CN209782713U - Combustion chamber of gas turbine and gas turbine - Google Patents
Combustion chamber of gas turbine and gas turbine Download PDFInfo
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- CN209782713U CN209782713U CN201822028188.7U CN201822028188U CN209782713U CN 209782713 U CN209782713 U CN 209782713U CN 201822028188 U CN201822028188 U CN 201822028188U CN 209782713 U CN209782713 U CN 209782713U
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Abstract
the utility model relates to a gas turbine technical field discloses a combustion chamber and gas turbine of gas turbine, this combustion chamber includes the machine casket and sets up the flame tube in the machine casket, and the head of flame tube is equipped with main combustion level fuel assembly and pre-combustion level fuel assembly, wherein, main combustion level fuel assembly includes main combustion level pipeline and sets up the main combustion level swirler between main combustion level pipeline and flame tube, the air inlet of main combustion level swirler communicates with the air intake on the machine casket, the fuel inlet of main combustion level swirler communicates with main combustion level pipeline; the pre-combustion stage fuel assembly comprises a pre-combustion stage pipeline, a pre-combustion stage nozzle is arranged at one end, facing the flame tube, of the pre-combustion stage pipeline, a plurality of jet holes are formed in the pre-combustion stage nozzle in the circumferential direction, an included angle with an opening deviating from the flame tube is formed between the axis of each jet hole and the axis of the pre-combustion stage nozzle, and the included angle is an acute angle.
Description
Technical Field
The utility model relates to a gas turbine technical field especially relates to a gas turbine's combustion chamber and gas turbine.
background
in a micro gas turbine, the temperature at the time of combustion of gas in a combustion chamber has a great influence on NOx, and the production amount and production rate of NOx increase exponentially with the rise of the combustion temperature. Therefore, the key to reducing the NOx emission of the micro gas turbine is to control the temperature in the combustion chamber to a low level (typically 1700K-1900K, which affects the combustion efficiency) and to make the temperature distribution in the combustion chamber uniform.
At present, a low NOx emission combustion chamber mainly comprises a fuel oil grading combustion chamber, a lean oil premixing and pre-evaporation combustion chamber, a lean oil direct injection combustion chamber and a rich oil combustion-quenching-lean oil combustion chamber, wherein the lean oil premixing and pre-evaporation combustion chamber has a larger limit on reducing NOx compared with other combustion chambers, the NOx emission can be reduced to a very low degree, the combustion is divided into a main combustion stage and a pre-combustion stage, the pre-combustion stage occupies a small amount of fuel and plays a role of a stable ignition source for diffusion combustion, the main combustion stage is ignited to enable the main combustion stage to stably combust, the main combustion stage occupies most of fuel, the main combustion stage is lean premixed combustion, the combustion temperature is low, and the reduction of the emission of nitrogen oxides is facilitated.
The lean extinction limit of the precombustion stage largely determines the amount of gas that can be distributed to the premixed main combustion stage, and the higher the proportion of gas that participates in premixing, the greater the potential for NOx reduction. In the prior art, the premixing-stage gas injection is usually diffusion injection, so that the gas is excessively dispersed, and the duty-stage flameout equivalence ratio cannot be further reduced.
SUMMERY OF THE UTILITY MODEL
the utility model provides a gas turbine's combustion chamber and gas turbine for reduce and fire out the equivalence ratio in the precombustion level, thereby make more gas distribute to premix the primary, further reduce NOx's emission.
An embodiment of the utility model provides a gas turbine's combustion chamber, this combustion chamber include the machine casket and set up the flame tube in the machine casket, just the head of flame tube is equipped with main burning level fuel assembly and precombustion level fuel assembly, wherein:
The main combustion stage fuel assembly comprises a main combustion stage pipeline and a main combustion stage swirler arranged between the main combustion stage pipeline and the flame tube, an air inlet of the main combustion stage swirler is communicated with an air inlet on the casing, and a fuel inlet of the main combustion stage swirler is communicated with the main combustion stage pipeline;
The pre-burning stage fuel assembly comprises a pre-burning stage pipeline, the pre-burning stage pipeline faces towards one end of the flame tube, a pre-burning stage nozzle is arranged at one end of the flame tube, a plurality of spray holes are arranged on the pre-burning stage nozzle along the circumferential direction, an opening deviates from an included angle of the flame tube by the aid of the axis of each spray hole and the axis of the pre-burning stage nozzle, and the included angle is an acute angle.
in the above embodiment, the plurality of injection holes are circumferentially arranged on the pre-combustion stage nozzle, and an included angle with an opening direction departing from the flame tube is formed between the axis of the injection holes and the axis of the pre-combustion stage nozzle, and the included angle is an acute angle, so that the pre-combustion stage nozzle can form gathering injection, the concentration of the pre-combustion stage fuel is improved, the pre-combustion stage flameout equivalence ratio is reduced, more fuel is distributed to the pre-combustion main stage, and the emission of NOx is further reduced.
when the pre-combustion stage nozzle is specifically arranged, the pre-combustion stage nozzle comprises a bottom wall and one end fixedly connected to the side wall of the bottom wall, the plurality of spray holes are formed in the bottom wall, and the bottom wall is inwards recessed to form a concave cavity along the direction deviating from the flame tube.
Optionally, the main combustion stage swirler is a radial swirler and includes a swirler top plate, a swirler bottom plate, and a plurality of vanes disposed between the swirler top plate and the swirler bottom plate;
the annular gap between the inner sleeve and the outer sleeve forms a main combustion stage premixing cavity. After the air enters the main combustion stage premixing cavity through the blades, the flow velocity is further improved, and tempering can be effectively prevented.
Optionally, an annular cavity is arranged in the top plate of the swirler, and a primary combustion stage first channel is formed, and the primary combustion stage first channel is communicated with the primary combustion stage pipeline;
Each blade is of a hollow structure and forms a main combustion stage second channel which is communicated with the main combustion stage first channel;
The surface of each blade is provided with at least one fuel inlet, and the fuel inlets are communicated with the corresponding main combustion stage second channels. By providing the fuel inlet on the vanes, the mixing effect of the fuel and air is improved.
The mixing effect of fuel and air can be further improved by reasonably arranging the position of the fuel inlet, and particularly, for each vane, the fuel inlet is arranged on the central line of the vane parallel to the axial direction of the main combustion stage swirler;
follow the flow direction of the main combustion stage fuel in the blade, the blade is equipped with first end and second end in proper order, first end with distance between the second end is h, the fuel entry is apart from the distance of first end is d, and
Optionally, the pre-combustion stage fuel assembly further comprises a pre-combustion stage swirler, the pre-combustion stage swirler is an axial swirler, and an air inlet of the pre-combustion stage swirler is communicated with the air inlet on the casing;
the main combustion stage swirler and the pre-combustion stage swirler are coaxially arranged, and the diameter of an inner sleeve of the main combustion stage swirler is larger than that of an outer sleeve of the pre-combustion stage swirler.
optionally, a gap is formed between an inner sleeve of the main combustion stage swirler and an outer sleeve of the pre-combustion stage swirler, and an annular air cooling channel is formed, and the air cooling channel is communicated with an air inlet on the casing;
the inner sleeve of the main combustion stage swirler and one end, facing the flame tube, of the outer sleeve of the pre-combustion stage swirler are fixedly connected through a connecting plate, and a plurality of pre-combustion stage cooling holes are formed in the connecting plate. When the combustion chamber works, a part of air enters an air cooling channel between the main combustion stage swirler and the pre-combustion stage swirler and is sprayed out from the pre-combustion stage cooling holes, so that the cooling effect is achieved, and an outer sleeve of the pre-combustion stage swirler is protected from being burnt.
Specifically, one end, facing the flame tube, of the outer sleeve of the pre-combustion stage swirler is located inside the inner sleeve of the main combustion stage swirler, and the connecting plate forms a horn-shaped structure with an opening facing the flame tube.
In order to protect the head part of the flame tube from being burnt, a plurality of head part cooling holes are formed in the side wall of the head part of the flame tube.
The embodiment of the utility model provides a gas turbine is still provided, including any one of the aforesaid combustor, in this combustor, through precombustion level fuel gathering formula spouting, realize lower flame-out equivalence ratio for more fuel participate in premixed combustion, further reduced NOx's emission.
Drawings
Fig. 1 is a cross-sectional view of a combustion chamber provided in an embodiment of the present invention;
FIG. 2 is a cross-sectional view of the assembled main and precombustion stage fuel assemblies provided by an embodiment of the present invention;
FIG. 3 is a half-sectional view of the main stage fuel assembly and the pre-stage fuel assembly shown in FIG. 2, as assembled;
FIG. 4 is a cross-sectional view of a pre-combustion stage showerhead in accordance with an embodiment of the present invention;
fig. 5 is a cross-sectional view of a flame tube according to an embodiment of the invention.
Reference numerals:
10-casing 11-air inlet
20-flame tube 21-head cooling hole 22-mixing hole
30-main combustion stage pipeline 40-main combustion stage swirler
401-fuel inlet 41-swirler top plate 42-swirler bottom plate 43-vanes
44-premixing cavity of main combustion stage 45-first channel of main combustion stage
50-precombustion stage pipeline 60-precombustion stage spray head 61-bottom wall 62-side wall 601-spray hole
70-precombustion stage swirler 80-air cooling channel 90-connecting plate 91-precombustion stage cooling hole
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention clearer, the present invention will be described in further detail with reference to the accompanying drawings, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
the embodiment of the utility model provides a gas turbine's combustion chamber, this combustion chamber are lean oil and mix the pre-evaporation combustion chamber in advance to, through precombustion level fuel in the flame tube gathering formula is spouted, realized lower flame-out equivalence ratio, and make more fuel participate in the main grade and mix the burning in advance, further reduced NOx's emission.
Specifically, this combustion chamber includes the quick-witted casket and sets up the flame tube in the quick-witted casket, and the head of flame tube is equipped with main burning level fuel assembly and precombustion level fuel assembly, wherein:
The main combustion stage fuel assembly comprises a main combustion stage pipeline and a main combustion stage swirler arranged between the main combustion stage pipeline and the flame tube, an air inlet of the main combustion stage swirler is communicated with an air inlet on the casing, and a fuel inlet of the main combustion stage swirler is communicated with the main combustion stage pipeline;
the pre-combustion stage fuel assembly comprises a pre-combustion stage pipeline, a pre-combustion stage nozzle is arranged at one end, facing the flame tube, of the pre-combustion stage pipeline, a plurality of jet holes are formed in the pre-combustion stage nozzle in the circumferential direction, an included angle with an opening deviating from the flame tube is formed between the axis of each jet hole and the axis of the pre-combustion stage nozzle, and the included angle is an acute angle.
In the above embodiment, a plurality of injection holes are circumferentially arranged on the pre-combustion stage nozzle, and an included angle is formed between the axis of the injection holes and the axis of the pre-combustion stage nozzle, wherein the opening direction of the included angle is away from the flame tube, and the included angle is an acute angle, that is, the injection directions of the injection holes are all gathered towards a certain point in the flame tube when the included angle is set, so that a gathering type injection is formed, the concentration degree of the pre-combustion stage fuel is improved, the flameout equivalence ratio of the pre-combustion stage is reduced, more fuel is distributed to the pre-combustion main stage, and the emission of NOx is further reduced.
For a clearer understanding of the structure of the combustion chamber provided by the embodiments of the present invention, reference will now be made to the following detailed description taken in conjunction with the accompanying drawings.
As shown in fig. 1, the combustion chamber includes a casing 10 and a flame tube 20 disposed in the casing 10, the casing 10 covers the flame tube 20 in a clearance fit manner, and at least one air inlet 11 is disposed on a side wall 62; the head of the flame tube 20 is provided with a main combustion stage fuel assembly and a precombustion stage fuel assembly, wherein the main combustion stage fuel assembly comprises a main combustion stage pipeline 30 and a main combustion stage swirler 40 arranged between the main combustion stage pipeline 30 and the flame tube 20, an air inlet of the main combustion stage swirler 40 is communicated with an air inlet 11 on the casing 10, a fuel inlet 401 of the main combustion stage swirler 40 is communicated with the main combustion stage pipeline 30, the main combustion stage pipeline 30 is used for conveying main combustion stage fuel, the main combustion stage fuel enters the main combustion stage swirler 40 from the fuel inlet 401, is premixed with air flowing from the air inlet, and premixed air flow enters the flame tube 20 for combustion reaction; the precombustion stage fuel assembly comprises a precombustion stage pipe 50 for conveying precombustion stage fuel into the flame tube 20, a precombustion stage nozzle 60 is arranged at one end of the precombustion stage pipe 50 facing the flame tube 20, and a plurality of jet holes 601 are circumferentially arranged on the precombustion stage nozzle 60, in order to increase the concentration ratio of the precombustion stage fuel when the precombustion stage fuel is ejected from the jet holes 601, an included angle of an opening, which is far away from the flame tube 20, is formed between the axis of each jet hole 601 and the axis of the precombustion stage nozzle 60, and the included angle is an acute angle, namely, when the precombustion stage fuel is ejected from the jet holes 601, the jet directions of the jet holes 601 are all gathered towards a certain point in the flame tube 20 to form a gathering type jet, so that the precombustion stage fuel is more gathered when being ejected from the jet holes 601, the precombustion stage flameout equivalence ratio is reduced.
The combustion chamber is provided with a main combustion stage and a pre-combustion stage which are independent, wherein the main combustion stage adopts a premixed combustion organization type, and fuel and air are premixed in a main combustion stage swirler 40, enter a flame tube 20 and are combusted under the ignition of pre-combustion stage flame. Specifically, referring to fig. 2 and 3, the main combustion stage swirler 40 is a radial swirler, and includes a swirler top plate 41, a swirler bottom plate 42, and a plurality of vanes 43 disposed between the swirler top plate 41 and the swirler bottom plate 42, where the vanes 43 are arranged along the circumferential direction, and a gap between two adjacent vanes 43 forms an air inlet of the main combustion stage swirler 40. Air and fuel enter the main combustion stage swirler 40 from corresponding inlets respectively and then are premixed, and form rotational flow under the action of the blades 43, so that the mixing effect is further enhanced, meanwhile, in order to improve the flow velocity of premixed air flow and prevent the occurrence of backfire in the combustion process, the main combustion stage swirler 40 further comprises an inner sleeve connected with a swirler top plate 41 and an outer sleeve connected with a swirler bottom plate 42, the inner sleeve and the outer sleeve are coaxially arranged, an annular gap between the inner sleeve and the outer sleeve forms a main combustion stage premixing cavity 44, the main combustion stage premixing cavity 44 is communicated with the flame tube 20, the flow velocity of the premixed air flow in the main combustion stage premixing cavity 44 is further improved, high-speed rotating jet flow is formed at the outlet of the main combustion stage premixing cavity 44, and the occurrence of backfire is effectively prevented.
with continued reference to fig. 2 and 3, an annular cavity is formed in the swirler ceiling 41 and forms a primary combustion stage first passage 45, and the primary combustion stage first passage 45 communicates with the primary combustion stage duct 30; each vane 43 has a hollow structure and forms a second passage of the main combustion stage, which communicates with the first passage 45 of the main combustion stage, and the surface of each vane 43 is provided with at leastOne fuel inlet 401, each fuel inlet 401 communicating with a respective primary fuel stage second passage. In this way, the main combustion stage fuel enters the main combustion stage first channel 45 from the main combustion stage pipe 30, is distributed in the main combustion stage second channel in each blade 43 along the circumferential direction, is finally ejected from the fuel inlet 401, enters the gap between the blades 43, and is mixed with the air flowing in from the air inlet, so that the mixing effect of the fuel and the air is improved. Specifically, for each vane 43, the fuel inlet 401 is disposed on a centerline of the vane 43 parallel to the axial direction of the main stage swirler 40, and, in the flow direction of the main stage fuel within the vane 43, each vane 43 is sequentially provided with a first end and a second end, the distance between the first end and the second end is h, the fuel inlets 401 are spaced from the first end by a distance d, andCan set up 1 ~ 5 fuel entry 401 on every blade 43, through reasonable position and the quantity that sets up fuel entry 401, can further improve the mixed effect of fuel and air.
the pre-burning stage adopts a diffusion burning organization form, occupies a small amount of fuel, plays a role in ignition, and ensures that flame is not extinguished and burning is stable during burning. The precombustion stage fuel is ejected from the precombustion stage nozzle 60, enters the flame tube 20, is diffused and mixed with air, and is combusted, and in the combustion chamber, the precombustion stage nozzle 60 can form a gathering type injection in the flame tube 20, so that the precombustion stage flameout equivalence ratio is reduced, and in a specific arrangement, as shown in fig. 4, the precombustion stage nozzle 60 comprises a bottom wall 61 and a side wall 62, one end of the side wall 62 is fixedly connected to the bottom wall 61, and the side wall 62 is enclosed into a tubular shape and is connected with the precombustion stage pipe 50; wherein, the spray holes 601 are disposed on the bottom wall 61 and distributed along the circumferential direction, and the bottom wall 61 may be configured as a flat plate, or, as shown in fig. 4, the bottom wall 61 is recessed inwards in a direction away from the flame tube 20 to form a concave cavity, so as to further improve the concentration ratio of the pre-combustion stage fuel. It should be noted that, besides being arranged circumferentially, the injection holes 601 may also be arranged in other similar arrangements, such as randomly distributed, and the like, which are not listed here.
In order to ensure that the pre-combustion stage fuel can be fully combusted in the flame tube 20, the pre-combustion stage fuel assembly further comprises a pre-combustion stage swirler 70, the pre-combustion stage swirler 70 is an axial swirler, and an air inlet of the pre-combustion stage swirler 70 is communicated with an air inlet 11 on the casing 10; referring to fig. 1 and 2 together, the main stage swirler 40 is arranged coaxially with the pre-stage swirler 70, and the diameter of the inner sleeve of the main stage swirler 40 is larger than that of the outer sleeve of the pre-stage swirler 70. In the combustion chamber, the main combustion stage swirler 40 and the pre-combustion stage swirler 70 are used for respectively providing required air for main combustion stage fuel and pre-combustion stage fuel, wherein the ratio of the air intake amount of the main combustion stage swirler 40 and the pre-combustion stage swirler 70 is kept within the range of 10: 1-4: 1. In addition, a gap is arranged between the inner sleeve of the main combustion stage swirler 40 and the outer sleeve of the pre-combustion stage swirler 70, an annular air cooling channel 80 is formed, and the air cooling channel 80 is communicated with the air inlet 11 on the casing 10; the inner sleeve of the main combustion stage swirler 40 and one end of the outer sleeve of the pre-combustion stage swirler 70 facing the flame tube 20 are fixedly connected through a connecting plate 90, and a plurality of pre-combustion stage cooling holes 91 are formed in the connecting plate 90. When the combustion chamber works, a part of air enters the air cooling channel 80 between the main combustion stage swirler 40 and the pre-combustion stage swirler 70 and is sprayed out from the pre-combustion stage cooling holes 91, so that the cooling effect is achieved, and the outer sleeve of the pre-combustion stage swirler 70 is protected from being burnt. Specifically, the end of the outer sleeve of the pre-combustion stage swirler 70 facing the combustor basket 20 is located inside the inner sleeve of the main combustion stage swirler 40, so that the connecting plate 90 forms a trumpet-shaped structure opening to the combustor basket 20, and further plays a role in protection.
In addition to the pre-combustion stage cooling holes 91, as shown in fig. 5, in the combustion chamber, a head cooling hole 21 may be further disposed on a side wall of a head portion of the combustor basket 20, the head cooling hole 21 may protect the head portion of the combustor basket 20 from being burnt, the pre-combustion stage cooling holes 91 and the head cooling hole 21 have a hole diameter of 0.8mm to 1.5mm, and a hole diameter too small to effectively form a film cooling, so as not to achieve a purpose of protecting the head portions of the pre-combustion stage swirler 70 and the combustor basket 20; too large a hole diameter may quench part of the combustion process, thereby reducing the ultimate operating efficiency of the combustion chamber. With continued reference to fig. 5, a plurality of mixing holes 22 are further disposed on the sidewall of the body of the flame tube 20 at intervals in a surrounding manner, the number of the mixing holes 22 may be 6 to 12, the aperture is in the range of 8mm to 20mm, and the plurality of mixing holes 22 enable the mixing air to enter the flame tube 20 more uniformly, so that the air and the high-temperature flue gas are mixed more uniformly, and the uniformity of the temperature of the outlet airflow of the combustion chamber and the energy utilization rate of the combustion chamber are improved.
When the combustor specifically works, high-pressure air compressed by a compressor enters the casing 10 from the air inlet 11, then the air enters the main combustion stage and the pre-combustion stage from the air inlet of the main combustion stage swirler 40 and the air inlet of the pre-combustion stage swirler 70 respectively, the air intake ratio of the main combustion stage and the pre-combustion stage is in the range of 10:1 to 4:1, part of the rest air passes through the head cooling hole 21 and the pre-combustion stage cooling hole 91 to play a cooling role so as to protect the head of the flame tube 20 and the outer sleeve of the pre-combustion stage swirler 70 from being burnt, and the rest air enters from the mixing hole 22 to adjust the distribution of the outlet temperature of the combustion chamber; the pre-combustion stage fuel enters the pre-combustion stage from the pre-combustion stage pipeline 50 and is ejected from the pre-combustion stage jet holes 601, the pre-combustion stage fuel and air entering the pre-combustion stage are mixed and combusted until the gas turbine reaches a specified working condition, the gas enters the annular main combustion stage first channel 45 from the main combustion stage pipeline 30 and is ejected from the fuel inlet 401 through the main combustion stage blades 43, the main combustion stage fuel and the air entering the main combustion stage are mixed and are ejected from the outlet after passing through the main combustion stage premixing cavity 44, and the gas is combusted under the ignition of the pre-combustion stage flame, the proportion of the main combustion stage and the pre-combustion stage gas after stable combustion is 7:1 to 4:1, the pre-combustion stage gas can be completely closed, and only the main combustion stage is combusted.
As can be seen from the above description, in the embodiment of the present invention, through set up a plurality of orifices 601 along circumference on precombustion stage nozzle 60, and make the axis of these orifices 601 and the axis of precombustion stage nozzle 60 between have the contained angle that the opening direction deviates from flame tube 20, and this contained angle is the acute angle, make like this to form the gathering formula by precombustion stage nozzle 60 and spout, the concentration degree of precombustion stage fuel has been improved, precombustion stage flame-out equivalence ratio has been reduced, thereby make more fuel distribute to and premix the main stage, further reduce NOx's emission.
The embodiment of the utility model provides a still provide a gas turbine, this gas turbine include any one of the above-mentioned combustion chamber, in this combustion chamber, through precombustion level fuel gathering formula injection, realize lower flame-out equivalence ratio for more fuel participates in premixed combustion, has further reduced NOx's emission.
It will be apparent to those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims and their equivalents, the present invention is also intended to include such modifications and variations.
Claims (10)
1. A combustion chamber of a gas turbine is characterized by comprising a casing and a flame tube arranged in the casing, wherein the head part of the flame tube is provided with a main combustion stage fuel assembly and a pre-combustion stage fuel assembly,
The main combustion stage fuel assembly comprises a main combustion stage pipeline and a main combustion stage swirler arranged between the main combustion stage pipeline and the flame tube, an air inlet of the main combustion stage swirler is communicated with an air inlet on the casing, and a fuel inlet of the main combustion stage swirler is communicated with the main combustion stage pipeline;
The pre-burning stage fuel assembly comprises a pre-burning stage pipeline, the pre-burning stage pipeline faces towards one end of the flame tube, a pre-burning stage nozzle is arranged at one end of the flame tube, a plurality of spray holes are arranged on the pre-burning stage nozzle along the circumferential direction, an opening deviates from an included angle of the flame tube by the aid of the axis of each spray hole and the axis of the pre-burning stage nozzle, and the included angle is an acute angle.
2. The combustor of claim 1, wherein the pre-combustion stage nozzle comprises a bottom wall and a side wall with one end fixedly connected to the bottom wall, the plurality of nozzle holes are formed in the bottom wall, and the bottom wall is recessed inward in a direction away from the liner to form a cavity.
3. The combustor of claim 1, wherein the primary combustion stage swirler is a radial swirler comprising a swirler top plate, a swirler bottom plate, and a plurality of vanes disposed between the swirler top plate and the swirler bottom plate;
The annular gap between the inner sleeve and the outer sleeve forms a main combustion stage premixing cavity.
4. the combustor of claim 3, wherein an annular cavity is provided in the swirler ceiling and forms a primary combustion stage first passage that communicates with the primary combustion stage conduit;
Each blade is of a hollow structure and forms a main combustion stage second channel which is communicated with the main combustion stage first channel;
the surface of each blade is provided with at least one fuel inlet, and the fuel inlets are communicated with the corresponding main combustion stage second channels.
5. the combustor of claim 4, wherein for each vane, the fuel inlet is disposed on a centerline of the vane parallel to an axial direction of the main combustion stage swirler;
Follow the flow direction of the main combustion stage fuel in the blade, the blade is equipped with first end and second end in proper order, first end with distance between the second end is h, the fuel entry is apart from the distance of first end is d, and
6. The combustor of claim 3, wherein the pre-stage fuel assembly further comprises a pre-stage swirler, the pre-stage swirler is an axial swirler, and an air inlet of the pre-stage swirler is communicated with an air inlet on the casing;
The main combustion stage swirler and the pre-combustion stage swirler are coaxially arranged, and the diameter of an inner sleeve of the main combustion stage swirler is larger than that of an outer sleeve of the pre-combustion stage swirler.
7. The combustor of claim 6, wherein a gap is formed between an inner sleeve of the main stage swirler and an outer sleeve of the pre-stage swirler, and an annular air cooling passage is formed, and the air cooling passage is communicated with an air inlet on the casing;
The inner sleeve of the main combustion stage swirler and one end, facing the flame tube, of the outer sleeve of the pre-combustion stage swirler are fixedly connected through a connecting plate, and a plurality of pre-combustion stage cooling holes are formed in the connecting plate.
8. The combustor of claim 7, wherein an end of the outer sleeve of the pre-stage swirler that faces the combustor basket is located inside an inner sleeve of the main stage swirler, and the connecting plate forms a trumpet structure that opens to the combustor basket.
9. the combustor of claim 1, wherein a plurality of head cooling holes are provided in a sidewall of said liner head.
10. a gas turbine comprising the combustor according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822028188.7U CN209782713U (en) | 2018-12-04 | 2018-12-04 | Combustion chamber of gas turbine and gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822028188.7U CN209782713U (en) | 2018-12-04 | 2018-12-04 | Combustion chamber of gas turbine and gas turbine |
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| CN209782713U true CN209782713U (en) | 2019-12-13 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109404967A (en) * | 2018-12-04 | 2019-03-01 | 新奥能源动力科技（上海）有限公司 | A kind of combustion chamber of gas turbine and gas turbine |
| CN114110662A (en) * | 2021-11-25 | 2022-03-01 | 同济大学 | Low-nitrogen combustion chamber of gas turbine |
-
2018
- 2018-12-04 CN CN201822028188.7U patent/CN209782713U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109404967A (en) * | 2018-12-04 | 2019-03-01 | 新奥能源动力科技（上海）有限公司 | A kind of combustion chamber of gas turbine and gas turbine |
| CN109404967B (en) * | 2018-12-04 | 2024-04-05 | 新奥能源动力科技（上海）有限公司 | Combustion chamber of gas turbine and gas turbine |
| CN114110662A (en) * | 2021-11-25 | 2022-03-01 | 同济大学 | Low-nitrogen combustion chamber of gas turbine |
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