CN107676815B - Combustor and gas turbine with same - Google Patents
Combustor and gas turbine with same Download PDFInfo
- Publication number
- CN107676815B CN107676815B CN201710791240.1A CN201710791240A CN107676815B CN 107676815 B CN107676815 B CN 107676815B CN 201710791240 A CN201710791240 A CN 201710791240A CN 107676815 B CN107676815 B CN 107676815B
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- Prior art keywords
- flow guide
- combustor
- peripheral
- guide sleeve
- nozzle
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
Abstract
The invention discloses a combustor and a gas turbine with the combustor, wherein the combustor comprises a combustion chamber outer cylinder, a flame tube, a central nozzle, a plurality of peripheral nozzles, a flow guide sleeve and a flow guide bent plate; the flame tube, the central nozzle and the plurality of peripheral nozzles are respectively arranged in the outer combustion chamber cylinder; the flow guide sleeve is sleeved in the outer combustion chamber cylinder and connected with the rear end of the flame tube, the flow guide sleeve is sleeved outside the peripheral nozzles, and flow guide holes corresponding to the peripheral nozzles are formed in the flow guide sleeve; the flow guide bent plate is arranged in the flow guide sleeve and positioned at the rear side of the flow guide hole and used for guiding air in a space between the flow guide sleeve and the peripheral nozzle to a first outer side space and a second outer side space respectively. The invention can effectively adjust the flow direction of the air flow, reduce the pressure loss when the air reverses, increase the uniformity of the peripheral nozzle flow field and the mixing field and improve the combustion performance of the combustor.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a combustor and a gas turbine with the combustor.
Background
In a combustor in the gas turbine, air flows from an annular channel between a combustor outer cylinder and a flame tube of the combustor in a reverse direction to the top and reaches the front ends of a central nozzle and a peripheral nozzle through a guide sleeve, the area between a combustor end cover and the nozzle is reversed, part of the air enters a space close to the combustor outer cylinder in the radial direction of the combustor outer cylinder in the peripheral nozzle, and part of the air enters the space far away from the combustor outer cylinder in the radial direction of the combustor outer cylinder in the central nozzle and/or the peripheral nozzle.
However, the air has a large radial velocity when reversing, so that the air flow rate of the space close to the outer cylinder of the combustor in the peripheral nozzle is far larger than the air flow rate of the space far away from the outer cylinder of the combustor in the peripheral nozzle, and the air flow is not uniform, which easily causes the non-uniform mixing of fuel and air and affects the performance of the combustor.
Disclosure of Invention
The present invention is directed to solving, at least to some extent, one of the technical problems in the related art.
Therefore, the invention provides the combustor of the gas turbine, which can effectively adjust the flow direction of the airflow, reduce the pressure loss during air reversion, increase the uniformity of a peripheral nozzle flow field and a mixing field and improve the combustion performance of the combustor.
The invention also provides a gas turbine.
A combustor of a gas turbine according to an embodiment of an aspect of the present invention includes a combustor basket; the flame tube is arranged in the combustion chamber outer tube; the central nozzle is arranged at the central position in the outer cylinder of the combustion chamber; a plurality of peripheral nozzles disposed within the combustor basket and spaced around the central nozzle; the flow guide sleeve is sleeved in the combustion chamber outer cylinder and is connected with the rear end of the flame tube so as to form an annular channel between the flame tube and the combustion chamber outer cylinder, the flow guide sleeve is sleeved outside the peripheral nozzles and is spaced apart from each peripheral nozzle, the flow guide sleeve is provided with flow guide holes corresponding to the peripheral nozzles respectively, part of air flow in the annular channel enters a space between the flow guide sleeve and the peripheral nozzles from the flow guide holes, and the other part of air flow in the annular channel enters an inner space in the peripheral nozzles and/or the central nozzle through the rear side of the flow guide sleeve; the flow guide bent plate is arranged on the outer wall surface of the peripheral nozzle and located on the rear side of the flow guide hole, and is used for guiding a part of air flow of the space between the flow guide sleeve and the peripheral nozzle to a first outer side space in the peripheral nozzle from the front side of the flow guide bent plate and guiding the other part of air flow of the space between the flow guide sleeve and the peripheral nozzle to a second outer side space of the peripheral nozzle from the rear side of the flow guide bent plate.
According to the combustor of the gas turbine, the flow direction of air flow can be effectively adjusted through the guide holes in the guide sleeve and the guide bent plates in the guide sleeve, the pressure loss during air reversion is reduced, the uniformity of a peripheral nozzle flow field and a mixing field is increased, and the combustion performance of the combustor is improved.
In some embodiments, the deflector bend plate is generally U-shaped opening forward.
In some embodiments, a first section of the flow directing flexural plate extends in the space between the flow directing sleeve and the peripheral nozzle and a second section of the flow directing flexural plate extends downstream toward the peripheral nozzle.
In some embodiments, the first section of the deflector shoe is mounted to the peripheral nozzle by a mounting bracket.
In some embodiments, the deflector vane is substantially sector-annular when viewed in an axial direction of the deflector sleeve.
In some embodiments, a plurality of the peripheral nozzles are uniformly arranged in a circumferential direction of the combustor outer casing.
In some embodiments, the cross section of the outer combustion chamber cylinder is divided into areas corresponding to the peripheral nozzles one by one, each area is provided with one peripheral nozzle, the radian of each area is theta 1, an included angle between two end points of the outer periphery of the flow guiding bent plate and two connecting lines of the center of the outer combustion chamber cylinder is theta 2, and theta 2 is 1/2-1/3 of theta 1.
In some embodiments, the guide bent plate, the guide holes, and the peripheral nozzles correspond one to each other.
In some embodiments, a baffle plate extending forwards is arranged on the front wall surface of the flow guiding bent plate.
In some embodiments, an end cover is provided at the aft end of the combustor basket, and the peripheral nozzles and the central nozzle extend through the end cover into the combustor basket.
According to another aspect of the invention, a fuel turbine is provided, the gas turbine comprising the combustor of the above-described embodiment.
Drawings
FIG. 1 is a cutaway elevational view of a combustor of a gas turbine according to an embodiment of the present invention;
FIG. 2 is an enlarged partial view of a combustor of a gas turbine according to an embodiment of the present invention;
FIG. 3 is a side view of a combustor of a gas turbine according to an embodiment of the present invention.
Reference numerals:
the combustor outer cylinder 1, the flame tube 2, the central nozzle 3, the peripheral nozzle 4, the flow guide sleeve 5, the flow guide bent plate 6, the first section 61, the second section 62, the annular channel 7, the flow guide hole 8, the outer space 9, the first outer space 91, the second outer space 92, the inner space 10, the area 11, the end cover 12 and the mounting bracket 13.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
As shown in fig. 1 to 3, a combustor of a gas turbine according to an embodiment of the present invention includes a combustor basket 1, a liner 2, a center nozzle 3, a plurality of peripheral nozzles 4, a guide sleeve 5, and a guide bent plate 6.
The liner 2 is disposed within the combustor basket 1 and is radially spaced from the combustor basket 1 to facilitate air entry, as indicated by the arrows on the outside of the liner 2 in FIG. 1.
The center nozzle 3 is provided at a central position in the combustor basket 1 so as to inject fuel into the combustor basket 2.
A plurality of peripheral nozzles 4 are provided in the combustor basket 1 and are spaced around the central nozzle 3 to facilitate fuel injection into the combustor basket 2.
The guide sleeve 5 is arranged in the combustion chamber outer cylinder 1 and connected with the rear end (for example, the left end shown in fig. 1) of the flame tube 2 so that the flame tube 2 and the guide sleeve 5 form an annular channel 7 together with the combustion chamber outer cylinder 4, the guide sleeve 5 is arranged outside the plurality of peripheral nozzles 4 and is spaced apart from each peripheral nozzle 4, the guide sleeve 5 is provided with guide holes 8 respectively corresponding to the peripheral nozzles 4, each peripheral nozzle 4 is spaced apart from the guide sleeve 5, a part of air flow in the annular channel 7 enters a space between the guide sleeve 5 and the peripheral nozzles 4 through the guide holes 8, and the other part of air flow in the annular channel 7 enters an inner space 10 in the peripheral nozzles 7 and/or the central nozzle 3 through the rear side of the guide sleeve 5.
It will be appreciated that the flow directing holes 8 are provided in a plurality and in one-to-one correspondence with the peripheral nozzles 4, i.e. one flow directing hole 8 for each peripheral nozzle 4. Here, the injection direction of the fuel or the mixture of the fuel and the air is "front" and the direction away from the injection direction is "rear", and for example, as shown in fig. 1, the fuel is injected from the left to the right, the left end of the combustor basket 2 is the rear end, and the right end of the combustor basket 2 is the front end. The "inner space" refers to a space inside the peripheral nozzle 4 along the radial direction of the guide sleeve 5 in the peripheral nozzle 4, that is, a space inside the peripheral nozzle 4 radially away from the inner wall surface of the guide sleeve 5 along the radial direction of the guide sleeve 5, and a space outside the peripheral nozzle 4 along the radial direction of the guide sleeve 5 in the peripheral nozzle 4 is an "outer space", that is, a space inside the peripheral nozzle 4 radially close to the inner wall surface of the guide sleeve 5 along the radial direction of the guide sleeve 5.
The deflector bend 6 is disposed in the deflector sleeve 5 and located at the rear side of the deflector hole 8 (e.g., the left side of the deflector hole 8 shown in fig. 1) for guiding a part of the air flow in the space between the deflector sleeve 5 and the peripheral nozzle 4 from the front side (e.g., the right side shown in fig. 1) of the deflector bend 6 to the first outside space 91 in the peripheral nozzle 4 and guiding another part of the air flow in the space between the deflector sleeve 5 and the peripheral nozzle 4 from the rear side (e.g., the left side shown in fig. 1) of the deflector bend 6 to the second outside space 92 of the peripheral nozzle 4. Here, "a first outside space" which is a space between the inner wall of the peripheral nozzle 4 and the flow guide bent plate 6, and "a second outside space" which is a space between the center body of the peripheral nozzle 4 and the flow guide bent plate 6, that is, the first outside space 91 is located outside the second outside space 92 in the radial direction of the peripheral nozzle, are formed in the above-described "outside space".
According to the combustor of the gas turbine, the air in the annular channel can be guided to respectively enter different spaces in the peripheral nozzle through the guide holes in the guide sleeve and the guide bent plates in the guide sleeve, so that the flowing direction of the air flow is effectively adjusted, the pressure loss during air reversion is reduced, the uniformity of a peripheral nozzle flow field and a mixing field is increased, and the combustion performance of the combustor is improved.
In some embodiments, deflector bend plate 6 is generally U-shaped with a forward facing opening (to the right as shown in fig. 1). In some alternative embodiments, a first section 61 of the deflector bend 6 extends in the space between the deflector sleeve 5 and the peripheral nozzle 4, and a second section 62 of the deflector bend 6 extends downstream towards the peripheral nozzle 4. As shown in fig. 1, the second section 62 of the deflector 6 extends from left to right. It will be appreciated that the second section 62 may extend into the peripheral nozzle 4, or may be rearward of the peripheral nozzle 4. In other words, as shown in fig. 1, in the longitudinal section of the combustor outer casing 1, the baffle 6 has a substantially U shape that is open to the right, the first section 61 of the baffle 6 is disposed in the space between the baffle sleeve 5 and the peripheral nozzle 4 and extends in the axial direction of the baffle sleeve 5, and the first section 61 of the baffle 6 is spaced apart from the baffle sleeve 5 and the peripheral nozzle 4, respectively, to divide the space between the baffle sleeve 5 and the peripheral nozzle 4 (the portion corresponding to the baffle 6) into different subspaces. The second section 62 of the baffle bend plate 6 is provided in the outer space 9 and extends in the axial direction of the peripheral nozzle 4 to divide the outer space 9 into a first outer space 91 and a second outer space 92 in the radial direction of the peripheral nozzle 9.
In some embodiments, the first section 61 of the deflector bend plate 6 is mounted to the peripheral nozzles 4 by mounting brackets 13. For example, as shown in fig. 1, one end of the mounting bracket 13 is connected to the peripheral nozzle 4, the other end of the mounting bracket 13 extends toward the guide sleeve 5, and the first section 61 of the deflector bend plate 6 is mounted on the mounting bracket 13. It will be appreciated that a portion of the air flow in the space between the baffle 5 and the peripheral nozzle 4 passes through the mounting bracket 13 into the first outer space 91 at the front side (right side as viewed in fig. 1) of the baffle 6, and another portion of the air flow in the space between the baffle 5 and the peripheral nozzle 4 enters the second outer space 92 at the rear side (left side as viewed in fig. 1) of the baffle 6.
In some embodiments, the deflector bend plate 6 is generally fan-shaped when viewed axially from the deflector sleeve 5. In other words, the deflector bend 6 is substantially sector-annular in cross section of the deflector sleeve 5. It will be appreciated that the outer and inner peripheries of the deflector shoes 6 are arcuate and that each arc is centered on the centre line of the peripheral nozzles 4 or each arc is centered on the centre line of the central nozzle 3.
In some embodiments, a plurality of peripheral nozzles 4 are arranged uniformly in the circumferential direction of the combustor basket 1. It will be appreciated that the central nozzle 3 is located in the centre of the outer combustion casing 1, i.e. the central nozzle 3 is arranged coaxially with the outer combustion casing 1 and a plurality of peripheral nozzles 4 are arranged at regular intervals around the central nozzle 3 in the circumferential direction of the outer combustion casing 1.
In some embodiments, the cross section of the combustor outer cylinder 1 is divided into areas 11 corresponding to the peripheral nozzles 4 one by one, one peripheral nozzle 4 is arranged in each area 11, the radian of each area 11 is theta 1, and an included angle between two connecting lines of two end points of the outer periphery of the flow guiding bent plate 6 and the center of the combustor outer cylinder 1 is theta 2, wherein theta 2 is 1/2-1/3 of theta 1. By arranging the fan-shaped flow guide bent plate in the form, flow errors in each space in the peripheral nozzle can be reduced, and the phenomenon of uneven flow in the peripheral nozzle is improved.
In some embodiments, the deflector shoes 6, the deflector holes 8 and the peripheral nozzles 4 correspond one to each other. In other words, the flow guiding bent plate 6 and the flow guiding holes 8 are provided with a plurality of peripheral nozzles 4, a plurality of flow guiding holes 8 and a plurality of flow guiding bent plates 6, which are in one-to-one correspondence with each other, that is, each peripheral nozzle 4 corresponds to one flow guiding bent plate 6 and one flow guiding hole 8, so that the flow guiding effect is improved, and the pressure loss is effectively reduced.
In some embodiments, a baffle (not shown) extending forward is provided on the front wall of the deflector bend plate 6. Furthermore, the baffle plate is connected between the first section 61 and the second section 62 of the flow guiding bent plate 6 and extends forwards to divide the space enclosed by the flow guiding bent plate 5, so that the problem of asymmetric flow caused by miscellaneous vortexes in the air flow flowing process is effectively solved, and the flow in different spaces in the peripheral nozzle 4 is further balanced. It will be appreciated that the baffles may correspond in the circumferential direction of the shroud 5 to the vanes of the swirler on the front side (right side as viewed in fig. 1) of the combustor to enhance the air and fuel mixing effect.
In some embodiments, the rear end (left end as shown in fig. 1) of the outer casing 1 is provided with an end cover 12 for closing the left end of the outer casing 1, and the peripheral nozzles 4 and the central nozzle 3 respectively extend into the outer casing 1 through the end cover 12. It will be appreciated that the peripheral nozzles 4 and the central nozzle 3 communicate with the flame tube 2, respectively.
A combustor of a gas turbine according to a specific embodiment of the present invention is described below with reference to fig. 1, 2, and 3.
As shown in fig. 1 to 3, the combustor of the gas turbine according to the present invention includes a combustor basket 1, a liner 2, a center nozzle 3, a plurality of peripheral nozzles 4, a guide sleeve 5, a guide bent plate 6, and an end cover 12. The combustor outer cylinder 1, the flame tube 2, the central nozzle 3 and the flow guide sleeve 5 are coaxially arranged, and the cross sections of the combustor outer cylinder 1, the flame tube 2 and the flow guide sleeve 5 are all circular.
The liner 2 is disposed within the outer combustor basket 1 and is radially spaced from the outer combustor basket 1 to facilitate air entry.
The center nozzle 3 is provided in the combustor outer cylinder 1 at the center of the combustor outer cylinder 1 so as to inject fuel into the combustor basket 2.
A plurality of peripheral nozzles 4 are provided in the combustor basket 1 and are arranged around the central nozzle 3 at regular intervals in the circumferential direction of the combustor basket 1, for example, as shown in fig. 3, the number of peripheral nozzles 4 is 8, and 8 peripheral nozzles 4 are arranged around the central nozzle 3 at regular intervals in the circumferential direction so as to inject fuel or a mixture of fuel and air into the combustor basket 2.
An end cover 12 is arranged at the left end of the combustion chamber outer cylinder 1 and used for sealing the left end of the combustion chamber outer cylinder 1, and the peripheral nozzle 4 and the central nozzle 3 respectively penetrate through the end cover 12 to extend into the combustion chamber outer cylinder 1 and are communicated with the flame tube 2.
The flow guide sleeve 5 is arranged in the combustion chamber outer cylinder 1 and is connected with the left end of the flame tube 2 so that an annular channel 7 is formed between the flame tube 2 and the flow guide sleeve 5 and the combustion chamber outer cylinder 4, a plurality of peripheral nozzles 4 are arranged on the inner side of the flow guide sleeve 5, and a plurality of flow guide holes 8 which correspond to the peripheral nozzles 4 one to one are formed in the flow guide sleeve 5. It will be appreciated that the guide sleeve 5 is spaced from the end cap 12, i.e. a gap is left between the left end of the guide sleeve 5 and the end cap 12 to facilitate the passage of part of the air in the annular passage 7 into the peripheral nozzles 4 and the central nozzle 3.
The flow guide bent plates 6 are multiple, the flow guide bent plates 6, the flow guide holes 8 and the peripheral nozzles 4 are in one-to-one correspondence, the flow guide bent plates 6 are arranged on the left sides of the flow guide holes 8 and face towards the right opening of the general U shape, the first sections 61 of the flow guide bent plates 6 extend into the space between the flow guide sleeve 5 and the peripheral nozzles 4, and the first sections 61 of the flow guide bent plates 6 are installed on the peripheral nozzles 4 through the installation supports 13 so as to divide the space between the flow guide sleeve 5 and the peripheral nozzles 4 into outer subspaces and inner subspaces. The second section 62 of the baffle 6 extends inside the peripheral nozzle 4 and in the axial direction of the peripheral nozzle 4 to divide the outer space 9 into a first outer space 91 and a second outer space 92 in the radial direction of the peripheral nozzle 9.
As shown in fig. 3, the baffle 6 is substantially fan-shaped when viewed in the axial direction of the baffle housing 5. It will be appreciated that the outer and inner peripheries of the deflector shoes 6 are arcuate and that each arc is centered on the centre line of the peripheral nozzles 4 or each arc is centered on the centre line of the central nozzle 3.
A part of the air flow in the annular channel 7 enters the space between the guide sleeve 5 and the peripheral nozzle 4 through the guide holes 8, and another part of the air flow in the annular channel 7 enters the inner space 10 in the peripheral nozzle 7 and/or the central nozzle 3. A part of the air flow in the space between the guide sleeve 5 and the peripheral nozzle 4 is guided from the right side of the guide bent plate 6 to the first outside space 91 in the peripheral nozzle 4, and another part of the air flow in the space between the guide sleeve 5 and the peripheral nozzle 4 is guided from the left side of the guide bent plate 6 to the second outside space 92 of the peripheral nozzle 4.
The cross section of the combustion chamber outer cylinder 1 is divided into areas 11 which correspond to the peripheral nozzles 4 one by one, one peripheral nozzle 4 is arranged in each area 11, the radian of each area 11 is theta 1, the included angle between two end points of the outer periphery of the flow guide bent plate 6 and two connecting lines of the center of the combustion chamber outer cylinder 1 is theta 2, wherein the theta 2 is 1/2-1/3 of the theta 1. By arranging the fan-shaped flow guide bent plate in the form, flow errors in each space in the peripheral nozzle can be reduced, and the phenomenon of uneven flow in the peripheral nozzle is improved.
According to an embodiment of another aspect of the invention, a fuel turbine, a gas turbine, comprises the combustor of the above-described embodiment.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
Claims (8)
1. A combustor for a gas turbine, comprising:
a combustion chamber outer cylinder;
the flame tube is arranged in the combustion chamber outer tube;
the central nozzle is arranged at the central position in the outer cylinder of the combustion chamber;
a plurality of peripheral nozzles disposed within the combustor basket and spaced around the central nozzle;
the flow guide sleeve is sleeved in the outer combustion chamber cylinder and is connected with the rear end of the flame tube so as to form an annular channel between the flame tube and the outer combustion chamber cylinder, the flow guide sleeve is sleeved outside the peripheral nozzles and is spaced apart from each peripheral nozzle, the flow guide sleeve is provided with a plurality of flow guide holes respectively corresponding to the peripheral nozzles, the flow guide holes radially penetrate through the peripheral wall of the flow guide sleeve along the flow guide sleeve, a part of air flow in the annular channel enters a space between the flow guide sleeve and the peripheral nozzles from the flow guide holes, and the other part of air flow in the annular channel flows into an inner space in the peripheral nozzles and/or the central nozzle through the rear end of the flow guide sleeve;
the flow guide bent plates are arranged on the outer wall surfaces of the peripheral nozzles and correspond to the peripheral nozzles respectively, the flow guide bent plates are correspondingly located on the rear sides of the flow guide holes respectively, the flow guide bent plates are approximately U-shaped and open forwards, and the flow guide bent plates are used for guiding one part of airflow in the space between the flow guide sleeve and the peripheral nozzles to a first outer side space in the peripheral nozzles from the front sides of the flow guide bent plates and guiding the other part of airflow in the space between the flow guide sleeve and the peripheral nozzles to a second outer side space of the peripheral nozzles from the rear sides of the flow guide bent plates.
2. The gas turbine combustor of claim 1, wherein a first section of the flow guide bent plate extends in a space between the flow guide sleeve and the peripheral nozzle, and a second section of the flow guide bent plate extends downstream toward the peripheral nozzle.
3. The gas turbine combustor of claim 1, wherein the first section of the flow deflection plate is mounted to the peripheral nozzle by a mounting bracket.
4. The gas turbine combustor according to claim 1, wherein the baffle plate is substantially annular sector as viewed in an axial direction of the guide sleeve.
5. The combustor of a gas turbine according to claim 1, wherein a cross section of the outer casing of the combustor is divided into regions corresponding to the peripheral nozzles one by one, each region has one peripheral nozzle, a radian of each region is θ 1, and an angle between two connecting lines between two end points of the outer periphery of the flow guiding bent plate and the center of the outer casing of the combustor is θ 2, where θ 2 is 1/2 to 1/3 of θ 1.
6. The combustor of a gas turbine according to any one of claims 1 to 5, wherein a partition plate extending forward is provided on a front wall surface of the baffle plate.
7. The combustor of a gas turbine according to any one of claims 1 to 5, wherein an end cover is provided to an aft end of the outer combustor can, and the peripheral nozzles and the center nozzle protrude into the outer combustor can through the end cover.
8. A gas turbine comprising a combustor of a gas turbine according to any one of claims 1 to 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710791240.1A CN107676815B (en) | 2017-09-05 | 2017-09-05 | Combustor and gas turbine with same |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710791240.1A CN107676815B (en) | 2017-09-05 | 2017-09-05 | Combustor and gas turbine with same |
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| CN107676815A CN107676815A (en) | 2018-02-09 |
| CN107676815B true CN107676815B (en) | 2020-03-10 |
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| CN201710791240.1A Active CN107676815B (en) | 2017-09-05 | 2017-09-05 | Combustor and gas turbine with same |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10935245B2 (en) * | 2018-11-20 | 2021-03-02 | General Electric Company | Annular concentric fuel nozzle assembly with annular depression and radial inlet ports |
| JP7112342B2 (en) * | 2019-01-25 | 2022-08-03 | 三菱重工業株式会社 | gas turbine combustor and gas turbine |
| US11175046B2 (en) * | 2019-05-09 | 2021-11-16 | General Electric Company | Combustor premixer assembly including inlet lips |
| CN113586245B (en) * | 2021-08-31 | 2022-04-26 | 中国联合重型燃气轮机技术有限公司 | Gas turbine's strutting arrangement and gas turbine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101029741A (en) * | 2006-02-27 | 2007-09-05 | 三菱重工业株式会社 | Combustor |
| CN203880748U (en) * | 2012-10-30 | 2014-10-15 | 通用电气公司 | Combustor |
| CN106287813A (en) * | 2015-06-26 | 2017-01-04 | 三菱日立电力系统株式会社 | Gas turbine burner |
| CN106524222A (en) * | 2015-09-10 | 2017-03-22 | 三菱日立电力系统株式会社 | Gas turbine combustor |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002039533A (en) * | 2000-07-21 | 2002-02-06 | Mitsubishi Heavy Ind Ltd | Combustor, gas turbine, and jet engine |
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2017
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101029741A (en) * | 2006-02-27 | 2007-09-05 | 三菱重工业株式会社 | Combustor |
| CN203880748U (en) * | 2012-10-30 | 2014-10-15 | 通用电气公司 | Combustor |
| CN106287813A (en) * | 2015-06-26 | 2017-01-04 | 三菱日立电力系统株式会社 | Gas turbine burner |
| CN106524222A (en) * | 2015-09-10 | 2017-03-22 | 三菱日立电力系统株式会社 | Gas turbine combustor |
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| CN107676815A (en) | 2018-02-09 |
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