CN204438187U - A kind of anti-backfire type nozzle - Google Patents
A kind of anti-backfire type nozzle Download PDFInfo
- Publication number
- CN204438187U CN204438187U CN201420872728.9U CN201420872728U CN204438187U CN 204438187 U CN204438187 U CN 204438187U CN 201420872728 U CN201420872728 U CN 201420872728U CN 204438187 U CN204438187 U CN 204438187U
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- China
- Prior art keywords
- trailing edge
- stage casing
- spray device
- seam
- centerbody
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Abstract
The utility model belongs to gas turbine field, disclose a kind of anti-backfire type nozzle, comprise centerbody, annular outer wall and propellant spray device, centerbody is in the center of annular outer wall, at least one propellant spray device is connected in the annular region between centerbody and annular outer wall, be equipped with inner chamber, fuel orifice, at least one radial fuel path and at least one radial air path in each propellant spray device, radial fuel path is connected with fuel orifice; The axis of described propellant spray device centrally body is divided into leading edge, stage casing and trailing edge, and trailing edge is provided with trailing edge passage; Axial air path, radial air path, inner chamber and trailing edge channel sequence are communicated with.The utility model introduces air by centerbody, and in trailing edge ejection, leading edge burner oil, air effectively can blow away the tail attachment in trailing edge downstream from trailing edge ejection, reduces the possibility that tempering occurs at trailing edge place, and then improves the anti-backfire performance of whole nozzle.
Description
Technical field
The utility model relates to gas turbine technology field, particularly a kind of anti-backfire type nozzle.
Background technology
Modern gas turbines combustion chamber burner comprises the assembly of one or more burner, and burner has the path be limited to wherein separately, and the flammable mixture of fuel and air flows by the burner inner liner of this path towards downstream.Flammable mixture, arriving the rear end of burner, is lighted and is burnt.Usual this burning appears in the recirculating zone of combustion zone, makes gas flow temperature obtain higher lifting, produces heat energy.
But sometimes can there is tempering near nozzle, near the burner that flammable mixture is gathered in nozzle or burner combustion, especially the propellant spray device burner oil of nozzle can be assembled fuel at its wall or form flammable tail at its trailing edge, facilitates the generation of tempering.This tempering phenomenon is once occur gas turbine can be made to shut down, seriously can cause repairing or the replacing of burner and even fuel nozzle.
Utility model content
(1) technical problem that will solve
The technical problems to be solved in the utility model is: during for solving existing gas turbine combustion, and nozzle place easily fuel concentration occurs, and causes tempering phenomenon occurs, and causes burner or the impaired problem of fuel injection device.
(2) technical scheme
In order to solve the problems of the technologies described above, the utility model provides a kind of anti-backfire type nozzle, comprise centerbody, annular outer wall and propellant spray device, centerbody is in the center of annular outer wall, at least one propellant spray device is connected in the annular region between centerbody and annular outer wall, inner chamber, fuel orifice, at least one radial fuel path and at least one radial air path is equipped with in each propellant spray device, one end of fuel orifice and radial fuel communication, the other end is in communication with the outside; The axis of described propellant spray device centrally body is divided into leading edge, stage casing and trailing edge, and trailing edge is provided with trailing edge passage; Be provided with at least one axial air path in centerbody, axial air path, radial air path, inner chamber and trailing edge channel sequence are communicated with.
Wherein, described stage casing arranges at least one row and stitches the stage casing passage formed, stage casing passage and inner space by middle sector hole or stage casing.
Wherein, described trailing edge passage is stitched by least one last person's marginal pore or trailing edge and forms, the cross section in described trailing edge seam or trailing edge hole is flaring type, and opening increases gradually from inside to outside, and two sides of the cross section in trailing edge seam or trailing edge hole and the angle of trailing edge axis are between 15 ° ~ 75 °.
Wherein, described trailing edge passage is stitched by least one last person's marginal pore or trailing edge and forms, the cross section in described trailing edge seam or trailing edge hole is flaring type, and opening increases gradually from inside to outside, and two sides of the cross section in trailing edge seam or trailing edge hole and the angle of trailing edge axis are between 15 ° ~ 45 °.
Wherein, described middle sector hole or stage casing seam are flaring type, and the outlet of middle sector hole or stage casing seam is tilted to trailing edge, and the angle of described middle sector hole or seam axis, stage casing and the local wall of propellant spray device is between 15 ° ~ 35 °.
Wherein, the diameter of described middle sector hole is between 1mm ~ 3mm, and the diameter in trailing edge hole is between 1mm ~ 5mm, and the axial length of stage casing seam or trailing edge seam is between 1mm ~ 2mm.Wherein, the total radical length often arranging stage casing passage accounts for 30% ~ 80% of stage casing radical length residing for it.
Wherein, total radical length of every last person's edge passage accounts for 30% ~ 80% of trailing edge radical length residing for it.
Wherein, in described centerbody, be provided with the axial fuel path and fuel inlet that are interconnected, axial fuel path and described radial fuel communication.
(3) beneficial effect
Technique scheme tool has the following advantages: the utility model anti-backfire type nozzle, air is introduced by centerbody, and spray in trailing edge, leading edge burner oil, air effectively can blow away the tail attachment in trailing edge downstream from trailing edge ejection, reduce the possibility that tempering occurs at trailing edge place, and then improve the anti-backfire performance of whole nozzle.
Accompanying drawing explanation
Fig. 1 is the profile of anti-backfire type nozzle described in the utility model embodiment one;
Fig. 2 is the stereogram of propellant spray device described in the utility model embodiment one;
Fig. 3 is the profile of propellant spray device described in the utility model embodiment one;
Fig. 4 is the stereogram of propellant spray device described in the utility model embodiment two;
Fig. 5 is the profile of propellant spray device described in the utility model embodiment two.
Wherein, 11, centerbody; 110, fuel inlet; 111, axial fuel path; 112, axial air path; 12, annular outer wall; 13, propellant spray device; 131, radial fuel path; 132, radial air path; 2, leading edge; 3, stage casing; 30, middle sector hole; 4, trailing edge; 40, trailing edge hole; 41, trailing edge seam; 42, trailing edge axis; 8, fuel orifice.
Detailed description of the invention
Below in conjunction with drawings and Examples, detailed description of the invention of the present utility model is described in further detail.Following examples for illustration of the utility model, but are not used for limiting scope of the present utility model.
Embodiment one:
With reference to Fig. 1, shown in 2 and 3, a kind of anti-backfire type nozzle for gas-turbine combustion chamber of the utility model, it comprises centerbody 11, annular outer wall 12 and propellant spray device 13, centerbody 11 is in annular outer wall 12 center, propellant spray device 13 is arranged between centerbody 11 and annular outer wall 12, each propellant spray device 13 all centrally body 11 radial direction arrange; At least one axial air path 112 is provided with in centerbody 11, inner chamber, fuel orifice 8, at least one radial fuel path 131 and at least one radial air path 132 is provided with in propellant spray device 13, one end of fuel orifice 8 is communicated with radial fuel path 131, and the other end is in communication with the outside; The axial location of described propellant spray device 13 is broadly divided into leading edge 2, stage casing 3 and trailing edge 4, and trailing edge 4 arranges trailing edge hole 40 or trailing edge seam 41, forms trailing edge passage; Axial air path 112 is by radial air path 132 and inner space; Ei chamber is stitched 41 with trailing edge hole 40 or trailing edge and is connected; air enters from the axial air path 112 of centerbody 11; after the trailing edge passage ejection of propellant spray device 13; effectively can blow away the wake's flow field because flow around bluff bodies causes; prevent fuel from assembling at this place, the wall at available protecting trailing edge 4 place, plays anti-backfire effect.
The trailing edge passage of described propellant spray device 13 comprises at least one last person's edge seam 41 or trailing edge hole 40; the cross section in this trailing edge seam 41 or trailing edge hole 40 is flaring type; two sides of the cross section in trailing edge seam 41 or trailing edge hole 40 and the angle of trailing edge axis 42 are between 15 ° ~ 75 °; axially outwards open in trailing edge hole 40 or trailing edge seam 41 relative trailing edges 4; the air guiding it to spray is to extrinsic deflection; not only there is axial velocity and blow away tail; there is tangential velocity simultaneously; the wall of protection both sides, not by the impact of low speed flow, makes fuel cannot assemble at this place simultaneously.
Preferably; the trailing edge 4 of described propellant spray device 13 arranges at least one last person's edge seam 41 or trailing edge hole 40; the cross section in this trailing edge seam 41 or trailing edge hole 40 is flaring type; two sides of the cross section in trailing edge seam 41 or trailing edge hole 40 and the angle of trailing edge axis 42 are between 15 ° ~ 45 °; strengthen this place's tangential velocity, protect this place's two side walls.
Preferably, the diameter of described middle sector hole 30 is between 1mm ~ 3mm, the diameter in trailing edge hole 40 is between 1mm ~ 5mm, often row stage casing 3 seam and trailing edge seam 41 all can arrange many, stage casing 3 is stitched and trailing edge stitches the axial length of 41 between 1mm ~ 2mm, often arrange the total radical length stitched in stage casing 3 and account for 30% ~ 80% of stage casing 3 radical length residing for it, total radical length of every last person's edge seam 41 accounts for 30% ~ 80% of trailing edge 4 radical length residing for it, and the air ensuring enough flows passes through.
Preferably, described gas-turbine combustion chamber anti-backfire type nozzle comprises at least one fuel inlet 110 and axial fuel path 111, fuel inlet 110 is communicated with radial fuel path 131 by axial fuel pipe, and axial fuel pipe can be arranged on nozzle center or outside.
Embodiment two:
The present embodiment is substantially identical with embodiment one, institute's difference is, as shown in Figures 4 and 5, the stage casing 3 of the propellant spray device 13 of the present embodiment anti-backfire type nozzle also arranges sector hole 30 or stage casing 3 at least one row and stitches, form stage casing passage, stage casing passage and inner space.The air entered by the axial air path 112 of centerbody 11 is through radial air path 132, inner chamber; finally after the ejection of stage casing passage; wall boundary layer, stage casing 3 can be blown away; prevent fuel from assembling at stage casing 3 near wall; reduce the fuel quantity near wall; the wall at available protecting stage casing 3 place, plays anti-backfire effect.
The cross section that the middle sector hole 30 of described propellant spray device 13 or stage casing 3 are stitched is flaring nibs, seam or inclined hole, R-joining, the angle of axis and the local wall of propellant spray device 13 is stitched between 15 ° ~ 35 ° in described middle sector hole 30 or stage casing 3, and the outlet that middle sector hole 30 or stage casing 3 are stitched deflects to trailing edge 4 direction.Substantially along wall flowing after air-flow ejection, the contact of isolated fuel and wall, forms a protective layer.
Preferably, one end of trailing edge 4 arranges trailing edge passage, and the other end is set to thin-wall construction, and thin-wall construction place does not establish trailing edge passage.The air of stage casing passage ejection blows to trailing edge 4 along wall, and can directly be blown away by the burning gases at thin-wall construction place, the gas of thin-wall construction both sides cannot be assembled at trailing edge 4 place, tempering phenomenon can not occur; In addition, thin-wall construction heat radiation is very fast, and trailing edge 4 temperature can not be too high, is conducive to protection propellant spray device 13.
Preferably, the diameter of described middle sector hole 30 is between 1mm ~ 3mm, often arrange stage casing 3 seam and can arrange many, the axial length that stage casing 3 is stitched is between 1mm ~ 2mm, often arrange the total radical length stitched in stage casing 3 and account for 30% ~ 80% of stage casing 3 radical length residing for it, under the prerequisite meeting anti-backfire requirement, do not affect the connection of propellant spray device 13 and itself and equipment.
As can be seen from the above embodiments, the utility model is by introducing air at centerbody 11, spray in the stage casing 3 of propellant spray device 13 and trailing edge 4, increase the flowing velocity in wall boundary layer, stage casing 3, reduce boundary layer sphere of action, blow away the fuel of stage casing 3 near wall, increase trailing edge 4 air velocity simultaneously, after reducing flow around bluff bodies there is possibility in tail, whole propellant spray device 13 is made to be in nonflammable region, increase its anti-backfire characteristic, effectively ensure the life-span of these parts and even whole nozzle; In addition one end of trailing edge 4 is set to thin-wall construction, the fuel gas at thin-walled place can directly blow away by the air of stage casing passage ejection, prevents fuel gas from assembling at trailing edge 4 place, avoids tempering occurs; And the trailing edge 4 of thin-wall construction dispels the heat comparatively fast, guarantee that the temperature of trailing edge 4 can not be higher, protection trailing edge 4.
The above is only preferred embodiment of the present utility model; should be understood that; for those skilled in the art; under the prerequisite not departing from the utility model know-why; can also make some improvement and replacement, these improve and replace and also should be considered as protection domain of the present utility model.
Claims (9)
1. an anti-backfire type nozzle, comprise centerbody (11), annular outer wall and propellant spray device (13), centerbody (11) is in the center of annular outer wall (12), at least one propellant spray device (13) is connected in the annular region between centerbody (11) and annular outer wall (12), it is characterized in that, inner chamber is equipped with in each propellant spray device (13), fuel orifice (8), at least one radial fuel path (131), and at least one radial air path (132), one end of fuel orifice (8) is communicated with radial fuel path (131), the other end is in communication with the outside, the axis of described propellant spray device (13) centrally body (11) is divided into leading edge (2), stage casing (3) and trailing edge (4), and trailing edge (4) is provided with trailing edge passage, be provided with at least one axial air path (112) in centerbody (11), axial air path (112), radial air path (132), inner chamber and trailing edge channel sequence are communicated with.
2. anti-backfire type nozzle as claimed in claim 1, it is characterized in that, described stage casing (3) arrange at least one row and stitch the stage casing passage formed, stage casing passage and inner space by middle sector hole (30) or stage casing.
3. anti-backfire type nozzle as claimed in claim 1, it is characterized in that, described trailing edge passage stitches (41) by least one last person's marginal pore (40) or trailing edge and forms, the cross section of described trailing edge seam (41) or trailing edge hole (40) is flaring type, opening increases gradually from inside to outside, and two sides of the cross section of trailing edge seam (41) or trailing edge hole (40) and the angle of trailing edge axis (42) are between 15 ° ~ 75 °.
4. anti-backfire type nozzle as claimed in claim 1, it is characterized in that, described trailing edge passage stitches (41) by least one last person's marginal pore (40) or trailing edge and forms, the cross section of described trailing edge seam (41) or trailing edge hole (40) is flaring type, opening increases gradually from inside to outside, and two sides of the cross section of trailing edge seam (41) or trailing edge hole (40) and the angle of trailing edge axis (42) are between 15 ° ~ 45 °.
5. the anti-backfire type nozzle as described in Claims 2 or 3 or 4, it is characterized in that, described middle sector hole (30) or stage casing seam are flaring type, the outlet of middle sector hole (30) or stage casing seam is tilted to trailing edge (4), and the axis of described middle sector hole (30) or stage casing seam and the angle of propellant spray device (13) local wall are between 15 ° ~ 35 °.
6. the anti-backfire type nozzle as described in Claims 2 or 3 or 4, it is characterized in that, the diameter of described middle sector hole (30) is between 1mm ~ 3mm, the diameter in trailing edge hole (40) is between 1mm ~ 5mm, and the axial length of stage casing seam or trailing edge seam (41) is between 1mm ~ 2mm.
7. anti-backfire type nozzle as claimed in claim 2, is characterized in that, the total radical length often arranging stage casing passage accounts for 30% ~ 80% of stage casing residing for it (3) radical length.
8. anti-backfire type nozzle as claimed in claim 1, it is characterized in that, total radical length of every last person's edge passage accounts for 30% ~ 80% of trailing edge residing for it (4) radical length.
9. anti-backfire type nozzle as claimed in claim 1, it is characterized in that, be provided with the axial fuel path (111) and fuel inlet (110) that are interconnected in described centerbody (110), axial fuel path (111) is communicated with described radial fuel path (131).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420872728.9U CN204438187U (en) | 2014-12-31 | 2014-12-31 | A kind of anti-backfire type nozzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420872728.9U CN204438187U (en) | 2014-12-31 | 2014-12-31 | A kind of anti-backfire type nozzle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204438187U true CN204438187U (en) | 2015-07-01 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420872728.9U Withdrawn - After Issue CN204438187U (en) | 2014-12-31 | 2014-12-31 | A kind of anti-backfire type nozzle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204438187U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104566467A (en) * | 2014-12-31 | 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 | Anti-backfire nozzle |
-
2014
- 2014-12-31 CN CN201420872728.9U patent/CN204438187U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104566467A (en) * | 2014-12-31 | 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 | Anti-backfire nozzle |
| CN104566467B (en) * | 2014-12-31 | 2018-02-23 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of anti-backfire type nozzle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Anti-backfire nozzle Effective date of registration: 20161104 Granted publication date: 20150701 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
|
| PLDC | Enforcement, change and cancellation of contracts on pledge of patent right or utility model | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20150701 Effective date of abandoning: 20180223 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20150701 Effective date of abandoning: 20180223 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20191211 Granted publication date: 20150701 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |