CN109185924B - Combustion chamber head device, combustion chamber and gas turbine - Google Patents
Combustion chamber head device, combustion chamber and gas turbine Download PDFInfo
- Publication number
- CN109185924B CN109185924B CN201810876019.0A CN201810876019A CN109185924B CN 109185924 B CN109185924 B CN 109185924B CN 201810876019 A CN201810876019 A CN 201810876019A CN 109185924 B CN109185924 B CN 109185924B
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- hole
- fuel
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- flange
- gas
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Classifications
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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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- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/60—Support structures; Attaching or mounting means
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
Abstract
The application discloses a head device of a combustion chamber, the combustion chamber and a gas turbine, so as to save the research and development time and cost of the combustion chamber. The head device of the combustion chamber comprises a flange, a gas collecting box, a head gas inlet piece, a main-stage fuel pipe, an auxiliary supporting rod, an on-duty fuel pipe and a plurality of main-stage fuel spray pipes, wherein the flange, the gas collecting box and the head gas inlet piece are coaxially arranged; the gas collecting box is fixed on the head gas inlet piece, the proximal cavity wall of the gas collecting box is provided with a second through hole and a third through hole which are radially symmetrical, a plurality of main-stage fuel spray pipes are in threaded connection with the distal cavity wall of the gas collecting box, and each main-stage fuel spray pipe is communicated with the inner cavity of the gas collecting box and extends into the premixing gas passage holes in a one-to-one correspondence manner; the class fuel pipe is fixed on the flange and penetrates through the first through hole; the main-stage fuel pipe is fixed in the flange and the second through hole, and the auxiliary supporting rod is fixed in the flange and the third through hole.
Description
Technical Field
The application relates to the technical field of gas turbines, in particular to a head device of a combustion chamber, the combustion chamber and the gas turbine.
Background
The gas turbine is a high-power and high-performance power machine which uses air as a medium and pushes the turbine machine to continuously do work by high-temperature gas. It is mainly composed of three large components of compressor, combustion chamber and turbine, and is matched with air-intake, air-exhaust, control, transmission and other auxiliary systems. The thermodynamic cycle process of the gas turbine is as follows:
the air compressor continuously sucks air from the external atmosphere and pressurizes the air, the temperature of the compressed air rises, the compressed air is beneficial to carrying out more violent chemical reaction with fuel, and the larger expansion ratio is also beneficial to releasing larger energy after the compressed air is combusted;
compressed air enters the combustion chamber after exiting the air compressor, firstly, the compressed air is mixed with injected fuel at the inlet of the combustion chamber, then the mixture is ignited and combusted, the temperature of the air rises hundreds of degrees or even thousands of degrees, and the pressure also increases rapidly;
the high-temperature and high-pressure fuel gas is sprayed out from the outlet of the combustion chamber, the turbine blades are pushed to do work while expanding, after the turbine converts the energy of the fuel gas into kinetic energy, one part of the fuel gas is used for compressing air of the compressor to continuously perform thermodynamic cycle, and the larger part of the fuel gas outputs torque of the rotor through the main shaft. The entire thermodynamic cycle achieves the final objective of converting fuel chemical energy into mechanical energy for the gas turbine.
The combustion chamber of a gas turbine requires a lot of experiments during the development process. When the combustion effect of different main-stage fuel spray pipes needs to be tested, the spray pipes need to be replaced. In the prior art, the spray pipe and the gas collecting box of the head device of the combustion chamber are welded and fixed and are not removable, and when the spray pipe is not applicable, the spray pipe needs to be reprocessed according to the design, so that the research and development time and the cost are greatly wasted.
Disclosure of Invention
An object of an embodiment of the application is to provide a head device of a combustion chamber, the combustion chamber and a gas turbine, so that the development time and cost of the combustion chamber are saved.
The embodiment of the application provides a head device of a combustion chamber, which comprises a flange, a gas collecting box, a head gas inlet piece, a main-stage fuel pipe, an auxiliary support rod, an on-duty-stage fuel pipe and a plurality of main-stage fuel spray pipes, wherein the flange, the gas collecting box and the head gas inlet piece are coaxially arranged from near to far, and the main-stage fuel spray pipes comprise: the head air inlet piece comprises a gas mixing cylinder and a plurality of premixed air channel holes which encircle the gas mixing cylinder and are parallel to the axial direction of the gas mixing cylinder, the proximal end of the gas mixing cylinder is provided with an end plate, and the center of the end plate is provided with a first through hole; the gas collecting box is fixed on the head gas inlet piece, the proximal cavity wall of the gas collecting box is provided with a second through hole and a third through hole which are radially symmetrical, a plurality of main-stage fuel spray pipes are in threaded connection with the distal cavity wall of the gas collecting box, and each main-stage fuel spray pipe is communicated with the inner cavity of the gas collecting box and extends into the premixing gas passage holes in a one-to-one correspondence manner; the class fuel pipe is fixed on the flange and penetrates through the first through hole; the main-stage fuel pipe is fixed in the flange and the second through hole, and the auxiliary supporting rod is fixed in the flange and the third through hole.
Optionally, the number of the primary fuel nozzles is 10-24 and is uniformly distributed on the distal cavity wall of the gas collecting box.
Preferably, the primary fuel lance has a boss defined outside the distal cavity wall of the manifold.
Optionally, the fuel outlets of the primary fuel nozzles are arranged in the axial direction of the primary fuel nozzles.
Optionally, the fuel outlets of the primary fuel nozzles are arranged radially of the primary fuel nozzles.
Optionally, the fuel outlets of the main stage fuel nozzles are at least two and are uniformly distributed along the circumferential direction of the main stage fuel nozzles.
Preferably, the flange is provided with a threaded hole at the position corresponding to the first through hole, a fourth through hole at the position corresponding to the second through hole and a fifth through hole at the position corresponding to the third through hole; the valve class fuel pipe, the main grade fuel pipe and the auxiliary supporting rod are provided with external threads, the valve class fuel pipe is fixed on the flange through being locked with the threaded holes in a threaded mode, the main grade fuel pipe penetrates through the fourth through hole and is fixed on the flange through a pair of first nuts located on two sides of the fourth through hole, and the auxiliary supporting rod penetrates through the fifth through hole and is fixed on the flange through a pair of second nuts located on two sides of the fifth through hole.
Preferably, the primary fuel pipe is welded with the second through hole, and the auxiliary supporting rod is welded with the third through hole.
The embodiment of the application also provides a combustion chamber, which comprises the head device according to any one of the technical schemes.
The embodiment of the application also provides a gas turbine, which comprises the combustion chamber according to the technical scheme.
The combustion chamber adopts the head device, when the combustion effect of different main-stage fuel spray pipes needs to be tested, only the main-stage fuel spray pipes need to be unscrewed and replaced, compared with the prior art, the research and development period of the combustion chamber is greatly saved, and the research and development cost is reduced.
Drawings
FIG. 1a is a cross-sectional view (first dimensional configuration) of a header assembly of an embodiment of the present application as applied to a combustion chamber;
FIG. 1b is a cross-sectional view (second dimensional configuration) of a header assembly of an embodiment of the present application as applied to a combustion chamber;
FIG. 2 is a cross-sectional perspective view of a head unit according to one embodiment of the present application;
FIG. 3 is a perspective view of a cross-section of a manifold and head air intake assembly according to an embodiment of the present application;
FIG. 4 is a cross-sectional view of a gas collection cartridge according to an embodiment of the present application;
FIG. 5 is a perspective view of a head air intake member according to an embodiment of the present application;
FIG. 6 is a cross-sectional view of an assembled gas collection cartridge and primary fuel nozzle in accordance with an embodiment of the present application;
FIG. 7 is a schematic cross-sectional view of a primary fuel lance in an embodiment of the application;
FIG. 8 is a schematic cross-sectional view of a main stage fuel nozzle in another embodiment of the application.
Reference numerals:
1-head device
10-flange
11-gas collecting box
12-head air intake
13-primary fuel pipe
14-auxiliary support bar
15-duty grade fuel pipe
16-primary fuel nozzle
161-boss
162-fuel outlet
121-inflator
122-premix gas passage
123-end plate
124-first through hole
111-second through hole
112-third through hole
101-threaded hole
102-fourth through hole
103-fifth through hole
17-first nut
18-second nut
2-casing
3-flame tube
201-high pressure air inlet
301-high pressure air jet orifice
302-high pressure air injection macropores
Detailed Description
In order to save the development time and cost of a combustion chamber of a gas turbine, the embodiment of the application provides a head device of the combustion chamber, the combustion chamber and the gas turbine. The present application will be further described in detail with reference to the following examples, in order to make the objects, technical solutions and advantages of the present application more apparent.
As shown in fig. 1a and fig. 2 to fig. 6, a head device 1 of a combustion chamber provided by an embodiment of the present application includes a flange 10, a gas collecting box 11, and a head gas inlet 12 coaxially disposed from the near to the far, and a main fuel pipe 13, an auxiliary support rod 14, an on-duty fuel pipe 15, and a plurality of main fuel nozzles 16, wherein: the head air intake 12 includes a gas cylinder 121 and a plurality of premix gas passage holes 122 surrounding the gas cylinder 121 and parallel to the axial direction of the gas cylinder 121, the proximal end of the gas cylinder 121 having an end plate 123, the center of the end plate 123 having a first through hole 124; the gas collecting box 11 is fixed on the head gas inlet piece 12, the proximal cavity wall of the gas collecting box 11 is provided with a second through hole 111 and a third through hole 112 which are radially symmetrical, a plurality of main-stage fuel spray pipes 16 are in threaded connection with the distal cavity wall of the gas collecting box 11, and each main-stage fuel spray pipe 16 is communicated with the inner cavity of the gas collecting box 11 and correspondingly stretches into the premixing gas passage hole 122 one by one; the class fuel pipe 15 is fixed to the flange 10 and passes through the first through hole 124; the primary fuel pipe 13 is fixed to the flange 10 and the second through hole 111, and the auxiliary support rod 14 is fixed to the flange 10 and the third through hole 112.
The combustion chamber generally comprises a casing 2, a flame tube 3, an ignition device (not shown in the figure) and the like in addition to the head device 1, wherein a high-pressure air inlet 201 is formed on the surface of the casing 2, and a high-pressure air injection small hole 301 and a high-pressure air injection large hole 302 are formed on the surface of the flame tube 3. The head air inlet 12 is fixed at the proximal end of the flame tube 3, the air mixing tube 121 and the plurality of premix air passage holes 122 are led to the flame tube 3, and the flange 10 is fixedly installed with the proximal end of the casing 1.
In the present application, with reference to the flange 10, the side of the defining member adjacent to the flange 10 is the proximal side, and correspondingly, the side of the defining member remote from the flange 10 is the distal side.
When the combustion chamber starts to work, firstly, the duty fuel pipe 15 is opened, and fuel sequentially enters the flame tube 3 through the duty fuel pipe 15 and the gas mixing cylinder 121; after a certain time interval, the main fuel pipe 13 is opened, and the fuel sequentially passes through the main fuel pipe 13, the gas collecting box 11, the plurality of main fuel spray pipes 16 and the plurality of premixed gas passage holes 122 to enter the flame tube 3, so that the fuel entering the flame tube 3 is ensured to be uniform in the section direction of the flame tube 3. The ignition device ignites fuel and air in the flame tube 3 to form high-temperature high-pressure fuel gas, and the fuel gas enters a turbine of a gas turbine to expand and do work.
The combustion chamber provided by the embodiment of the application adopts the design of the head device 1, and when the combustion effect of different main-stage fuel spray pipes 16 is required to be tested, the main-stage fuel spray pipes 16 are only required to be unscrewed and replaced, so that compared with the prior art, the development period of the combustion chamber is greatly saved, and the development cost is reduced.
In the embodiment of the application, the number of the main-stage fuel spray pipes 16 is 10-24 and the main-stage fuel spray pipes 16 are uniformly distributed on the far side cavity wall of the gas collecting box 11, and the fuel entering the flame tube 3 after passing through the head gas inlet piece 12 is more uniform due to the larger number of the main-stage fuel spray pipes 16 which are uniformly distributed, so that the uniform and full combustion of the fuel is facilitated, and the fuel utilization rate is improved.
As shown in fig. 6-8, the primary fuel lance 16 is further configured with a boss 161 defined on the outside of the distal cavity wall of the manifold 11. This facilitates positioning of the mounting of the main stage fuel lance 16 to the manifold 11 such that the main stage fuel lance 16 extends into the premix gas passage aperture 122 to a suitable length.
The particular configuration of the fuel outlets 162 of the primary fuel nozzles 16 is not limited, as shown in FIG. 7, and in an alternative embodiment, the fuel outlets 162 of the primary fuel nozzles 16 are disposed axially of the primary fuel nozzles 16. In another alternative embodiment, as shown in FIG. 8, the fuel outlets 162 of the primary fuel nozzles 16 are disposed radially of the primary fuel nozzles 16. The corresponding structural design can be performed according to the fuel injection direction. In addition, as shown in FIG. 8, the fuel outlets 162 of the primary fuel nozzles 16 may be at least two and evenly distributed along the circumference of the primary fuel nozzles 16, which also facilitates more even and dispersed fuel injection.
Referring to fig. 1a, 1b, and 2 to 5, the flange 10 has a threaded hole 101 corresponding to the first through hole 124, a fourth through hole 102 corresponding to the second through hole 111, and a fifth through hole 103 corresponding to the third through hole 112; the on-duty fuel pipe 15, the main fuel pipe 13, and the auxiliary support rod 14 have external threads, the on-duty fuel pipe 15 is fixed to the flange 10 by being screwed with the screw hole 101, the main fuel pipe 13 passes through the fourth through hole 102 and is fixed to the flange 10 by a pair of first nuts 17 located at both sides of the fourth through hole 102, and the auxiliary support rod 14 passes through the fifth through hole 103 and is fixed to the flange 10 by a pair of second nuts 18 located at both sides of the fifth through hole 103.
By comparing the designs shown in fig. 1a and fig. 1b, when the axial dimensions of the casing 2 and the flame tube 3 of the combustion chamber are adjusted due to the design, processing and installation modes (for example, D1 in fig. 1a is adjusted to D2 in fig. 1 b), the lengths of the main fuel pipe 13, the auxiliary support rod 14 and the duty fuel pipe 15 penetrating out of the flange 10 can be adjusted, so that the head device 1 can be matched with the design and installation requirements of the combustion chamber, and the development time and cost of the combustion chamber are further saved.
In the above embodiment of the present application, the primary fuel pipe 13 is optionally welded to the second through hole 111, and the auxiliary support rod 14 is welded to the third through hole 112. In addition, if the distal end of the primary fuel pipe 13 is designed with an annular flange, the primary fuel pipe 13 and the second through hole 111 may be fixedly connected by a screw or bolt disposed at the annular flange, and the auxiliary support rod 14 and the third through hole 112 may also correspondingly adopt such a fastening connection design scheme.
The embodiment of the application also provides a combustion chamber, which comprises the head device of any one of the technical schemes. The design of the head device greatly saves the research and development period of the combustion chamber and reduces the research and development cost.
The embodiment of the application also provides a gas turbine, which comprises the combustion chamber of the technical scheme. By adopting the design scheme of the head device, the research and development period of the combustion chamber of the gas turbine is greatly shortened, and the research and development cost is reduced.
It will be apparent to those skilled in the art that various modifications and variations can be made to the present application without departing from the spirit or scope of the application. Thus, it is intended that the present application also include such modifications and alterations insofar as they come within the scope of the appended claims or the equivalents thereof.
Claims (8)
1. The utility model provides a head device of combustion chamber, its characterized in that includes flange, gas collection casket and the head air inlet piece of from near to far coaxial setting to and main level fuel pipe, auxiliary stay pole, class on duty fuel pipe and a plurality of main level fuel spray pipe, wherein:
the head air inlet piece comprises a gas mixing cylinder and a plurality of premixed air channel holes which encircle the gas mixing cylinder and are parallel to the axial direction of the gas mixing cylinder, the proximal end of the gas mixing cylinder is provided with an end plate, and the center of the end plate is provided with a first through hole;
the gas collecting box is fixed on the head gas inlet piece, the proximal cavity wall of the gas collecting box is provided with a second through hole and a third through hole which are radially symmetrical, a plurality of main-stage fuel spray pipes are in threaded connection with the distal cavity wall of the gas collecting box, and each main-stage fuel spray pipe is communicated with the inner cavity of the gas collecting box and extends into the premixing gas passage holes in a one-to-one correspondence manner;
the class fuel pipe is fixed on the flange and penetrates through the first through hole;
the main-stage fuel pipe is fixed on the flange and the second through hole, and the auxiliary supporting rod is fixed on the flange and the third through hole;
the number of the main-stage fuel spray pipes is 10-24 and the main-stage fuel spray pipes are uniformly distributed on the far-side cavity wall of the gas collecting box;
the primary fuel lance has a boss defined outside the distal cavity wall of the manifold.
2. The header assembly of claim 1, wherein the fuel outlets of the primary fuel nozzles are disposed axially of the primary fuel nozzles.
3. The header assembly of claim 1, wherein the fuel outlets of the primary fuel nozzles are disposed radially of the primary fuel nozzles.
4. A header assembly as claimed in claim 3 wherein the primary fuel nozzles have at least two fuel outlets and are evenly distributed along the circumference of the primary fuel nozzles.
5. The head device according to any one of claims 1 to 4, wherein the flange is provided with a threaded hole corresponding to the first through hole, a fourth through hole corresponding to the second through hole, and a fifth through hole corresponding to the third through hole;
the valve class fuel pipe, the main grade fuel pipe and the auxiliary supporting rod are provided with external threads, the valve class fuel pipe is fixed on the flange through being locked with the threaded holes in a threaded mode, the main grade fuel pipe penetrates through the fourth through hole and is fixed on the flange through a pair of first nuts located on two sides of the fourth through hole, and the auxiliary supporting rod penetrates through the fifth through hole and is fixed on the flange through a pair of second nuts located on two sides of the fifth through hole.
6. The header assembly of claim 5, wherein the primary fuel tube is welded to the second through hole and the secondary support rod is welded to the third through hole.
7. A combustion chamber comprising a header assembly as claimed in any one of claims 1 to 6.
8. A gas turbine comprising the combustor of claim 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810876019.0A CN109185924B (en) | 2018-08-03 | 2018-08-03 | Combustion chamber head device, combustion chamber and gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810876019.0A CN109185924B (en) | 2018-08-03 | 2018-08-03 | Combustion chamber head device, combustion chamber and gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109185924A CN109185924A (en) | 2019-01-11 |
| CN109185924B true CN109185924B (en) | 2023-09-12 |
Family
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810876019.0A Active CN109185924B (en) | 2018-08-03 | 2018-08-03 | Combustion chamber head device, combustion chamber and gas turbine |
Country Status (1)
| Country | Link |
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| CN (1) | CN109185924B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111043625B (en) * | 2019-12-31 | 2024-06-04 | 新奥能源动力科技（上海）有限公司 | Combustion chamber of miniature gas turbine and miniature gas turbine |
| CN114738799B (en) * | 2022-04-20 | 2024-03-26 | 新奥能源动力科技（上海）有限公司 | Head assembly of dual-fuel combustion chamber, combustion chamber and gas turbine |
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