JP6960345B2 - Gas turbine combustor and transition piece flow sleeve - Google Patents

Description

The present invention relates to a gas turbine combustor and a transition piece flow sleeve, and in particular, a plurality of them are provided on the dorsal side surface, the ventral side surface, and the side outlet side of the transition piece flow sleeve, and are 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 for guiding compressed air discharged from a compressor in a flow path.

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

Usually, on the dorsal, ventral, and side surfaces of the transition piece flow sleeve, several rows of impingement holes (air introduction holes) are arranged in the axial direction, and dozens of them are arranged in the circumferential direction of each row.

In addition, in the case of a structure in which the compressed air discharged from the compressor directly collides with the transition piece flow sleeve, the flow of the compressed air discharged from the compressor fluctuates, resulting in the introduction of unstable compressed air and fluctuations in dynamic pressure. The transition piece may vibrate, causing wear and damage (cracks) in each part.

Further, when the flow rate deviates at the position of each impingement hole, unintended dynamic pressure fluctuation or excessive pressure loss may occur due to the high flow velocity, especially in the impingement hole having a large flow rate.

In a gas turbine combustor, a technology that rectifies the compressed air supplied to the transition piece flow sleeve on the outer surface of the transition piece flow sleeve to mitigate the deviation of the compressed air introduced into each of the multiple impingement holes. It is described in Patent Document 1-3.

In Patent Document 1, the 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 holes (impingement holes) 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 the transition is due to the presence of the cooling sleeve in the liner. The cross flow that flows from the piece into the space between the liner of the liner part and the transition piece flow sleeve flows along the concave part of the cooling sleeve, the convex part acts as a guide for the jet flow, and the cross flow flows into the concave part. It is stated that the jet flow is unaffected by the cross flow and, as a result, effectively cools the liner.

Further, in Patent Document 2, a transition piece is attached to the rear end portion of the inner cylinder of the liner, and the outside of the transition piece is surrounded by a transition piece flow sleeve at a predetermined interval to form a cooling passage, and the transition piece flow is formed. It is described that a large number of circular cooling holes are formed in the sleeve, and cooling air is guided from the cooling holes and ejected toward the transition piece.

Further, Patent Document 3 describes a gas turbine in which a transition piece is convected-cooled by a transition piece flow sleeve, and high-pressure air introduced from a compressor is introduced from a diffuser into a ventral passenger compartment and a back passenger compartment. It is stated that after flowing through the gap between the transition piece and the transition piece flow sleeve installed on the outer periphery thereof, the flow passes through the gap between the liner and the liner flow lobe arranged on the concentric circles on the outer periphery of the liner. There is.

Japanese Unexamined Patent Publication No. 2015-135111 Japanese Patent No. 3054420 Japanese Unexamined Patent Publication No. 2000-146186

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, causing fluctuations in the flow of the compressed air, so that the transition piece flow sleeve is vibrated. This may cause 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 amount of inflow air several times depending on the position of the impingement hole (upstream side or downstream side). , Increases pressure loss.

Further, in the conventional structure, since a large amount of compressed air flows in from the impingement hole on the combustor burner side (upstream side), the cooling on the turbine side (downstream side) of the transition piece main body becomes insufficient. That is, when compressed air from the compressor is introduced into the vehicle interior 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, so that the turbine side ( The amount of compressed air entering the impingement hole on the downstream side) decreases, and the cooling on the turbine side (downstream side) becomes insufficient.

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

On the other hand, in Patent Document 1, the cross flow flowing from the transition 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, and the convex portion guides the jet flow. It is stated that the jet flow is unaffected by the cross flow and, as a result, effectively cools the liner, as it guides the cross flow to flow into the recesses. There is no effect of alleviating the flow rate deviation at the inlet of the impingement hole, and reduction of the pressure loss at the inlet of the impingement hole cannot be expected.

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

Further, in Patent Document 3, high-pressure air introduced from the compressor is introduced from the diffuser into the ventral and dorsal passenger compartments of the transition piece flow sleeve, and the transition piece and the transition piece flow installed on the outer periphery thereof are introduced. It is stated that after flowing through the gap between the sleeves, the flow will pass through the gap between the liner and the liner flow probe placed on the concentric circles around the liner, but at the impingement hole that is the entrance to the transition piece flow sleeve. It is not stated to mitigate the deviation.

The present invention has been made in view of the above points, and an object of the present invention is to reduce the exciting force of the compressed air discharged from the compressor to the transition piece flow sleeve and suppress the occurrence of cracks and wear. It is to provide a gas turbine combustor and a transition piece flow sleeve which can be used.

In the gas turbine combustor of the present invention, in order to achieve the above object, a transition piece of a combustor through which high-temperature combustion gas flows and a transition piece flow around the transition piece and containing the transition piece flow. A sleeve, a flow path formed between the transition piece flow sleeve and the transition piece to flow compressed air discharged from the compressor , a ventral side surface of the transition piece flow sleeve on the compressor side, and the above. A plurality of impingements are provided on each outlet side of the dorsal side surface, which is a surface facing the ventral side surface, and the side surface connecting the dorsal side surface and the ventral side surface, and guide the compressed air discharged from the compressor to the flow path. A gas turbine combustor provided with a hole, characterized in that a rectifying structure for controlling the flow rate of the compressed air entering the impingement hole is arranged on the ventral side surface of the transition piece flow sleeve. ..

Further, the transition piece flow sleeve of the present invention is a transition piece flow sleeve of a combustor containing a transition piece through which high-temperature combustion gas flows in order to achieve the above object. A plurality of impingements are provided on the ventral side surface of the transition piece flow sleeve, which is the surface on the compressor side, the dorsal side surface, which is the surface facing the ventral side surface, and the outlet side of the side surface connecting the dorsal side surface and the ventral side surface. together and a placement hole, the ventral surface of the transition piece flow sleeve, characterized in that the rectifier structure is arranged to control the flow rate of the incoming Ru compressed air to the impingement holes.

According to the present invention, it is possible to reduce the exciting force of the compressed air discharged from the compressor on the transition piece flow sleeve and suppress the occurrence of cracks and wear.

It is a figure which shows the whole structure of the gas turbine combustor for a general power plant. It is a figure which shows the detail of the turbine side of the gas turbine combustor for demonstrating the flow of compressed air around a transition piece in the gas turbine combustor of this invention. It is sectional drawing along the line AA of FIG. It is a figure which shows the detail of the turbine side 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 the rectifying plate as Example 2 of the gas turbine combustor of this invention. It is a perspective view which shows another example of the specific structure of the straightening vane 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. FIG. 5 is a perspective view showing 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 examples. In each of the embodiments described below, the same reference numerals are used for the same components.

FIG. 1 shows the overall configuration of a gas turbine combustor for a general power plant, which is the subject of the present invention.

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

Then, the compressed air 100 introduced from the air compressor 300 is used from the diffuser 1 on the ventral side of the passenger compartment 2 (the space on the inner peripheral side of the passenger compartment) and the back side of the passenger compartment 3 (the space on the outer peripheral side of the passenger compartment). It flows into the 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 ventral passenger compartment 2 enters the flow path 9 formed by the transition piece flow sleeve 5 and the transition piece 4 from the ventral side of the transition piece 4. The flow 20 becomes the flow 20, and the rest passes through between the adjacent transition pieces 4 and wraps around to the passenger compartment 3 on the back side, and then enters the flow path 9 formed by the transition piece flow sleeve 5 and the transition piece 4. Become.

After that, the compressed air 100 flowing into the flow path 9 becomes a flow 102 passing through a gap between the liner 6 and the liner flow sleeve 7 arranged concentrically on the outer circumference of the liner 6, as shown by the flow 101. Then, the flows are reversed and become flows 103 and 104 to be introduced into the burner section, mixed with the fuel supplied from the fuel systems 200 and 201, flames 105 and 106 are formed in the combustion chamber 8 inside the liner 6, and high temperature and high pressure combustion is performed. It becomes gas 107. After that, the combustion gas 108 is introduced from the transition piece 4 to the turbine 301. In the gas turbine, the work generated when the high-temperature and high-pressure combustion gas 108 adiabatically expands is converted into the axial rotational force in the turbine 301. As a result, the output is obtained from the generator 302.

In some plants, the gas turbine is used as a power source for fluid compression by rotating another compressor instead of the generator 302 by utilizing the axial rotational force in the turbine 301.

By the way, 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 each outlet side (turbine side) of the back side surface, the ventral side surface, and the side surface. A configuration having a plurality of impingement holes 22 for guiding the compressed air 100 to the flow path 9 as cooling air for the transition piece 4 (see FIG. 8) is adopted.

FIG. 2 shows a configuration in which a plurality of impingement holes 22 for guiding 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, there are a plurality of (three locations in FIG. 2) impingement holes 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 surface (dorsal side surface, ventral side surface, both side surfaces) of the transition piece flow sleeve 5 on the outlet side. Has been done. Further, as shown in FIG. 3, the transition piece flow sleeve 5 is arranged so as to include the transition piece 4, and the 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 ventral passenger compartment 2 is formed by the transition piece flow sleeve 5 and the transition piece 4 from the ventral side of the transition piece 4 through the impingement hole 22. The flow 20 enters the flow path 9 to be processed, and the rest passes through the space between the adjacent transition pieces 4 and goes around to the passenger compartment 3 on the back side, and then enters the flow path 9 through the impingement hole 22. Become.

In each impingement hole 22, compressed air 100 is ejected toward the transition piece 4 arranged with a predetermined gap from the transition piece flow sleeve 5 and collides with the outer surface of the transition piece 4, so that the transition piece 4 is formed. It's cooling.

However, in the configuration of FIG. 2, the compressed air 100 discharged from the compressor 300 keeps the dynamic pressure in the vicinity of the ventral guide 11 provided on the ventral side surface for fixing the transition piece 4 and the transition piece flow sleeve 5. The collision may occur, and this collision may cause the transition piece 4 and the transition piece flow sleeve 5 to be vibrated, causing 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 inside the transition piece flow sleeve 5, but on the downstream side (turbine side) in the combustor axial direction. As shown in FIG. 8, the distance between the combustor cans (box-shaped object formed by the transition piece 4 and the transition piece flow sleeve 5) adjacent to each other in the circumferential direction (distance between the two combustor cans in the circumferential direction) is set. It becomes narrower toward the downstream side (turbine side) in the combustor axial direction. Therefore, 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, it is the gas turbine combustor of the present invention that solves the above-mentioned problems.

FIG. 4 shows Example 1 of the gas turbine combustor of the present invention.

The gas turbine combustor of this embodiment shown in FIG. 4 has substantially the same configuration as that shown in FIGS. 2 and 3, but in this embodiment, the impingement hole 22 is formed 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.

The rectifying plate 12 is supported by a ventral guide 11 that fixes the ventral side surface of the transition piece 4 and the transition piece flow sleeve 5, and the ventral guide 11 receives pressure from the upstream to the downstream with respect to the air flow. For example, it is formed in a conical shape so as to expand the projected area (in addition, it may be a quadrangular pyramid or a triangular pyramid).

Further, the straightening vane 12 is formed on the most combustor burner side of the plurality of (three in this embodiment) 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 the flow velocity to some extent. However, according to the configuration of the present embodiment described above, the ventral guide 11 is formed by the rectifying plate 12 formed in a conical shape so as to expand the pressure receiving projected area from the upstream to the downstream with respect to the air flow. The angle of entry of the compressed air 100 with respect to the transition piece flow sleeve 5 becomes small, and the flow velocity also decreases due to the friction loss while flowing on the surface of the rectifying plate 12.

Moreover, at the end of the straightening vane 12, the flow velocity is further reduced by separating the flow and generating a vortex, the static pressure is restored when the transition piece flow sleeve 5 is reached, and the transition piece flow sleeve 5 by the compressed air 100 is used. The exciting force of is reduced.

Further, since the compressed air 100 flows evenly into the impingement hole 22 of the transition piece flow sleeve 5 by the pressure difference between the inside and outside of the transition piece flow sleeve 5, the pressure due to the excessive flow rate flowing into the specific impingement hole 22. The loss and the flow rate deviation in the axial impingement hole 22 of the transition piece 4 can be alleviated. As a result, the temperature deviation in the axial direction of the transition piece 4 can be reduced, and the cooling performance can be improved.

Further, 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 is compared with the flow rate of the compressed air 100 in the passenger compartment 3 on the back side of the transition piece flow sleeve 5. The flow rate was small, and there was a flow rate deviation between the ventral passenger compartment 2 and the back passenger compartment 3, but due to the installation of the rectifying plate 12, the transition piece flow sleeve 5 had a transition in the impingement hole 22. Since the compressed air 100 is evenly flowed by the pressure difference between the inside and outside of the piece flow sleeve 5, the flow deviation of the compressed air 100 flowing into the ventral passenger compartment 2 and the back passenger compartment 3 can be alleviated.

According to this embodiment, the exciting force of the transition piece flow sleeve 5 due to 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 pressure loss can be reduced by evenly flowing the compressed air 100 discharged from the compressor 300 into each impingement hole 22 formed in the transition piece flow sleeve 5.

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

That is, conventionally, the compressed air 100 flowing into the impingement hole 22 is arranged on the ventral side of the transition piece flow sleeve 5 which is the closest position when viewed from the outlet of the diffuser 1 (the entrance of the vehicle interior). Although concentrated on 22, according to this embodiment, it is possible to increase the flow rate of the compressed air 100 that wraps around 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 flow rate between the ventral side and the back side of the transition piece 4 increases. It is possible to alleviate the temperature deviation.

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

The straightening vane 12 of the present embodiment shown in the figure is provided with at least one (one or a plurality) corner or circular protrusions 23 on the surface of the conical straightening vane 12.

In FIG. 5, the protrusions 23 are regularly provided on the surface of the straightening vane 12 in the circumferential direction and the axial direction, but the protrusions 23 do not have to be regularly provided and may be provided irregularly (randomly). good.

By providing the angular or circular protrusions 23 on the rectifying plate 12, the compressed air 100 flows on the surface of the protrusions 23, and the effect of the fluid friction and the minute vortex induced downstream of the protrusions 23 causes the compressed air 100 to flow. Since the flow velocity is reduced, further effects can be expected.

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

In the straightening vane 12 of the present embodiment shown in the figure, the downstream end surface 24 of the straightening vane 12 is formed in one or a plurality of curved and / or uneven shapes.

By forming the downstream end face of the straightening vane 12 into one or more curved and / or uneven shapes, flow separation can be generated on the downstream side of the downstream end face 24 of the straightening vane 12. The flow velocity can be reduced as in Example 2, and further effects can be expected.

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

In this embodiment shown in FIG. 7, in addition to the configuration of the first embodiment, a plurality of third units that control 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 the rectifying structures of No. 2, are arranged (the rectifying plate may have 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 located between the circumferential directions of the impingement hole 22, and the rectifying plate 25b is placed. It is arranged on each side surface of the transition piece flow sleeve 5 in which the impingement hole 22 is not formed.

The straightening vane 25a arranged between the circumferential directions of the impingement hole 22 and the straightening vane 25b arranged on the side surface of the transition piece flow sleeve 5 in which the impingement hole 22 is not formed are the transition piece flow sleeve 5. A transition in which the impingement hole 22 is not formed from the straightening vane 25a arranged between the circumferential directions of the impingement hole 22 and a plurality of arrangements that are gradually offset from the axial direction of the side surface of the above. The straightening vane 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 of the gas turbine combustor (the outlet of the transition piece 4 of the combustor), the distance between the adjacent transition pieces 4 in particular, the downstream end (turbine side), is set. Narrow (see Figure 8).

Therefore, the flow rate of the compressed air 100 flowing through 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 high, and the compressed air 100 that also flows in is higher than the dorsal side and the ventral side of the transition piece flow sleeve 5. The amount of is small.

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

In addition, on the upstream side (burner side) of the combustor in the axial direction, the distance between the adjacent transition pieces 4 is wide (the transition pieces 4 are not arranged in parallel with the adjacent transition pieces 4, and the combustor. Since the upstream side (burner side) in the axial direction of the combustor is wide and the downstream side (turbine side) in the axial direction of the combustor is narrowed, the upstream side (burner side) in the axial direction of the combustor is By providing a rectifying plate 25b larger than the axial downstream side (turbine side) of the combustor (because the distance between adjacent transition pieces 4 becomes wider), the impingement hole 22 in the combustor axial direction is provided as compared with the conventional structure. It is possible to make the amount of air flowing into the turbine uniform.

According to this embodiment, in addition to the effect of the first embodiment, the flow velocity of the side surface portion of the transition piece flow sleeve 5, which has a small inflow amount in the conventional structure, can be reduced, and the static pressure can be restored. By equalizing the inflow of compressed air 100 into the axially downstream impingement hole 22 of the combustor, the impingement hole 22 located on the axially downstream side (turbine side) of the combustor of the transition piece flow sleeve 5. In addition, by flowing compressed air 100 having a structure equal to or higher than that of the conventional structure (close to the average value), cooling of the main body of the transition piece 4 on the downstream side in the axial direction can be improved.

The present invention is not limited to the above-described examples, and includes various modifications. For example, the above-described embodiment has been described in detail in order to explain the present invention in an easy-to-understand manner, and is not necessarily limited to the one including all the described configurations. Further, it is possible to replace a part of the configuration of one embodiment with the configuration of another embodiment, and it is also possible to add the configuration of another embodiment to the configuration of one embodiment. Further, it is possible to add / delete / replace a part of the configuration of each embodiment with another configuration.

1 ... Diffuser, 2 ... Car room (ventral side), 3 ... Car room (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 ... impingement hole, 23 ... protrusion, 24 ... downstream end face of rectifying plate, 100 ... Compressed air, 105, 106 ... Flame, 107, 108 ... Combustion gas, 200, 201 ... Fuel system, 300 ... Compressor, 301 ... Turbine, 302 ... Generator.

Claims (13)

It is formed between the transition piece of the combustor through which the high-temperature combustion gas flows, the transition piece flow sleeve that surrounds the transition piece and contains the transition piece, and the transition piece flow sleeve and the transition piece. the a flow path for flowing the compressed air discharged from the compressor, and wherein the ventral aspect is a surface of the compressor side is ventral side surface opposed to the dorsal surface and the back side surface of the transition piece flow sleeve belly A gas turbine combustor provided on each outlet side of a side surface connecting to the side surface and provided with an impingement hole for guiding compressed air discharged from the compressor to the flow path.
A gas turbine combustor characterized in that a rectifying structure for controlling the flow rate of the compressed air entering the impingement hole is arranged on the ventral side surface of the transition piece flow sleeve. The gas turbine combustor according to claim 1.
The rectifying structure is a gas turbine combustor characterized in that the projected pressure receiving area expands from upstream to downstream with respect to the flow of compressed air. The gas turbine combustor according to claim 1 or 2.
A gas turbine combustor characterized in that the rectifying structure is supported by a ventral guide that fixes the ventral side of the transition piece and the transition piece flow sleeve. The gas turbine combustor according to any one of claims 1 to 3.
The gas turbine combustor is characterized in that the rectifying structure is arranged on the combustor burner side of the impingement holes provided in plurality on the outlet side of the ventral side surface of the transition piece flow sleeve. The gas turbine combustor according to any one of claims 1 to 4.
The gas turbine combustor, wherein the rectifying structure is a conical, quadrangular pyramid, or triangular pyramid-shaped rectifying plate. The gas turbine combustor according to claim 5.
A gas turbine combustor characterized in that at least one corner or circular protrusion is provided on the surface of the straightening vane. The gas turbine combustor according to claim 5 or 6.
A gas turbine combustor characterized in that the downstream end face of the straightening vane is formed in a plurality of curved and / or concavo-convex shapes. The gas turbine combustor according to any one of claims 1 to 7.
A gas turbine combustor characterized in that at least one second rectifying structure that controls the flow rate of the compressed air entering the impingement hole is arranged on a side surface of the transition piece flow sleeve. The gas turbine combustor according to claim 8.
The gas turbine combustor is characterized in that the second rectifying structure is arranged so as to block the flow of the compressed air entering the impingement hole on the combustor burner side. The gas turbine combustor according to claim 8 or 9.
The second rectifying structure is a gas characterized by being a rectifying plate arranged between the circumferential directions of the impingement hole and the side surface of the transition piece flow sleeve in which the impingement hole is not formed. Turbine combustor. The gas turbine combustor according to claim 10.
The rectifying plate arranged between the circumferential direction of the impingement hole and the side surface of the transition piece flow sleeve in which the impingement hole is not formed is formed in the axial direction and the vertical direction of the side surface of the transition piece flow sleeve. A gas turbine combustor characterized in that a plurality of gas turbine combustors are arranged in a stepwise manner. The gas turbine combustor according to claim 11.
A gas characterized in that the rectifying plate arranged on the side surface of the transition piece flow sleeve in which the impingement hole is not formed is larger than the rectifying plate arranged between the circumferential directions of the impingement hole. Turbine combustor. A transition piece flow sleeve for a combustor that contains a transition piece through which high-temperature combustion gas flows.
The transition piece flow sleeve includes a ventral side surface of the transition piece flow sleeve on the compressor side, a dorsal side surface facing the ventral side surface, and a side surface connecting the dorsal side surface and the ventral side surface, respectively. together comprises a plurality of impingement holes on the outlet side of the ventral surface of the transition piece flow sleeve, the rectifying structure is arranged to control the flow rate of the incoming Ru compressed air to the impingement holes Transition piece flow sleeve featuring.

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