CN114046537A - Combined premixing nozzle of microminiature gas turbine - Google Patents
Combined premixing nozzle of microminiature gas turbine Download PDFInfo
- Publication number
- CN114046537A CN114046537A CN202111504225.7A CN202111504225A CN114046537A CN 114046537 A CN114046537 A CN 114046537A CN 202111504225 A CN202111504225 A CN 202111504225A CN 114046537 A CN114046537 A CN 114046537A
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- Prior art keywords
- oil
- gas turbine
- combined
- nozzle
- cavity
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles (AREA)
Abstract
The invention discloses a combined premixing nozzle of a microminiature gas turbine, which comprises an oil transportation structure, a first rotational flow structure, a second rotational flow structure and a shell; an oil injection ring plate is arranged between the oil conveying structure and the shell; the first rotational flow structure is arranged between the oil injection ring plate and the oil transportation structure; the second rotational flow structure is arranged between the oil injection annular plate and the shell; an oil cavity is formed in the top end of the oil injection ring plate; a plurality of oil film nozzles which are arranged in a staggered mode are arranged on the inner side and the outer side of the oil cavity; the combined premixing nozzle of the microminiature gas turbine has the advantages that the structure is simple, the use is convenient, the uniform and continuous oil injection effect is ensured through the oil cavity and the oil film nozzles arranged on the two sides of the oil cavity, the buffering effect is realized when the oil delivery quantity is changed through the oil cavity, and the better oil injection effect is ensured; the oil film nozzles on the inner side and the outer side are arranged in a staggered mode, so that each oil film nozzle can spray oil with the same oil pressure, and a good oil spraying effect is guaranteed.
Description
Technical Field
The invention relates to the field of nozzles, in particular to a combined premixing nozzle of a microminiature gas turbine.
Background
Liquid fuel gas turbines, fuel atomization and premixing with air are key factors affecting ignition and combustion performance. With the development of micro gas turbines, the combustion performance and emission requirements are more and more emphasized. However, because the combustion chamber of the micro-aircraft engine is small in size, the micro-aircraft engine rarely adopts a complex-structure composite nozzle like a large-scale gas turbine, but mostly adopts a single form such as a pressure type, an evaporation type and the like.
The pressure type (direct injection and centrifugal) nozzle is widely applied to the micro gas turbine. In order to ensure a satisfactory outlet temperature distribution of the combustion chamber, the number of nozzles must not be too small. In the low-power state caused by the above, the oil supply pressure is very low, the fuel atomization quality is poor, the combustion efficiency is very low, and even stable combustion cannot be realized, so that two-way centrifugal nozzles or circumferential staged oil supply is adopted. However, pressure nozzles are still required to achieve atomization at higher supply pressures. Along with the continuous promotion of combustion chamber pressure ratio, pressure type nozzle spray cone angle diminishes and influences main burning zone fuel distribution for combustion chamber outlet temperature field quality worsens.
Based on the above situation, the present invention provides a combined premixing nozzle for a micro gas turbine, which can effectively solve the above problems.
Disclosure of Invention
The invention aims to provide a combined premixing nozzle of a microminiature gas turbine. The combined premixing nozzle of the microminiature gas turbine has the advantages that the structure is simple, the use is convenient, the uniform and continuous oil injection effect is ensured through the oil cavity and the oil film nozzles arranged on the two sides of the oil cavity, the buffering effect is realized when the oil delivery quantity is changed through the oil cavity, and the better oil injection effect is ensured; the oil film nozzles on the inner side and the outer side are arranged in a staggered mode, so that each oil film nozzle can spray oil with the same oil pressure, and a good oil spraying effect is guaranteed.
The invention is realized by the following technical scheme:
a combined premixing nozzle of a microminiature gas turbine comprises an oil conveying structure, a first rotational flow structure, a second rotational flow structure and a shell; an oil injection ring plate is arranged between the oil conveying structure and the shell; the first rotational flow structure is arranged between the oil injection ring plate and the oil transportation structure; the second rotational flow structure is arranged between the oil injection annular plate and the shell; an oil cavity is formed in the top end of the oil injection ring plate; and a plurality of oil film nozzles which are arranged in a staggered mode are arranged on the inner side and the outer side of the oil cavity.
According to the oil cavity, the uniform and continuous oil injection effect is ensured through the oil cavity and the oil film nozzles arranged on the two sides of the oil cavity, and the oil cavity plays a role in buffering when the oil delivery quantity changes, so that a better oil injection effect is ensured; the oil film nozzles on the inner side and the outer side are arranged in a staggered mode, so that each oil film nozzle can spray oil with the same oil pressure, and a good oil spraying effect is guaranteed.
Preferably, the oil delivery structure comprises a first oil pipe and a second oil pipe arranged in the first oil pipe; the top of the first oil pipe is provided with a centrifugal chamber formed by a partition plate; the second oil pipe is communicated to the centrifugal chamber; the top of the centrifugal chamber is provided with a centrifugal nozzle; the first oil pipe is provided with a plurality of branch pipes communicated to the oil chamber.
Preferably, the surface of the oil injection ring plate is fixedly provided with a baffle corresponding to each oil film nozzle.
Preferably, the first swirl structure comprises a plurality of first swirl vanes equidistantly arranged around the oil delivery structure; and the first swirl vanes are spirally twisted.
Preferably, the second swirl structure comprises a plurality of second swirl vanes equidistantly arranged around the oil injection ring plate; and the second swirl vanes are spirally twisted.
Preferably, the outer side of the bottom end of the first oil pipe is also provided with threads.
Compared with the prior art, the invention has the following advantages and beneficial effects:
the combined premixing nozzle of the microminiature gas turbine has the advantages that the structure is simple, the use is convenient, the uniform and continuous oil injection effect is ensured through the oil cavity and the oil film nozzles arranged on the two sides of the oil cavity, the buffering effect is realized when the oil delivery quantity is changed through the oil cavity, and the better oil injection effect is ensured; the oil film nozzles on the inner side and the outer side are arranged in a staggered mode, so that each oil film nozzle can spray oil with the same oil pressure, and a good oil spraying effect is guaranteed.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view of another embodiment of the present invention;
FIG. 3 is a schematic top view of the present invention;
fig. 4 is a schematic cross-sectional view taken along line a-a in fig. 3.
Detailed Description
In order that those skilled in the art will better understand the technical solutions of the present invention, the following description of the preferred embodiments of the present invention is provided in conjunction with specific examples, but it should be understood that the drawings are for illustrative purposes only and should not be construed as limiting the patent; for the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; it will be understood by those skilled in the art that certain well-known structures in the drawings and descriptions thereof may be omitted. The positional relationships depicted in the drawings are for illustrative purposes only and are not to be construed as limiting the present patent.
Example 1:
as shown in fig. 1 to 4, a combined premixing nozzle of a micro gas turbine includes an oil delivery structure 1, a first swirling structure 2, a second swirling structure 3 and a housing 4; an oil injection annular plate 5 is arranged between the oil transportation structure 1 and the shell 4; the first rotational flow structure 2 is arranged between the oil injection ring plate 5 and the oil transportation structure 1; the second rotational flow structure 3 is arranged between the oil injection ring plate 5 and the shell 4; an oil cavity 51 is formed in the top end of the oil injection ring plate 5; the inner side and the outer side of the oil cavity 51 are both provided with a plurality of oil film nozzles 52 which are arranged in a staggered mode.
According to the invention, the uniform and continuous oil injection effect is ensured through the oil cavity 51 and the oil film nozzles 52 arranged on the two sides of the oil cavity 51, and the oil cavity 51 plays a role in buffering when the oil delivery quantity changes, so that a better oil injection effect is ensured; the oil film nozzles 52 on the inner side and the outer side are arranged in a staggered mode, so that each oil film nozzle 52 can spray oil with the same oil pressure, and a good oil spraying effect is guaranteed.
The section of the oil chamber 51 is half-moon shaped; an inner cavity air flow channel is formed between the oil conveying structure 1 and the oil injection ring plate 5; an outer cavity air flow channel is arranged between the oil injection ring plate 5 and the shell 4.
Further, in another embodiment, the oil transportation structure 1 includes a first oil pipe 11 and a second oil pipe 12 disposed in the first oil pipe 1; a centrifugal chamber 14 formed by a partition plate 13 is arranged at the top of the first oil pipe 11; the second oil pipe 12 is communicated to a centrifugal chamber 14; the top of the centrifugal chamber 14 is provided with a centrifugal nozzle 15; the first oil pipe 1 is provided with a plurality of branch pipes 16 communicating to the oil chamber 51.
Through the cooperation of the nozzle 15 of the centrifugal chamber 14 and the oil film nozzle 52, the function of double-oil-way atomization is realized, the sprayed oil can be better mixed with air, a better ignition effect is realized, and the high-efficiency stable-point operation of the gas turbine is ensured.
Further, in another embodiment, a baffle plate 53 is fixedly arranged on the surface of the oil injection ring plate 5 corresponding to each oil film nozzle 52.
Through the baffle 53, the sprayed oil is better guided to form an oil film, and better atomization and ignition effects are ensured.
Further, in another embodiment, the first swirling structure 2 comprises a plurality of first swirling vanes equidistantly arranged around the oil transportation structure 1; and the first swirl vanes are spirally twisted.
Further, in another embodiment, the second swirl structure 3 comprises a plurality of second swirl vanes equidistantly arranged around the oil injection ring plate 5; and the second swirl vanes are spirally twisted.
First whirl blade and second whirl blade all are the spiral distortion form, ensure under the prerequisite that does not increase the aerodynamic loss of air, strengthen the air whirl effect, guarantee better atomizing and ignition effect.
Further, in another embodiment, the outer side of the bottom end of the first oil pipe 11 is provided with a thread 17.
Through screw thread 17, be connected nozzle and other structures, guarantee better connection effect.
The nozzle is integrally formed by adopting an additive manufacturing technology, and the whole nozzle is a whole and has better mechanical strength.
The working principle of one embodiment of the invention is as follows:
a high-pressure air at the outlet of a diffuser passes through a second swirler 3 and a first swirler 2 to form a rotating airflow and then flows into an outer cavity air flow passage and an inner cavity air flow passage. When the engine is started and operates under a low working condition, the fuel oil flow required by combustion is low, the fuel oil enters the centrifugal chamber 14 through the second oil pipe 12 in a tangential direction, and the fuel oil forms an oil film under the two-way action of tangential centrifugal force and the partition plate 13 and clings to the inner wall of the centrifugal chamber 14, and is sprayed out through the nozzle 15 under the action of certain oil pressure. The ejected oil film forms an oil film at the inner side surface of the oil chamber 51. The oil film is cut and atomized under the action of rotational flow air in the outer cavity air flow channel and the inner cavity air flow channel. However, when the rotation speed of the gas turbine is increased, the first oil pipe 11 is opened, the fuel oil flows into the oil cavity 51 through the 3 branch pipes 16, the fuel oil flows out through the oil film nozzles 52 arranged on the inner wall and the outer wall of the oil cavity 51 under low oil pressure, an oil film is formed on the inner wall and the outer wall, and the fuel oil is sheared and atomized under the action of swirling air in the outer cavity air flow channel and the inner cavity air flow channel.
According to the description of the invention and the attached drawings, the combined premixing nozzle for the microminiature gas turbine of the invention can be easily manufactured or used by those skilled in the art, and can produce the positive effects described in the invention.
Unless otherwise specified, in the present invention, if there is an orientation or positional relationship indicated by terms of "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., based on the orientation or positional relationship shown in the drawings, it is only for convenience of describing the present invention and simplifying the description, rather than to indicate or imply that the device or element so referred to must have a particular orientation, be constructed and operated in a particular orientation, therefore, the terms describing orientation or positional relationship in the present invention are for illustrative purposes only, and should not be construed as limiting the present patent, specific meanings of the above terms can be understood by those of ordinary skill in the art in light of the specific circumstances in conjunction with the accompanying drawings.
Unless expressly stated or limited otherwise, the terms "disposed," "connected," and "connected" are used broadly and encompass, for example, being fixedly connected, detachably connected, or integrally connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications and equivalent variations of the above embodiments according to the technical spirit of the present invention are included in the scope of the present invention.
Claims (6)
1. A combined premixing nozzle of a microminiature gas turbine is characterized in that: the device comprises an oil transportation structure (1), a first rotational flow structure (2), a second rotational flow structure (3) and a shell (4); an oil injection annular plate (5) is arranged between the oil conveying structure (1) and the shell (4); the first rotational flow structure (2) is arranged between the oil injection ring plate (5) and the oil transportation structure (1); the second rotational flow structure (3) is arranged between the oil injection ring plate (5) and the shell (4); an oil cavity (51) is formed in the top end of the oil injection ring plate (5); the inner side and the outer side of the oil cavity (51) are respectively provided with a plurality of staggered oil film nozzles (52).
2. The combined premixing nozzle for a micro gas turbine as claimed in claim 1, wherein: the oil conveying structure (1) comprises a first oil pipe (11) and a second oil pipe (12) arranged in the first oil pipe (1); a centrifugal chamber (14) formed by a partition plate (13) is arranged at the top of the first oil pipe (11); the second oil pipe (12) is communicated to a centrifugal chamber (14); the top of the centrifugal chamber (14) is provided with a centrifugal nozzle (15); the first oil pipe (1) is provided with a plurality of branch pipes (16) communicated to the oil chamber (51).
3. The combined premixing nozzle for a micro gas turbine as claimed in claim 1, wherein: and a baffle (53) is fixedly arranged on the surface of the oil injection ring plate (5) corresponding to each oil film nozzle (52).
4. The combined premixing nozzle for a micro gas turbine as claimed in claim 1, wherein: the first cyclone structure (2) comprises a plurality of first cyclone blades which are equidistantly arranged around the oil transportation structure (1); and the first swirl vanes are spirally twisted.
5. The combined premixing nozzle for a micro gas turbine as claimed in claim 1, wherein: the second swirl structure (3) comprises a plurality of second swirl blades which are equidistantly arranged around the oil injection ring plate (5); and the second swirl vanes are spirally twisted.
6. The combined premixing nozzle for a micro gas turbine as claimed in claim 1, wherein: and the outer side of the bottom end of the first oil pipe (11) is also provided with a thread (17).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111504225.7A CN114046537A (en) | 2021-12-10 | 2021-12-10 | Combined premixing nozzle of microminiature gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111504225.7A CN114046537A (en) | 2021-12-10 | 2021-12-10 | Combined premixing nozzle of microminiature gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114046537A true CN114046537A (en) | 2022-02-15 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111504225.7A Pending CN114046537A (en) | 2021-12-10 | 2021-12-10 | Combined premixing nozzle of microminiature gas turbine |
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| Country | Link |
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| CN (1) | CN114046537A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114857619A (en) * | 2022-04-29 | 2022-08-05 | 江苏中科能源动力研究中心 | Micro-mixing combustion chamber of gas turbine |
| CN115127122A (en) * | 2022-06-29 | 2022-09-30 | 中国航发湖南动力机械研究所 | Nozzle with premixing cavity and application thereof |
-
2021
- 2021-12-10 CN CN202111504225.7A patent/CN114046537A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114857619A (en) * | 2022-04-29 | 2022-08-05 | 江苏中科能源动力研究中心 | Micro-mixing combustion chamber of gas turbine |
| CN114857619B (en) * | 2022-04-29 | 2024-01-26 | 江苏中科能源动力研究中心 | Micro-mixed combustion chamber of gas turbine |
| CN115127122A (en) * | 2022-06-29 | 2022-09-30 | 中国航发湖南动力机械研究所 | Nozzle with premixing cavity and application thereof |
| CN115127122B (en) * | 2022-06-29 | 2023-09-12 | 中国航发湖南动力机械研究所 | Nozzle with premixing cavity and application thereof |
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