CN211424473U - Nozzle, combustion chamber and gas turbine - Google Patents
Nozzle, combustion chamber and gas turbine Download PDFInfo
- Publication number
- CN211424473U CN211424473U CN201922500057.9U CN201922500057U CN211424473U CN 211424473 U CN211424473 U CN 211424473U CN 201922500057 U CN201922500057 U CN 201922500057U CN 211424473 U CN211424473 U CN 211424473U
- Authority
- CN
- China
- Prior art keywords
- nozzle
- fuel outlet
- flow
- guide body
- fuel
- 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.)
- Withdrawn - After Issue
Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 20
- 239000000446 fuel Substances 0.000 claims abstract description 60
- 238000002347 injection Methods 0.000 claims abstract description 23
- 239000007924 injection Substances 0.000 claims abstract description 23
- 239000004020 conductor Substances 0.000 claims abstract description 14
- 239000007789 gas Substances 0.000 description 23
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 5
- 238000000034 method Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 239000007921 spray Substances 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 229910002091 carbon monoxide Inorganic materials 0.000 description 1
- 239000003245 coal Substances 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
- 230000010349 pulsation Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000005496 tempering Methods 0.000 description 1
Images
Landscapes
- Fuel-Injection Apparatus (AREA)
Abstract
The utility model relates to a show technical field, disclose a nozzle, combustion chamber and gas turbine. Wherein, the nozzle includes: a housing provided with a fuel inlet and a fuel outlet; a flow conductor at least partially disposed within the fuel outlet and cooperating with the fuel outlet to form an injection opening; the flow guide body is movable in an axial direction of the fuel outlet, and a flow area of the injection opening has a change as a position of the flow guide body in the axial direction changes. In the nozzle, the guide body and the fuel outlet of the shell are matched to form an injection opening in a surrounding mode, and the guide body can move along the axial direction of the fuel outlet so as to change the flow cross-sectional area of the injection opening, namely, the flow area of the nozzle outlet can be changed by adjusting the axial position of the guide body, and further the jet speed of the nozzle is changed; in summary, the nozzle can change the speed of the outlet jet, so that the requirements of the gas turbine on different injection speeds of the fuel can be met.
Description
Technical Field
The utility model relates to a gas turbine technical field, in particular to nozzle, combustion chamber and gas turbine.
Background
With the increasing standards for pollution control, gas turbines are gaining more and more attention, and their combustion products mainly include NOx (nitrogen oxides), CO (carbon monoxide) and UHC (unburned hydrocarbons), which are emitted in much lower amounts than conventional coal and fuel combustion. Gas turbines can be classified according to their power range: micro gas turbines, small gas turbines, light gas turbines and heavy duty gas turbines.
Taking a micro gas turbine as an example, the core components of the micro gas turbine comprise a combustion chamber, a compressor and a turbine. The combustion chamber is a power source of the gas turbine, and the performance of the combustion chamber directly influences the overall performance of the whole combustion engine. The nozzle is a key part of the combustion chamber and plays an important role in tissue combustion and pollutant control.
The outlet speed of the nozzle has great influence on fuel combustion, the outlet speed is too high, the pressure loss is large, combustion pulsation is easy to generate, and instability is increased. The outlet speed is too low, so that tempering is easy to generate, carbon deposit on the surface of the nozzle is increased, and the service life of the nozzle is shortened. In the actual operation process of the gas turbine, different injection speeds are sometimes needed to meet the actual requirements, and the common method is to replace a new nozzle, so that the gas turbine needs to be configured with a larger number of nozzles (especially for test debugging) and is higher in cost.
SUMMERY OF THE UTILITY MODEL
The utility model discloses a nozzle, combustion chamber and gas turbine, the purpose provides a can change nozzle outlet jet velocity's nozzle to satisfy gas turbine to jet velocity's demand.
In order to achieve the above purpose, the utility model provides the following technical scheme:
a nozzle, comprising:
a housing provided with a fuel inlet and a fuel outlet;
a flow conductor at least partially disposed within the fuel outlet and cooperating with the fuel outlet to form an injection opening; the flow guide body is movable in an axial direction of the fuel outlet, and a flow area of the injection opening has a change as a position of the flow guide body in the axial direction changes.
The nozzle is internally provided with a flow guide body, the flow guide body and the fuel outlet of the shell are matched to form an injection opening in a surrounding mode, and the flow guide body can move along the axial direction of the fuel outlet so as to change the flow cross-sectional area of the injection opening, namely, the flow area of the nozzle outlet can be changed by adjusting the axial position (the position along the axial direction) of the flow guide body, and further the jet speed of the nozzle is changed; in summary, the nozzle can change the speed of the outlet jet, so that the requirements of the gas turbine on different injection speeds of the fuel can be met.
Optionally, a connecting rod extending along the axis direction of the fuel outlet is arranged in the casing, and the flow guide body is sleeved on the connecting rod and can move along the connecting rod.
Optionally, an external thread is arranged on the connecting rod; the flow guide body is provided with a threaded hole matched with the external thread, and the flow guide body is in threaded connection with the connecting rod.
Optionally, the inner wall surface of the fuel outlet comprises a conical surface.
Optionally, the flow guiding body comprises a conical part, and the end surface of the larger end of the conical part faces the outward side of the fuel outlet; the injection opening is formed between the outer side surface of the tapered portion and the inner wall surface of the fuel outlet.
Optionally, the flow guiding body further comprises a boss arranged on the end face of the larger end of the conical portion.
Optionally, an inner hexagonal groove is formed in the boss, and the inner hexagonal groove faces to the outward side of the fuel outlet.
Optionally, the outer side surface of the boss includes two planes parallel to each other.
A combustion chamber comprising a nozzle as claimed in any one of the preceding claims.
A gas turbine comprises the combustion chamber.
Drawings
Fig. 1 is a schematic cross-sectional view of a nozzle according to an embodiment of the present invention;
fig. 2 is a schematic cross-sectional structural view of a nozzle according to an embodiment of the present invention;
fig. 3 is a schematic cross-sectional view of a flow guiding body according to an embodiment of the present invention;
fig. 4 is a schematic bottom view of a baffle according to an embodiment of the present invention;
fig. 5 is a schematic diagram illustrating a structural comparison of a nozzle in different injection speed states according to an embodiment of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
In a first aspect, as shown in fig. 1 and 2, an embodiment of the present invention provides a nozzle, including:
a housing 1 provided with a fuel inlet and a fuel outlet;
a flow guide body 2 which is at least partially arranged in the fuel outlet and is matched with the fuel outlet to form an injection opening 3, wherein the flow guide body 2 can move along the axis o direction of the fuel outlet; the flow area of the spray opening 3 has a variation as the position of the flow conductor 2 in the direction of the axis o varies. The 'flow area' may also be referred to as 'flow cross-sectional area', in particular the cross-sectional area of the ejection opening 3 perpendicular to the ejection direction of the jet.
The nozzle is provided with a guide body 2, the guide body 2 and a fuel outlet of the shell 1 are matched to form an injection opening 3, and the guide body 2 can move along the axis o direction of the fuel outlet, so that the flow cross-sectional area of the injection opening 3 is changed, namely, the flow area of the nozzle outlet can be changed by adjusting the axial position (the position along the axis o direction) of the guide body 2, and further the jet speed of the nozzle is changed; in summary, the nozzle can change the speed of the outlet jet, so that the requirements of the gas turbine on different injection speeds of the fuel can be met.
In a specific embodiment, as shown in fig. 1 and fig. 2, a connecting rod 4 extending along an axis o direction of the fuel outlet is disposed in the housing 1, and the flow guiding body 2 is sleeved on the connecting rod 4 and can move along the connecting rod 4.
Illustratively, as shown in fig. 1 and 3, the connecting rod 4 is provided with an external thread 41; the guide body 2 is provided with a threaded hole 21 matched with the external thread 41, and the guide body 2 is in threaded connection with the connecting rod 4. Furthermore, by rotating the baffle body 2, the baffle body 2 can move along the connecting rod 4, thereby realizing the adjustment of the axial position of the baffle body 2.
Illustratively, as shown in fig. 1 and 2, the connecting rod 4 may be fixed to the housing 1 of the nozzle at one end and extend to a position near the fuel outlet and be provided with an external thread 41 at the other end. Specifically, a fuel channel 11 is arranged in the shell 1, a fuel inlet and a fuel outlet are respectively positioned at two ends of the channel 11, a vertical corner is arranged in the middle of the channel 11, and one end of the connecting rod 4 extends to the vertical corner and is fixedly connected with the inner wall of the channel 11.
For example, the flow guiding body 2 and the connecting rod 4 may be in interference fit or in clearance fit and fixed by a nut, and the fixing function may be achieved, and the specific manner is not discussed in detail here.
In a specific embodiment, as shown in fig. 1 and 2, the inner wall surface of the fuel outlet includes a tapered surface 110. When the flow conductor 2 moves along the central axis (i.e. the axis o) of the conical surface 110, i.e. when the axial position of the flow conductor 2 changes, the gap between the flow conductor 2 and the conical surface 110 also changes, which results in a change of the flow area of the annular ejection opening 3 and thus in a change of the nozzle jet velocity. Illustratively, the tapered surface is a conical surface.
In a specific embodiment, as shown in fig. 3, the flow conductor 2 may include a tapered portion 22; a 'tapered portion' means that the structural portion becomes progressively narrower from one end to the other end of the body; specifically, the shape of the end face of the tapered portion 22 and/or the cross section perpendicular to the extending direction is not limited, and may be circular, square, or polygonal; the outer side surface of the tapered portion 22 is not limited, and may be an arc surface or a stepped surface. For example, in the baffle of the embodiment of the present invention, the cross section of the tapered portion 22 is circular, and the outer side surface is a conical surface. For example, the outer side surface 220 of the cone 22 may match the fuel outlet cone surface 110.
Specifically, as shown in fig. 1, 2 and 3, the larger end face of the tapered portion 22 faces the outward side of the fuel outlet (i.e., the outward side of the housing 1), and the smaller end face faces the inward side of the fuel outlet (i.e., the inward side of the internal passage 11); an annular injection opening 3 is formed between the outer side surface 220 of the conical portion 22 and the conical surface 110 of the fuel outlet.
Specifically, an annular injection opening 3 is defined between the conical surface 110 of the fuel outlet and the outer side surface 220 of the conical portion 22, and as the axial position of the flow conductor 2 changes, a gap between the conical surface 110 of the fuel outlet and the outer side surface 220 of the conical portion 22 gradually changes, which causes a change in the flow area of the annular injection opening 3, and thus changes the nozzle jet velocity.
Further, as shown in fig. 1, 2 and 3, the flow guiding body 2 may further include a cylindrical portion 23, and the cylindrical portion 23 is connected to the smaller end surface of the tapered portion 22, and is close to the inside of the channel 11; threaded holes 21 are provided in the columnar portion 23 and the tapered portion 22 so as to communicate with each other.
In a specific embodiment, as shown in fig. 3 and 4, the baffle 2 may further include a boss 24 disposed on an end surface of the larger end of the tapered portion 22. The boss 24 is provided to facilitate adjustment of the axial position of the baffle 2 by a tool.
For example, as shown in fig. 3 and 4, the boss 24 may be provided with an inner hexagonal groove 241, and the inner hexagonal groove 241 faces the outside of the fuel outlet (i.e., the side facing the outside of the casing 1). Furthermore, the baffle 2 may be rotated by using a socket head wrench, thereby achieving adjustment of the axial position of the baffle 2. Alternatively, the bottom of the hexagonal socket 241 may communicate with the threaded hole 21 in the tapered portion 22.
Illustratively, as shown in fig. 3 and 4, the outer side surface of the boss 24 may include two planes 242 parallel to each other. Furthermore, a solid wrench can be used to rotate the baffle 2, thereby adjusting the axial position of the baffle 2.
Of course, the specific arrangement of the boss is not limited to the above embodiments, and other structural designs that facilitate the operation of the tool also belong to the protection scope of the embodiments of the present invention.
Specifically, as shown in fig. 1 and 2, the compressed gas fuel flows in from the fuel inlet of the housing 1, flows through the channel 11 in the housing 1, and is ejected out from the fuel outlet, and the flow area of the gas can be gradually reduced in the process; for example, the flow area at the fuel inlet end may be set to be larger than the flow area at the fuel outlet end, and may be specifically 2 times or more. As shown in fig. 5, for example, under normal operation, the relative positions of the flow guiding body 2 and the fuel outlet of the housing 1 in the nozzle may be as shown in fig. 5 (a); if it is desired to increase the nozzle exit velocity, flow conductor 2 may be rotated to move towards the fixed end of connecting rod 4 (towards the interior of channel 11) so that the flow area of annular spray opening 3 is reduced, as shown in fig. 5 (b). If it is desired to reduce the nozzle exit velocity, flow conductor 2 may be rotated to move away from the fixed end of connecting rod 4 (toward the exterior of housing 1) to increase the flow area of annular spray opening 3, as shown in fig. 5 (c).
In a second aspect, embodiments of the present invention further provide a combustion chamber, which includes the nozzle according to any one of the above embodiments.
In a third aspect, embodiments of the present invention further provide a gas turbine, which includes the above-mentioned combustion chamber.
Illustratively, the gas turbine engine may also include a compressor, turbine, etc. structure.
It will be apparent to those skilled in the art that various changes and modifications may be made to the embodiments of the present invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims and their equivalents, the present invention is also intended to include such modifications and variations.
Claims (10)
1. A nozzle, comprising:
a housing provided with a fuel inlet and a fuel outlet;
a flow conductor at least partially disposed within the fuel outlet and cooperating with the fuel outlet to form an injection opening; the flow guide body is movable in an axial direction of the fuel outlet, and a flow area of the injection opening has a change as a position of the flow guide body in the axial direction changes.
2. The nozzle of claim 1 wherein a connecting rod is disposed in the housing and extends along an axis of the fuel outlet, and the flow conductor is disposed on and movable along the connecting rod.
3. The nozzle of claim 2, wherein the connecting rod is provided with external threads; the flow guide body is provided with a threaded hole matched with the external thread, and the flow guide body is in threaded connection with the connecting rod.
4. The nozzle of claim 1, wherein the inner wall surface of the fuel outlet comprises a conical surface.
5. The nozzle of any one of claims 1-4, wherein the flow conductor includes a tapered portion, the larger end of the tapered portion facing the outward side of the fuel outlet; the injection opening is formed between the outer side surface of the tapered portion and the inner wall surface of the fuel outlet.
6. The nozzle of claim 5 wherein the flow conductor further comprises a boss disposed on the end face of the larger end of the cone.
7. The nozzle of claim 6, wherein the boss is provided with an internal hexagonal recess facing an outward side of the fuel outlet.
8. The nozzle of claim 6 wherein the outer side of the boss comprises two planes that are parallel to each other.
9. A combustion chamber comprising a nozzle according to any one of claims 1 to 8.
10. A gas turbine comprising the combustor of claim 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922500057.9U CN211424473U (en) | 2019-12-31 | 2019-12-31 | Nozzle, combustion chamber and gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922500057.9U CN211424473U (en) | 2019-12-31 | 2019-12-31 | Nozzle, combustion chamber and gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211424473U true CN211424473U (en) | 2020-09-04 |
Family
ID=72286098
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922500057.9U Withdrawn - After Issue CN211424473U (en) | 2019-12-31 | 2019-12-31 | Nozzle, combustion chamber and gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211424473U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111043626A (en) * | 2019-12-31 | 2020-04-21 | 新奥能源动力科技（上海）有限公司 | Nozzle, combustion chamber and gas turbine |
| CN114543085A (en) * | 2022-02-21 | 2022-05-27 | 四川铭能科技开发有限公司 | Burner nozzle adaptable to various gas fuels |
-
2019
- 2019-12-31 CN CN201922500057.9U patent/CN211424473U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111043626A (en) * | 2019-12-31 | 2020-04-21 | 新奥能源动力科技（上海）有限公司 | Nozzle, combustion chamber and gas turbine |
| CN111043626B (en) * | 2019-12-31 | 2024-06-04 | 新奥能源动力科技（上海）有限公司 | Nozzle, combustion chamber and gas turbine |
| CN114543085A (en) * | 2022-02-21 | 2022-05-27 | 四川铭能科技开发有限公司 | Burner nozzle adaptable to various gas fuels |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20200904 Effective date of abandoning: 20240604 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20200904 Effective date of abandoning: 20240604 |