CN107702144B - Combustor and gas turbine with same - Google Patents
Combustor and gas turbine with same Download PDFInfo
- Publication number
- CN107702144B CN107702144B CN201710791237.XA CN201710791237A CN107702144B CN 107702144 B CN107702144 B CN 107702144B CN 201710791237 A CN201710791237 A CN 201710791237A CN 107702144 B CN107702144 B CN 107702144B
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- combustor
- flow
- peripheral
- flow guide
- nozzle
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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
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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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
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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 at the rear side of the flow guide hole and used for guiding airflow into an outer side space in the peripheral nozzle and an inner side space in the peripheral nozzle 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 in the combustion chamber outer cylinder; 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 and between the flow guide sleeve and the combustion chamber outer cylinder, the flow guide sleeve is sleeved outside the peripheral nozzles, and the flow guide sleeve is provided with flow guide holes corresponding to the peripheral nozzles respectively; the flow guiding bent plate is arranged at the rear side of the flow guiding hole and used for guiding one part of air flow in the annular channel from the front side of the flow guiding bent plate to the outer side space in the peripheral nozzle through the flow guiding hole and guiding the other part of air flow from the rear side of the flow guiding bent plate to the inner side space in the peripheral nozzle and/or the central nozzle.
According to the combustor of the gas turbine, the flow direction of air flow can be effectively adjusted through the flow guide bent plate and the flow guide holes in the flow guide bushing, 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 within the annular channel and a second section of the flow directing flexural plate extends downstream toward the peripheral nozzles.
In some embodiments, the deflector bend plate passes through the deflector hole and is connected to a rear sidewall surface of the deflector hole.
In some embodiments, the deflector vane is substantially sector-annular when viewed in an axial direction of the deflector sleeve.
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 inner space 10, the area 11 and the end cover 12.
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 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 flow guide sleeve 5 is arranged in the combustion chamber outer cylinder 1 and connected with the rear end (such as the left end shown in figure 1) 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, the flow guide sleeve 5 is arranged outside the plurality of peripheral nozzles 4, and the flow guide sleeve 5 is provided with flow guide holes 8 corresponding to the peripheral nozzles 4 respectively. 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 baffle bend 6 is disposed behind the baffle hole 8 (e.g., left side as viewed in fig. 1) for directing a portion of the air flow in the annular passage 7 from the front side of the baffle bend 6 (e.g., right side as viewed in fig. 1) through the baffle hole 8 into the outer space 9 in the peripheral nozzle 4 and directing another portion of the air flow from the rear side of the baffle bend 6 (e.g., left side as viewed in fig. 1) into the inner space 10 in the peripheral nozzle 4 and/or the central nozzle 3. Here, the "outer space" refers to a space outside the peripheral nozzle 4 in the radial direction of the guide sleeve 5 in the peripheral nozzle 4, that is, a space inside the peripheral nozzle 4 close to the inner wall surface of the guide sleeve 5 in the radial direction of the guide sleeve 5, and the "inner space" refers to a space inside the peripheral nozzle 4 in the radial direction of the guide sleeve 5 in the peripheral nozzle 4, that is, a space inside the peripheral nozzle 4 away from the inner wall surface of the guide sleeve 5 in the radial direction of the guide sleeve 5.
According to the combustor of the gas turbine, the air in the annular channel can be guided to enter different spaces in the peripheral nozzle through the guide holes in the guide bent plate and the guide bush, so that the flowing direction of the air flow is effectively adjusted, the pressure loss during air reversion is reduced, the uniformity of a flow field and a mixing field of the peripheral nozzle 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 6 extends within the annular channel 7 and a second section 62 of the deflector 6 extends towards the downstream side of 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 on the rear side (e.g., the left side as viewed in FIG. 1) 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 provided in the annular passage 7 and extends in the axial direction of the combustor outer casing 1, and the first section 61 of the baffle 6 is spaced apart from the baffle sleeve 5 and the combustor outer casing 1, respectively, to divide the annular passage 7 (the portion corresponding to the baffle 6) into different sub-annular passages. A second section 62 of the deflector bend 6 is arranged in the outer space 9 and extends in the axial direction of the peripheral nozzle 4.
In some embodiments, the deflector bend plate 6 passes through the deflector hole 8 and is connected to a rear wall surface (a left side wall surface as shown in fig. 1) of the deflector hole 8. In other words, the guide bent plate 6 passes through and is installed on the rear side wall surface of the guide hole 8 from the rear side wall surface of the guide hole 8 to guide a part of the air flow to a space inside the nozzle 4 close to the inner wall surface of the guide sleeve 5 in the radial direction of the guide sleeve 5, and further improve the guide effect. It will be understood that the arrangement of the deflector bend 6 is not limited thereto, for example, the deflector bend 6 is installed at the left end of the deflector sleeve 5, and a part of the air flow can be guided to the outer space 9 through the deflector holes 8.
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, a plurality of flow guide holes 8 are formed in the flow guide sleeve 5, and the flow guide holes 8 correspond to the peripheral nozzles 4 one to one. 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 multiple flow guide bent plates 6 are arranged, 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 in a general U shape, the flow guide bent plates 6 penetrate through the flow guide holes 8 and are connected with the left side wall surfaces of the flow guide holes 8, first sections 61 of the flow guide bent plates 6 are arranged in the annular channel 7 and extend along the axial direction of the combustion chamber outer barrel 1, the first sections 61 of the flow guide bent plates 6 are respectively spaced from the flow guide sleeve 5 and the combustion chamber outer barrel 1 to divide the annular channel 7 into an outer annular channel and an inner annular channel along the radial direction of the combustion chamber outer barrel 1, and second sections 62 of the flow guide bent plates 6 are arranged in the outer.
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 inner annular channel from the right side of the diversion bent plate 6 and then enters the outer space 9 through the diversion holes 8, namely the space in the peripheral nozzle 4 close to the inner wall surface of the diversion sleeve 5 along the radial direction of the diversion sleeve 5.
Another part of the air flow in the annular channel 7 enters the outer annular channel from the left side of the deflector 6 and is guided to the inner space 10 in the central nozzle 3 and the peripheral nozzle 4, i.e. the space in the peripheral nozzle 4 away from the inner wall surface of the deflector sleeve 5 in the radial direction of the deflector sleeve 5.
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 at the central position in the outer barrel of the combustion chamber;
the central nozzle is arranged in the combustion chamber outer cylinder;
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, the flow guide sleeve is provided with a plurality of flow guide holes respectively corresponding to the peripheral nozzles, and the flow guide holes penetrate through the peripheral wall of the flow guide sleeve along the radial direction of the flow guide sleeve;
the flow guiding bent plates are arranged on the flow guiding sleeve and respectively correspond to the peripheral nozzles, the flow guiding bent plates are respectively and correspondingly positioned at the rear sides of the flow guiding holes, the flow guiding bent plates are in a U shape which is opened forwards, and the flow guiding bent plates are used for guiding one part of air flow in the annular channel from the front sides of the flow guiding bent plates to the outer side space in the peripheral nozzles through the flow guiding holes and guiding the other part of air flow from the rear sides of the flow guiding bent plates to the inner side space in the peripheral nozzles and/or the central nozzles.
2. The gas turbine combustor of claim 1, wherein a first section of the flow directing bent plate extends within the annular passage and a second section of the flow directing bent plate extends downstream toward the peripheral nozzle.
3. The gas turbine combustor according to claim 1, wherein the baffle plate passes through the baffle hole and is connected to a rear sidewall surface of the baffle hole.
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.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710791237.XA CN107702144B (en) | 2017-09-05 | 2017-09-05 | Combustor and gas turbine with same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710791237.XA CN107702144B (en) | 2017-09-05 | 2017-09-05 | Combustor and gas turbine with same |
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| Publication Number | Publication Date |
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| CN107702144A CN107702144A (en) | 2018-02-16 |
| CN107702144B true CN107702144B (en) | 2020-03-10 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201710791237.XA Active CN107702144B (en) | 2017-09-05 | 2017-09-05 | Combustor and gas turbine with same |
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| CN (1) | CN107702144B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111380077B (en) * | 2018-12-28 | 2024-07-09 | 中国联合重型燃气轮机技术有限公司 | Combustor of gas turbine |
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| CN101029741A (en) * | 2006-02-27 | 2007-09-05 | 三菱重工业株式会社 | Combustor |
| CN103375811A (en) * | 2012-04-27 | 2013-10-30 | 通用电气公司 | Combustor |
| CN203880748U (en) * | 2012-10-30 | 2014-10-15 | 通用电气公司 | Combustor |
| CN104296160A (en) * | 2014-09-22 | 2015-01-21 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Flow guide bush of combustion chamber of combustion gas turbine and with cooling function |
| CN105051458A (en) * | 2013-03-21 | 2015-11-11 | 三菱重工业株式会社 | Combustor and gas turbine |
| CN106287813A (en) * | 2015-06-26 | 2017-01-04 | 三菱日立电力***株式会社 | Gas turbine burner |
| CN106524222A (en) * | 2015-09-10 | 2017-03-22 | 三菱日立电力***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
- 2017-09-05 CN CN201710791237.XA patent/CN107702144B/en active Active
Patent Citations (7)
| 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 |
| CN103375811A (en) * | 2012-04-27 | 2013-10-30 | 通用电气公司 | Combustor |
| CN203880748U (en) * | 2012-10-30 | 2014-10-15 | 通用电气公司 | Combustor |
| CN105051458A (en) * | 2013-03-21 | 2015-11-11 | 三菱重工业株式会社 | Combustor and gas turbine |
| CN104296160A (en) * | 2014-09-22 | 2015-01-21 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Flow guide bush of combustion chamber of combustion gas turbine and with cooling function |
| CN106287813A (en) * | 2015-06-26 | 2017-01-04 | 三菱日立电力***株式会社 | Gas turbine burner |
| CN106524222A (en) * | 2015-09-10 | 2017-03-22 | 三菱日立电力***株式会社 | Gas turbine combustor |
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| CN107702144A (en) | 2018-02-16 |
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