CN116658935A - Combustion chamber head, combustion chamber, gas turbine - Google Patents
Combustion chamber head, combustion chamber, gas turbine Download PDFInfo
- Publication number
- CN116658935A CN116658935A CN202210144280.8A CN202210144280A CN116658935A CN 116658935 A CN116658935 A CN 116658935A CN 202210144280 A CN202210144280 A CN 202210144280A CN 116658935 A CN116658935 A CN 116658935A
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- CN
- China
- Prior art keywords
- micro
- combustion
- combustion chamber
- holes
- head
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- 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.)
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Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 166
- 239000000446 fuel Substances 0.000 claims abstract description 45
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims abstract description 28
- 229910052739 hydrogen Inorganic materials 0.000 claims abstract description 28
- 239000001257 hydrogen Substances 0.000 claims abstract description 28
- 239000007789 gas Substances 0.000 claims abstract description 13
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 10
- 230000008602 contraction Effects 0.000 claims abstract description 6
- 238000001816 cooling Methods 0.000 claims description 31
- 239000000112 cooling gas Substances 0.000 claims description 18
- 239000012530 fluid Substances 0.000 abstract description 4
- 238000005496 tempering Methods 0.000 abstract description 4
- 230000010355 oscillation Effects 0.000 description 3
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000001939 inductive effect Effects 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 239000003350 kerosene Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000008033 biological extinction Effects 0.000 description 1
- 229910002092 carbon dioxide Inorganic materials 0.000 description 1
- 239000001569 carbon dioxide Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000002803 fossil fuel Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000002269 spontaneous effect Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- 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
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The invention discloses a combustion chamber head, a combustion chamber and a gas turbine, and relates to the technical field of aviation gas turbines. The combustion chamber head comprises a body, a plurality of micro combustion holes are formed in the body, an air flow channel of each micro combustion hole penetrates through the body, the upstream of the air flow channel of each micro combustion hole is a contraction section, and the downstream of the air flow channel of each micro combustion hole is an expansion section; a delivery conduit for supplying hydrogen fuel to the micro combustion holes; the nozzle is close to the corresponding outlet of the micro combustion hole and is communicated with the conveying pipeline and the micro combustion hole, the micro combustion holes realize micropore lean combustion, the contact area of fuel and air can be increased, the emission of NOX is reduced, the airflow channel of the micro combustion hole adopts a shape which is contracted first and then expanded, the fluid flow characteristic is utilized, enough space is reserved for a backflow area, and tempering is effectively prevented.
Description
Technical Field
The invention relates to the technical field of aviation gas turbines, in particular to a combustion chamber head, a combustion chamber and a gas turbine.
Background
The hydrogen fuel only generates water vapor after combustion, and compared with the traditional fossil fuel, the hydrogen fuel can realize the zero emission of real carbon dioxide. However, the flame temperature is higher when the hydrogen fuel is burned than the aviation kerosene, and more NOx emissions are easily produced when the hydrogen fuel is burned in air. The temperature of a conventional aviation gas turbine combustor will exceed 2000 ℃ with an equivalence ratio approaching 1, resulting in a higher level of NOx production. And the temperature of the combustion chamber of the aeroengine burning hydrogen is higher, so that the pollution of NOx emission is larger.
The ideal mode of controlling NOx emission is to use premixed combustion, but hydrogen fuel is gas, flame propagation speed is faster, spontaneous combustion tempering is easy to occur, non-premixed combustion is needed, but partial hot spots are easy to cause by using non-premixed combustion, and the NOx emission is increased.
The lean extinction equivalent of the hydrogen fuel is lower than that of aviation kerosene, and the combustion heat of the hydrogen fuel is higher, so that the main combustion area of the combustion chamber can work in a lower equivalent ratio area. However, with a lower stoichiometry, the flame itself has an increased fluctuation in heat release rate, is easily coupled with the thermo-acoustic characteristics of the combustion chamber, induces combustion instabilities, and produces a larger pressure value, which presents a significant challenge for the strength and life of the engine. The combustion of hydrogen fuel increases the temperature of the adiabatic flame, increases the laminar flame speed, sharply reduces the ignition delay time, seriously aggravates the flame combustion oscillation level and greatly affects the combustion chamber.
Disclosure of Invention
The invention aims to overcome the defects in the prior art and provides a combustion chamber head, a combustion chamber and a gas turbine.
The invention solves the technical problems by the following technical scheme:
a combustion chamber head comprising a body, the body being provided with: the airflow channels of the micro combustion holes penetrate through the body, the upstream parts of the airflow channels of the micro combustion holes are contraction sections, and the downstream parts of the airflow channels of the micro combustion holes are expansion sections; a delivery conduit for supplying hydrogen fuel to the micro combustion holes; the nozzles are in one-to-one correspondence with the micro combustion holes, and are close to the corresponding outlets of the micro combustion holes and communicated with the conveying pipeline and the micro combustion holes.
In this scheme, set up a plurality of miniature combustion holes on the body of combustion chamber and realize micropore lean combustion, can increase fuel and air area of contact, reduce NOX's emission to miniature combustion hole's air current passageway adopts the shape of contracting earlier and then expanding, thereby utilizes fluid flow characteristic, utilizes the shrink section of upstream to accelerate the incoming flow and reduces tempering danger, utilizes the expansion section of low reaches can guarantee that the flame face expands outward, leaves for backflow region sufficient space, effectively prevents tempering through the runner structure that has upstream shrink section and low reaches expansion section promptly.
Preferably, the normal direction of the nozzle is 90 degrees to the flow direction of the air flow in the micro combustion hole.
In the scheme, the normal direction of the nozzle is 90 degrees with the flow direction of the air flow in the micro combustion hole, so that the hydrogen fuel sprayed by the nozzle enters the micro combustion hole in a transverse spraying mode, and is quickly mixed with air in the air flow channel of the micro combustion hole for combustion, so that local hot spots are eliminated, the temperature of the fuel gas is reduced, and the emission of NOx can be inhibited.
Preferably, the micro combustion holes are arranged along the circumferential direction of the body in a plurality of circles, and the micro combustion holes are distributed on the body in a plurality of layers.
In this scheme, through arrange many rings of combustion holes on the body to many rings of miniature combustion holes become the multilayer setting, can split into a large amount of little flames with the flame of combustion zone, increase the area of contact of fuel and air.
Preferably, the number of the conveying pipelines is several, and each conveying pipeline is arranged between two adjacent layers of the micro combustion holes and used for supplying hydrogen fuel to the micro combustion holes on two sides of the conveying pipeline.
In the scheme, the micro combustion holes are distributed on two sides of the conveying pipeline, hydrogen fuel is supplied to the micro combustion holes on two sides of the conveying pipeline through the conveying pipeline, and the micro combustion holes on two sides share one conveying pipeline, so that the structure is simplified.
Preferably, the body is further provided with a fuel manifold, and a plurality of the delivery pipes are communicated with the fuel manifold in a parallel arrangement mode and are used for distributing hydrogen fuel to a plurality of the delivery pipes.
In the scheme, the plurality of conveying pipelines are arranged in parallel and communicated with the fuel main pipe, so that layered supply of hydrogen fuel is realized, different equivalent ratios can be allocated on different layers, and natural frequencies for inducing combustion oscillation are avoided more flexibly.
Preferably, the body is further provided with a cooling air slit and a cooling hole, the cooling hole is communicated with the cooling air slit, an outlet of the cooling hole is positioned between two adjacent layers of micro combustion holes, and cooling air enters the head of the combustion chamber through the cooling air slit and flows into the combustion zone through the cooling hole; and/or, the adjacent two layers of the micro combustion holes are staggered.
In the scheme, the cooling gas slits and the cooling holes are arranged, the cooling gas enters the head of the combustion chamber through the cooling gas slits and flows into the combustion zone through the cooling holes, the cooling gas not only cools the head of the combustion chamber, but also is positioned between two adjacent layers of miniature combustion holes, and the cooling gas can also play a role in separating each small flame, so that the flames are effectively prevented from being connected in series; the adjacent two layers of the micro combustion holes are arranged in a staggered manner, so that the series connection of the flame root parts of the adjacent two layers of the micro combustion holes can be further reduced or prevented.
Preferably, a boss is arranged at the downstream of the micro combustion hole airflow.
In the scheme, the boss is arranged at the downstream of the airflow of the micro combustion hole, and a larger backflow area can be formed at the downstream through the boss, so that flame can be well stabilized.
Preferably, the outlet section of the micro combustion hole is arch-shaped.
In the scheme, the section of the outlet of the miniature combustion hole is arranged into an arch shape, so that cooling gas for cooling the head of the combustion chamber can enter through the annular cooling gas slits which are distributed radially.
The invention also provides a combustion chamber, which comprises the flame tube and further comprises the combustion chamber head, wherein the combustion chamber head is positioned at the end part of the flame tube.
The invention also provides a gas turbine comprising the combustion chamber.
The invention has the positive progress effects that: the body of the combustion chamber is provided with a plurality of micro combustion holes to realize micropore lean combustion, so that the contact area of fuel and air can be increased, NOX emission is reduced, an airflow channel of the micro combustion holes adopts a shape of shrinking before expanding, the flow characteristics of fluid are utilized, the upstream shrinkage section is utilized to accelerate incoming flow so as to reduce backfire danger, the downstream expansion section is utilized to ensure that the flame surface expands outwards, and enough space is reserved for a backflow area, namely, backfire is effectively prevented through a flow channel structure with the upstream shrinkage section and the downstream expansion section.
Drawings
FIG. 1 is a cross-sectional view of a combustion chamber according to an embodiment of the present invention.
FIG. 2 is a partial view of a combustion chamber head of an embodiment of the present invention.
FIG. 3 is a partial cross-sectional view of a combustion chamber head in accordance with one embodiment of the present invention.
Fig. 4 is a partially enlarged view of fig. 3 at a.
FIG. 5 is yet another partial cross-sectional view of a combustion chamber head of an embodiment of the present invention.
Description of the reference numerals
Combustion chamber head 1
Body 2
Micro combustion hole 3
Delivery pipe 4
Spout 5
Fuel manifold 6
Cooling gas slit 7
Cooling holes 8
Boss 9
Combustion chamber 10
Detailed Description
The invention is further illustrated by means of the following examples, which are not intended to limit the scope of the invention.
The invention provides a combustion chamber head, a combustion chamber and a gas turbine. As shown in fig. 2-5, the combustion chamber head comprises a body 2, a plurality of micro combustion holes 3, a conveying pipeline 4 and a plurality of nozzles 5 are arranged on the body 2, an air flow channel of the micro combustion holes 3 penetrates through the body 2, the upstream of the air flow channel of the micro combustion holes 3 is a contraction section, and the downstream is an expansion section; the delivery pipe 4 is used for supplying hydrogen fuel to the micro combustion holes 3; the nozzles 5 are in one-to-one correspondence with the micro combustion holes 3, and the nozzles 5 are close to the outlets of the corresponding micro combustion holes 3 and are communicated with the conveying pipeline 4 and the micro combustion holes 3. The micro-porous lean combustion is realized by arranging the micro combustion holes 3 on the body 2 of the combustion chamber 10, the contact area of fuel and air can be increased, the emission of NOX is reduced, the airflow channel of the micro combustion holes 3 adopts a shape which is contracted firstly and then expanded, the fluid flow characteristic is utilized, the upstream contraction section is utilized to accelerate incoming flow so as to reduce the backfire risk, the downstream expansion section is utilized to ensure that the flame surface is expanded outwards, and enough space is reserved for the backflow area, namely, backfire can be effectively prevented through the flow channel structure with the upstream contraction section and the downstream expansion section.
In this embodiment, the combustion chamber head is annular and is formed by integrating a plurality of fan-shaped annular bodies 2 as shown in fig. 2, but in other embodiments, the combustion chamber head may be formed integrally by a whole ring.
As shown in fig. 5, the normal direction of the nozzle 5 is 90 ° to the flow direction of the air flow in the micro combustion hole 3. The normal direction of the nozzle 5 is 90 degrees with the flow direction of the air flow in the micro combustion hole 3, so that the hydrogen fuel injected by the nozzle 5 enters the micro combustion hole 3 in a transverse injection mode, and is quickly mixed with the air in the air flow channel of the micro combustion hole 3 for combustion, so that local hot spots are eliminated, the gas temperature is reduced, and the emission of NOx can be inhibited.
In this embodiment, the normal direction of the nozzle 5 and the flow direction of the air flow in the micro combustion hole 3 are set at 90 degrees, but may be set adjacent to 90 degrees in other embodiments, so that the hydrogen fuel injected by the nozzle enters the micro combustion hole in a transverse injection manner, for example, the angle between the normal direction of the nozzle 5 and the flow direction of the air flow in the micro combustion hole 3 may be 80-90 degrees.
As shown in fig. 2 to 4, the micro combustion holes 3 are provided with a plurality of circles along the circumferential direction of the body 2, and the plurality of circles of micro combustion holes 3 are distributed in a plurality of layers on the body 2. Through arranging the multiturn combustion hole on body 2 to multiturn miniature combustion hole 3 becomes the multilayer setting, can split into a large amount of little flames with the flame of combustion zone, increase the area of contact of fuel and air.
As shown in fig. 2 to 3, the number of the transfer pipes 4 is several, and each transfer pipe 4 is provided between the adjacent two layers of the micro combustion holes 3 for supplying hydrogen fuel to the micro combustion holes 3 on both sides thereof. The micro combustion holes 3 are distributed on two sides of the conveying pipeline 4, hydrogen fuel is provided for the micro combustion holes 3 on two sides of the conveying pipeline 4, and the micro combustion holes 3 on two sides share one conveying pipeline 4, so that the structure is simplified.
As shown in fig. 2, the body 2 is further provided with a fuel manifold 6, and a plurality of delivery pipes 4 are communicated with the fuel manifold 6 in a parallel arrangement for distributing hydrogen fuel to the plurality of delivery pipes 4. The plurality of conveying pipelines 4 are arranged in parallel and communicated with the fuel main pipe 6 to realize layered supply of hydrogen fuel, and different equivalent ratios can be allocated on different layers, so that natural frequencies for inducing combustion oscillation are avoided more flexibly.
In the present embodiment, a plurality of fuel manifolds 6 are provided and distributed on the fan-shaped annular body 2, however, in other embodiments, one fuel manifold 6 may be provided, and the hydrogen fuel is delivered to the multi-layer delivery pipeline through the fuel manifold 6, so as to realize layered supply of the hydrogen fuel.
As shown in fig. 2 and 5, the body 2 is further provided with a cooling air slit 7 and a cooling hole 8, the cooling hole 8 is communicated with the cooling air slit 7, an outlet of the cooling hole 8 is positioned between two adjacent layers of micro combustion holes 3, and cooling air enters the combustion chamber head 1 through the cooling air slit 7 and flows into the combustion zone through the cooling hole 8.
Through set up cooling gas slit 7 and cooling hole 8 on body 2 to communicate cooling hole 8 to cooling gas slit 7, thereby make the cooling gas get into combustion chamber head 1 through cooling gas slit 7 and flow into the combustion zone through cooling hole 8, the cooling gas not only can cool down combustion chamber head 1, and cooling hole 8 is located between adjacent two-layer miniature combustion hole 3 in addition, and the cooling gas can also play the effect of separating every little flame, effectively prevents the flame series connection.
As shown in fig. 2-4, adjacent two layers of micro combustion holes 3 are staggered. The adjacent two layers of micro combustion holes 3 are arranged in a staggered manner, so that the series connection of the flame root parts of the adjacent two layers of micro combustion holes 3 can be reduced or prevented.
As shown in fig. 5, a boss 9 is provided downstream of the micro combustion hole 3 in the air flow. By providing the boss 9 downstream of the micro burner port 3, a larger recirculation zone can be formed downstream, and the flame can be stabilized better.
As shown in fig. 4, the outlet section of the micro combustion hole 3 is arch-shaped, so that the cooling air of the cooling head part can enter through the annular cooling air slits 7 distributed in radial direction, and the hydraulic diameter of the outlet section of the micro combustion hole 3 is preferably in the range of 1.5mm-3mm.
As shown in fig. 1, the present invention further provides a combustion chamber 10, which includes a flame tube, and further includes the aforementioned combustion chamber head 1, which is located at an end of the flame tube.
The present invention also provides a gas turbine comprising the aforementioned combustor 10.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the principles and spirit of the invention, but such changes and modifications fall within the scope of the invention.
Claims (10)
1. The utility model provides a combustion chamber head, includes the body, its characterized in that is provided with on the body:
the airflow channels of the micro combustion holes penetrate through the body, the upstream parts of the airflow channels of the micro combustion holes are contraction sections, and the downstream parts of the airflow channels of the micro combustion holes are expansion sections;
a delivery conduit for supplying hydrogen fuel to the micro combustion holes;
the nozzles are in one-to-one correspondence with the micro combustion holes, and are close to the corresponding outlets of the micro combustion holes and communicated with the conveying pipeline and the micro combustion holes.
2. The combustor head of claim 1, wherein a normal direction of said ports is 90 ° from a flow direction of air flow in said micro-combustion holes.
3. The combustor head of claim 1, wherein said micro-combustor holes are provided with a plurality of turns along the circumference of said body, said plurality of turns being distributed in multiple layers on said body.
4. The combustion chamber head as in claim 3 wherein said plurality of transfer ducts are provided and each of said transfer ducts is disposed between two adjacent layers of said micro-combustion holes for supplying hydrogen fuel to the micro-combustion holes on both sides thereof.
5. The combustion chamber head of claim 4 wherein said body further includes a fuel manifold, a plurality of said transfer tubes communicating with said fuel manifold in a parallel arrangement for distributing hydrogen fuel to a plurality of said transfer tubes.
6. The combustion chamber head as claimed in claim 3, wherein the body is further provided with a cooling gas slit and a cooling hole, the cooling hole is communicated with the cooling gas slit, an outlet of the cooling hole is positioned between two adjacent layers of the micro combustion holes, and cooling gas enters the combustion chamber head through the cooling gas slit and flows into the combustion zone through the cooling hole; and/or the micro combustion holes of two adjacent layers are staggered.
7. The combustor head of claim 1, wherein a boss is disposed downstream of said micro-combustor flow.
8. The combustor head of claim 6, wherein said micro-combustor has an exit cross-section that is arched.
9. A combustion chamber comprising a flame tube, wherein the combustion chamber further comprises a combustion chamber head as claimed in any one of claims 1 to 8, the combustion chamber head being located at an end of the flame tube.
10. A gas turbine comprising a combustion chamber according to claim 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210144280.8A CN116658935A (en) | 2022-02-17 | 2022-02-17 | Combustion chamber head, combustion chamber, gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210144280.8A CN116658935A (en) | 2022-02-17 | 2022-02-17 | Combustion chamber head, combustion chamber, gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116658935A true CN116658935A (en) | 2023-08-29 |
Family
ID=87708461
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210144280.8A Pending CN116658935A (en) | 2022-02-17 | 2022-02-17 | Combustion chamber head, combustion chamber, gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116658935A (en) |
-
2022
- 2022-02-17 CN CN202210144280.8A patent/CN116658935A/en active Pending
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