CN110779041A - Nozzle device of combustion chamber of gas turbine - Google Patents
Nozzle device of combustion chamber of gas turbine Download PDFInfo
- Publication number
- CN110779041A CN110779041A CN201910954691.1A CN201910954691A CN110779041A CN 110779041 A CN110779041 A CN 110779041A CN 201910954691 A CN201910954691 A CN 201910954691A CN 110779041 A CN110779041 A CN 110779041A
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- China
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- fuel
- main
- gas turbine
- main fuel
- end cover
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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
Abstract
The invention discloses a nozzle device of a combustion chamber of a gas turbine, which belongs to the technical field of gas turbines, and comprises an end cover and a plurality of mutually independent fuel cavities arranged in the end cover, wherein one side of the end cover is connected with a plurality of fuel pipelines, each fuel pipeline is respectively communicated with each fuel cavity, and the other side of the end cover is provided with a jet pipe group and a jet orifice group which are respectively arranged on different fuel cavities; the injection hole group comprises a plurality of first fuel injection holes communicated with the fuel chamber; the jet pipe group comprises a plurality of main fuel jet pipes communicated with the fuel chamber, and each main fuel jet pipe is provided with a plurality of second fuel jet holes so as to achieve the purposes of enabling fuel to enter a swirler and a flame tube in a grading manner, achieving stable combustion, promoting uniform mixing of fuel and air and inhibiting combustion oscillation.
Description
Technical Field
The invention belongs to the technical field of gas turbines, and particularly relates to a nozzle device of a combustion chamber of a gas turbine.
Background
In order to realize stable combustion and low pollution emission of the combustion chamber of the gas turbine, the common practice of the design of the combustion chamber of the international heavy-duty gas turbine is to adopt a combined combustion mode of diffusion combustion and premixed combustion in the combustion chamber.
Dry Low NOx (DLN) combustion technology is the mature technology for controlling pollutant emission commonly adopted by heavy-duty gas turbines in the world today, and the most critical technology is to realize uniform mixing of fuel and air and dilute-phase premixed combustion. The most substantial advantage of lean premixed combustion is its low flame temperature, which directly affects the formation of NOx.
DLN technology has incomparable advantages in pollutant control, but also has problems of poor combustion stability, flashback, reduced load regulation range, and easy occurrence of combustion oscillation.
In order to avoid the problems as much as possible, the diffusion combustion is the simplest and most effective method by selecting one path of fuel.
Disclosure of Invention
In view of the above, in order to solve the above problems of the prior art, the present invention provides a nozzle device for a gas turbine combustor, which achieves the purposes of achieving staged fuel entry into the swirler and the combustor basket, achieving stable combustion, promoting uniform mixing of fuel and air, and suppressing occurrence of combustion oscillation.
The technical scheme adopted by the invention is as follows: a nozzle device of a combustion chamber of a gas turbine comprises an end cover and a plurality of mutually independent fuel cavities arranged in the end cover, wherein one side of the end cover is connected with a plurality of fuel pipelines, each fuel pipeline is respectively communicated with each fuel cavity, and the other side of the end cover is provided with a jet pipe group and a jet hole group which are respectively arranged on different fuel cavities; the injection hole group comprises a plurality of first fuel injection holes communicated with the fuel chamber; the jet pipe group comprises a plurality of main fuel jet pipes communicated with the fuel chamber, each main fuel jet pipe is provided with a plurality of second fuel jet holes, and the first fuel jet holes and the second fuel jet holes can realize that fuel enters the swirler and the flame tube in a grading manner.
Furthermore, 2-4 fuel pipelines are arranged, and each fuel pipeline is divided into a main fuel pipeline and an on-duty fuel pipeline; each fuel cavity is divided into a main fuel cavity and an on-duty fuel cavity, the main fuel cavity and the on-duty fuel cavity are respectively communicated with a main fuel pipeline and an on-duty fuel pipeline, and the main fuel pipeline and the on-duty fuel pipeline respectively introduce fuel gas into the main fuel cavity and the on-duty fuel cavity.
Further, the end cover is of a circular structure, and the main fuel chamber and the duty fuel chamber are annular, so that fuel can be supplied in a staged manner, and reasonable arrangement of the main fuel nozzles and the first fuel spray holes is facilitated.
Furthermore, the main fuel pipeline and the duty fuel pipeline are respectively communicated with the main fuel cavity and the duty fuel cavity through fuel pipeline interfaces so as to realize the sealing assembly connection of the main fuel pipeline and the duty fuel pipeline and supply fuel gas.
Furthermore, each main fuel spray pipe is divided into 1-3 groups according to the size, and each group comprises 4-24 main fuel spray pipes so as to achieve uniform mixing of fuel and air in a flow passage of the swirler.
Further, the fuel injection device comprises 1-3 main fuel cavities, a plurality of fuel injection pipe interfaces are arranged on each main fuel cavity, each main fuel injection pipe interface is connected with each main fuel injection pipe, so that the main fuel injection pipes are hermetically assembled and connected, and each main fuel injection pipe is respectively inserted into a corresponding stage of swirler.
Furthermore, 4-8 second fuel spray holes are formed in the main fuel spray pipe, and the main fuel spray pipe comprises a steel pipe and a plug installed at the end of the steel pipe.
Further, each fuel nozzle interface corresponding to each main fuel cavity is arranged in the circumferential direction, so that the main fuel nozzles are reasonably arranged.
Furthermore, each first fuel spray hole is arranged on one side of the on-duty fuel cavity along the same circumferential direction, and an included angle of 30-70 degrees is formed between the central axis of each first fuel spray hole and the central axis of the end cover, so that diffusion combustion is carried out in the flame tube after the fuel spray holes are sprayed out from the on-duty fuel spray holes.
The heat shield is made of high-temperature alloy materials; the heat shield plate and the end cover are pressed and sealed through the plug-in piece through bolts.
The invention has the beneficial effects that:
1. the nozzle device of the combustion chamber of the gas turbine is used for a fuel grading supply system and is assembled on a gas turbine combustion and pressure cylinder body, the central axis of the whole device is coaxial with the axis of a flame tube, main fuel spray pipes at all levels are respectively inserted into corresponding levels of swirlers, and the uniform mixing of fuel and air is realized in a swirler runner; the on-duty fuel directly enters the flame tube through the first fuel jet hole to be combusted, so that the fuel enters the swirler and the flame tube in a grading manner, and the burner has the advantages of stable combustion, promotion of uniform mixing of the fuel and air and inhibition of combustion oscillation.
Drawings
FIG. 1 is a left-hand schematic view of the overall construction of a gas turbine combustor nozzle assembly provided in accordance with the present invention;
FIG. 2 is a right-hand schematic view of the overall construction of a gas turbine combustor nozzle assembly provided in accordance with the present invention;
FIG. 3 is a schematic top view of an end cover of a gas turbine combustor nozzle assembly provided by the present invention;
FIG. 4 is a schematic bottom view of an end cover of a gas turbine combustor nozzle assembly according to the present invention;
FIG. 5 is a schematic cross-sectional view of a gas turbine combustor nozzle arrangement provided by the present invention;
FIG. 6 is a schematic illustration of the construction of a main fuel nozzle of a gas turbine combustor nozzle assembly provided by the present invention;
FIG. 7 is a schematic cross-sectional view of a primary fuel nozzle of a gas turbine combustor nozzle assembly provided by the present invention;
the drawings are labeled as follows:
1-end cover, 2-main fuel pipeline, 3-duty fuel pipeline, 4-bolt, 5-main fuel spray hole, 6-main fuel spray pipe, 7-duty fuel pipeline interface, 8-main fuel pipeline interface, 9-fuel spray pipe interface, 10-duty fuel spray hole, 11-heat shield, 12-plug, 13-duty fuel cavity, 14-first main fuel cavity, 15-first main fuel spray pipe, 16-second main fuel cavity, 17-second main fuel spray pipe, 18-plug and 19-steel pipe.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the embodiments of the present invention, it should be noted that the indication of the orientation or the positional relationship is based on the orientation or the positional relationship shown in the drawings, or the orientation or the positional relationship which is usually placed when the product of the present invention is used, or the orientation or the positional relationship which is usually understood by those skilled in the art, or the orientation or the positional relationship which is usually placed when the product of the present invention is used, and is only for the convenience of describing the present invention and simplifying the description, but does not indicate or imply that the indicated device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and therefore, cannot be understood as limiting the present invention. Furthermore, the terms "first" and "second" are used merely to distinguish one description from another, and are not to be construed as indicating or implying relative importance.
In the description of the embodiments of the present invention, it should be further noted that the terms "disposed" and "connected" are to be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected, unless explicitly stated or limited otherwise; may be directly connected or indirectly connected through an intermediate. The specific meanings of the above terms in the present invention can be understood in specific cases by those skilled in the art; the drawings in the embodiments are used for clearly and completely describing the technical scheme in the embodiments of the invention, and obviously, the described embodiments are a part of the embodiments of the invention, but not all of the embodiments. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Example 1
As shown in fig. 1 and 2, the present embodiment specifically provides a gas turbine combustion chamber nozzle device, which includes an end cover 1, wherein the end cover 1 has a circular structure, and the end cover 1 is used as a main body of the gas turbine combustion chamber nozzle device, is assembled on a gas turbine combustion and pressure cylinder body, and acts on a fuel staged supply system.
The fuel end cover further comprises a plurality of mutually independent fuel cavities arranged inside the end cover 1, and each fuel cavity is divided into a main fuel cavity and an on-duty fuel cavity 13. In the present embodiment, two main fuel chambers, a first main fuel chamber 14 and a second main fuel chamber 16, respectively, and one on duty fuel chamber 13 are provided. Preferably, the first main fuel chamber 14, the second main fuel chamber 16 and the duty fuel chamber 13 are all provided with annular cavities, and the three are arranged inside the end cover 1 in a concentric annular manner.
A plurality of primary fuel lances 6 are also included, and in this embodiment the plurality of primary fuel lances 6 are divided into two groups by size length, one group being a plurality of first primary fuel lances 15 and the other group being a plurality of second primary fuel lances 17.
As shown in fig. 3, 4 and 5, three fuel pipelines are connected to one side of the end cover 1, which are two main fuel pipelines 2 and one on-duty fuel pipeline 3, the two main fuel pipelines 2 are respectively communicated with a first main fuel chamber 14 and a second main fuel chamber 16, main fuel pipeline interfaces 8 communicated with the inside of the first main fuel chamber 14 and the second main fuel chamber 16 are respectively arranged at one side of the first main fuel chamber 14 and the second main fuel chamber 16, and the two main fuel pipelines 2 are respectively connected to the end cover 1 by welding through the corresponding main fuel pipeline interfaces 8; a plurality of fuel nozzle interfaces 9 are respectively arranged on the other sides of the first main fuel cavity 14 and the second main fuel cavity 16, a plurality of first main fuel nozzles 15 are connected to the first main fuel cavity 14 in a welding mode through the fuel nozzle interfaces 9, a plurality of second main fuel nozzles 17 are connected to the second main fuel cavity 16 in a welding mode through the fuel nozzle interfaces 9, so that fuel gas enters the first main fuel cavity 14 and the second main fuel cavity 16 through an air inlet pipeline and then enters the first main fuel nozzles 15 and the second main fuel nozzles 17 respectively, and is sprayed out through main fuel spray holes 5 in the first main fuel nozzles 15 and the second main fuel nozzles 17 to be premixed and combusted after being mixed in a premixing cavity. Preferably, the respective fuel nozzle ports 9 of the first main fuel chamber 14 are arranged in the same circumferential direction, and the respective fuel nozzle ports 9 of the second main fuel chamber 16 are arranged in another circumferential direction.
As shown in fig. 1, 4 and 5, an on-duty fuel pipeline interface 7 communicated with the inside of the on-duty fuel cavity is arranged at one side of the on-duty fuel cavity, the on-duty fuel pipeline 3 is welded on the end cover 1 through the on-duty fuel pipeline interface 7 corresponding to the on-duty fuel pipeline interface, and a plurality of on-duty fuel spray holes 10 communicated with the inside of the on-duty fuel cavity are arranged at the other side of the on-duty fuel cavity. Each on-duty fuel spray hole 10 is arranged at one side of the on-duty fuel chamber 13 along the same circumferential direction, an included angle of 30-70 degrees is formed between the central axis of the on-duty fuel spray hole 10 and the central axis of the end cover 1 (as shown in fig. 5), and after the fuel gas enters the on-duty fuel chamber 13 through the air inlet pipeline, the fuel gas is sprayed out from the on-duty fuel spray holes 10 and is subjected to diffusion combustion in the flame tube.
Arranging two main fuel pipelines 2 and one on-duty fuel pipeline 3 at one side of an end cover 1, arranging each first main fuel spray pipe 15, each second main fuel spray pipe 17 and each on-duty fuel spray hole 10 at the other side of the end cover 1, and respectively arranging a plurality of main fuel spray holes 5 and 4-8 main fuel spray holes 5 on the first main fuel spray pipe 15 and the second main fuel spray pipe 17, as shown in fig. 6 and 7, in the embodiment, five main fuel spray holes 5 are respectively arranged on the first main fuel spray pipe 15 and the second main fuel spray pipe 17, wherein the main fuel spray pipe 6 comprises a steel pipe 19 and a plug 18 arranged at the end of the steel pipe 19, and the assembly modes between the two are three types: and performing cold nitrogen assembly, assembly surface sealing welding or spot welding on the sealing surface after the cold nitrogen assembly.
In the above, the first main fuel nozzles 15 and the second main fuel nozzles 17 are divided into two groups according to the size and length, each group includes 4 to 24 main fuel nozzles, for example, in the present embodiment, there are 12 first main fuel nozzles, and there are 12 second main fuel nozzles, and of course, the specific number of the first main fuel nozzles 15 and the second main fuel nozzles 17 may be designed according to actual requirements.
As shown in fig. 1 and 5, the heat shield comprises a heat shield 11 and an insert 12, wherein the heat shield 11 is assembled in the middle of the end cover 1, and the heat shield 11 is made of high-temperature alloy material and can prevent high-temperature ablation; the insert 12 is in clearance fit with the central hole of the end cover 1, and the insert 12 is fixed by the bolt 4 and compresses and seals the heat shield 11 and the end cover 1.
The invention is not limited to the above alternative embodiments, and any other various forms of products can be obtained by anyone in the light of the present invention, but any changes in shape or structure thereof, which fall within the scope of the present invention as defined in the claims, fall within the scope of the present invention.
Claims (10)
1. A nozzle device of a combustion chamber of a gas turbine comprises an end cover and is characterized by further comprising a plurality of mutually independent fuel cavities arranged in the end cover, wherein one side of the end cover is connected with a plurality of fuel pipelines which are respectively communicated with the fuel cavities, and the other side of the end cover is provided with a jet pipe group and a jet hole group which are respectively arranged on different fuel cavities; the injection hole group comprises a plurality of first fuel injection holes communicated with the fuel chamber; the jet pipe group comprises a plurality of main fuel jet pipes communicated with the fuel chamber, and each main fuel jet pipe is provided with a plurality of second fuel jet holes.
2. The gas turbine combustor nozzle assembly of claim 1, wherein there are 2-4 said fuel lines, each said fuel line being divided into a main fuel line and an on-duty fuel line; each fuel cavity is divided into a main fuel cavity and an on-duty fuel cavity, and the main fuel cavity and the on-duty fuel cavity are respectively communicated with a main fuel pipeline and an on-duty fuel pipeline.
3. The gas turbine combustor nozzle assembly of claim 2, wherein the end cap is circular in configuration and the main and on-duty fuel plenums are annular in shape.
4. The gas turbine combustor nozzle arrangement of claim 2, wherein the main fuel conduit and the on-duty fuel conduit are each in communication with the main fuel plenum and the on-duty fuel plenum, respectively, through fuel conduit interfaces.
5. The gas turbine combustor nozzle assembly of claim 1, wherein each main-fuel nozzle is divided into 1-3 groups by size, each group including 4-24 main-fuel nozzles.
6. The gas turbine combustor nozzle assembly of claim 2, comprising 1-3 main fuel cavities, each main fuel cavity having a plurality of fuel nozzle ports, each fuel nozzle port having a respective main fuel nozzle connected thereto.
7. The gas turbine combustor nozzle assembly of claim 1, 5 or 6, wherein the main fuel nozzle has 4-8 second fuel nozzles, and the main fuel nozzle comprises a steel tube and a plug mounted on an end of the steel tube.
8. The gas turbine combustor nozzle arrangement of claim 6, wherein each fuel nozzle interface corresponding to each of the main fuel cavities is arranged in a circumferential direction.
9. The gas turbine combustor nozzle arrangement of claim 2, wherein each of the first fuel nozzle holes is disposed on one side of the on-duty fuel plenum in a same circumferential direction, and a central axis of the first fuel nozzle hole is angled from a central axis of the end cover by 30 ° to 70 °.
10. The gas turbine combustor nozzle assembly of claim 1, further comprising a heat shield and an insert mounted to a central portion of the end cap, the heat shield being a superalloy material; the heat shield plate and the end cover are pressed and sealed through the plug-in piece through bolts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910954691.1A CN110779041B (en) | 2019-10-09 | 2019-10-09 | Nozzle device of combustion chamber of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910954691.1A CN110779041B (en) | 2019-10-09 | 2019-10-09 | Nozzle device of combustion chamber of gas turbine |
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| Publication Number | Publication Date |
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| CN110779041A true CN110779041A (en) | 2020-02-11 |
| CN110779041B CN110779041B (en) | 2020-11-24 |
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| CN201910954691.1A Active CN110779041B (en) | 2019-10-09 | 2019-10-09 | Nozzle device of combustion chamber of gas turbine |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202813443U (en) * | 2012-09-12 | 2013-03-20 | 中国科学院工程热物理研究所 | Lean pre-mixing combustion room of gas turbine |
| CN107781848A (en) * | 2017-11-23 | 2018-03-09 | 上海泛智能源装备有限公司 | A kind of combustion chamber of gas turbine and gas turbine |
| CN209068550U (en) * | 2018-08-03 | 2019-07-05 | 新奥能源动力科技（上海）有限公司 | Head device, combustion chamber and the gas turbine of combustion chamber |
| CN110131750A (en) * | 2019-04-26 | 2019-08-16 | 沈阳航空航天大学 | A kind of gas turbine low discharging burning chamber of using gas fuel |
| CN209399411U (en) * | 2018-08-03 | 2019-09-17 | 新奥能源动力科技（上海）有限公司 | A kind of nozzle of combustion chamber, combustion chamber and miniature gas turbine |
-
2019
- 2019-10-09 CN CN201910954691.1A patent/CN110779041B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202813443U (en) * | 2012-09-12 | 2013-03-20 | 中国科学院工程热物理研究所 | Lean pre-mixing combustion room of gas turbine |
| CN107781848A (en) * | 2017-11-23 | 2018-03-09 | 上海泛智能源装备有限公司 | A kind of combustion chamber of gas turbine and gas turbine |
| CN209068550U (en) * | 2018-08-03 | 2019-07-05 | 新奥能源动力科技（上海）有限公司 | Head device, combustion chamber and the gas turbine of combustion chamber |
| CN209399411U (en) * | 2018-08-03 | 2019-09-17 | 新奥能源动力科技（上海）有限公司 | A kind of nozzle of combustion chamber, combustion chamber and miniature gas turbine |
| CN110131750A (en) * | 2019-04-26 | 2019-08-16 | 沈阳航空航天大学 | A kind of gas turbine low discharging burning chamber of using gas fuel |
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| Publication number | Publication date |
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| CN110779041B (en) | 2020-11-24 |
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