JP2006144694A - Gas turbine combustor - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a gas turbine combustor improving durability of a combustor tail pipe by preventing thermal cycle fatigue of a connecting part of the combustor tail pipe and a bypass pipe. <P>SOLUTION: If combustion gas is caught in a bypass elbow 7 as indicated in an arrow D, the combustion gas is circulated in the bypass elbow 7 as indicated in an arrow E to generate so-called cavity flow. A partition plate 9 is inserted in the bypass elbow 7 along an un-indicated center axis direction of the bypass elbow 7 to suppress the flow. Consequently, a space near an attachment part 7a in the bypass elbow is divided and the cavity flow generated in the space is suppressed and high temperature combustion gas is prevented from flowing into the bypass elbow 7. <P>COPYRIGHT: (C)2006,JPO&NCIPI

Description

  The present invention relates to a structure of a bypass pipe constituting a gas turbine combustor.

  Conventionally, a gas turbine combustor has been provided with a combustor tail tube that guides the combustion gas to a turbine located behind, but the wall surface of the combustor tail tube is constantly exposed to high-temperature combustion gas. Therefore, a structure is adopted in which an air passage is provided inside the side wall portion forming the combustor tail pipe, and air is introduced and cooled from the outside to the inside (this is called film cooling). . Furthermore, the combustor tail cylinder is opened and closed so that the air-fuel ratio of the premixed combustor can be maintained at an appropriate value during partial load operation in order to adjust the amount of combustion air flowing from the compressor into the combustor inner cylinder. A bypass pipe with a controllable bypass valve is connected.

  FIG. 9 is a longitudinal sectional view schematically showing a schematic configuration of such a conventional gas turbine combustor. As shown in the figure, the gas turbine combustor 1 includes a tail cylinder 4 having an internal space as a combustion chamber, and an inner cylinder 6 having a mechanism for forming a premixed gas. A pilot nozzle 2 communicating with the pilot cone 5 is disposed at the axial center position of the cylinder 6. A main nozzle 8 communicating with the main burner 3 serving as a premixer is disposed around the pilot nozzle 2.

  The main fuel supplied to the main nozzle 8 is mixed with the combustion air supplied to the inner cylinder 6 as shown by the arrow A, and forms a premixed gas in the main burner 3. On the other hand, the pilot fuel supplied to the pilot nozzle 2 generates a pilot flame (diffusion flame) by the pilot nozzle 2. Then, the premixed gas is injected into the tail cylinder 4 and ignited by a pilot flame in the tail cylinder 4 to generate a premixed flame in the tail cylinder 4. Further, a bypass elbow 7 (corresponding to the bypass pipe) protrudes from the outer surface of the tail cylinder 4 toward the compartment casing (not shown), and a bypass valve BV is provided at the tip thereof.

  By the way, in the combustor having the above-described structure, there is a problem in that the connecting portion between the combustor transition and the bypass pipe is exposed to high-temperature combustion gas and is overheated. Since the film cooling structure is adopted for the side wall of the combustor tail tube, overheating does not occur, but the connection between the combustor tail tube and the bypass pipe overheats, resulting in a temperature difference at the boundary. Thermal stress caused by Furthermore, repeated generation of thermal stress causes thermal fatigue in the combustor tail cylinder, which is a factor that lowers durability.

In view of this, Patent Document 1 has been developed by the present applicant to cool the connecting portion between the combustor tail tube and the bypass pipe, prevent the occurrence of thermal fatigue in this portion, and improve the durability of the combustor tail tube. Is disclosed.
Japanese Patent Laid-Open No. 2004-92409

  However, the conventional configuration as described above may cause further problems. Specifically, in the conventional gas turbine combustor 1 shown in FIG. 9, the bypass air introduced into the tail cylinder 4 as indicated by the arrow B from the bypass elbow 7 by changing the opening degree of the bypass valve BV. The load is adjusted by increasing / decreasing the combustion air indicated by the arrow A. However, under the high load operation conditions where the bypass valve is fully closed to slightly opened, the amount of air flowing in from the bypass valve BV is small, and the high-temperature combustion gas circulating in the tail cylinder 4 as indicated by the arrow C is in the bypass elbow 7. As a result, the flow becomes unstable and the temperature of the base 7a of the bypass elbow fluctuates, which may cause damage due to thermal cycle fatigue.

  In view of the above-described problems, the present invention provides a gas turbine combustion which improves the durability of the combustor tail by preventing the occurrence of thermal cycle fatigue at the connection between the combustor tail and the bypass pipe. The purpose is to provide a vessel.

  In order to achieve the above object, according to the present invention, there is provided a gas turbine combustor in which air compressed by a compressor and fuel are reacted and burned, and the generated combustion gas is introduced into a turbine through a combustor tail tube. In the gas turbine combustor provided with a bypass pipe for introducing air into the combustor tail cylinder on the outer surface of the combustor tail cylinder, the gas turbine combustor is provided along the axial direction of the bypass pipe, and a space in the bypass pipe is formed. It has a partition plate to be divided.

  A gas turbine combustor that reacts and combusts air compressed by a compressor and fuel, and introduces the generated combustion gas to the turbine through the combustor tail tube, on the outer surface of the combustor tail tube. In the gas turbine combustor provided with a bypass pipe for introducing air into the combustor tail tube, a plurality of plates are arranged in a circumferential direction on the inner peripheral surface of the side wall of the bypass pipe and opposed to the plates. A through hole is provided in each side wall of the bypass pipe, and purge air is introduced from the through hole between the plate and the side wall of the bypass pipe, and the root is formed along the inner peripheral surface of the side wall of the bypass pipe by the purge air. A film air flow toward the part is formed.

  A gas turbine combustor that reacts and combusts air compressed by a compressor and fuel, and introduces the generated combustion gas to the turbine through the combustor tail tube, on the outer surface of the combustor tail tube. In the gas turbine combustor provided with a bypass pipe for introducing air into the combustor tail tube, the inner peripheral surface of the bypass pipe is formed in a substantially arc shape concentric with the inner peripheral surface of the side wall in the circumferential direction. A plurality of sleeves are continuously provided, and through holes are provided in the bypass pipe side walls facing the respective sleeves, and purge air is caused to flow between the sleeves and the bypass pipe side walls through the through holes. A film air flow is formed by air along the inner peripheral surface of the side wall of the bypass pipe toward the base of the bypass pipe.

  A gas turbine combustor that reacts and combusts air compressed by a compressor and fuel, and introduces the generated combustion gas to the turbine through the combustor tail tube, on the outer surface of the combustor tail tube. In the gas turbine combustor provided with a bypass pipe for introducing air into the combustor tail tube, a through hole is provided in a side wall of the bypass pipe, and purge air is jet-injected into the bypass pipe from the through hole. It is characterized by.

  Furthermore, the through-hole is opened from the outer peripheral surface to the inner peripheral surface of the bypass pipe side wall toward the base portion side of the bypass pipe. Alternatively, the through hole is opened from the outer peripheral surface to the inner peripheral surface of the bypass pipe side wall so as to be inclined in the circumferential direction of the bypass pipe.

  A gas turbine combustor that reacts and combusts air compressed by a compressor and fuel, and introduces the generated combustion gas to the turbine through the combustor tail tube, on the outer surface of the combustor tail tube. In the gas turbine combustor provided with a bypass pipe for introducing air into the combustor tail tube, a slit extending in a circumferential direction of the bypass pipe is provided on a side wall of the bypass pipe, and purge air flows into the bypass pipe from the slit. It was made to let it be made to do.

  ADVANTAGE OF THE INVENTION According to this invention, the gas turbine combustor which aimed at the durability improvement of a combustor tail cylinder can be provided by preventing generation | occurrence | production of the heat cycle fatigue in the connection part of a combustor tail cylinder and a bypass pipe. .

  Specifically, by providing a partition plate that is provided along the axial direction of the bypass pipe and divides the space in the bypass pipe, the cavity flow formed in this space is suppressed, and high-temperature combustion into the bypass pipe is performed. Gas inflow can be prevented.

  In addition, on the inner peripheral surface of the side wall of the bypass pipe, a plurality of plates are connected in the circumferential direction, and through holes are provided in the side walls of the bypass pipe facing each plate, and between the through hole and the plate and the side wall of the bypass pipe. The purge air is caused to flow in, and the purge air forms a film air flow along the inner peripheral surface of the bypass pipe along the side wall of the bypass pipe. It is possible to prevent contact and to suppress the temperature rise of the inner peripheral surface of the side wall of the bypass pipe.

  A plurality of sleeves formed in a substantially arc shape concentric with the inner peripheral surface of the side wall in the circumferential direction on the inner peripheral surface of the bypass pipe are continuously provided, and through holes are respectively formed in the bypass pipe side walls facing the respective sleeves. The purge air is allowed to flow between the sleeve and the bypass pipe side wall from the through hole, and a film air flow toward the root of the bypass pipe along the inner peripheral surface of the bypass pipe is formed by the purge air. As a result, a film air flow is more reliably formed.

  Further, by providing a through hole in the bypass pipe side wall and jetting purge air from the through hole into the bypass pipe, an air curtain is formed to prevent combustion gas from flowing into the bypass pipe. In addition, the gas temperature can be lowered by mixing the combustion gas and the purge air, and the wall surface temperature at the base portion and the vicinity thereof can be lowered.

  Furthermore, by opening the through hole from the outer peripheral surface to the inner peripheral surface of the bypass pipe side wall toward the base of the bypass pipe, the inflow of combustion gas is further suppressed and mixing with purge air is further promoted. The gas temperature is more effectively lowered.

  Alternatively, by opening the through-hole obliquely in the circumferential direction of the bypass pipe from the outer peripheral surface to the inner peripheral surface of the bypass pipe side wall, the contact of the combustion gas flowing into the bypass pipe with the inner peripheral surface of the bypass pipe side wall is prevented. And the temperature rise of the bypass pipe side wall inner peripheral surface is suppressed.

  Moreover, by providing a slit extending in the circumferential direction of the bypass pipe in the bypass pipe side wall, and by allowing purge air to flow into the bypass pipe from the slit, the mixing with the high-temperature combustion gas flowing into the bypass pipe is made more uniform, The wall surface temperature of the root portion of the bypass pipe can be lowered. In addition, the thin air film layer formed by the slits can suppress the inflow of combustion gas into the bypass pipe in the entire cross section of the bypass pipe.

  Hereinafter, embodiments of the present invention will be described with reference to the drawings. In addition, the same code | symbol is attached | subjected to the part which is common in the said prior art example, and detailed description is abbreviate | omitted suitably.

  FIG. 1 is a diagram schematically showing a configuration of a gas turbine combustor according to a first embodiment of the present invention. FIG. 1 (a) is a longitudinal sectional view of a bypass elbow, and FIGS. 1 (b) and (c) are views. It is a cross-sectional view of the vicinity of the base. As described above, in the high load operation condition where the bypass valve is fully closed to slightly opened, the amount of inflow air from the bypass valve BV is small, and the combustion gas in the tail cylinder 4 is caught in the bypass elbow 7 and the flow is increased. It becomes unstable.

  In this case, when the combustion gas is entrained in the bypass elbow 7 as shown by the arrow D in FIG. 4A, this becomes a so-called cavity flow that circulates in the bypass elbow 7 as shown by the arrow E. Therefore, in order to suppress this flow, the partition plate 9 is inserted into the bypass elbow 7 along the center axis direction (not shown) of the bypass elbow 7. Thereby, the space near the base portion 7 a in the bypass elbow 7 is divided to suppress the cavity flow formed in this space, and the inflow of high-temperature combustion gas into the bypass elbow 7 is prevented.

  Specifically, the partition plate 9 is arranged so that the inside of the bypass elbow 7 is divided into two along the flow of the combustion gas indicated by the arrow C as indicated by a solid line in FIG. Alternatively, as shown by a two-dot chain line, the partition plate 9 may be arranged in a direction perpendicular to the flow of the combustion gas. In addition, it is possible to analyze the direction in which the cavity flow is likely to occur, and to arrange the partition plate 9 in the direction most effective in suppressing this. Alternatively, as shown in FIG. 5C, two partition plates 9 may be provided so as to intersect each other perpendicularly when viewed from the axial direction of the bypass elbow 7 and arranged in a cross shape. Thereby, formation of a cavity flow can be suppressed more effectively.

  FIG. 2 is a diagram schematically showing the configuration of the gas turbine combustor according to the second embodiment of the present invention. FIG. 2A is a cross-sectional view of the vicinity of the root portion of the bypass elbow, and FIG. (C) is a longitudinal sectional view. In this embodiment, as shown in FIGS. 4A and 4B, on the inner peripheral surface of the side wall of the bypass elbow 7, the plate 10 is connected in the circumferential direction, and on the side wall of the bypass elbow 7 facing each plate 10. Each of the through holes 7b is arranged in the circumferential direction and the axial direction of the bypass elbow 7 so as to have a plurality of openings. Then, as indicated by an arrow F, purge air is caused to flow in and collide with the plate 10, and then a film air flow is formed along the inner peripheral surface of the bypass elbow 7 toward the root portion 7a. Thereby, it is prevented that high temperature combustion gas contacts the inner peripheral surface of the side wall of the bypass elbow 7, and the temperature rise of the inner peripheral surface of the side wall of the bypass elbow 7 is suppressed.

  As shown in FIG. 5A, the plate 10 may be combined in a rectangular frame shape as viewed from the axial direction of the bypass elbow 7 so that each vertex contacts the inner peripheral surface of the side wall of the bypass elbow 7. . At this time, a space is formed independently between each plate 10 and the side wall inner peripheral surface of the bypass elbow 7, so by adjusting the number and size of the corresponding through holes 7 b. The flow rate of purge air introduced into each space can be adjusted in the circumferential direction of the bypass elbow 7.

  This makes it possible to balance the flow rate of purge air against the pressure deviation in the bypass elbow 7. In addition, the flow rate of the purge air can be increased by increasing the number of through holes 7b or increasing the diameter in a portion that requires further cooling. The combination of the plates 10 is not limited to a quadrangle, and may be another polygon.

  Moreover, as shown in the figure (c), it is good also as a structure which opened the through-hole 7b diagonally downward (base part side) from the outer peripheral surface of the bypass elbow 7 side wall to the inner peripheral surface. As a result, purge air is introduced into the bypass elbow 7 obliquely downward as indicated by an arrow F, so that the film air flow toward the root portion 7a along the inner peripheral surface of the bypass elbow 7 is ensured. It is formed.

  In addition, it is desirable that the upper end of the plate 10 be provided with a lid 10 a that closes the opening between the inner wall surface of the bypass elbow 7. Thereby, the introduced purge air is surely ejected from the lower end of the plate 10, so that the film air flow is more reliably formed. Further, since the so-called passage area is narrowed by covering, the flow rate is increased even when the purge air flow rate is the same, and a larger purge effect can be obtained. In addition, although the structure which opened the through-hole 7b diagonally downward and the structure which provided the cover 10a are drawn collectively in the figure (c), of course, you may comprise these separately.

  FIG. 3 is a diagram schematically showing the configuration of the gas turbine combustor according to the third embodiment of the present invention. FIG. 3 (a) is a cross-sectional view of the vicinity of the root portion of the bypass elbow, and FIG. (C) is a longitudinal sectional view. In this embodiment, as shown in FIGS. 4A and 4B, the inner wall of the bypass elbow 7 is formed in a substantially arc shape concentric with the inner wall of the side wall of the bypass elbow 7, and the inner wall of the side wall at both circumferential ends. A plurality of sleeves 11 fixed to each other are arranged in the circumferential direction of the bypass elbow 7, and through holes 7 b are arranged in the circumferential direction and the axial direction of the bypass elbow 7 on the side wall of the bypass elbow 7 facing each sleeve 11. The structure is open.

  Then, as indicated by an arrow F, purge air flows in and collides with the sleeve 11, and then a film air flow is formed along the inner peripheral surface of the bypass elbow 7 toward the root portion 7a. Thus, in the same manner as in the second embodiment, high temperature combustion gas is prevented from coming into contact with the inner peripheral surface of the side wall of the bypass elbow 7, and the temperature rise of the inner peripheral surface of the bypass elbow 7 is suppressed. In the present embodiment, since the sleeve 11 has a shape along the bypass elbow 7, the film air flow is more reliably formed than in the case of the second embodiment.

  Since each space is formed independently between each sleeve 11 and the inner peripheral surface of the side wall of the bypass elbow 7, each space can be adjusted by adjusting the number and size of the corresponding through holes 7b. The flow rate of the purge air introduced into the can be adjusted in the circumferential direction of the bypass elbow 7. This makes it possible to balance the flow rate of purge air against the pressure deviation in the bypass elbow 7. In addition, the flow rate of the purge air can be increased by increasing the number of through holes 7b or increasing the diameter in a portion that requires further cooling.

  The number of sleeves 11 is not limited to four as shown in FIG. In this case, as the number of sleeves 11 increases, the flow rate of purge air can be finely adjusted in the circumferential direction of the bypass elbow 7.

  Moreover, as shown in the figure (c), it is good also as a structure which opened the through-hole 7b diagonally downward (base part side) from the outer peripheral surface of the bypass elbow 7 side wall to the inner peripheral surface. As a result, purge air is introduced into the bypass elbow 7 obliquely downward as indicated by an arrow F, so that the film air flow toward the root portion 7a along the inner peripheral surface of the bypass elbow 7 is ensured. It is formed.

  In addition, it is desirable that the upper end of the sleeve 11 is provided with a lid 11a that closes the opening between the inner wall and the inner peripheral surface of the bypass elbow 7. Thereby, the introduced purge air is surely ejected from the lower end of the sleeve 11, so that a film air flow is more reliably formed. Further, since the so-called passage area is narrowed by covering, the flow rate is increased even when the purge air flow rate is the same, and a larger purge effect can be obtained. In addition, in the same figure (c), although the structure which opened the through-hole 7b diagonally downward and the structure which provided the lid | cover 11a are drawn collectively, of course, you may comprise these separately.

  FIG. 4 is a diagram schematically illustrating the configuration of a gas turbine combustor according to a fourth embodiment of the present invention. FIG. 4A is a longitudinal sectional view of a bypass elbow, and FIG. It is a cross-sectional view. In this embodiment, as shown in the figure, a plurality of through holes 7b are arranged in the circumferential direction and the axial direction of the bypass elbow 7 in the side wall of the bypass elbow 7 near the base portion 7a. Then, purge air is introduced from here as indicated by arrow F.

  In this case, the diameter of the through-hole 7b is set to 2 to 3 mm, for example, and an air curtain is formed by jetting purge air from the side wall of the bypass elbow 7 toward the center so that the combustion gas is bypassed as indicated by an arrow D. Inflow into the elbow 7 is suppressed. In addition, the gas temperature is lowered by mixing combustion gas and purge air, and the wall surface temperature at the base portion 7a and the vicinity thereof is lowered.

  The arrangement of the through holes 7b may be one step or a plurality of steps in the axial direction of the bypass elbow 7. In the case of a plurality of stages, the through holes 7b of each stage are arranged alternately in the axial direction of the bypass elbow 7 or arranged in directions in which the angles are slightly shifted when viewed from the center, so that the space near the base 7a Is filled with purge air as much as possible to prevent the combustion gas from flowing into the bypass elbow 7 more effectively.

  FIG. 5 is a diagram schematically showing the configuration of the gas turbine combustor according to the fifth embodiment of the present invention, and is a longitudinal sectional view of a bypass elbow. In the present embodiment, in addition to the configuration of the fourth embodiment, the through hole 7b is opened obliquely downward (at the base portion side) from the outer peripheral surface to the inner peripheral surface of the bypass elbow 7 side wall. Thus, purge air is introduced into the bypass elbow 7 obliquely downward as indicated by an arrow F, and is opposed to the combustion gas flowing into the bypass elbow 7 as indicated by an arrow D. As a result, inflow of combustion gas is further suppressed, mixing with purge air is further promoted, and the gas temperature is more effectively lowered.

  FIG. 6 is a diagram schematically showing the configuration of the gas turbine combustor according to the sixth embodiment of the present invention, and is a cross-sectional view of the vicinity of the root portion of the bypass elbow. In the present embodiment, in addition to the configuration of the fourth embodiment, the through hole 7b is opened obliquely in the circumferential direction from the outer peripheral surface to the inner peripheral surface of the bypass elbow 7 side wall. As a result, purge air is introduced into the bypass elbow 7 obliquely in the circumferential direction as shown by the arrow F, and swirl is given. And the film air flow of the circumferential direction along the side wall inner peripheral surface of the bypass elbow 7 is formed with a centrifugal force. As a result, the contact of the combustion gas flowing into the bypass elbow 7 with the inner peripheral surface of the bypass elbow 7 is prevented, and the temperature rise of the inner peripheral surface of the bypass elbow 7 is suppressed.

  FIG. 7 is a diagram schematically showing the configuration of the gas turbine combustor according to the seventh embodiment of the present invention, and is a perspective view of the vicinity of the root portion of the bypass elbow. In the present embodiment, the fifth embodiment and the sixth embodiment are combined, and the through-hole 7b (not shown here) is inclined obliquely downward and circumferentially from the outer peripheral surface to the inner peripheral surface of the bypass elbow 7 side wall. It is configured to open diagonally. As a result, the purge air is introduced into the bypass elbow 7 obliquely downward and obliquely in the circumferential direction as indicated by the arrow F, and swirl is given.

  Then, a film air flow is formed in the circumferential direction along the inner peripheral surface of the side wall of the bypass elbow 7 and toward the base portion by centrifugal force. As a result, contact of the combustion gas flowing into the bypass elbow 7 with the inner peripheral surface of the bypass elbow 7 side wall is surely prevented, particularly with the inner peripheral surface of the bypass elbow 7 side wall, and the temperature rise particularly at the base portion is ensured. It is suppressed.

  FIG. 8 is a diagram schematically illustrating the configuration of the gas turbine combustor according to the eighth embodiment of the present invention. In this embodiment, instead of the through hole 7b, a plurality of slits 7c extending in the circumferential direction of the bypass elbow 7 are arranged in the circumferential direction or the axial direction and opened. 4A is a longitudinal sectional view of the bypass elbow when the slits 7c are arranged in the axial direction, and FIG. 4B is a transverse sectional view near the base portion when the slits 7c are arranged in the circumferential direction.

  In the case of arranging in the axial direction, for example, as shown in FIG. 4A, one slit per stage is arranged in a direction shifted in angle from the center so as to extend over the entire circumference. When arranged in the circumferential direction, for example, as shown in FIG. 5B, the slits are arranged over the entire circumference, leaving the side walls between the slits so that there is no problem in strength. In this way, if the space near the base portion 7a is filled with purge air as much as possible, the inflow of combustion gas into the bypass elbow 7 can be more effectively suppressed. Of course, the configurations shown in FIGS. 6A and 6B may be combined.

  As in the present embodiment, the purge air hole is made into a narrow slit, so that the mixing with the high-temperature combustion gas flowing into the bypass elbow can be made more uniform, and the wall surface temperature of the bypass elbow root can be lowered. In addition, the thin air film layer formed by the slits can suppress the inflow of combustion gas into the bypass elbow in the entire cross section of the bypass elbow.

  Further, although not shown, the slit 7c may be opened obliquely downward (at the base portion side) from the outer peripheral surface to the inner peripheral surface of the bypass elbow 7 side wall. Thus, in the same manner as in the fifth embodiment, purge air is introduced obliquely downward into the bypass elbow 7 and faces the combustion gas flowing into the bypass elbow 7. As a result, inflow of combustion gas is further suppressed, mixing with purge air is further promoted, and the gas temperature is more effectively lowered.

The figure which shows typically the structure of the gas turbine combustor which concerns on Example 1 of this invention. The figure which shows typically the structure of the gas turbine combustor which concerns on Example 2 of this invention. The figure which shows typically the structure of the gas turbine combustor which concerns on Example 3 of this invention. The figure which shows typically the structure of the gas turbine combustor which concerns on Example 4 of this invention. The figure which shows typically the structure of the gas turbine combustor which concerns on Example 5 of this invention. The figure which shows typically the structure of the gas turbine combustor which concerns on Example 6 of this invention. The figure which shows typically the structure of the gas turbine combustor which concerns on Example 7 of this invention. The figure which shows typically the structure of the gas turbine combustor which concerns on Example 8 of this invention. The longitudinal cross-sectional view which shows typically schematic structure of the conventional gas turbine combustor.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 Gas turbine combustor 2 Pilot nozzle 3 Main burner 4 Tail cylinder 5 Pilot cone 6 Inner cylinder 7 Bypass elbow 8 Main nozzle 9 Partition plate 10 Plate 11 Sleeve BV Bypass valve

Claims (7)

A gas turbine combustor that reacts and compresses air compressed by a compressor and fuel and introduces the generated combustion gas into a turbine through a combustor tail,
In the gas turbine combustor provided with a bypass pipe for introducing air into the combustor tail tube on the outer surface of the combustor tail tube,
A gas turbine combustor provided with a partition plate provided along the axial direction of the bypass pipe and dividing a space in the bypass pipe. A gas turbine combustor that reacts and compresses air compressed by a compressor and fuel and introduces the generated combustion gas into a turbine through a combustor tail,
In the gas turbine combustor provided with a bypass pipe for introducing air into the combustor tail tube on the outer surface of the combustor tail tube,
On the inner peripheral surface of the side wall of the bypass pipe, a plurality of plates are connected in the circumferential direction, and through holes are provided in the side walls of the bypass pipe facing the plates, and the plate and the bypass pipe are provided from the through holes. A gas turbine combustor characterized in that purge air is allowed to flow between the side wall and the purge air to form a film air flow toward the root along the inner peripheral surface of the side wall of the bypass pipe. A gas turbine combustor that reacts and compresses air compressed by a compressor and fuel and introduces the generated combustion gas into a turbine through a combustor tail,
In the gas turbine combustor provided with a bypass pipe for introducing air into the combustor tail tube on the outer surface of the combustor tail tube,
In the inner peripheral surface of the side wall of the bypass pipe, a plurality of sleeves formed in a substantially arc shape concentric with the inner peripheral surface of the side wall are provided in a circumferential direction, and each of the bypass pipe side walls facing the respective sleeves is provided. A film which has a through hole, allows purge air to flow between the sleeve and the bypass pipe side wall from the through hole, and is directed toward the root of the bypass pipe along the inner peripheral surface of the bypass pipe by the purge air. A gas turbine combustor characterized by forming an air flow. A gas turbine combustor that reacts and compresses air compressed by a compressor and fuel and introduces the generated combustion gas into a turbine through a combustor tail,
In the gas turbine combustor provided with a bypass pipe for introducing air into the combustor tail tube on the outer surface of the combustor tail tube,
A gas turbine combustor characterized in that a through hole is provided in a side wall of the bypass pipe, and purge air is jetted into the bypass pipe from the through hole.   5. The gas turbine combustor according to claim 4, wherein the through hole is opened from an outer peripheral surface to an inner peripheral surface of the bypass pipe side wall toward a base portion side of the bypass pipe.   5. The gas turbine combustor according to claim 4, wherein the through hole is opened obliquely in a circumferential direction of the bypass pipe from an outer peripheral surface to an inner peripheral surface of the bypass pipe side wall. A gas turbine combustor that reacts and compresses air compressed by a compressor and fuel and introduces the generated combustion gas into a turbine through a combustor tail,
In the gas turbine combustor provided with a bypass pipe for introducing air into the combustor tail tube on the outer surface of the combustor tail tube,
A gas turbine combustor, wherein a slit extending in a circumferential direction of the bypass pipe is provided on a side wall of the bypass pipe, and purge air is allowed to flow into the bypass pipe from the slit.

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