JP2008121961A - Acoustic liner for gas turbine combustor - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide an acoustic liner for a gas turbine combustor which reduces the consumption of purging air to increase the amount of combustion air burned in a gas turbine combustor, thereby lowers the temperature of combustion gas, and reduces the produced amount (the emitted amount) of NOx. <P>SOLUTION: A housing 11b is provided with at least one purge hole 14 bored in a surface facing a wall surface of a combustion cylinder 2 wherein static pressure is increased when a gas turbine is operated, and along with the pressure increase, combustion gas in the combustion cylinder 2 is jetted into a resonance space. <P>COPYRIGHT: (C)2008,JPO&INPIT

Description

  The present invention relates to an acoustic liner for a gas turbine combustor having a resonance space for suppressing combustion vibration inside a housing.

As an acoustic liner for a gas turbine combustor, for example, one disclosed in Patent Document 1 is known.
Japanese translation of PCT publication No. 2004-509313 (FIG. 5A)

However, the acoustic liner for a gas turbine combustor disclosed in Patent Document 1 has a large number of openings (purge holes) provided in a surface (second member) facing the wall surface of the combustion cylinder in the circumferential direction. It is provided uniformly (evenly) along. Therefore, the ratio of the purge air flowing into the resonance space through these many openings becomes high, and the amount of combustion air burned in the combustor of the gas turbine is reduced correspondingly, and the temperature of the combustion gas is increased. There is a problem in that the amount of NO _x (nitrogen oxide) generated (discharged amount) increases due to the increase.

The present invention has been made in view of the above circumstances, and can reduce the consumption of purge air, and accordingly, can increase the amount of combustion air burned in the combustor of the gas turbine. it can be, as well as being able to reduce the temperature of the combustion gases, and an object thereof is to provide an acoustic liner for a gas turbine combustor capable of reducing the generation amount of the NO _X (the emissions).

The present invention employs the following means in order to solve the above problems.
An acoustic liner for a gas turbine combustor according to the present invention includes a plurality of holes drilled along a circumferential direction on a wall surface of a combustion cylinder in which a combustion region is formed, and a region in which these many holes are drilled. An acoustic liner for a gas turbine combustor, which is disposed so as to surround an outer peripheral side of the combustion cylinder and includes a housing in which a resonance space is formed with a wall surface of the combustion cylinder. When the turbine is in operation, the static pressure in the combustion cylinder increases, and accordingly, the combustion gas in the combustion cylinder blows into the resonance space and faces the wall of the combustion cylinder. At least one purge hole is formed.

According to such an acoustic liner for a gas turbine combustor, the purge hole is provided only in a place where the high-temperature combustion gas in the combustion cylinder is ejected into the resonance space. The number of holes (that is, the opening area of the entire purge hole) can be reduced, and the consumption of purge air flowing from the purge hole into the resonance space can be reduced.
In addition, the purge air flowing into the resonance space from the purge hole has a high static pressure in the combustion cylinder, and the high temperature combustion gas in the combustion cylinder is ejected into the resonance space via the purge hole. Since the purge air is supplied intensively (pinpoint), the inflow of high-temperature combustion gas from the combustion cylinder into the resonance space is suppressed by the dynamic pressure of the purge air.

  An acoustic liner for a gas turbine combustor according to the present invention includes a plurality of holes drilled along a circumferential direction on a wall surface of a combustion cylinder in which a combustion region is formed, and a region in which these many holes are drilled. An acoustic liner for a gas turbine combustor comprising a housing that is disposed so as to surround an outer peripheral side of the combustion cylinder in which a resonance space is formed between the combustion cylinder and a wall surface of the combustion cylinder. In addition, a plurality of purge holes are evenly formed along the circumferential direction and along the entire circumference on the other side surface.

According to such an acoustic liner for a gas turbine combustor, the purge holes are provided only on one side surface and / or the other side surface of the housing. The total opening area) can be reduced, and the consumption of purge air flowing from the purge hole into the resonance space can be reduced.
Further, the purge air flowing into the resonance space from the purge hole flows along the wall surface of the combustion cylinder so as to cover (block) the entire hole (that is, the combustion cylinder in the resonance space). Since an air layer is formed by purge air in the vicinity of the wall surface, the flow of high-temperature combustion gas from the combustion cylinder into the resonance space is suppressed.

  An acoustic liner for a gas turbine combustor according to the present invention includes a plurality of holes drilled along a circumferential direction on a wall surface of a combustion cylinder in which a combustion region is formed, and a region in which these many holes are drilled. An acoustic liner for a gas turbine combustor comprising a housing that is disposed so as to surround an outer peripheral side of the combustion cylinder in which a resonance space is formed between the combustion cylinder and a wall surface of the combustion cylinder. When the gas turbine is operated on the other side and / or on the other side, the static pressure in the combustion cylinder is increased, and accordingly, the combustion gas in the combustion cylinder is ejected into the resonance space. At least one purge hole is formed on the upstream and / or downstream side of the wall surface of the combustion cylinder.

According to such an acoustic liner for a gas turbine combustor, the purge hole is provided only in a place where the static pressure in the combustion cylinder becomes high and the high-temperature combustion gas in the combustion cylinder is ejected into the resonance space. Therefore, the number of purge holes is larger than that formed along the circumferential direction on one side surface and / or the other side surface of the housing (that is, the opening area of the entire purge hole). Can be reduced, and the consumption of purge air flowing into the resonance space from the purge hole can be further reduced.
Further, the purge air flowing into the resonance space from the purge hole has a high static pressure in the combustion cylinder when the gas turbine is operated, and accordingly, the high-temperature combustion gas in the combustion cylinder is in the resonance space. The purge air flows along the wall surface of the combustion cylinder at the location where the gas is ejected to cover (block) the hole at the location (that is, near the wall surface of the combustion cylinder in the resonance space). Therefore, the flow of high-temperature combustion gas from the combustion cylinder into the resonance space is suppressed.

In the acoustic liner for a gas turbine combustor, it is more preferable that a partition plate for partitioning the resonance space in the circumferential direction is provided inside the housing.
According to such an acoustic liner for a gas turbine combustor, the purge air supplied through the purge hole can be prevented from diffusing in the circumferential direction in the resonance space. For example, the purge air flowing into the combustion cylinder is supplied more concentratedly (more effectively) to the place where the static pressure in the combustion cylinder becomes high and the high-temperature combustion gas in the combustion cylinder is ejected into the resonance space. Therefore, the flow of high-temperature combustion gas from the combustion cylinder into the resonance space can be efficiently suppressed by using less purge air.

The gas turbine combustor or the gas turbine according to the present invention can reduce the consumption of purge air, and accordingly, can increase the amount of combustion air burned in the gas turbine combustor. A dexterous acoustic liner is provided.
According to such a gas turbine combustor or a gas turbine, the consumption amount of the combustion air burned in the gas turbine combustor can be increased by the amount corresponding to the reduction in the consumption amount of the purge air, and the temperature of the combustion gas Can be reduced, and the generation amount (discharge amount) of NO _X (nitrogen oxide) can be reduced.

According to the present invention, the amount of purge air consumed can be reduced, and the amount of combustion air burned in the combustor of the gas turbine can be increased correspondingly, thereby reducing the temperature of the combustion gas. it is possible to, an effect that the generation amount of the NO _X (the discharge amount) can be reduced.

Hereinafter, a first embodiment of an acoustic liner for a gas turbine combustor according to the present invention will be described with reference to FIGS. 1 to 4.
1 is a cross-sectional view of a main part of a gas turbine combustor equipped with an acoustic liner for a gas turbine combustor according to the present embodiment, FIG. 2 is a cross-sectional view taken along the line AA in FIG. 1, and FIG. 3 is according to the present embodiment. It is a figure which shows a part of acoustic liner for gas turbine combustors, Comprising: (a) is a top view, (b) is a perspective view, FIG. 4 is the relationship between the static pressure and circumferential angle in the wall surface of a combustion cylinder, It is a graph which shows the relationship between the temperature in a cavity (resonance space) and the circumferential direction angle in the wall surface vicinity of a combustion cylinder.

As shown in FIG. 1, a gas turbine combustor (hereinafter referred to as “combustor”) 1 including an acoustic liner (hereinafter referred to as “acoustic liner”) 11 for a gas turbine combustor according to the present embodiment is provided. A combustion cylinder 2 is provided. The combustion cylinder 2 forms a combustion region 3 inside, and has a cylindrical shape in contact with the compressed air flow 4 on the outside. A plurality (eight in this embodiment) of premixing nozzles 5 and one pilot nozzle 6 are provided on the upstream side of the combustion cylinder 2. A bypass channel 8 for introducing air is provided on the wall surface located on the downstream side of the combustion cylinder 2.
The premixing nozzles 5 are provided at regular intervals (45 ° intervals) along the circumferential direction, and the pilot nozzles 6 are provided so as to be positioned substantially at the center of the premixing nozzles 5.

  Now, as shown in FIG. 2, the acoustic liner 11 according to the present embodiment has a large number of holes 11a drilled along the circumferential direction in the wall surface of the combustion cylinder 2, and a region in which these holes 11a are provided. The housing 11b is disposed so as to surround the outer peripheral side of the combustion cylinder 2 (the side in contact with the cooling air region 4 when viewed from the combustion cylinder 2) and forms a cavity (resonance space) between the combustion cylinder 2 and the wall surface. It is structured as an element.

  The housing 11b is attached so as to go around the outer periphery of the combustion cylinder 2, and no partition is provided inside the housing 11b, and the inside of the housing 11b forms an integral space.

  Reference numeral 13 in FIG. 2 is a high temperature region in the combustion region 3 where the temperature is higher than others. This high temperature region 13 is located generally downstream of the premixing nozzle 5. The wall surface of the combustion cylinder 2 at a location close to the high temperature region 13 is provided with many holes 11a, and the wall surface of the combustion cylinder 2 at a location farther from the high temperature region 13 is provided with fewer holes 11a. Or the hole 11a is not provided.

Moreover, as shown in FIG. 3, the purge hole 14 is provided in the surface (outer peripheral surface) facing the wall surface of the combustion cylinder 2 of the housing 11b.
A plurality (eight in this embodiment) of the purge holes 14 are formed along the circumferential direction. When the gas turbine is operated, the purge hole 14 has a high static pressure in the combustion cylinder 2 (combustion region 3), and accordingly, high-temperature combustion gas in the combustion cylinder 2 is injected into the cavity. It is provided corresponding to the place to come.

When the gas turbine is in operation, the static pressure in the combustion cylinder 2 is increased, and accordingly, the hot combustion gas in the combustion cylinder 2 is ejected into the cavity (position in the circumferential direction and in the axial direction). The position) can be analyzed (determined) using numerical calculation such as CFD. FIG. 4 is a graph showing a specific example of the analysis result. The solid line in FIG. 4 shows the relationship between the static pressure near the wall surface of the combustion cylinder 2 and the circumferential angle, and the broken line in FIG. 4 shows the relationship between the temperature in the cavity near the wall surface of the combustion cylinder 2 and the circumferential angle. Is shown. Further, it can be seen from FIG. 4 that the peaks (maximum values) of the broken line and the solid line appear at equal intervals (45 ° intervals) along the circumferential direction. This is the same as the arrangement interval of the premixing nozzles 5.
In addition, when the gas turbine is operated, the static pressure in the combustion cylinder 2 is increased, and accordingly, the place where the high-temperature combustion gas in the combustion cylinder 2 is ejected into the cavity is the gas turbine (or gas Since it differs depending on the type of the turbine combustor), it is necessary to specify for each model using numerical calculation such as CFD.

According to the acoustic liner 11 according to the present embodiment, the purge hole 14 is provided only in a place where the high-temperature combustion gas in the combustion cylinder 2 is ejected into the cavity, so that the purge hole is more than the conventional one. 14 (that is, the opening area of the entire purge hole 14) can be reduced, and the consumption of purge air flowing from the purge hole 14 into the cavity can be reduced.
Further, the purge air flowing into the cavity from the purge hole 14 has a high static pressure in the combustion cylinder 2, and the purge hole 14 is formed at a place where the high-temperature combustion gas in the combustion cylinder 2 is ejected into the cavity. Since the purge air is supplied intensively (pinpoint) through the air, the inflow of high-temperature combustion gas from the combustion cylinder 2 into the cavity is suppressed by the dynamic pressure of the purge air. Become.

And according to the gas turbine combustor 1 or gas turbine provided with such an acoustic liner 11, the consumption of the combustion air combusted by the gas turbine combustor 1 is reduced by the amount of the purge air consumption reduced. It can be increased, the temperature of the combustion gas can be reduced, and the generation amount (discharge amount) of NO _X (nitrogen oxide) can be reduced.

A second embodiment of the acoustic liner according to the present invention will be described with reference to FIG.
FIG. 5 is a view showing a part of the acoustic liner according to the present embodiment, in which (a) is a plan view and (b) is a perspective view.
The acoustic liner 20 according to the present embodiment is different from that of the first embodiment described above in that a purge hole 21 is provided instead of the purge hole 14. Since other components are the same as those of the first embodiment described above, description of these components is omitted here.
In addition, the same code | symbol is attached | subjected to the member same as 1st Embodiment mentioned above.

  As shown in FIG. 5, when the gas turbine is operated, the purge hole 21 has a high static pressure in the combustion cylinder 2 (combustion region 3), and accordingly, the high-temperature combustion gas in the combustion cylinder 2 is reduced. A total of nine places are provided at three locations in the circumferential direction and three rows in the axial direction, respectively, at locations where the air is ejected into the cavity. Each purge hole 21 has a smaller diameter than the purge hole 14 described above, and the entire opening area of the purge hole 21 is set to be substantially the same as the entire opening area of the purge hole 14 described above. .

According to the acoustic liner 20 according to the present embodiment, the purge hole 21 is provided only in the place where the high-temperature combustion gas in the combustion cylinder 2 is ejected into the cavity, so that the purge hole 21 is more than the conventional one. 21 (ie, the opening area of the entire purge hole 21) can be reduced, and the consumption of purge air flowing from the purge hole 21 into the cavity can be reduced.
Further, the purge air flowing into the cavity from the purge hole 21 has a high static pressure in the combustion cylinder 2, and the purge hole 21 is formed at a place where the high-temperature combustion gas in the combustion cylinder 2 is ejected into the cavity. Since the purge air is supplied intensively (pinpoint) through the air, the inflow of high-temperature combustion gas from the combustion cylinder 2 into the cavity is suppressed by the dynamic pressure of the purge air. Become.
Although the number of purge holes 21 is large, the ejection of high-temperature combustion gas can be suppressed in a wider range than in the case of one purge hole 14, but the jet of purge air ejected from the purge hole 21 has been described above. It becomes weaker than the jet of purge air ejected from the purge hole 14. Therefore, the jet strength of the purge air can be adjusted by adjusting the number of purge holes while maintaining the entire opening area of the purge hole 21.

And according to the gas turbine combustor 1 or gas turbine provided with such an acoustic liner 20, the consumption of the combustion air burned in the gas turbine combustor 1 is reduced by the amount of the consumption of the purge air reduced. It can be increased, the temperature of the combustion gas can be reduced, and the generation amount (discharge amount) of NO _X (nitrogen oxide) can be reduced.

A third embodiment of the acoustic liner according to the present invention will be described with reference to FIG. FIG. 6 is a perspective view showing a part of the acoustic liner according to the present embodiment.
The acoustic liner 30 according to this embodiment is different from that of the above-described embodiment in that a purge hole 31 is provided instead of the purge holes 14 and 21. Since other components are the same as those in the above-described embodiment, description of these components is omitted here.
In addition, the same code | symbol is attached | subjected to the member same as embodiment mentioned above.

  As shown in FIG. 6, the purge holes 31 are arranged uniformly on one side surface of the housing 11 b (upstream side surface in the present embodiment) along the circumferential direction and over the entire circumference.

According to the acoustic liner 30 according to the present embodiment, since the purge holes 31 are provided only on one side surface of the housing 11b, the number of the purge holes 31 (that is, the opening of the entire purge hole 31 is larger than the conventional one). Area) can be reduced, and the consumption of purge air flowing into the cavity from the purge hole 31 can be reduced.
The purge air flowing into the cavity from the purge hole 31 flows along the wall surface of the combustion cylinder 2 so as to cover (block) the entire hole 11a (that is, the combustion cylinder in the cavity). 2), an air layer of purge air is formed in the vicinity of the wall surface 2), so that the flow of high-temperature combustion gas from the combustion cylinder 2 into the cavity is suppressed.

And according to the gas turbine combustor 1 or gas turbine provided with such an acoustic liner 30, the consumption of the combustion air combusted by the gas turbine combustor 1 is reduced by the amount of the purge air consumption reduced. It can be increased, the temperature of the combustion gas can be reduced, and the generation amount (discharge amount) of NO _X (nitrogen oxide) can be reduced.

A sound liner according to a fourth embodiment of the present invention will be described with reference to FIG. FIG. 7 is a perspective view showing a part of the acoustic liner according to the present embodiment.
The acoustic liner 40 according to the present embodiment is different from that of the third embodiment described above in that a purge hole 41 is provided instead of the purge hole 31. Since other components are the same as those of the third embodiment described above, description of these components is omitted here.
In addition, the same code | symbol is attached | subjected to the member same as 3rd Embodiment mentioned above.

  As shown in FIG. 7, when the gas turbine is operated, the purge hole 41 has a high static pressure in the combustion cylinder 2 (combustion region 3). It is provided in a concentrated manner (locally) at a place where it is ejected into the cavity.

According to the acoustic liner 40 according to the present embodiment, the purge hole 41 is provided only in a place where the static pressure in the combustion cylinder 2 becomes high and the high-temperature combustion gas in the combustion cylinder 2 is ejected into the cavity. Therefore, the number of purge holes 41 (that is, the entire opening area of the purge holes 41) can be reduced as compared with the third embodiment described above, and the purge air flowing into the cavity from the purge holes 41 can be reduced. Consumption can be further reduced.
Further, the purge air flowing into the cavity from the purge hole 41 has a high static pressure in the combustion cylinder 2 (combustion region 3) when the gas turbine is operated, and accordingly, The high-temperature combustion gas flows along the wall surface of the combustion cylinder 2 where the high-temperature combustion gas is ejected into the cavity so as to cover (block) the hole 11a at the position (that is, the combustion cylinder 2 in the cavity). As a result, an air layer of purge air is formed in the vicinity of the wall surface of the gas, so that inflow of high-temperature combustion gas from the combustion cylinder 2 into the cavity is suppressed.

And according to the gas turbine combustor 1 or gas turbine provided with such an acoustic liner 40, the consumption of the combustion air combusted by the gas turbine combustor 1 is reduced by the amount of the consumption of the purge air reduced. It can be increased, the temperature of the combustion gas can be reduced, and the generation amount (discharge amount) of NO _X (nitrogen oxide) can be reduced.

A fifth embodiment of an acoustic liner according to the present invention will be described with reference to FIG. FIG. 8 is a perspective view showing a part of the acoustic liner according to the present embodiment.
The acoustic liner 50 according to the present embodiment is different from those of the first embodiment and the second embodiment described above in that a purge hole 51 is provided instead of the purge holes 14 and 21. Since other components are the same as those in the first embodiment and the second embodiment described above, description of these components is omitted here.
In addition, the same code | symbol is attached | subjected to the member same as 1st Embodiment mentioned above and 2nd Embodiment.

  As shown in FIG. 8, the purge holes 51 are evenly arranged on both side surfaces (upstream side surface and downstream side surface) of the housing 11 b along the circumferential direction and over the entire circumference. The purge holes 51 are arranged so that the purge holes 51 on one side and the purge holes 51 on the other side do not overlap in the circumferential direction, that is, the purge hole 51 on one side is the purge hole 51 on the other side. And the purge hole 51. Each purge hole 51 has the same approximate diameter as the purge hole 31 described above, and the number of purge holes 51 is set to be substantially the same as the number of purge holes 31 described above.

According to the acoustic liner 50 according to the present embodiment, since the purge holes 51 are provided only on both side surfaces of the housing 11b, the number of the purge holes 51 (that is, the opening of the entire purge hole 51 is larger than the conventional one). Area) can be reduced, and the consumption of purge air flowing into the cavity from the purge hole 51 can be reduced.
Further, the purge air flowing into the cavity from the purge hole 51 flows along the wall surface of the combustion cylinder 2 so as to cover (block) the entire hole 11a (that is, the combustion cylinder in the cavity). 2), an air layer of purge air is formed in the vicinity of the wall surface 2), so that the flow of high-temperature combustion gas from the combustion cylinder 2 into the cavity is suppressed.

And according to the gas turbine combustor 1 or gas turbine provided with such an acoustic liner 50, the consumption of the combustion air combusted by the gas turbine combustor 1 is reduced by the amount of the consumption of the purge air reduced. It can be increased, the temperature of the combustion gas can be reduced, and the generation amount (discharge amount) of NO _X (nitrogen oxide) can be reduced.

A sixth embodiment of the acoustic liner according to the present invention will be described with reference to FIG. FIG. 9 is a perspective view showing a part of the acoustic liner according to the present embodiment.
The acoustic liner 60 according to the present embodiment is different from those of the first embodiment and the second embodiment described above in that a purge hole 61 is provided instead of the purge holes 14 and 21. Since other components are the same as those in the first embodiment and the second embodiment described above, description of these components is omitted here.
In addition, the same code | symbol is attached | subjected to the member same as 1st Embodiment mentioned above and 2nd Embodiment.

  As shown in FIG. 9, each purge hole 61 is a slit-like hole (a long hole extending along the circumferential direction) having a constant width in the circumferential direction, and one side surface of the housing 11 b (upstream side in the present embodiment). And a plurality of (for example, eight) are arranged along the circumferential direction along the circumferential direction.

According to the acoustic liner 60 according to the present embodiment, the purge hole 61 is provided only on one side surface of the housing 11b. Therefore, the entire opening area of the purge hole 61 can be reduced as compared with the conventional one. The consumption of purge air flowing into the cavity from the purge hole 61 can be reduced.
Further, the purge air flowing into the cavity from the purge hole 61 flows along the wall surface of the combustion cylinder 2 so as to cover (block) the entire hole 11a (that is, the combustion cylinder in the cavity). 2), an air layer of purge air is formed in the vicinity of the wall surface 2), so that the flow of high-temperature combustion gas from the combustion cylinder 2 into the cavity is suppressed.

And according to the gas turbine combustor 1 or gas turbine provided with such an acoustic liner 60, the consumption of the combustion air burned in the gas turbine combustor 1 is reduced by the amount of the consumption of the purge air reduced. It can be increased, the temperature of the combustion gas can be reduced, and the generation amount (discharge amount) of NO _X (nitrogen oxide) can be reduced.

A seventh embodiment of an acoustic liner according to the present invention will be described with reference to FIG. FIG. 10 is a perspective view showing a part of the acoustic liner according to the present embodiment.
The acoustic liner 70 according to the present embodiment is different from those of the first embodiment and the second embodiment described above in that a purge hole 71 is provided instead of the purge holes 14 and 21. Since other components are the same as those in the first embodiment and the second embodiment described above, description of these components is omitted here.
In addition, the same code | symbol is attached | subjected to the member same as 1st Embodiment mentioned above and 2nd Embodiment.

  As shown in FIG. 10, each of the purge holes 71 is a slit-like hole (a long hole extending along the circumferential direction) having a constant width in the circumferential direction, and both side surfaces (upstream side surface and downstream side) of the housing 11b. Side surface) along the circumferential direction and uniformly disposed over the entire circumference. Each of the purge holes 71 is arranged such that the purge hole 71 on one side and the purge hole 71 on the other side do not overlap in the circumferential direction, that is, the purge hole 71 on one side is the purge hole 71 on the other side. And the purge hole 71 are formed so as to be located approximately in the middle. The opening area of the entire purge hole 71 is set to be substantially the same as the opening area of the entire purge hole 61 described above.

According to the acoustic liner 70 according to the present embodiment, the purge holes 71 are provided only on both side surfaces of the housing 11b, so the number of purge holes 71 (that is, the opening of the entire purge hole 71 is larger than the conventional one). Area) can be reduced, and the consumption of purge air flowing into the cavity from the purge hole 71 can be reduced.
The purge air flowing into the cavity from the purge hole 71 flows along the wall surface of the combustion cylinder 2 so as to cover (block) the entire hole 11a (that is, the combustion cylinder in the cavity). 2), an air layer of purge air is formed in the vicinity of the wall surface 2), so that the flow of high-temperature combustion gas from the combustion cylinder 2 into the cavity is suppressed.

And according to the gas turbine combustor 1 or gas turbine provided with such an acoustic liner 70, the consumption of the combustion air combusted by the gas turbine combustor 1 is reduced by the amount of the consumption of the purge air reduced. It can be increased, the temperature of the combustion gas can be reduced, and the generation amount (discharge amount) of NO _X (nitrogen oxide) can be reduced.

An eighth embodiment of an acoustic liner according to the present invention will be described with reference to FIG. FIG. 11 is a perspective view showing a part of the acoustic liner according to the present embodiment.
The acoustic liner 80 according to the present embodiment is different from that of the above-described embodiment in that a partition plate 81 that partitions (divides) the cavity in the circumferential direction is provided inside the housing 11b. Since other components are the same as those in the above-described embodiment, description of these components is omitted here.
In addition, the same code | symbol is attached | subjected to the member same as embodiment mentioned above.

As shown in FIG. 11, when the gas turbine is operated, the partition plate 81 has a high static pressure in the combustion cylinder 2 (combustion region 3), and accordingly, the high-temperature combustion gas in the combustion cylinder 2 is reduced. In the present embodiment, a total of 16 sheets are arranged so as to surround (partition) two places for each place so as to enclose (partition) a place where the air is ejected into the cavity.
In addition, FIG. 11 has shown the example which applied the partition plate 81 to the acoustic liner 11 of 1st Embodiment.

  According to the acoustic liner 80 according to the present embodiment, for example, the purge air supplied through the purge hole 14 can be prevented from diffusing in the circumferential direction in the cavity. The purge air that flows into the combustion cylinder 2 is supplied more concentratedly (more effectively) to the place where the static pressure in the combustion cylinder 2 becomes high and the high-temperature combustion gas in the combustion cylinder 2 is ejected into the cavity. Therefore, the flow of high-temperature combustion gas from the combustion cylinder 2 into the cavity can be efficiently suppressed by using less purge air.

  In the above-described embodiment, the case where each purge hole is formed so as to have the same (or substantially the same) size (opening area) as the other purge holes has been described as a specific example. However, the present invention is not limited to these. For example, the present invention is located in the vicinity of the place where the static pressure in the combustion cylinder 2 becomes high and the high-temperature combustion gas in the combustion cylinder 2 is ejected into the cavity. The size of the purge hole in the circumferential direction can be appropriately changed as necessary, for example, by increasing the size of the purge hole to be performed and reducing the size of the purge hole located at other locations.

Further, the acoustic liners 11, 20, 30, 40, 50, 60, 70, 80 are not limited to those having a cross-sectional shape as shown in FIG. 2, but have a cross-sectional shape as shown in FIG. It may be a thing.
That is, many holes 11a drilled along the circumferential direction on the wall surface of the combustion cylinder 2 excluding a part in the circumferential direction (upper part in FIGS. 1 and 12), and combustion in a region where these holes 11a are provided. Two housings 11b which are arranged so as to surround the outer peripheral side of the cylinder 2 (the side in contact with the cooling air region 4 when viewed from the combustion cylinder 2) and form a cavity (resonance space) with the wall surface of the combustion cylinder 2. It may be configured as a main element.
The housing 11b is attached to the outer periphery of the combustion cylinder 2 excluding a part in the circumferential direction, and no partition is provided inside each housing 11b. The interior of each housing 11b forms an integral space. Yes.

Further, an acoustic liner 11, 20, 30, 40, 50, 60, 70, 80 is disposed on the upstream side of the combustion cylinder 2, and this acoustic liner 11, 20, 30, 40, 50, 60, 70, 80 is bypassed. The acoustic liner 11, 20, 30, 40, 50, 60, 70, 80 can be disposed between the flow path 8.
In this case, the cross-sectional shape of the acoustic liner arranged on the upstream side is as shown in FIG. 2, and the cross-sectional shape of the acoustic liner arranged on the downstream side is as shown in FIG. The cross-sectional shape of the acoustic liner may be different between the downstream side.
In this case, the purge hole may be provided only in either the acoustic liner disposed on the upstream side or the acoustic liner disposed on the downstream side.

  Furthermore, the purge holes described in the first to fourth embodiments and the sixth embodiment need not be provided on the upstream side, and can be provided on the downstream side.

It is principal part sectional drawing of the gas turbine combustor which comprised the acoustic liner which concerns on 1st Embodiment of this invention. It is AA arrow sectional drawing of FIG. It is a figure which shows a part of acoustic liner concerning 1st Embodiment of this invention, Comprising: (a) is a top view, (b) is a perspective view. It is a graph which shows the relationship between the static pressure in the wall surface vicinity of a combustion cylinder, and the circumferential direction angle, and the relationship between the temperature in a cavity in the wall surface of a combustion cylinder, and the circumferential direction angle. It is a figure which shows a part of acoustic liner concerning 2nd Embodiment of this invention, Comprising: (a) is a top view, (b) is a perspective view. It is a perspective view which shows a part of acoustic liner concerning 3rd Embodiment of this invention. It is a perspective view which shows a part of acoustic liner concerning 4th Embodiment of this invention. It is a perspective view which shows a part of acoustic liner concerning 5th Embodiment of this invention. It is a perspective view which shows a part of acoustic liner concerning 6th Embodiment of this invention. It is a perspective view which shows a part of acoustic liner concerning 7th Embodiment of this invention. It is a perspective view which shows a part of acoustic liner concerning 8th Embodiment of this invention. It is a figure which shows the acoustic liner which concerns on other embodiment of this invention, Comprising: It is a figure similar to FIG.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 Gas turbine combustor 2 Combustion cylinder 3 Combustion area | region 11 Acoustic liner 11a Hole 11b Housing 14 Purge hole 20 Acoustic liner 21 Purge hole 30 Acoustic liner 31 Purge hole 40 Acoustic liner 41 Purge hole 50 Acoustic liner 51 Purge hole 60 Acoustic liner 61 Purge Hole 70 Acoustic liner 71 Purge hole 80 Acoustic liner 81 Partition plate

Claims (6)

Arranged so as to surround a large number of holes drilled along the circumferential direction on the wall surface of the combustion cylinder in which a combustion region is formed, and to surround the outer peripheral side of the combustion cylinder in the region where these many holes are drilled And an acoustic liner for a gas turbine combustor comprising a housing in which a resonance space is formed between the combustion cylinder wall surface and
When the gas turbine of the housing is operated, the static pressure in the combustion cylinder becomes high, and the combustion gas in the combustion cylinder is ejected into the resonance space along with the static pressure in the combustion cylinder. An acoustic liner for a gas turbine combustor, characterized in that at least one purge hole is formed in a surface facing the gas turbine. Arranged so as to surround a large number of holes drilled along the circumferential direction on the wall surface of the combustion cylinder in which a combustion region is formed, and to surround the outer peripheral side of the combustion cylinder in the region where these many holes are drilled And an acoustic liner for a gas turbine combustor comprising a housing in which a resonance space is formed between the combustion cylinder wall surface and
An acoustic liner for a gas turbine combustor, characterized in that a plurality of purge holes are evenly formed along one side and / or the other side of the housing along the circumferential direction. Arranged so as to surround a large number of holes drilled along the circumferential direction on the wall surface of the combustion cylinder in which a combustion region is formed, and to surround the outer peripheral side of the combustion cylinder in the region where these many holes are drilled And an acoustic liner for a gas turbine combustor comprising a housing in which a resonance space is formed between the combustion cylinder wall surface and
When the gas turbine is operated on one side surface and / or the other side surface of the housing, the static pressure in the combustion cylinder is increased, and accordingly, the combustion gas in the combustion cylinder is moved into the resonance space. An acoustic liner for a gas turbine combustor, wherein at least one purge hole is formed on an upstream side and / or a downstream side of a wall surface of the combustion cylinder ejected on the gas cylinder.   The acoustic liner for a gas turbine combustor according to any one of claims 1 to 3, wherein a partition plate that partitions the resonance space in a circumferential direction is provided inside the housing.   A gas turbine combustor comprising the acoustic liner for a gas turbine combustor according to any one of claims 1 to 4.   A gas turbine comprising the gas turbine combustor according to claim 5.

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