JP2019132218A - Gas turbine combustor and transition piece flow sleeve - Google Patents

Abstract

To reduce an excitation force to a transition piece flow sleeve caused by compressed air discharged from a compressor, and to suppress the generation of cracks and wear.SOLUTION: A gas turbine combustor comprises: a transition piece 4 of the combustor in which a high-temperature combustion gas flow; a transition piece flow sleeve 5 for encapsulating the transition piece 4; a flow passage 9 formed between the transition piece flow sleeve 5 and the transition piece 4, and making compressed air 100 discharged from a compressor flow; and impingement holes 22 formed at outlet sides of a backside face, a body side face and a side face of the transition piece flow sleeve 5 in a plurality of pieces, and introducing the compressed air 100 discharged from the compressor into the flow passage 9. A rectification structure 12 for controlling a flow rate of the compressed air 100 intruding into the impingement holes 22 is arranged at the body side face of the transition piece flow sleeve 5.SELECTED DRAWING: Figure 4

Description

  The present invention relates to a gas turbine combustor and a transition piece flow sleeve, and in particular, a plurality of transition piece flow sleeves are provided on the rear side, the ventral side, and the side of the side of the transition piece flow sleeve, and formed between the transition piece flow sleeve and the transition piece. The present invention relates to a gas turbine combustor and a transition piece flow sleeve suitable for those having an impingement hole that guides compressed air discharged from a compressor to a flow path.

  In general, in a gas turbine combustor, compressed air discharged from a compressor used for combustion and cooling is introduced inside a transition piece flow sleeve and guided to a burner of the combustor.

  Normally, several rows of impingement holes (air introduction holes) are arranged in the axial direction and several tens of rows in the circumferential direction of each row on the back side, abdomen side, and side surfaces of the transition piece flow sleeve.

  Also, in the case of a structure in which the compressed air discharged from the compressor collides directly with the transition piece flow sleeve, due to fluctuations in the flow of compressed air discharged from the compressor, along with the introduction of unstable compressed air and dynamic pressure fluctuations The transition piece may vibrate and wear or damage (crack) may occur in each part.

  Further, when there is a deviation in the flow rate at the position of each impingement hole, an impingement hole having a large flow rate may cause unintended dynamic pressure fluctuations or excessive pressure loss due to the high flow velocity.

  In a gas turbine combustor, there is a technology for rectifying the compressed air supplied to the transition piece flow sleeve on the outer surface of the transition piece flow sleeve to alleviate the deviation of the compressed air introduced into each of the plurality of impingement holes. It is described in Patent Documents 1-3.

  In Patent Document 1, a liner of a gas turbine combustor is surrounded by a transition piece flow sleeve with a cooling hole and cooled by air supplied through the cooling hole, and the transition piece is surrounded by a porous sleeve. After the compressed air is supplied through the hole (impingement hole) of the perforated sleeve and collides with the transition piece, it flows into the space between the liner and the transition piece flow sleeve, and there is a cooling sleeve in the liner. The cross flow that flows from the piece into the space between the liner of the liner portion and the transition piece flow sleeve flows along the concave portion of the cooling sleeve, the convex portion serves as a guide for jet flow, and the cross flow flows into the concave portion. So that the jet Row without being affected by cross-flow, as a result, it has been described that to effectively cool the liner.

  In Patent Document 2, a transition piece is attached to the rear end of the liner inner cylinder, and a cooling passage is formed by surrounding the outside of the transition piece with a transition piece flow sleeve at a predetermined interval. It is described that a plurality of circular cooling holes are formed in the sleeve, and cooling air is guided from the cooling holes to be ejected toward the transition piece.

  Further, Patent Document 3 discloses a gas turbine that convectively cools a transition piece with a transition piece flow sleeve, and high-pressure air introduced from a compressor is introduced from a diffuser into a ventral compartment and a back compartment. After flowing through the gap between the transition piece and the transition piece flow sleeve installed on the outer periphery of the transition piece, it is described that the flow passes through the gap between the liner and the liner flow srobe arranged concentrically on the outer periphery of the liner. Yes.

JP2015-135111A Japanese Patent No. 3054420 JP 2000-146186 A

  However, in the conventional structure around the transition piece flow sleeve, the compressed air discharged from the compressor directly collides with the transition piece flow sleeve, and the flow of the compressed air fluctuates. There is a risk of causing cracks and wear.

  In addition, the compressed air introduced inward from the impingement hole provided in the transition piece flow sleeve has a difference in the inflow air amount several times depending on the position of the impingement hole (upstream or downstream). , Increase pressure loss.

  Furthermore, in the conventional structure, since a large amount of compressed air flows from the impingement hole on the combustor burner side (upstream side), cooling on the turbine side (downstream side) of the transition piece body is insufficient. That is, when compressed air from the compressor is introduced into the vehicle compartment and enters a plurality of impingement holes, a large amount of compressed air enters the holes on the combustor burner side (upstream side) of the impingement holes. Compressed air entering the impingement hole on the downstream side is reduced, and cooling on the turbine side (downstream side) is insufficient.

  In addition, the flow rate of compressed air in the passenger compartment on the back side of the transition piece flow sleeve is smaller than the flow rate of compressed air in the passenger compartment on the ventral side of the transition piece flow sleeve into which the compressed air is introduced. There is also a problem that a flow rate deviation occurs in the vehicle compartment on the back side.

  On the other hand, in Patent Document 1, a cross flow that flows from a transition piece into a space between a liner of a liner portion and a transition piece flow sleeve flows along a concave portion of the cooling sleeve, and the convex portion is a guide for jet flow. It is described that the jet flow is not affected by the cross flow, and as a result, the liner is effectively cooled. There is no effect of reducing the flow rate deviation at the inlet of the impingement, and it is not expected to reduce the pressure loss at the inlet of the impingement hole.

  Further, in Patent Document 2, a cooling passage is formed by surrounding the outside of a transition piece with a transition piece flow sleeve at a predetermined interval, and a plurality of circular cooling holes are formed in the transition piece flow sleeve. Although it is described that the cooling air is guided from the cooling holes and ejected toward the transition piece, it is not described that the transition piece flow sleeve has a function of adjusting the introduced air.

  Further, Patent Document 3 discloses that high-pressure air introduced from a compressor is introduced from a diffuser to the abdominal side surface and back side passenger compartment of the transition piece flow sleeve, the transition piece, and a transition piece flow installed on the outer periphery thereof. It is described that after flowing through the gap of the sleeve, it will flow through the gap between the liner and the liner flow srobe arranged concentrically on the outer circumference of the liner, but the impingement hole that becomes the entrance of the transition piece flow sleeve There is no mention of mitigating the deviation.

  The present invention has been made in view of the above points, and its object is to reduce the vibration force applied to the transition piece flow sleeve by the compressed air discharged from the compressor, thereby suppressing the occurrence of cracks and wear. It is to provide a gas turbine combustor and a transition piece flow sleeve that can be used.

  In order to achieve the above object, a gas turbine combustor according to the present invention includes a transition piece of a combustor through which high-temperature combustion gas flows, and a transition piece flow around the transition piece and including the transition piece. A sleeve, a flow path formed between the transition piece flow sleeve and the transition piece, for flowing compressed air discharged from the compressor, and on the outlet side of the back side, the ventral side, and the side of the transition piece flow sleeve. A plurality of gas turbine combustors provided with an impingement hole for guiding compressed air discharged from the compressor to the flow path, and entering the impingement hole on the ventral side surface of the transition piece flow sleeve A rectifying structure for controlling the flow rate of the compressed air is disposed. It is characterized in that is.

  In order to achieve the above object, the transition piece flow sleeve of the present invention is a transition piece flow sleeve of a combustor that contains a transition piece through which high-temperature combustion gas flows, and the transition piece flow sleeve comprises: A flow rate of the compressed air entering the impingement hole on the ventral side of the transition piece flow sleeve is provided with a plurality of impingement holes on the back side, the ventral side, and the outlet sides of the transition piece flow sleeve. A rectifying structure for controlling the flow is disposed.

  ADVANTAGE OF THE INVENTION According to this invention, the vibration force to the transition piece flow sleeve by the compressed air discharged from the compressor can be reduced, and generation | occurrence | production of a crack and wear can be suppressed.

It is a figure showing the whole gas turbine combustor composition for power plants. It is a figure which shows the detail by the side of the turbine of the gas turbine combustor for demonstrating the flow of the compressed air around the transition piece in the gas turbine combustor of this invention. It is sectional drawing along the AA line of FIG. It is a figure which shows the detail by the side of the turbine of the gas turbine combustor of Example 1 of the gas turbine combustor of this invention. It is a perspective view which shows an example of the specific structure of a baffle plate as Example 2 of the gas turbine combustor of this invention. It is a perspective view which shows the other example of the specific structure of a baffle plate as Example 3 of the gas turbine combustor of this invention. It is a perspective view which shows one transition piece flow sleeve as Example 4 of the gas turbine combustor of this invention. It is a perspective view which shows two adjacent transition piece flow sleeves.

  Hereinafter, the gas turbine combustor and the transition piece of the present invention will be described based on the illustrated embodiments. In the embodiments described below, the same reference numerals are used for the same components.

  In FIG. 1, the whole structure of the gas turbine combustor for the general power plants used as the object of this invention is shown.

  As shown in FIG. 1, a gas turbine combustor that is an object of the present invention includes a transition piece 4 of a combustor through which high-temperature combustion gas 107 flows, and a transition piece 4 around the transition piece 4. The transition piece flow sleeve 5 to be included, the flow path 9 that is formed between the transition piece flow sleeve 5 and the transition piece 4 and flows the high-temperature and high-pressure compressed air 100 discharged from the compressor 300, and the transition piece 4 are connected. And a liner flow sleeve 7 connected to the transition piece flow sleeve 5 and arranged concentrically on the outer periphery of the liner 6 to form a gap through which the flow 102 of compressed air 100 passes.

  Then, the compressed air 100 introduced from the air compressor 300 is separated from the diffuser 1 to the abdominal side passenger compartment 2 (inner side space in the passenger compartment) and back side passenger compartment 3 (outer side space in the passenger compartment). And flows into a gap (flow path 9) formed by the transition piece flow sleeve 5 and the transition piece 4 (indicated by arrows 20 and 21).

  That is, a part of the compressed air 100 introduced from the diffuser 1 into the abdominal compartment 2 enters the flow path 9 formed by the transition piece flow sleeve 5 and the transition piece 4 from the abdomen side of the transition piece 4. The flow 21 becomes the flow 20, and the rest passes through the adjacent transition piece 4 and wraps around the back cabin 3, and then enters the flow path 9 formed by the transition piece flow sleeve 5 and the transition piece 4. Become.

  Thereafter, the compressed air 100 flowing into the flow path 9 becomes a flow 102 passing through the gap between the liner 6 and the liner flow sleeve 7 disposed concentrically on the outer periphery of the liner 6 as indicated by a flow 101. Then, the flow is reversed and introduced into the burner section 103 and 104, mixed with the fuel supplied from the fuel systems 200 and 201, and forms flames 105 and 106 in the combustion chamber 8 inside the liner 6 to form high-temperature and high-pressure combustion. It becomes gas 107. Thereafter, the combustion gas 108 is introduced into the turbine 301 from the transition piece 4. In the gas turbine, the work generated when the high-temperature and high-pressure combustion gas 108 adiabatically expands is converted into axial torque in the turbine 301. Thus, an output is obtained from the generator 302.

  There is also a plant that uses a gas turbine as a power source for fluid compression by rotating another compressor instead of the generator 302 using the shaft rotational force in the turbine 301.

  Incidentally, in recent years, in the gas turbine combustor for a general power plant shown in FIG. 1, the transition piece flow sleeve 5 is discharged from the compressor 300 to the outlet side (turbine side) of the back side, the belly side, and the side. A configuration (see FIG. 8) including a plurality of impingement holes 22 that guides the compressed air 100 as cooling air for the transition piece 4 to the flow path 9 is employed.

  FIG. 2 shows a configuration in which a plurality of impingement holes 22 that guide the compressed air 100 discharged from the compressor 300 to the flow path 9 are provided on the outlet side (turbine side) of the transition piece flow sleeve 5.

  As shown in FIG. 2, on the outlet side (turbine side) of the transition piece flow sleeve 5, a plurality of impingement holes (three in FIG. 2) that guide the compressed air 100 discharged from the compressor 300 to the flow path 9. 22 is formed.

  More specifically, as shown in FIG. 8, the impingement holes 22 are arranged in a plurality of rows in the circumferential direction on the entire outlet side of the transition piece flow sleeve 5 (back side surface, abdominal side surface, both side surfaces). Has been. Further, as shown in FIG. 3, the transition piece flow sleeve 5 is disposed so as to contain the transition piece 4, and a flow path 9 is formed in the gap between the transition piece flow sleeve 5 and the transition piece 4.

  The flow of the compressed air 100 around the transition piece 4 in this configuration is as follows. That is, a part of the compressed air 100 introduced from the diffuser 1 into the abdominal compartment 2 is formed by the transition piece flow sleeve 5 and the transition piece 4 via the impingement hole 22 from the abdomen side of the transition piece 4. The flow 20 enters the flow path 9, and the rest flows through the adjacent transition piece 4, wraps around the back cabin 3, and then enters the flow path 9 via the impingement hole 22. Become.

  In each impingement hole 22, the compressed air 100 is jetted toward the transition piece 4 arranged with a predetermined gap from the transition piece flow sleeve 5, and the transition piece 4 is caused to collide with the outer surface of the transition piece 4. It is cooling.

  However, in the configuration of FIG. 2, the compressed air 100 discharged from the compressor 300 maintains a dynamic pressure in the vicinity of the ventral guide 11 provided on the ventral side surface that fixes the transition piece 4 and the transition piece flow sleeve 5. The collision may cause the transition piece 4 and the transition piece flow sleeve 5 to vibrate and cause cracks and wear of each part.

  Further, the compressed air 100 introduced into the flow path 9 from the impingement hole 22 provided in the transition piece flow sleeve 5 flows to the inside of the transition piece flow sleeve 5, but the downstream side (turbine side) in the combustor axial direction is As shown in FIG. 8, the interval (circumferential interval between the two combustor cans) between the combustor cans (box-like object formed by the transition piece 4 and the transition piece flow sleeve 5) adjacent in the circumferential direction is as follows. It becomes narrower toward the downstream side in the combustor axial direction (turbine side). For this reason, it is difficult for air to flow on the downstream side, and among the plurality of impingement holes 22 formed, the impingement holes 22 on the upstream side (burner side) in the combustor axial direction (the three impingement holes 22 in FIG. 2). A lot of air flows on the left side.

  Therefore, the gas turbine combustor of the present invention has solved the above-described problems.

  FIG. 4 shows a first embodiment of the gas turbine combustor according to the present invention.

  The gas turbine combustor of the present embodiment shown in FIG. 4 is substantially the same as the configuration shown in FIGS. 2 and 3, but in this embodiment, the impingement hole 22 is provided on the ventral side surface of the transition piece flow sleeve 5. A rectifying plate 12 is arranged as a rectifying structure that controls the flow rate of the compressed air 100 that enters.

  This baffle plate 12 is supported by a ventral side guide 11 that fixes the ventral side surfaces of the transition piece 4 and the transition piece flow sleeve 5, and receives pressure from the upstream side to the downstream side with respect to the air flow. In order to increase the projected area, for example, it is formed in a conical shape (otherwise, it may be a quadrangular pyramid shape or a triangular pyramid shape).

  Further, the rectifying plate 12 has an impingement formed on the most combustor burner side among a plurality (three in this embodiment) of impingement holes 22 provided on the outlet side of the ventral side surface of the transition piece flow sleeve 5. It is arranged at a position close to the ment hole 22.

  Therefore, in the case of the conventional structure without the rectifying plate 12, the compressed air 100 discharged from the compressor 300 collides with the surface of the transition piece flow sleeve 5 arranged substantially perpendicular to the flow while maintaining a certain flow velocity. However, according to the above-described configuration of the present embodiment, the ventral guide 11 has the flow straightening plate 12 formed in a conical shape so that the pressure receiving projection area increases from the upstream to the downstream with respect to the air flow. The incident angle of the compressed air 100 with respect to the transition piece flow sleeve 5 is reduced, and the flow velocity is also reduced due to friction loss while flowing on the surface of the rectifying plate 12.

  Moreover, at the end of the rectifying plate 12, the flow is separated and a vortex is generated, whereby the flow velocity is further reduced. When the flow reaches the transition piece flow sleeve 5, the static pressure is recovered and the transition piece flow sleeve 5 by the compressed air 100 is recovered. The excitation force is reduced.

  Further, since the compressed air 100 flows uniformly into the impingement hole 22 of the transition piece flow sleeve 5 by the internal / external differential pressure of the transition piece flow sleeve 5, the pressure caused by an excessive flow rate flowing into the specific impingement hole 22. Loss and flow rate deviation in the impingement hole 22 in the axial direction of the transition piece 4 can be reduced. Thereby, the temperature deviation of the axial direction of the transition piece 4 can be reduced and cooling performance can be improved.

  Further, the flow rate of the compressed air 100 in the passenger compartment 3 on the back side of the transition piece flow sleeve 5 is compared with the flow rate of the compressed air 100 in the passenger compartment 2 on the ventral side of the transition piece flow sleeve 5 into which the compressed air 100 is introduced. Although the flow rate was small and a flow rate deviation occurred between the abdominal compartment 2 and the back compartment 3, the flow straightening plate 12 was installed, so the transition piece flow sleeve 5 had a transition in the impingement hole 22. Since the compressed air 100 is evenly introduced by the internal / external pressure difference of the piece flow sleeve 5, the flow rate deviation of the compressed air 100 flowing through the abdominal compartment 2 and the back compartment 3 can be reduced.

  According to such a present Example, the vibration force of the transition piece flow sleeve 5 by dynamic pressure can be reduced by receiving the compressed air 100 discharged from the compressor 300 over a wide area by the rectifying plate 12. The occurrence of cracks and wear can be suppressed.

  Further, the compressed air 100 discharged from the compressor 300 flows evenly into the impingement holes 22 formed in the transition piece flow sleeve 5, whereby pressure loss can be reduced.

  Furthermore, the cooling of the transition piece 4 can be improved by flowing more compressed air 100 to the downstream side (turbine side) of the impingement hole 22 formed in the transition piece flow sleeve 5 than in the past.

  In other words, conventionally, the compressed air 100 flowing into the impingement hole 22 is located on the ventral side of the transition piece flow sleeve 5 that is closest to the outlet of the diffuser 1 (inlet of the passenger compartment). However, according to the present embodiment, it is possible to increase the flow rate of the compressed air 100 that circulates to the back side of the transition piece flow sleeve 5. As a result, the flow rate of the compressed air (cooling air) 100 introduced from the impingement hole 22 arranged on the back side of the transition piece flow sleeve 5 increases, and the transition piece 4 has a gap between the ventral side and the back side. It becomes possible to reduce the temperature deviation.

  FIG. 5 shows an example of a specific configuration of the rectifying plate 12 as a second embodiment of the gas turbine combustor of the present invention.

  The rectifying plate 12 of this embodiment shown in the figure is provided with at least one (one or a plurality) of square or circular projections 23 on the surface of the conical rectifying plate 12.

  In FIG. 5, the protrusions 23 are regularly provided on the surface of the rectifying plate 12 in the circumferential direction and the axial direction. However, the protrusions 23 are not necessarily provided regularly, and may be provided irregularly (randomly). good.

  By providing the rectifying plate 12 with the corners and the circular protrusions 23, the compressed air 100 flows on the surface of the protrusions 23, thereby causing fluid friction and the effect of micro vortices induced downstream of the protrusions 23. Since the flow velocity is reduced, further effects can be expected.

  FIG. 6 shows another example of the specific configuration of the rectifying plate 12 as the third embodiment of the gas turbine combustor of the present invention.

  In the current plate 12 of this embodiment shown in the figure, the downstream end surface 24 of the current plate 12 is formed in one or more curved shapes and / or irregular shapes.

  Since the downstream end surface of the rectifying plate 12 is formed in one or a plurality of curved shapes and / or irregular shapes, it is possible to cause flow separation on the downstream side of the downstream end surface 24 of the rectifying plate 12, As in Example 2, the flow rate can be reduced, and further effects can be expected.

  FIG. 7 shows one transition piece flow sleeve 5 as a fourth embodiment of the gas turbine combustor of the present invention.

  In the present embodiment shown in FIG. 7, in addition to the configuration of the first embodiment, a plurality of second control units for controlling the flow rate of the compressed air 100 discharged from the compressor 300 entering the impingement hole 22 on the side surface of the transition piece flow sleeve 5. The rectifying plates 25a and 25b, which are two rectifying structures, are disposed (the rectifying plate may be at least one (rectifying plate 25a)).

  The rectifying plates 25a and 25b described above are arranged so as to block the flow of the compressed air 100 entering the impingement hole 22 on the combustor burner side, the rectifying plate 25a is disposed between the circumferential directions of the impingement holes 22, and the rectifying plate 25b is The impingement holes 22 are respectively formed on the side surfaces of the transition piece flow sleeve 5 in which the impingement holes 22 are not formed.

  The rectifying plate 25a disposed between the impingement holes 22 in the circumferential direction and the rectifying plate 25b disposed on the side surface of the transition piece flow sleeve 5 where the impingement holes 22 are not formed are the transition piece flow sleeve 5. A plurality of transitions in which the impingement holes 22 are not formed by the rectifying plates 25 a disposed between the impingement holes 22 in the circumferential direction are arranged in a stepwise manner in the axial direction of the side surfaces of the impingement holes 22. A rectifying plate 25b arranged on the side surface of the piece flow sleeve 5 is formed large.

  In the conventional structure, in order to reduce the deviation of the gas temperature in the circumferential direction of the turbine inlet (outlet of the transition piece 4 of the combustor) of the gas turbine combustor, the interval between the downstream ends (turbine side) of the adjacent transition pieces 4 is Narrow (see FIG. 8).

  For this reason, the flow rate of the compressed air 100 flowing in the axially downstream end (turbine side) of the combustor is small, and the amount of the compressed air 100 flowing into the transition piece flow sleeve 5 from the impingement hole 22 is also small. On the contrary, at the position of the impingement hole 22 on the upstream side (burner side), the passing flow velocity between the adjacent transition pieces 4 is fast, and the compressed air 100 also flows in compared with the back side and the abdominal side of the transition piece flow sleeve 5. The amount of is small.

  In the above-described embodiment, a plurality of rectifying plates 25a and 25b are installed on the side surface of the transition piece flow sleeve 5, and therefore, the rectifying plates 25a and 25b are used for the upstream side in the axial direction (burner side) of the combustor. The flow of the compressed air 100 can be blocked, and the uniform compressed air 100 can flow into each impingement hole 22 by reducing the flow velocity, generating a separation vortex, and correcting the flow direction downstream.

  In addition, since the interval between the adjacent transition pieces 4 is wide on the axially upstream side (burner side) of the combustor (the transition piece 4 is not arranged in parallel with the adjacent transition piece 4, the combustor The upstream side of the combustor (burner side) is wide and the downstream side in the axial direction of the combustor (turbine side) is inclined and arranged so that the upstream side of the combustor (burner side) is By providing a rectifying plate 25b larger than the downstream side (turbine side) in the axial direction of the combustor, the impingement hole 22 in the axial direction of the combustor as compared with the conventional structure is provided. It becomes possible to equalize the amount of air flowing into the.

  According to the present embodiment, in addition to the effects of the first embodiment, it is possible to reduce the flow velocity of the side surface portion of the transition piece flow sleeve 5 in which the inflow amount is small in the conventional structure, and to restore the static pressure. The impingement hole 22 positioned on the downstream side (turbine side) of the combustor in the combustor of the transition piece flow sleeve 5 by equalizing the amount of the compressed air 100 flowing into the impingement hole 22 in the axial direction of the combustor. Moreover, the cooling in the axial direction downstream side of the main body of the transition piece 4 can be improved by flowing the compressed air 100 of the conventional structure or more (close to the average value).

  In addition, this invention is not limited to an above-described Example, Various modifications are included. For example, the above-described embodiments have been described in detail for easy understanding of the present invention, and are not necessarily limited to those having all the configurations described. Further, a part of the configuration of one embodiment can be replaced with the configuration of another embodiment, and the configuration of another embodiment can be added to the configuration of one embodiment. Further, it is possible to add, delete, and replace other configurations for a part of the configuration of each embodiment.

  DESCRIPTION OF SYMBOLS 1 ... Diffuser, 2 ... Car compartment (abdominal side), 3 ... Car compartment (back side), 4 ... Transition piece, 5 ... Transition piece flow sleeve, 6 ... Liner, 7 ... Liner flow sleeve, 8 ... Combustion chamber, 9 ... Flow path formed by transition piece and transition piece flow sleeve, 11 ... Ventral guide, 12, 25a, 25b ... Rectifying plate, 22 ... Impingment hole, 23 ... Protrusion, 24 ... Downstream end face of the baffle plate, 100 ... Compressed air, 105, 106 ... flame, 107, 108 ... combustion gas, 200, 201 ... fuel system, 300 ... compressor, 301 ... turbine, 302 ... generator.

Claims (13)

A combustor transition piece through which hot combustion gas flows, a transition piece flow sleeve around the transition piece and enclosing the transition piece, and formed between the transition piece flow sleeve and the transition piece. A plurality of flow paths for flowing compressed air discharged from the compressor, and a plurality of outlets on the back side, the ventral side, and the side of the transition piece flow sleeve, and the compressed air discharged from the compressor is supplied to the flow path A gas turbine combustor with an impingement hole leading to
A gas turbine combustor, wherein a rectifying structure for controlling a flow rate of the compressed air entering the impingement hole is disposed on a ventral side surface of the transition piece flow sleeve. A gas turbine combustor according to claim 1,
The gas flow combustor according to claim 1, wherein the rectifying structure is configured such that a pressure receiving projection area increases from upstream to downstream with respect to the flow of the compressed air. A gas turbine combustor according to claim 1 or 2,
The gas turbine combustor, wherein the rectifying structure is supported by a ventral guide for fixing the transition piece and a ventral side surface of the transition piece flow sleeve. A gas turbine combustor according to any one of claims 1 to 3,
2. The gas turbine combustor according to claim 1, wherein a plurality of the rectifying structures are arranged on the combustor burner side of the impingement hole provided on the outlet side of the ventral side surface of the transition piece flow sleeve. A gas turbine combustor according to any one of claims 1 to 4,
The gas turbine combustor, wherein the rectifying structure is a rectifying plate having a conical shape, a quadrangular pyramid shape, or a triangular pyramid shape. A gas turbine combustor according to claim 5,
A gas turbine combustor, wherein at least one square or circular protrusion is provided on a surface of the current plate. A gas turbine combustor according to claim 5 or 6,
A gas turbine combustor, wherein a downstream end face of the current plate is formed in a plurality of curved and / or irregular shapes. A gas turbine combustor according to any one of claims 1 to 7,
The gas turbine combustor, wherein at least one second rectifying structure for controlling a flow rate of the compressed air entering the impingement hole is disposed on a side surface of the transition piece flow sleeve. A gas turbine combustor according to claim 8,
The gas turbine combustor, wherein the second rectifying structure is disposed so as to block a flow of the compressed air entering the impingement hole on the combustor burner side. A gas turbine combustor according to claim 8 or 9,
The gas is characterized in that the second rectifying structure is a rectifying plate disposed between circumferential directions of the impingement holes and on a side surface of the transition piece flow sleeve in which the impingement holes are not formed. Turbine combustor. A gas turbine combustor according to claim 10,
The rectifying plates arranged between the circumferential directions of the impingement holes and on the side surface of the transition piece flow sleeve where the impingement holes are not formed are arranged in the axial direction and the vertical direction of the side surface of the transition piece flow sleeve. A gas turbine combustor, wherein a plurality of gas turbine combustors are arranged so as to be shifted in stages. A gas turbine combustor according to claim 11,
The gas is characterized in that the rectifying plate disposed on the side surface of the transition piece flow sleeve in which the impingement hole is not formed is larger than the rectifying plate disposed between the circumferential directions of the impingement holes. Turbine combustor. A transition piece flow sleeve of a combustor containing a transition piece through which hot combustion gas flows;
The transition piece flow sleeve has a plurality of impingement holes on the back side, the ventral side, and the outlet side of the transition piece flow sleeve, and the impingement hole on the vent side of the transition piece flow sleeve. A transition piece flow sleeve characterized in that a rectifying structure for controlling the flow rate of the compressed air entering is disposed.

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