JP2002242702A - Cooling structure for wall surface of gas turbine combustor - Google Patents

Abstract

PROBLEM TO BE SOLVED: To prevent local temperature rises of the interior wall of a combustor downstream of a combustor penetrating member. SOLUTION: A structure is provided with a combustor inner-cylinder shell 55 and a cylindrical heat insulating member 155 positioned inside the shell. On a heat insulating member 155D located downstream of the penetrating member 159 penetrating both the shell and the heat insulating member, a line of pin fins 155P is positioned which is composed of columnar protrusions protruding perpendicularly from the downstream outer peripheral part of the penetrating member. Since the line of pin fins 155P has a greater efficiency of heat transfer to and from cooling air than a fin-ring channel 155b provided in the portion 155U of the heat insulating member upstream of the penetrating member, the cooling ability of the heat insulating member increases at the downstream portion of the penetrating member so that, even if a vortex of combustion gas is generated on the wall surface of the heat insulating member downstream of the penetrating member by the presence of the penetrating member and causes a local increase in heat load on the wall surface, local temperature rises of the wall surface of the heat insulating member are prevented.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

The present invention relates to a gas turbine, and more particularly, to a wall cooling structure of a gas turbine combustor.

[0002]

2. Description of the Related Art Since a wall of a gas turbine combustor is a part which is in direct contact with a high-temperature combustion gas, various means for cooling the wall are taken. Normally, the wall cooling of the combustor is performed by combined cooling using cooling air that combines convection cooling and film cooling.

FIG. 1 is a cross-sectional view showing an example of a gas turbine combustor that performs combined cooling using cooling air. In FIG. 1, a combustor 1 supplies an inner cylinder 5b having an internal space as a combustion chamber for burning fuel supplied from a main nozzle 33, and combustion gas generated by combustion in the inner cylinder to a turbine first stage stationary blade. Transition piece 5a having outlet 51
Are joined. The fuel is injected into the inner cylinder 5b from the main nozzle 33 as a premixed air previously mixed with air, and is ignited by the pilot flame generated by the pilot nozzle 31 in the inner cylinder 5b to generate a premixed flame in the inner cylinder. .

FIG. 10 is an enlarged sectional view of a wall surface of the inner cylinder 5b for explaining a conventional wall cooling method for the inner cylinder 5b. Figure 1
As shown in FIG. 0, the wall surface of the inner cylinder 5b is actually formed by joining a plurality of cylindrical shells 55 having different diameters in the axial direction via stepped portions. Each stepped shell functions as a structural material forming an inner cylinder, and a heat shield member 155 constituting a combustion chamber wall surface is arranged inside each stepped shell 55. The heat shielding member 155 protects the shell 55, which is a structural material of the inner cylinder, from the flame inside the inner cylinder,
This is for preventing a reduction in strength.

Conventionally, as the heat shielding member 155, a cylindrical fin ring having a large number of axial grooves 155b formed on the outer periphery is used. FIG. 11 is a cross-sectional view of FIG.
2 shows a cross section along the line XI. The fin ring 155 is formed by forming a large number of grooves 155b in the axial direction on the outer periphery of a cylindrical substrate by machining. As shown in FIG. 10, the fin rings 155 are fixed to the shell 55 by brazing or the like at the ends of the stepped portions on the small-diameter side (the fuel nozzle side) and are held in the shell 55.

The cooling air is supplied from the inside of the casing 7 (FIG. 1) to the shell and the fin ring 155 through a plurality of inlets 57 provided on the periphery of the small-diameter end of the stepped shell 55 (indicated by 55a in FIG. 10). Fin ring 155
The fin ring 155 itself is convectively cooled through the outer circumferential axial groove, and the adjacent stepped shell 55
(Indicated by 55b in FIG. 10) in the axial direction along the inner surface of the fin ring. Thereby, the combustion chamber wall surface of the adjacent stepped portion shell 55b (that is, the fin ring 155) is formed.
The film cooling of (b inner surface) is performed.

[0007]

However, in the conventional combustor wall cooling structure as shown in FIG. 10, although cooling of the combustor wall is generally performed well, if there is a member penetrating through the fin ring, the cooling is not performed. It has been found that the temperature of the heat shielding member (fin ring) locally increases on the downstream side in the combustion gas flow direction, and in extreme cases, a problem occurs in that the heat shielding member is burned.

FIG. 12 is a sectional view similar to FIG. 10 for explaining this problem. The gas turbine combustor may be provided with a member that extends through the inner cylinder (shell) 55 and the heat shielding member (fin ring) 155 into the combustion chamber.
For example, FIG. 1 shows a combustor that performs premix combustion,
In order to supply secondary combustion air to the diffusion flame formed by the main nozzle in a combustor that performs diffusion combustion of a different type from the above, as shown in FIG.
And a tubular penetrating member (scoop) 159 that communicates with the outside of the inner cylinder and the combustion chamber is provided. The scoop supplies high-pressure combustion air in a casing outside the inner cylinder to the diffusion flame in the combustion chamber as secondary air.

In addition to the scoop, a plurality of igniter tubes for inserting an igniter (ignition plug) for igniting fuel in the combustion chamber at the time of starting the gas turbine into the combustion chamber, and a plurality of combustors in FIG. In a gas turbine having a configuration in which a plurality of gas turbines are arranged, a cross-fire tube (connecting pipe) or the like for connecting adjacent combustors to each other and propagating a flame from one to the other is used. There are various types of penetrating members penetrating through. When such a penetrating member 159 is present on the inner peripheral surface of the heat shielding member 155, a vortex of the combustion gas flow is generated immediately downstream of the penetrating member 159 as shown in FIG. Since the heat transfer between the heat shield member and the heat shield member is turbulent heat transfer, the heat transfer coefficient locally increases immediately downstream of the penetrating member, and the heat load of the heat shield member increases. Further, the heat shielding member 15
5 When the film is cooled on the inner peripheral surface by the cooling air, the flow from the opening of the penetrating member is blocked at the portion immediately downstream of the penetrating member 159, so that the cooling air does not reach and the film cooling is not performed. The heat load on the wall surface of the heat shielding member 155 will further increase.

For this reason, on the downstream side of the penetrating member 159, the fin-ring type convection cooling alone cannot absorb the increase in the local heat load of the heat shielding member 155, and the local temperature rise of the heat shielding member occurs. There is a high possibility that the members will burn out.

In view of the above problems, the present invention absorbs a local increase in heat load of a heat shielding member downstream of a penetrating member such as a scoop of a gas turbine combustor, and causes a local temperature increase of the heat shielding member. It is an object of the present invention to provide a gas turbine combustor wall cooling structure capable of preventing the occurrence of the above problem.

[0012]

According to the first aspect of the present invention, a cylindrical inner cylinder having an internal space forming a combustion chamber is attached to the inner surface of the inner cylinder over the entire circumference,
A heat shielding member constituting a cylindrical combustion chamber wall in which combustion gas flows in the axial direction inside, and between the cooling air flowing between the heat shielding member and the inner cylinder in the axial direction of the inner cylinder and the heat shielding member. A gas turbine combustor wall cooling structure, comprising: a heat exchange means for promoting heat exchange of the gas turbine; and a tubular penetration member penetrating through the inner cylinder and the heat shielding member and opening into the combustion chamber from outside the inner cylinder. The heat exchange means may be configured such that the heat transfer coefficient between the cooling air and the heat shielding member at the downstream portion of the through member in the combustion gas flow direction is such that the cooling air at the upstream side of the through member in the combustion gas flow direction. A heat transfer coefficient between the gas turbine combustor and the heat shield member.

[0013] That is, in the gas turbine combustor wall cooling structure of the first aspect, the heat exchange means has a lower portion between the cooling air and the heat shielding member in the downstream portion of the penetrating member in the flow direction of the combustion gas than in the upstream portion. Since the transmissivity is set to be large, the cooling capacity for the heat shielding member on the downstream side of the penetrating portion increases. Therefore, even when the heat load of the heat shielding member locally increases on the downstream side of the penetrating member, the temperature of the heat shielding member can be kept low.

According to the second aspect of the present invention, the heat exchange means on the downstream side of the penetrating member in the flow direction of the combustion gas includes a pin fin array comprising a plurality of projections projecting at right angles from the outer periphery of the heat shielding member. A gas turbine combustor wall cooling structure according to claim 1 comprising:

That is, in the gas turbine combustor wall cooling structure of the second aspect, the heat exchange means includes a pin fin row at a downstream portion of the penetrating member in the flow direction of the combustion gas. Pin fin cooling, for example, has a higher heat transfer coefficient than fin ring cooling, so the cooling capacity for the heat shield member downstream of the penetrating portion increases, and the heat load of the heat shield member locally increases downstream of the penetrating member. Even in this case, the temperature of the heat shielding member can be kept low.

According to the third aspect of the present invention, the heat exchange means on the downstream side of the penetrating member in the combustion gas flow direction has a plurality of tubular internal parts extending in the heat shielding member in a direction along the inner cylinder axis. A cooling air passage, wherein the internal cooling air passage is provided at a cooling air inlet opening at an outer peripheral portion of the heat shielding member on the downstream side in the combustion gas flow direction of the penetrating member, and a cooling air opening at a downstream end of the heat shielding member. The gas turbine combustor wall cooling structure according to claim 1, further comprising an outlet, wherein the cooling air flowing through the internal cooling air passage flows into the combustion chamber from the cooling air outlet along the inner peripheral surface of the inner cylinder. Provided.

That is, in the gas turbine combustor wall cooling structure according to the third aspect, the heat exchange means is a tubular internal cooling air passage formed in the heat shielding member at a downstream portion of the penetrating member in the flow direction of the combustion gas. It has. The cooling by the internal cooling passage has a higher heat transfer coefficient than, for example, fin ring cooling, so that the cooling capacity for the heat shielding member on the downstream side of the penetrating portion increases, and the heat load of the heat shielding member on the downstream side of the penetrating member is locally reduced. Even when the temperature increases, the temperature of the heat shielding member can be kept low.

According to the fourth aspect of the present invention, the heat exchanging means on the downstream side in the combustion gas flow direction of the penetrating member includes a plurality of axially extending grooves provided on the outer peripheral portion of the heat shielding member. 2. The gas turbine combustor wall cooling structure according to claim 1, further comprising: an oblique turbulator including a projection extending obliquely in a groove transverse direction in the groove. 3.

That is, in the gas turbine combustor wall cooling structure according to the fourth aspect, the heat exchange means includes an axial groove and an oblique turbulator on the outer peripheral portion of the heat shielding member on the downstream side in the combustion gas flow direction of the penetrating member. I have. By providing the oblique turbulator, the cooling air flow flowing in the groove generates a vortex when passing through the turbulator, and the heat transfer between the cooling air and the outer periphery of the heat shielding member becomes turbulent heat transfer. For this reason, for example, the heat transfer coefficient is increased as compared with the case where cooling is performed only by the fin ring, and the cooling capacity for the heat shielding member on the downstream side of the penetrating portion is increased. Can be kept low even when the temperature increases locally.

According to the fifth aspect of the present invention, the heat exchange means on the upstream side of the penetrating member in the combustion gas flow direction includes a plurality of axially extending grooves provided all around the outer periphery of the heat shielding member. The gas turbine combustor wall cooling structure according to claim 1, comprising:

That is, in the gas turbine combustor wall cooling structure according to the fifth aspect, the cooling means on the upstream side in the combustion gas flow direction of the penetrating member includes a fin ring. In the upstream part of the penetrating member, since the local heat load of the heat shielding member does not increase due to the penetrating member unlike the downstream part, the wall temperature of the heat shielding member is sufficiently lowered by performing cooling using the fin ring. It can be maintained.

According to the sixth aspect of the present invention, a cylindrical inner cylinder having an internal space constituting a combustion chamber, and the inner cylinder is attached to the inner surface of the inner cylinder over the entire circumference, and the combustion gas flows in the interior in the axial direction. A gas turbine combustor wall cooling structure, comprising: a heat shielding member forming a flowing cylindrical combustion chamber wall; and a cooling air passage through which cooling air flows in the axial direction of the inner cylinder between the heat shielding member and the inner cylinder. A gas turbine combustor wall cooling structure including a tubular through member that penetrates through the inner cylinder and the heat shielding member and opens into the combustion chamber from outside the inner cylinder, wherein the cooling air passage is , A part of the cooling air,
A film cooling air supply port for flowing along the inner peripheral surface of the heat shield member from a downstream portion of the heat shield member in the combustion gas flow direction of the penetrating member. A structure is provided.

That is, in the gas turbine combustor wall cooling structure according to the sixth aspect, the cooling air is supplied from the downstream portion of the penetrating member in the combustion gas flow direction along the inner peripheral surface of the heat shielding member. For this reason, a cooling air film is formed between the combustion gas formed on the downstream side of the penetrating member and the inner peripheral surface of the heat shielding member, thereby preventing a local temperature rise of the heat shielding member.

According to the seventh aspect of the present invention, the film cooling air supply means includes a heat-shielding member which is provided between the heat-shielding member and the through-member penetrating portion, on the downstream side of the outer periphery of the penetrating member in the flow direction of the combustion gas. A cooling air supply port formed of a gap with a member, and cooling air provided around the opening of the penetrating member and flowing into the combustion chamber from the cooling air passage through the cooling air supply port to the heat shield member inner peripheral surface. Deflecting means for flowing along the downstream side in the combustion gas flow direction.
2. The gas turbine combustor wall cooling structure according to 1.

That is, in the gas turbine combustor wall cooling structure according to the seventh aspect, the film cooling air supply means introduces cooling air from the downstream side in the combustion gas flow direction around the opening of the penetrating member, and the cooling air is supplied by the deflection means. The air is caused to flow along the inner peripheral surface of the heat shielding member. For this reason,
A cooling air film is formed between the combustion gas and the inner peripheral surface of the heat shield member from a portion immediately downstream of the penetrating member, thereby preventing a local temperature rise of the heat shield member.

According to the invention described in claim 8, the cooling air passage has a plurality of tubular members extending in the direction along the inner cylinder axis in the heat shielding member on the downstream side in the combustion gas flow direction of the penetrating member. An internal cooling air passage, and a cooling air inlet to the internal cooling air passage that is opened at an outer peripheral portion of the heat shielding member on the downstream side of the through member in the combustion gas flow direction, and wherein the film cooling air supply means includes: The gas turbine according to claim 6, further comprising: a film cooling air supply port that opens on an inner peripheral surface of the heat shielding member on the downstream side of the penetrating member and that discharges cooling air in the internal cooling air passage into a combustion chamber. A combustor wall cooling structure is provided.

That is, in the gas turbine combustor wall cooling structure according to the eighth aspect, a tubular internal cooling air passage is formed in the heat shielding member on the downstream side in the combustion gas flow direction of the penetrating member. Cooling air in the air passage is discharged from an opening provided in the heat shielding member to form a cooling air film. As a result, both the improvement of the cooling capacity by the internal cooling air passage of the heat shielding member and the prevention of the local heat load increase of the heat shielding member wall surface by the film cooling can be performed at the same time. Is prevented.

[0028]

Embodiments of the present invention will be described below with reference to the accompanying drawings. (1) First Embodiment FIGS. 2 and 3 are sectional views similar to FIG. 12 showing a first embodiment of a gas turbine combustor wall cooling structure of the present invention. In FIG. 2, 55 indicates an inner cylinder shell, and 155 indicates a heat shielding member. Reference numeral 159 denotes a penetrating member such as a cross fire tube and a scoop, similar to FIG. In the present embodiment, as shown in FIG. 2, the upstream portion 155U of the penetrating member 159 of the heat shielding member 155 is a fin ring in which a groove 155b is formed in the outer periphery along the entire circumference.

FIG. 3 shows a cross section along the line III-III in FIG. Heat shielding member portion 1 downstream of penetrating member 159
55D has a so-called pin fin structure in which a large number of cylindrical projections 155P projecting vertically from the outer periphery of the heat shielding member are arranged. As shown in FIG. 2, in the present embodiment, the cooling air is supplied to the shell 5 in the upstream portion of the heat shielding member.
5, a plurality of cooling air inlets 57 provided over the entire circumference.
Flows into the annular space between the shell and the heat shield member, passes through the groove 155b of the fin ring, and cools the upstream portion 155U of the heat shield member. Further, in the heat shielding member penetrating portion of the penetrating member 159, a part of the cooling air is supplied to the penetrating member 159.
And flows into the combustion chamber through a semi-annular space 159a formed between the heat shield member upstream portion 155U.

On the other hand, on the downstream side of the penetrating member, the cooling air passes through a semi-annular space 159b formed around the downstream half of the outer periphery of the penetrating member 159 of the shell 55 penetrating portion, and the cooling air flows into the shell and the heat shielding member downstream portion 155D. And flows into the pin fin row 155P arranged on the outer periphery of the heat shielding member downstream portion 155, flows in the pin fin row in the axial direction of the inner cylinder, and flows downstream from the end of the heat shielding member. It flows out along the inner wall surface of the member. Since the pin fin row is composed of a large number of column rows having a small diameter, the heat transfer area with the cooling air passing through the pin fin row is much larger than that of the fin ring. For this reason, the upstream portion 155U is used in the downstream portion 155D of the penetration member 159 of the heat shielding member.
The heat transfer coefficient between the cooling air and the heat shielding member is greatly increased. For this reason, even when eddies of the combustion gas are generated on the inner peripheral surface of the heat shield member 155D on the downstream side of the penetrating member 159, and the heat load locally increases, the heat shield member is sufficiently cooled. And no local temperature rise occurs.

The pin fin row is provided only on the portion of the outer periphery of the downstream portion 155 of the heat shielding member, which is directly downstream of the penetrating member 159, and the remaining portion of the outer periphery is formed by the groove 1 of the fin ring.
55b may be extended from the upstream member 155U. However, while the fin ring groove 155b is formed by machining, the pin fin row can be easily formed together with the heat shielding member by precision casting, and can be formed at a lower cost than the processing cost of the fin ring groove. For this reason, the upstream portion 155U and the downstream portion 155D of the heat shielding member are formed separately, and the downstream portion 155D is formed with a pin fin row on the entire periphery thereof, and the fin ring groove 1 is formed.
55b and the downstream portion 15
The heat shield member 155 may be formed by joining the 5D and the 5D integrally by brazing or the like in the axial direction. When the fin ring groove 155b is formed in the heat shielding member, the groove 1
On both sides of 55b, thick portions are formed on the outer periphery of the heat shielding member in the axial direction. Therefore, if the groove 155b is formed over the entire length of the heat shielding member, a relatively large thermal stress may be generated in the thick portion due to a temperature gradient in the axial direction. On the other hand, in the pin fin row, since the thick portion is not continuous in the axial direction, no thermal stress is generated even if there is a large temperature gradient in the axial direction. Therefore, by forming the pin fin array over the entire outer periphery of the downstream portion 155D of the heat shielding member as described above, a secondary effect that thermal stress generated in the heat shielding member is reduced can also be obtained.

(2) Second Embodiment FIG. 4 is an enlarged sectional view of the inner cylinder wall similar to FIG. 2 showing a second embodiment of the gas turbine combustor wall cooling structure of the present invention. In the present embodiment, the first cooling method described above is characterized in that the cooling method of the downstream portion 155D of the penetrating member 159 of the heat shielding member 155 is an internal cooling air passage extending in the axial direction in the heat shielding member instead of the pin fin row. Is different from the embodiment of FIG.

FIG. 5 is a diagram showing the configuration of the downstream portion 155D of the heat shielding member 155 of this embodiment. The downstream portion 155D of the heat shielding member of this embodiment is a cylindrical member having a relatively large plate pressure, and has a large number of cooling air passages 551 having a rectangular cross section arranged in the axial direction inside the cylindrical wall. In this embodiment, the downstream portion 155D of the heat shielding member 155 is used.
Is formed, for example, by joining two cylindrical members 550a and 550b by brazing or the like. The inner cylindrical member 550a has a groove with a rectangular cross section extending in the axial direction on the outer periphery, and the outer cylindrical member 550b
Has a flat inner peripheral surface. Therefore, the inner cylindrical member 550a is inserted into the outer cylindrical member 550a, and the outer peripheral surface 550a of the inner cylindrical member and the inner peripheral surface of the outer cylindrical member 550b are joined by brazing or the like to form the heat shielding member 155. By doing so, the upper part of the outer circumferential groove of the inner cylindrical member 550a is covered by the outer cylindrical member 550b, and a large number of independent tubular internal cooling air passages 551 having a rectangular cross section are formed in the heat shielding member. Is done.

As shown in FIG. 4, a downstream portion 155D of the heat shielding member 155 is joined to an upstream portion 155U having a fin ring cooling structure as in the first embodiment.
The heat shielding member 155 is formed. In this embodiment,
When joining the heat shield member 155 assembled in this manner to the shell 55, a seal ring 553 made of a heat-resistant material is inserted around the outer periphery of the heat shield member downstream portion 155D. The seal ring 553 is provided for the purpose of preventing cooling air from flowing through a gap between the outer circumference of the outer cylindrical member 550b and the inner circumference of the shell 55.

In this embodiment, the cooling air flows into the annular space between the shell and the heat shielding member from a plurality of cooling air inlets 57 provided over the entire periphery of the shell 55 in the upstream portion of the heat shielding member. Then, the upstream portion 155U of the heat shielding member is cooled by passing through the groove 155b of the fin ring. Further, in the heat-shielding member penetrating portion of the penetrating member 159, a part of the cooling air is supplied to the penetrating member 159 and the heat-shielding member upstream portion
The air flows into the combustion chamber through the semi-annular space 159a formed between 5U. On the other hand, on the downstream side of the penetrating member, the cooling air passes through a semi-annular space 159b formed around the downstream half of the outer periphery of the penetrating member 159 of the shell 55 penetrating portion, and the cooling air flows between the shell and the heat shielding member downstream portion 155D. It flows into the annular space, and flows into each cooling air passage 551 from a cooling air inlet 550c formed in each internal cooling air passage on the outer periphery of the outer cylindrical member 550b. And the cooling air is
After flowing through each cooling air passage 551 and convectively cooling the downstream portion 155D of the heat shield member, the heat is discharged from the end of the downstream portion 155D in the axial direction along the inner peripheral surface of the heat shield member of the adjacent shell.

As shown in FIG. 11, when the fin ring cooling structure is adopted, a gap 155c is required between the outer periphery of the fin ring 155 and the inner periphery of the shell 55 in consideration of thermal expansion. The gap 155c needs to be set considerably large in consideration of the processing accuracy of the fin ring and the mounting error. For this reason, in the fin ring cooling structure, a considerable portion of the supplied cooling air does not pass through the fin ring groove 155b and the gap 1 does not contribute to the cooling of the fin ring.
As a result, the heat transfer coefficient between the cooling air and the fin rings may not be sufficiently increased.

In this embodiment, the downstream portion 1 of the heat shielding member
Since the seal ring 553 is provided on the outer periphery of the outer cylindrical member 550b of the outer cylindrical member 550b
The cooling air is prevented from leaking into the combustion chamber from between the outer peripheral surface of the shell 55 and the inner peripheral surface of the shell 55, so that all the cooling air flowing into the shell flows through the internal cooling air passage 551. Therefore, in the downstream portion 155D, the heat transfer coefficient between the cooling air and the heat shielding member 155 is lower than the upstream portion 1
It becomes much larger than the heat transfer coefficient at 55U. As a result, in the present embodiment, a vortex of the combustion gas is generated on the downstream side of the penetrating member 159 and the downstream portion 15 of the heat shielding member is formed.
Even when the heat load locally increases in 5D, it is possible to sufficiently keep the wall temperature of the heat shielding member low.

In the embodiment shown in FIG. 2, all the cooling air flowing into the internal cooling air passage 551 is
It is released from the end along the heat shield member wall surface of the next shell, but also in the present embodiment, as in the fifth embodiment described later, from the film cooling air supply port provided in the inner cylindrical member 550a. If the cooling air in the tubular internal air passage 551 is injected into the combustion chamber to cool the inner peripheral surface of the inner cylindrical member 550a by film, the wall temperature of the heat shielding member (the wall temperature of the inner cylindrical member) can be further assured. Can be prevented from locally increasing in temperature.

(3) Third Embodiment FIG. 6 is an enlarged sectional view of the inner cylinder wall similar to FIG. 2, showing a third embodiment of the gas turbine combustor wall cooling structure of the present invention. In the present embodiment, a groove 165 extending in the axial direction is formed in the outer peripheral portion of the heat-shielding member 155 at the outer peripheral portion also at the downstream portion 155D of the penetrating member 159 similarly to the upstream portion 155U. However, while the groove 155b is a simple fin ring groove in the upstream portion 155U, the groove 165 of the downstream portion 155D is
The first point is that the groove width is wider than the groove 155b of 55U, and the oblique turbulator 167 is formed in the groove.
This is different from the second embodiment. FIG. 7 shows VI of FIG.
5 shows a cross section along the line I-VII. As shown in FIG. 7, the oblique turbulator 167 is formed of a plurality of protrusions extending so as to form a predetermined angle θ in an oblique direction with respect to a direction transverse to the groove 165.

As described above, when the oblique turbulator 167 is disposed in the groove 165, the cooling air flowing in the groove 165 becomes turbulent when passing over the oblique turbulator 167.
A vortex of cooling air is generated downstream of the turbulator 167. Since the oblique turbulator 167 is formed at an angle with respect to the transverse direction, the vortex of the cooling air generated as described above causes the oblique turbulator 1 as shown in FIG.
It moves inside the groove 165 along the back surface of 67.
As described above, when the vortex of the cooling air is generated, the heat transfer between the cooling air and the heat shielding member 155 is turbulent heat transfer at the location where the vortex is generated, and the heat transfer coefficient is significantly larger than that in the case of the laminar heat transfer. To increase. Moreover, in the oblique turbulator 167,
Since the generated vortex moves over a wide range along the back surface of each turbulator 167, the overall heat transfer coefficient greatly increases. Therefore, the penetrating member 15
9 Even when the vortex of the combustion gas is generated on the inner peripheral surface of the heat shield member 155D on the downstream side, and the heat load is locally increased, the heat shield member is sufficiently cooled, and the heat shield member is locally cooled. No significant temperature rise occurs.

In this embodiment, the groove 165 and the oblique turbulator 167 are formed integrally with the heat shielding member downstream portion 155D by precision casting or the like, and are brazed to the heat shielding member upstream portion 155U of the fin ring structure. Are joined.

(4) Fourth Embodiment Next, a fourth embodiment of the present invention will be described. In the above-described first to third embodiments, the heat transfer rate between the cooling air flowing through the outer peripheral portion of the heat shielding member and the heat shielding member on the downstream side in the combustion gas flow direction of the penetrating member is increased. By increasing the cooling capacity of the shielding member, a local increase in the heat load on the inner peripheral surface of the heat shielding member caused by the generation of the vortex by the combustion gas downstream of the penetrating member has been absorbed. On the other hand, the present embodiment is different from the above-described embodiments in that the local increase in the heat load on the inner peripheral surface of the heat shielding member due to the generation of the vortex on the downstream side of the penetrating member is prevented.

FIG. 8 is an enlarged sectional view of the inner cylindrical wall similar to FIG. 2 showing the present embodiment. In the present embodiment, the fin groove 155b is formed on the outer peripheral surface of the heat shielding member 155 over the entire length including the downstream portion 155D of the penetrating member 159, similarly to the conventional one in FIG. However, in the present embodiment, a part of the cooling air flowing between the heat shielding member 155 and the shell 55 is discharged from the downstream side of the heat shielding member 155 of the penetrating member 159 to the combustion chamber, and the downstream side of the penetrating member of the heat shielding member 155. The point that a film cooling air supply means flowing along the inner wall of the portion 155D is provided is different from the cooling structure of FIG.

In this embodiment, the film cooling air supply means is a semi-annular cooling air supply port provided between the outer periphery of the penetrating member and the heat shielding member 155 in the penetrating portion of the penetrating member 159 of the heat shielding member 155. Gap 171 and the penetrating member 1
And a semicircular lip (deflecting plate) 173 provided on the outer peripheral downstream side of the tip of the projecting portion of the combustion chamber 59.
In the present embodiment, the space between the heat shield plate on the upstream side of the penetrating member 159 and the outer peripheral portion of the penetrating member is sealed by a heat-resistant seal member 175, and the cooling air does not flow into the combustion chamber from the upstream side of the penetrating member 159. It has been like that.

In FIG. 8, most of the cooling air flowing between the shell 55 and the heat shielding member 155 from the cooling air inlet 57 provided around the entire circumference of the shell 55 is shown in FIG.
Flows in the fin ring groove 155b and heat shield member 1
55 is cooled from the outer periphery thereof, and a part of the cooling air is discharged to the combustion chamber from a semi-annular space 171 between the outer periphery downstream of the penetrating member 159 and the heat shielding member. This cooling air flow is applied to the deflecting plate 17 which is disposed in the vicinity of the protruding end (opening) of the penetration member 159 near the inner peripheral surface of the heat shielding member 155.
3, the deflection plate 173 and the heat shielding member 15
5 flows downstream from the gap between the inner peripheral surface and the inner peripheral surface. Therefore, a film of cooling air is formed on the downstream side of the penetrating member 159 along the inner peripheral surface of the heat shielding member.

As described above, the heat load on the heat shielding member wall surface on the downstream side of the penetrating member 159 is increased due to the generation of the vortex of the combustion gas and the cooling air supplied from the upstream side of the penetrating member. This is because the film is blocked by the penetrating member projection and cannot reach the downstream side. In the present embodiment, since the film cooling is performed by directly supplying the cooling air to the downstream side of the penetrating member as described above, the low pressure portion does not occur on the downstream side of the penetrating member, so that the combustion gas is downstream of the penetrating member. Is prevented from being caught and vortices are generated,
A film of cooling air is formed on the heat shield member wall surface on the downstream side of the penetrating member. Therefore, the heat load on the inner wall of the heat shielding member is prevented from locally increasing due to the presence of the penetrating member, and the local temperature rise of the heat shielding member does not occur.

(5) Fifth Embodiment Next, a fifth embodiment of the present invention will be described. Also in the present embodiment, the film cooling air is supplied to the heat shielding member wall surface on the downstream side of the penetrating member in the same manner as in the fourth embodiment, thereby preventing the generation of the vortex of the combustion gas by the penetrating member and the heat shielding member wall surface. Is the same as that of the fourth embodiment, but the method of supplying cooling air for cooling the film is different from that of the fourth embodiment.

FIG. 9 is an enlarged view of the inner cylinder wall similar to FIG. 8 showing this embodiment. As shown in FIG. 9, the downstream portion 155 </ b> D of the penetrating member of the heat shielding member 155 of the present embodiment has the same configuration as that of the above-described second embodiment. The cooling air passage 551 is formed. However, in the present embodiment, the seal ring 553 that seals between the outer periphery of the outer cylindrical member 550b and the shell 55 is provided near the downstream end of the heat shielding member 155, and is provided on the downstream side of the penetrating member 159. Each internal cooling air passage 551 has a seal ring 553.
A plurality of cooling air inlets 550c perforated in the outer cylindrical member 550b are provided in an upstream portion, and the inner cylindrical member 550a discharges cooling air in each cooling air passage 551 to the combustion chamber. Cooling air outlets 550d
Are formed along each cooling air passage 551.

In this embodiment, each cooling air passage 551 located downstream from the cooling air inlet 550c and the penetrating member 159 is provided.
Is discharged from the plurality of cooling air outlets 550d to the combustion chamber downstream of the penetrating member 159. For this reason, similarly to the fourth embodiment, it is possible to prevent the generation of the vortex of the combustion gas by the penetrating member and to cool the film of the heat shielding member wall surface, and the local heat load on the heat shielding member wall surface downstream of the penetrating member is achieved. Is prevented from increasing. In this embodiment,
Since the tubular internal cooling air passage 551 having a large cooling capacity is provided in the heat shielding member portion 155D on the downstream side of the penetrating portion similarly to the second embodiment described above, the heat shielding member 155 can be formed in addition to the above-described heat load increase prevention. Since the cooling capacity also increases, it is possible to reliably prevent the temperature of the heat shielding member from rising.

[0050]

According to the present invention, the temperature of the heat shielding member locally increases downstream of the penetrating member due to the presence of the penetrating member penetrating the heat shielding member of the gas turbine combustor. It has the common effect that it can be prevented. In other words, according to the first to fifth aspects of the present invention, the heat transfer coefficient between the heat shield member on the downstream side of the penetrating member and the cooling air is made larger than the heat transfer coefficient of the heat shield member on the upstream side of the penetrating member. Because the cooling capacity of the downstream heat shielding member increases,
A local temperature rise of the heat shield member on the downstream side of the penetrating member is prevented.

According to the present invention, the film cooling air is supplied to the wall of the heat shielding member on the downstream side of the penetrating member, so that the heat is locally heated on the wall of the heat shielding member on the downstream side of the penetrating member. Since the load is prevented from increasing, a local temperature rise of the heat shielding member on the downstream side of the penetrating member is prevented.

[Brief description of the drawings]

FIG. 1 is a sectional view showing an example of an air-cooled gas turbine combustor.

FIG. 2 is a sectional view showing a first embodiment of the gas turbine combustor wall cooling structure of the present invention.

FIG. 3 is a sectional view taken along line III-III of FIG. 2;

FIG. 4 is a sectional view showing a second embodiment of the gas turbine combustor wall cooling structure of the present invention.

FIG. 5 is a diagram illustrating a tubular internal cooling air passage according to a second embodiment.

FIG. 6 is a sectional view showing a third embodiment of the gas turbine combustor wall cooling structure of the present invention.

FIG. 7 is a sectional view taken along the line VII-VII in FIG. 6;

FIG. 8 is a sectional view showing a fourth embodiment of the gas turbine combustor wall cooling structure of the present invention.

FIG. 9 is a sectional view showing a fifth embodiment of the gas turbine combustor wall cooling structure of the present invention.

FIG. 10 is a sectional view showing a conventional gas turbine combustor wall cooling structure.

FIG. 11 is a sectional view taken along the line XI-XI in FIG. 10;

FIG. 12 is a cross-sectional view similar to FIG. 10, illustrating a problem of the related art.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 ... Gas turbine combustor 5b ... Inner cylinder 55 ... Shell 155 ... Heat shielding member 155P ... Pin fin row 159 ... Penetrating member 551 ... Tubular internal cooling air passage

 ──────────────────────────────────────────────────続 き Continuing on the front page (72) Inventor Tsuyoshi Kitamura 2-1-1 Shinhama, Arai-machi, Takasago City, Hyogo Prefecture Inside the Takasago Research Laboratory, Mitsubishi Heavy Industries, Ltd. No. 1 Inside the Mitsubishi Heavy Industries, Ltd. Takasago Research Laboratory

Claims (8)

[Claims] 1. A cylindrical inner cylinder having an internal space forming a combustion chamber, and a cylindrical combustion chamber wall attached to the inner surface of the inner cylinder over the entire circumference and through which combustion gas flows in an axial direction. A heat shielding member, heat exchange means for promoting heat exchange between the cooling air flowing in the axial direction of the inner cylinder between the heat shielding member and the inner cylinder, and the heat shielding member, A tubular through-hole member that penetrates through the shielding member and opens into the combustion chamber from the outside of the inner cylinder, wherein the heat exchange means is located downstream of the through-member in the combustion gas flow direction. The heat transfer coefficient between the cooling air and the heat shielding member at the side portion is set to be larger than the heat transfer coefficient between the cooling air and the heat shielding member on the upstream side in the combustion gas flow direction of the penetrating member. Gas turbine combustion characterized by being Wall cooling structure. 2. The heat exchanger according to claim 1, wherein the heat exchange means on the downstream side in the combustion gas flow direction of the penetrating member includes a pin fin array comprising a plurality of projections projecting at right angles from the outer periphery of the heat shielding member. Gas turbine combustor wall cooling structure. 3. The heat exchange means on the downstream side of the penetrating member in the direction of combustion gas flow includes a plurality of tubular internal cooling air passages extending in a direction along an inner cylinder axis in the heat shielding member. The air passage includes a cooling air inlet opening at an outer peripheral portion of the heat shielding member on the downstream side in the combustion gas flow direction of the penetrating member, and a cooling air outlet opening at a downstream end of the heat shielding member. The cooling air flowing through the passage flows into the combustion chamber from the cooling air outlet along the inner peripheral surface of the inner cylinder.
2. The gas turbine combustor wall cooling structure according to 1. 4. A heat exchange means on the downstream side of the penetrating member in the combustion gas flow direction includes a plurality of axially extending grooves provided on an outer peripheral portion of the heat shielding member, and a plurality of grooves in the grooves in a direction transverse to the grooves. The gas turbine combustor wall cooling structure according to claim 1, further comprising an oblique turbulator including a projection extending obliquely. 5. The heat exchange means on the upstream side of the penetrating member in the direction of combustion gas flow includes a plurality of axially extending grooves provided over the entire outer peripheral portion of the heat shielding member. The gas turbine combustor wall cooling structure according to any one of the above items. 6. A cylindrical inner cylinder having an internal space constituting a combustion chamber, and a cylindrical combustion chamber wall attached to the inner surface of the inner cylinder over the entire circumference and through which combustion gas flows in an axial direction. A heat shielding member, a cooling air passage through which cooling air flows in the axial direction of the inner cylinder between the heat shielding member and the inner cylinder, and a combustion chamber that penetrates the inner cylinder and the heat shielding member from outside the inner cylinder. And a tubular through-hole member that opens into the gas turbine combustor wall cooling structure, wherein the cooling air passage partially transfers the cooling air downstream of the heat shielding member in the combustion gas flow direction of the through-hole member. A gas turbine combustor wall cooling structure, characterized by comprising film cooling air supply means flowing from a side portion along the inner peripheral surface of the heat shielding member. 7. The cooling air supply means, comprising: a cooling air supply comprising a gap between the outer surface of the through member penetrating portion of the heat shielding member on the downstream side of the outer periphery of the penetrating member in the flow direction of combustion gas and the heat shielding member. Port, provided around the opening of the penetrating member, the cooling air flowing into the combustion chamber from the cooling air passage through the cooling air supply port to the downstream side in the combustion gas flow direction along the heat shield member inner peripheral surface. The gas turbine combustor wall cooling structure according to claim 6, further comprising: a deflecting unit that flows toward the gas turbine combustor. 8. The cooling air passage has a plurality of tubular internal cooling air passages extending in a direction along an inner cylinder axis in the heat shielding member on a downstream side of the through member in a combustion gas flow direction;
A cooling air inlet to the internal cooling air passage opening at an outer peripheral portion of the heat shielding member on the downstream side in the combustion gas flow direction of the penetrating member, wherein the film cooling air supply means includes: Open to the inner peripheral surface on the downstream side of the member,
The gas turbine combustor wall cooling structure according to claim 6, further comprising: a film cooling air supply port that discharges cooling air in the internal cooling air passage into a combustion chamber.