozzle according to claim 2, it is characterised in that：The airport
(9) angle with the axis of the conical inner body (1) is 0-45 °.
4. gas-turbine combustion chamber blade bleed swirl nozzle according to claim 2, it is characterised in that：The airport
(9) aperture is 0.5-2mm.
5. gas-turbine combustion chamber blade bleed swirl nozzle according to claim 2, it is characterised in that：The housing
(8) contraction section (10) is provided with, the conical end is located in the contraction section (10).
6. gas-turbine combustion chamber blade bleed swirl nozzle according to claim 1, it is characterised in that：First rotation
It is 4-6 to flow the number of blade (5), and the number of second swirl vane (7) is 4-6.
7. gas-turbine combustion chamber blade bleed swirl nozzle according to claim 1, it is characterised in that：First rotation
The 2-5 spray-holes (6) are provided with stream blade (5).
8. gas-turbine combustion chamber blade bleed swirl nozzle according to claim 1, it is characterised in that：The fuel spray
The aperture of perforation (6) is 0.1-0.5mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410699685.3A CN104534514B (en) | 2014-11-27 | 2014-11-27 | A kind of gas-turbine combustion chamber blade bleed swirl nozzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410699685.3A CN104534514B (en) | 2014-11-27 | 2014-11-27 | A kind of gas-turbine combustion chamber blade bleed swirl nozzle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104534514A CN104534514A (en) | 2015-04-22 |
| CN104534514B true CN104534514B (en) | 2017-09-15 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410699685.3A Active CN104534514B (en) | 2014-11-27 | 2014-11-27 | A kind of gas-turbine combustion chamber blade bleed swirl nozzle |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1491383A (en) * | 1974-10-07 | 1977-11-09 | Parker Hannifin Corp | Air-atomising fuel nozzle |
| US6068467A (en) * | 1998-02-09 | 2000-05-30 | Mitsubishi Heavy Industries, Ltd. | Combustor |
| CN101055093A (en) * | 2006-04-14 | 2007-10-17 | 三菱重工业株式会社 | Premixing combustion mouth for gas turbine |
| CN101313178A (en) * | 2005-11-26 | 2008-11-26 | 西门子公司 | A combustion apparatus |
| CN102695919A (en) * | 2009-11-09 | 2012-09-26 | 三菱重工业株式会社 | Combustion burner for gas turbine |
| CN204313314U (en) * | 2014-11-27 | 2015-05-06 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas-turbine combustion chamber blade bleed swirl nozzle |
-
2014
- 2014-11-27 CN CN201410699685.3A patent/CN104534514B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1491383A (en) * | 1974-10-07 | 1977-11-09 | Parker Hannifin Corp | Air-atomising fuel nozzle |
| US6068467A (en) * | 1998-02-09 | 2000-05-30 | Mitsubishi Heavy Industries, Ltd. | Combustor |
| CN101313178A (en) * | 2005-11-26 | 2008-11-26 | 西门子公司 | A combustion apparatus |
| CN101055093A (en) * | 2006-04-14 | 2007-10-17 | 三菱重工业株式会社 | Premixing combustion mouth for gas turbine |
| CN102695919A (en) * | 2009-11-09 | 2012-09-26 | 三菱重工业株式会社 | Combustion burner for gas turbine |
| CN204313314U (en) * | 2014-11-27 | 2015-05-06 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas-turbine combustion chamber blade bleed swirl nozzle |
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| Publication number | Publication date |
|---|---|
| CN104534514A (en) | 2015-04-22 |
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Effective date of registration: 20190820 Granted publication date: 20170915 |
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Effective date of registration: 20200121 Address after: 102209 Beijing Changping District in the future of the national electric investment group Park in the future science city south of Beijing Patentee after: China United heavy-duty gas turbine technology Co., Ltd. Address before: 100084, Beijing, Haidian District science and Technology Park, Tsinghua Science and technology building, block C, 10 Patentee before: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. |