CN112984559A - Flame tube, combustion chamber, and gas turbine - Google Patents
Flame tube, combustion chamber, and gas turbine Download PDFInfo
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- CN112984559A CN112984559A CN202110296765.4A CN202110296765A CN112984559A CN 112984559 A CN112984559 A CN 112984559A CN 202110296765 A CN202110296765 A CN 202110296765A CN 112984559 A CN112984559 A CN 112984559A
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- resonant cavity
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 20
- 230000002829 reductive effect Effects 0.000 claims description 4
- 239000011159 matrix material Substances 0.000 claims description 3
- 230000001629 suppression Effects 0.000 abstract description 13
- 239000007789 gas Substances 0.000 description 11
- 230000010355 oscillation Effects 0.000 description 6
- 230000036961 partial effect Effects 0.000 description 6
- 230000000694 effects Effects 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 230000000670 limiting effect Effects 0.000 description 3
- 230000002401 inhibitory effect Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 239000000112 cooling gas Substances 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
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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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/30—Exhaust heads, chambers, or the like
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Soundproofing, Sound Blocking, And Sound Damping (AREA)
Abstract
The invention provides a flame tube, a combustion chamber and a gas turbine, wherein the flame tube comprises: a cylinder (10) and a resonant cavity (20) formed on the wall of the cylinder (10); the resonant cavity (20) is divided into a plurality of layers of chambers along the wall thickness direction of the cylinder wall, wherein at least one layer of the chambers is divided into a plurality of sub-chambers; the combustion area of the flame tube is communicated with the chambers of the innermost layer through first through holes (1), the chambers of the adjacent layers are communicated through second through holes (2), and the chambers of the outermost layer are communicated with the outside through third through holes (3). The resonant cavity 20 of the flame tube has a wide suppression frequency range and strong sound wave suppression capability.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a flame tube, a combustion chamber and a gas turbine.
Background
The gas turbine mainly comprises three parts, namely a gas compressor, a combustion chamber and a turbine, wherein the gas exhausted by the gas compressor is mixed with fuel in the combustion chamber and then participates in combustion, and the generated hot gas is conveyed to the turbine to do work. Because the combustion chamber of the gas turbine works under the condition of lean combustion, the thermo-acoustic instability is easy to appear, the resonant cavity is a passive control means in the prior art, and is formed by connecting a thin tube and a closed cavity beside a flame tube, the ideal resonant cavity can eliminate sound waves with specific frequency, so that the transmission loss of the sound waves is infinite, and the characteristic of the common resonant cavity in the combustion chamber is used for reducing high-frequency oscillation to achieve the purpose of inhibiting the thermo-acoustic oscillation.
However, the frequency range of the resonant cavity structure in the related art capable of suppressing the acoustic wave is limited, and the suppression capability is also weak. Therefore, the present application is mainly based on the problem of providing a resonant cavity structure, which can widen the suppression frequency range of the resonant cavity and enhance the suppression capability of the resonant cavity.
Disclosure of Invention
The present invention is directed to solving, at least to some extent, one of the technical problems in the related art. To this end, an embodiment of the present invention proposes a flame tube comprising: the resonant cavity is formed on the wall of the cylinder;
the resonant cavity is divided into a plurality of layers of chambers along the wall thickness direction of the cylinder wall, wherein at least one layer of the chambers is divided into a plurality of sub-chambers;
the combustion area of the flame tube is communicated with the chambers of the innermost layer through first through holes, the chambers of the adjacent layers are communicated through second through holes, and the chambers of the outermost layer are communicated with the outside through third through holes.
The invention has at least the following beneficial effects: the sound wave suppression capability of the resonant cavity after at least one layer of cavity is divided into a plurality of sub-cavities is obviously improved, and the frequency range of sound wave suppression is obviously widened.
In some embodiments, the total flow area of the third through holes is greater than the total flow area of the second through holes of the same layer; the total flow area of the third through holes is larger than that of the first through holes.
In some embodiments, the resonant cavity is divided into two layers of chambers along the wall thickness direction of the cylinder wall, wherein the inner chamber is divided into a plurality of sub-chambers, and each sub-chamber is communicated with the outer chamber through the second through hole.
In some embodiments, the resonant cavity is divided into two layers of chambers along the wall thickness direction of the cylinder wall, wherein the outer chamber is divided into a plurality of sub-chambers, and each sub-chamber is communicated with the inner chamber through the second through hole.
In some embodiments, the resonant cavity is divided into two layers of chambers along the wall thickness direction of the cylinder wall, wherein each two layers of chambers are divided into a plurality of sub-chambers, and the sub-chambers adjacent to each other between the two layers are communicated with each other through the second through hole.
In some embodiments, a plurality of said sub-chambers are arranged in a matrix; and/or the resonant cavity is formed outside the outer circumferential surface of the cylinder wall.
In some embodiments, the resonant cavity is divided into three or more layers of chambers along the wall thickness direction of the cylinder wall, each layer of the chambers is divided into a plurality of sub-chambers, wherein the number of sub-chambers of the innermost layer of the chambers is gradually reduced to the number of sub-chambers of the outermost layer of the chambers.
In some embodiments, the space of the inner chamber is larger than that of the outer chamber in any two adjacent layers of the chambers.
The present invention also provides a combustion chamber comprising: a combustor casing and a liner of an embodiment of the present invention; the combustor casing has an airflow inlet and an airflow outlet, and the flame tube is disposed in the combustor casing.
The invention also provides a gas turbine comprising the combustion chamber of the embodiment of the invention.
Drawings
FIG. 1 is a cross-sectional partial structure of a combustor basket according to an embodiment of the present invention;
FIG. 2 is a partial schematic longitudinal cross-sectional view of the liner of FIG. 1;
FIG. 3 is a schematic diagram showing the muffling effect of the resonant cavity of the flame tube in the related art;
FIG. 4 is a schematic illustration of the muffling effect of the resonant cavity of the flame tube of FIG. 1;
FIG. 5 is a cross-sectional partial structure of a flame tube according to another embodiment of the invention;
FIG. 6 is a partial structural view in longitudinal section of the flame tube of FIG. 5;
FIG. 7 is a cross-sectional partial schematic view of a combustor basket according to yet another embodiment of the present invention;
FIG. 8 is a partial structure diagram of the flame tube of FIG. 7 in longitudinal section.
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.
Referring to fig. 1-2, the present embodiment provides a flame tube, including: a cylinder 10 and a resonant cavity 20 formed on a wall of the cylinder 10; the resonant cavity 20 can eliminate sound waves with specific frequency, so as to achieve the purpose of inhibiting thermoacoustic oscillation. Wherein, a plurality of resonant cavities 20 may be simultaneously disposed on the cylinder 10, and the plurality of resonant cavities 20 are spaced around the outer circumferential surface of the cylinder 10. Wherein, a resonant cavity 20 can also be arranged on the transition section at the rear side of the flame tube, and the scheme of the following embodiment can also be adopted for the corresponding resonant cavity 20.
In order to widen the suppression frequency range of the resonant cavity 20 and enhance the suppression capability of the resonant cavity 20, in the present embodiment, the resonant cavity 20 is configured to be divided into a plurality of layers of chambers 21 along the wall thickness direction of the cylinder wall, wherein at least one layer of chambers 21 is divided into a plurality of sub-chambers 211; the combustion zone 11 of the flame tube is communicated with the chamber 21 at the innermost layer through the first through hole 1, the chambers at the adjacent layers are communicated through the second through hole 2, and the chamber at the outermost layer is communicated with the outside through the third through hole 3. Through experiments, the sound wave suppression capability of the resonant cavity 20 after the at least one layer of chamber 21 is divided into the plurality of sub-chambers 211 is obviously improved, referring to fig. 3 and 4, fig. 3 is a schematic diagram of the sound attenuation effect of the resonant cavity 20 in the related art, fig. 4 is a schematic diagram of the sound attenuation effect of the resonant cavity 20 in the embodiment, and it can be obviously seen that the frequency range of sound wave suppression is obviously widened.
Referring to fig. 1 and 2, the airflow can enter the chamber 21 through the third through hole 3, then enter the sub-chambers 211 through the second through holes 2 from the chamber 21, and finally enter the combustion zone 11 of the flame tube through the corresponding first through holes 1 from the sub-chambers 211. In some embodiments, the total flow area of the third through holes 3 is larger than that of the second through holes 2 of the same layer; the total flow area of the third through hole 3 is larger than that of the first through hole 1, so that the stability of air flow flowing in different spaces can be improved, and noise is reduced. The number of the first through holes 1, the number of the second through holes 2, and the number of the third through holes 3 may be multiple, the total flow area of the first through holes 1 is the sum of the flow areas of all the first through holes 1, the total flow area of the second through holes 2 in the same layer is the sum of the flow areas of all the second through holes 2 in the same layer, if the resonant cavity 20 is divided into two layers of cavities along the wall thickness direction of the cylinder wall, only one layer of the second through holes 2 exists, as shown in fig. 1 and 2, specifically, the total flow area of the third through holes 3 is the sum of the flow areas of all the third through holes 3.
The total flow area of the second through holes 2 in the same layer may be larger than the total flow area of the third through holes 3, smaller than the total flow area of the third through holes 3, or equal to the total flow area of the third through holes 3, and is specifically selected according to design requirements (meeting the requirements of suppression frequency and effect). The plurality of first through holes 1, the plurality of second through holes 2, and the plurality of third through holes 3 may be uniformly distributed, or may be non-uniformly distributed when necessary.
In some embodiments, the number of the first through holes 1 and the second through holes 2 may be only one, as long as at least one hole is ensured on each of the upper layer and the lower layer of the chamber 21 or the sub-chamber 211, and the chamber 21 or the sub-chamber 211 is ensured not to be a dead space.
The total flow area of the first through holes 1, the total flow area of the second through holes 2 in the same layer, and the total flow area of the third through holes 3 can be changed by adjusting the number and the aperture size of the holes, and in some embodiments, the aperture of the third through holes 3 < the aperture of the second through holes 2 < the aperture of the first through holes 1. Wherein, the first through hole 1, the second through hole 2 and the third through hole 3 can be circular through holes.
In some embodiments, the resonant cavity 20 is divided into two layers along the wall thickness direction of the cylinder wall, as shown in fig. 1 and 2, the inner chamber 21 is divided into a plurality of sub-chambers 211, and each sub-chamber 211 is communicated with the outer chamber 21 through the second through hole 2. The first through hole 1 is a basic open structure of the resonant cavity 20, and the second through hole 2 is a cooling gas to be introduced into the outer cavity 21 to balance the temperature and the flow field of the resonant cavity 20; the third through hole 3 is for introducing cooling air to balance the temperature and flow field inside the whole resonator 20, and this scheme is mainly aimed at high frequency oscillation.
In some embodiments, the resonant cavity 20 is divided into two layers along the wall thickness direction of the cylinder wall, as shown in fig. 5 and 6, wherein the outer chamber 21 is divided into a plurality of sub-chambers 211, and each sub-chamber 211 is communicated with the inner chamber 21 through the second through hole 2, which is mainly aimed at the oscillation with lower frequency.
In some embodiments, the resonant cavity 20 is divided into two layers along the wall thickness direction of the cylinder wall, as shown in fig. 7 and 8, wherein each of the two layers of the cavity 21 is divided into a plurality of sub-cavities 211, and the sub-cavities 211 adjacent to each other between the two layers are communicated with each other through the second through hole 2.
The three embodiments described above can respectively aim at the oscillation with different frequencies, and in any case, the function of changing the target frequency can be realized by adjusting parameters such as the size of the chamber 21, the sub-chamber 211, the size of the first through hole 1, the second through hole 2, and the third through hole 3, and the like.
In some embodiments, the sub-chambers 211 are distributed in a matrix shape, and the sub-chambers 211 in the same layer have the same space size and are uniformly distributed; the entire cavity 20 may be rectangular or circular and may be selected by one skilled in the art according to the actual design requirements.
Further, the resonant cavity 20 is formed outside the outer circumferential surface of the cylinder wall, that is, the structure forming the resonant cavity 20 is protruded outside the outer circumferential surface of the cylinder wall, and in some embodiments, the resonant cavity 20 may also be formed inside the inner circumferential surface of the cylinder wall, so that the structure forming the resonant cavity 20 is protruded inside the inner circumferential surface of the cylinder wall (not shown in the corresponding figures).
In some embodiments, the resonant cavity 20 is divided into more than three layers of chambers 21 along the wall thickness direction of the cylinder wall, and each layer of chambers 21 is divided into a plurality of sub-chambers 211, wherein the number of sub-chambers 211 of the innermost layer of chambers 21 is gradually reduced to the number of sub-chambers 211 of the outermost layer of chambers 21. That is, the inner layer chamber 21 is divided into a greater number of sub-chambers 211 than the outer layer chamber 21, and the sub-chambers 211 of the inner layer chamber 21 have smaller spaces.
In some embodiments, in any two adjacent layers of chambers 21, the space of the inner chamber 21 is larger than the space of the outer chamber 21. This arrangement enables the sound suppression effect of the resonator 20 to be optimized.
All the above embodiments are designed for different design requirements, and those skilled in the art can make corresponding modifications according to the modified idea of the present embodiment, which is within the protection scope of the present invention as long as the inventive concept is the same as the present embodiment.
The present embodiment further provides a combustion chamber comprising: a combustion chamber housing and a liner of the present embodiment; the combustor casing has an airflow inlet and an airflow outlet, and the flame tube is disposed in the combustor casing.
The embodiment further provides a gas turbine, which comprises the combustion chamber in the embodiment, and also comprises a compressor, a turbine and the like.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; may be mechanically coupled, may be electrically coupled or may be in communication with each other; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the present invention, unless otherwise expressly stated or limited, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
In the present disclosure, the terms "one embodiment," "some embodiments," "an example," "a specific example," or "some examples" and the like mean that a specific feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present disclosure. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
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 (10)
1. A flame tube, comprising: a cylinder (10) and a resonant cavity (20) formed on the wall of the cylinder (10);
the resonant cavity (20) is divided into a plurality of layers of chambers along the wall thickness direction of the cylinder wall, wherein at least one layer of the chambers is divided into a plurality of sub-chambers;
the combustion area of the flame tube is communicated with the chambers of the innermost layer through first through holes (1), the chambers of the adjacent layers are communicated through second through holes (2), and the chambers of the outermost layer are communicated with the outside through third through holes (3).
2. The flame tube according to claim 1, characterized in that the total flow area of the third through holes (3) is larger than the total flow area of the second through holes (2) of the same layer; the total flow area of the third through holes (3) is larger than that of the first through holes (1).
3. The flame tube according to claim 1, characterized in that the resonant cavity (20) is divided into two layers of chambers along the wall thickness direction of the tube wall, wherein the inner chamber is divided into a plurality of sub-chambers, each of which is communicated with the outer chamber through the second through hole (2).
4. The flame tube according to claim 1, characterized in that the resonant cavity (20) is divided into two layers of chambers along the wall thickness direction of the tube wall, wherein the outer chamber is divided into a plurality of sub-chambers, each of which is communicated with the inner chamber through the second through hole (2).
5. The flame tube according to claim 1, characterized in that the resonant cavity (20) is divided into two layers along the wall thickness direction of the tube wall, wherein each of the two layers of the chamber is divided into a plurality of sub-chambers, and the sub-chambers adjacent to each other between the two layers are communicated with each other through the second through hole (2).
6. The combustor basket of claim 1, wherein a plurality of said sub-chambers are arranged in a matrix; and/or the resonant cavity (20) is formed outside the outer circumferential surface of the cylinder wall.
7. The flame tube according to claim 1, wherein the resonant cavity (20) is divided into three or more layers in the wall thickness direction of the tube wall, each layer of the chambers is divided into a plurality of sub-chambers, and the number of sub-chambers of the innermost layer of the chambers is gradually reduced to the number of sub-chambers of the outermost layer of the chambers.
8. The flame tube of claim 1, wherein the space of the inner chamber is larger than the space of the outer chamber in any two adjacent layers of the chambers.
9. A combustor, comprising: a combustor casing and a liner according to any one of claims 1 to 8; the combustor casing has an airflow inlet and an airflow outlet, and the flame tube is disposed in the combustor casing.
10. A gas turbine comprising the combustor of claim 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110296765.4A CN112984559A (en) | 2021-03-19 | 2021-03-19 | Flame tube, combustion chamber, and gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110296765.4A CN112984559A (en) | 2021-03-19 | 2021-03-19 | Flame tube, combustion chamber, and gas turbine |
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| Publication Number | Publication Date |
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| CN112984559A true CN112984559A (en) | 2021-06-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110296765.4A Pending CN112984559A (en) | 2021-03-19 | 2021-03-19 | Flame tube, combustion chamber, and gas turbine |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113483360A (en) * | 2021-08-12 | 2021-10-08 | 中国联合重型燃气轮机技术有限公司 | Combustor liner for gas turbine and gas turbine |
| CN113719861A (en) * | 2021-09-10 | 2021-11-30 | 中国联合重型燃气轮机技术有限公司 | Combustion chamber and gas turbine with same |
| CN114811649A (en) * | 2022-04-07 | 2022-07-29 | 中国联合重型燃气轮机技术有限公司 | Combustion chamber and gas turbine with same |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| DE2844349A1 (en) * | 1977-10-11 | 1979-04-12 | Snecma | COMBUSTION DEVICE FOR TURBO ENGINE |
| CN102956228A (en) * | 2011-08-10 | 2013-03-06 | 通用电气公司 | Acoustic dampening device for use in gas turbine engine |
| CN103975199A (en) * | 2011-09-23 | 2014-08-06 | 西门子公司 | A combustor resonator section with an internalthermal barrier coating and method of fabricating the same |
| CN104676649A (en) * | 2015-02-05 | 2015-06-03 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Damping thermo-acoustic vibration acoustic flame tube |
| CN109563994A (en) * | 2016-07-25 | 2019-04-02 | 西门子股份公司 | Gas-turbine unit with loop resonator |
-
2021
- 2021-03-19 CN CN202110296765.4A patent/CN112984559A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2844349A1 (en) * | 1977-10-11 | 1979-04-12 | Snecma | COMBUSTION DEVICE FOR TURBO ENGINE |
| CN102956228A (en) * | 2011-08-10 | 2013-03-06 | 通用电气公司 | Acoustic dampening device for use in gas turbine engine |
| CN103975199A (en) * | 2011-09-23 | 2014-08-06 | 西门子公司 | A combustor resonator section with an internalthermal barrier coating and method of fabricating the same |
| CN104676649A (en) * | 2015-02-05 | 2015-06-03 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Damping thermo-acoustic vibration acoustic flame tube |
| CN109563994A (en) * | 2016-07-25 | 2019-04-02 | 西门子股份公司 | Gas-turbine unit with loop resonator |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113483360A (en) * | 2021-08-12 | 2021-10-08 | 中国联合重型燃气轮机技术有限公司 | Combustor liner for gas turbine and gas turbine |
| CN113483360B (en) * | 2021-08-12 | 2022-11-18 | 中国联合重型燃气轮机技术有限公司 | Combustor liner for gas turbine and gas turbine |
| CN113719861A (en) * | 2021-09-10 | 2021-11-30 | 中国联合重型燃气轮机技术有限公司 | Combustion chamber and gas turbine with same |
| CN114811649A (en) * | 2022-04-07 | 2022-07-29 | 中国联合重型燃气轮机技术有限公司 | Combustion chamber and gas turbine with same |
| CN114811649B (en) * | 2022-04-07 | 2024-05-10 | 中国联合重型燃气轮机技术有限公司 | Combustion chamber and gas turbine with same |
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Application publication date: 20210618 |