JP2005002899A - Gas turbine burner - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a gas turbine burner whose easiness of manufacturing can be improved while preserving its cooling performance. <P>SOLUTION: A burner 140 blends and burns fuel and high-pressure air compressed by a compressor 110 to feed the produced burning gas to a turbine 150. The burner 140 is equipped with a cylindrical liner 2 for producing internally the burning gas, a tail pipe 4 that has a plurality of depressions 10 in an outer surface 4a and leads the burning gas produced in the liner 2 to the turbine 150, and a tail pipe free sleeve 5 provided so as to encompass at least part of an outer surface 4a of the tail pipe 4. <P>COPYRIGHT: (C)2005,JPO&NCIPI

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a gas turbine combustor that generates combustion gas to be introduced into a turbine by mixing and burning high-pressure air compressed by a compressor and fuel.
[0002]
[Prior art]
Generally, a gas turbine combustor mixes high-pressure air introduced from a compressor and fuel to form a combustion chamber that generates high-temperature and high-pressure combustion gas, and guides the combustion gas from the liner to the turbine. And a tail tube.
[0003]
As a method of cooling the above-mentioned tail tube, conventionally, the liner side of the outer surface (outer wall surface) of the tail tube is covered with a flow sleeve (guide wall), so that high-pressure air from the compressor is supplied to the outer surface of the flow sleeve and the tail tube. A plurality of air introduction holes (small hole groups) that communicate the inside and outside of the transition piece to a portion of the transition piece that is not covered by the flow sleeve on the turbine side of the transition piece. ) To introduce high-pressure air into the transition piece, form a layer of cooling air between the combustion gas and the inner surface of the transition piece, and film cool the turbine side of the transition piece (for example, (See Patent Document 1).
[0004]
In addition, the impingement that covers the outer surface of the tail cylinder with an impingement cover (covering cylinder) and cools the tail cylinder by colliding a jet of high-pressure air against the tail cylinder from the cooling air hole (impingement hole) provided in the impingement cover There is a cooling system (see, for example, Patent Document 2 and Patent Document 3).
[0005]
In recent years, with the demand for higher output and higher efficiency for gas turbine plants, the combustion gas temperature tends to increase year by year, and in order to lower the temperature of the members constituting the tail cylinder to below the allowable temperature There is a need to improve the cooling performance of the transition piece.
[0006]
However, when trying to improve the cooling performance in the convection cooling method as described in Patent Document 1 described above, the gap distance between the tail tube and the flow sleeve is reduced to narrow the flow path of high-pressure air and increase the flow velocity. As a result, the pressure loss when high-pressure air flows through the gap increases, and the gas turbine efficiency decreases.
[0007]
Moreover, when it is going to improve cooling performance in the impingement cooling system as described in Patent Document 2 and Patent Document 3 described above, it is necessary to increase the collision speed of the air jet against the tail cylinder. The diameter of the air hole must be reduced, and as a result, the pressure loss of the high-pressure air also increases and the gas turbine efficiency decreases.
[0008]
From such a background, by providing ribs (rib-like fins) in the circumferential direction on the outer surface of the tail tube, turbulence of high-pressure air flowing through the gap between the tail tube and the flow sleeve is promoted for cooling. There is a gas turbine combustor (see, for example, Patent Document 4). In this case, even if the gap between the transition piece and the flow sleeve is not narrowed, the convective heat transfer coefficient is increased by the turbulent flow promoting effect and the heat transfer area is increased by the rib, so that the heat radiation amount can be increased. It is possible to improve the cooling performance while suppressing an increase in pressure loss of high-pressure air.
[0009]
[Patent Document 1]
JP-A-5-141269
[Patent Document 2]
Japanese Patent Publication No.54-11443
[Patent Document 3]
JP 2001-289060 A
[Patent Document 4]
Japanese Patent Laid-Open No. 10-82527
[0010]
[Problems to be solved by the invention]
However, there are the following problems in the above-described prior art.
That is, according to the gas turbine combustor having the structure in which the rib is provided on the outer surface of the transition piece as described in Patent Document 4, the cooling performance of the transition piece is suppressed while suppressing the increase in the pressure loss of the high-pressure air as described above. However, since the molding of the rib is usually performed by scraping the outer surface of the tail tube leaving the rib portion, the amount of machining is very large, and the outer surface of the tail tube is a complicated tertiary. Since it has an original curved surface, the above-described cutting process is not easy, so that the time required for the rib processing work becomes long, resulting in an increase in manufacturing cost.
[0011]
The present invention has been made in view of such problems, and an object of the present invention is to provide a gas turbine combustor capable of improving manufacturability while maintaining cooling performance.
[0012]
[Means for Solving the Problems]
(1) In order to achieve the above object, the present invention provides a gas turbine combustor that mixes and burns high-pressure air compressed by a compressor and fuel, and supplies the generated combustion gas to a turbine. A cylindrical liner that internally generates a plurality of indentations on the outer surface, and guides the combustion gas generated by the liner to the turbine, and wraps at least a part of the outer surface of the tail cylinder And a flow sleeve provided as described above.
[0013]
In the gas turbine combustor of the present invention, high-pressure air from the compressor is introduced into the gap between the tail cylinder and the flow sleeve, and the tail cylinder is cooled by convection cooling. At this time, since the outer surface of the transition piece is provided with a plurality of recesses, the heat transfer area on the outer surface of the transition piece is increased to increase the amount of heat dissipation, and in addition to the transition between the transition piece and the flow in the downstream area of the recess. Since the secondary flow is generated in the cooling air flowing in the gap with the sleeve and the turbulent flow is promoted, the convective heat transfer coefficient is increased. As a result, in the gas turbine combustor of the present invention, it is possible to cool the tail cylinder effectively compared to the case where the outer surface of the tail cylinder is flat. For example, a rib is provided on the outer surface of the tail cylinder described above. Compared to a conventional structure that performs turbulent flow enhanced cooling, the cooling performance is equivalent or better.
[0014]
Here, the production of the tail tube having the conventional structure in which the rib is provided on the outer surface is usually performed by scraping the outer surface of the tail tube while leaving the rib portion, so that the amount of machining is very large, and Since the outer surface of the tail tube has a complicated three-dimensional curved surface, the above-described cutting process is not easy, so that the time required for the rib processing work becomes long, resulting in an increase in manufacturing cost.
[0015]
On the other hand, in the present invention, for example, it is sufficient to provide a recess on the outer surface of the tail cylinder using a cutting tool such as a reamer or a drill, and the amount of machining can be significantly reduced compared to the case where the rib is provided. it can. Furthermore, since it is not necessary to scrape the outer surface of the tail tube along a complicated three-dimensional curved surface as in the case of providing a rib, the machining operation can be facilitated as compared with the conventional structure. Thereby, the production period of the transition piece can be shortened, and as a result, the production cost can be reduced. From the above, according to the present invention, the ease of manufacturing can be improved while maintaining the cooling performance.
[0016]
(2) In order to achieve the above object, the present invention is also directed to a gas turbine combustor that mixes and burns high-pressure air compressed by a compressor and fuel and supplies the generated combustion gas to a turbine. A cylindrical liner that generates gas inside, a plurality of depressions on the outer surface, a tail cylinder that guides the combustion gas generated by the liner to the turbine, and a plurality of cooling air holes, An impingement cover provided so as to wrap at least part of the outer surface of the tail tube.
[0017]
(3) In the above (1) or (2), preferably, a plurality of air introduction holes that communicate the inside and the outside of the tail tube are provided in a portion of the tail tube that is not covered by the flow sleeve or the impingement cover. And
[0018]
(4) In any one of the above (1) to (3), and preferably, at least one of an opening area, a depth, and an installation interval of the depression is changed according to a portion of the tail tube. To do.
[0019]
In general, since the heat load that the tail tube receives from the combustion gas generated by the liner differs depending on the part, the required cooling performance also differs depending on the part. Therefore, it is preferable to change the opening area, depth, and installation interval of the depressions according to the part so as to satisfy the cooling performance required in each part of the tail tube.
[0020]
Here, normally, the flow velocity of the combustion gas flowing in the transition piece is larger because the flow passage area is narrowed on the turbine side, which is the outlet side, than the liner side, which is the inlet side. The heat load to be received is larger on the turbine side.
[0021]
Therefore, in the present invention, for example, the installation interval of the depressions provided on the outer surface of the transition piece is reduced as it goes from the liner side to the turbine side, and the opening area of the depression is reduced as it goes from the liner side of the transition piece to the turbine side. . Thereby, the number of depressions provided on the turbine side of the transition piece can be made larger than that on the liner side, and the cooling performance on the turbine side can be partially improved. As a result, the temperature distribution of the entire transition piece can be made uniform, and the occurrence of local thermal stress can be suppressed.
[0022]
(5) In said (4), More preferably, the installation space | interval of the said hollow provided in the outer surface of the said tail cylinder shall become narrow as it goes to the said turbine side from the said liner side.
[0023]
(6) In the above (4) or (5), preferably, the opening area of the depression provided on the outer surface of the tail tube is reduced from the liner side toward the turbine side.
[0024]
(7) In any one of the above (1) to (6), the opening shape of the recess is circular.
[0025]
(8) In any one of the above (1) to (7), the opening shape of the recess is an ellipse.
[0026]
DETAILED DESCRIPTION OF THE INVENTION
Embodiments of a gas turbine combustor according to the present invention will be described below with reference to the drawings.
First, a first embodiment of the present invention will be described below with reference to FIGS.
[0027]
FIG. 1 is a schematic configuration diagram schematically showing an overall configuration of a gas turbine including a first embodiment of a gas turbine combustor according to the present invention.
As shown in FIG. 1, the gas turbine 100 includes a compressor 110 that compresses air, a passenger compartment 130 into which high-pressure air compressed by the compressor 110 is introduced via a diffuser 120, and the passenger compartment 130. A combustor 140 that generates a combustion gas by mixing high-pressure air introduced from the fuel and fuel, a turbine 150 into which the combustion gas generated by the combustor 140 is introduced, and the combustion gas adiabatically expanded in the turbine 150. And a generator 160 that generates electric power by converting the amount of work generated during the operation into a shaft rotational force. A plurality of the combustors 140 are arranged in the circumferential direction of the gas turbine 100.
[0028]
The combustor 140 includes a substantially cylindrical liner 2 that internally forms a combustion chamber 1 in which high-pressure air introduced from the vehicle interior 130 and fuel supplied from the fuel system 170 are mixed and combusted, and the liner 2. The burner 3 is provided at the end of the combustion chamber 1 to generate a flame in the combustion chamber 1, the tail cylinder 4 that guides the combustion gas generated in the liner 2 to the turbine 150, and the liner side of the tail cylinder 4 so as to be wrapped. And a liner flow sleeve 6 provided concentrically on the outer peripheral side so as to wrap the liner 2.
[0029]
The transition pipe flow sleeve 5 and the liner flow sleeve 6 are arranged at a predetermined distance from the transition cylinder 4 and the liner 2, respectively. A flow passage gap S1 through which the cooling air flows), and a flow passage gap S2 are formed between the liner flow sleeve 6 and the liner 2, respectively. That is, the high-pressure air compressed by the compressor 110 is introduced from the passenger compartment 130 into the flow passage gap S1, and after flowing in the flow passage gap S2, the direction is reversed and introduced into the combustion chamber 1. ing.
[0030]
FIG. 2 is a side sectional view showing the detailed structure of the combustor 140 in the vicinity of the transition piece 4, and FIG. 3 is a sectional view taken along the line III-III in FIG.
As shown in FIGS. 2 and 3, the high-pressure air introduced from the passenger compartment 130 into the flow passage gap S1 becomes a high-speed air flow f1, and is convected through the tail cylinder 4 exposed to high-temperature combustion gas and receiving a heat load. It is designed to cool. A plurality of circular recesses 10 are provided on the outer surface 4a of the tail cylinder 4 at substantially equal intervals.
[0031]
In the above, the combustor 140 constitutes a gas turbine combustor described in the claims, and the tail cylinder flow sleeve 5 constitutes a flow sleeve provided so as to enclose at least a part of the outer surface of the tail cylinder.
[0032]
Next, the operation obtained by the first embodiment of the gas turbine combustor of the present invention having the above configuration will be described below.
In the gas turbine combustor according to the present embodiment, as described above, the high-pressure air compressed by the compressor 110 is introduced from the passenger compartment 130 into the flow passage gap S1, and becomes a high-speed air flow f1 so that the tail cylinder 4 is moved. Cool by convection. At this time, since a plurality of depressions 10 are provided on the outer surface 4a of the tail cylinder 4, the heat transfer area of the outer surface 4a of the tail cylinder 4 is increased and the heat radiation amount is increased, and the downstream area of the depression 10 is increased. , The secondary flow is generated in the cooling air flowing in the flow passage gap S1 and the turbulent flow is promoted, so that the convective heat transfer coefficient is increased. As a result, in the combustor 140 of the present embodiment, the tail cylinder 4 can be convectively cooled more effectively than when the outer surface 4a of the tail cylinder is flat. Compared to a structure in which ribs are provided on the outer surface of the tail cylinder as described in JP-A-10-82527 to perform turbulent flow enhanced cooling, the cooling performance is equivalent or better.
[0033]
Thus, according to the gas turbine combustor of the present embodiment, it is possible to have a cooling performance equivalent to or higher than that of the structure provided with the ribs, and to further improve the ease of manufacturing the tail cylinder 4. This ease of manufacture will be described below with reference to a structure in which ribs are provided on the outer surface of the tail cylinder as described in Patent Document 4 of the above-mentioned prior art as a comparative example.
[0034]
FIG. 4 is a side sectional view showing the structure of a comparative example in which ribs are provided on the outer surface of the transition piece. In FIG. 4, the same parts as those in FIG. 2 described above are denoted by the same reference numerals, and description thereof is omitted.
As shown in FIG. 4, a rib 11 is provided on the outer surface 4'a of the tail cylinder 4 'over the circumference in the circumferential direction. Further, the rib 11 is arranged in the axial direction of the tail cylinder 4' (see FIG. 4). 4 in the left-right direction). With such a structure, the cooling performance is improved by promoting the turbulent flow of the cooling air.
[0035]
Here, in general, the tail tube is manufactured by joining two base metal flat plates corresponding to the upper half and the lower half separately by press working and then joining them by welding. At this time, there are the following two methods for manufacturing the transition piece 4 'of the comparative example.
[0036]
One is a method in which the rib 11 is cut out from the tail tube 4 'welded and joined after press-molding the upper and lower base metal plates. However, this processing method has the following problems. That is, in this processing method, the rib 11 portion must be left and other portions must be scraped off, resulting in a very large amount of shaving. In addition, since a strong material is used because the high temperature and high pressure resistance is required for the tail tube, it takes a lot of work to cut the tail tube in such a large amount. It takes a long time to complete.
[0037]
Furthermore, the following problems also exist regarding processing accuracy. That is, in general, there is a phenomenon called a springback phenomenon in which the base material is slightly restored by elasticity even if it is pressed with a precisely manufactured stamping die at the time of pressing, and the curved surface of the tail cylinder 4 'molded for this purpose. The shape may deviate from the design shape. In this case, when the rib 11 is machined with a three-dimensional machine tool, the curved shape of the tail cylinder 4 'is deviated from the design shape, so that the amount of machining differs from the design value, and the height of the rib 11 is the design value. It may be different from that. In this way, when the processing accuracy of the ribs 11 decreases, the cooling performance may decrease. Further, as described above, since the high temperature and high pressure resistance is required for the tail tube, a strong material is used. Therefore, when performing the above cutting, the tail tube 4 'is fixed with a strong force. As a result, the tail cylinder 4 'may be deformed.
[0038]
As shown in FIG. 5, the second method of manufacturing the tail tube 4 'is to preliminarily mold the ribs 11 on the base plate 4'A of the upper half and the lower half of the tail tube 4'. Then, each base material flat plate 4'A is pressed and then joined by welding. However, this processing method has the following problems. That is, first of all, as in the first method, there is no change in the amount of machining, and the time required for production becomes long. Regarding processing accuracy, there is a possibility that the rib 11 provided in advance when the base plate 4'A is pressed is crushed and deformed by the pressing die. In this case, the pressing die may be damaged. Further, since the ribs 11 are separately processed on the upper and lower base metal flat plates 4′A, depending on the difference in compression / extension of the upper and lower base metal flat plates 4′A during pressing, they are joined by welding. In some cases, the upper and lower ribs 11 may not be aligned. As described above, the processing accuracy of the ribs 11 may be reduced and the cooling performance may be reduced.
[0039]
As a method for forming the rib 11, in addition to the above-described cutting method, a method of joining the rib 11 to the base metal plate 4 ′ A by welding is conceivable, but in this case, the rib 11 is deformed by heat. There is a risk of breakage, and even if they are joined, the center part of the joining surface of the ribs 11 may float from the surface of the base material flat plate 4'A, so that the heat transfer efficiency is lowered. The method is done.
[0040]
As described above, when producing a tail tube having a rib structure as in the above comparative example, the amount of machining is very large, and it is very difficult to machine with high precision. Requires a lot of labor, and the time required for manufacturing and processing has become longer. As a result, the manufacturing cost has been increased.
[0041]
On the other hand, in this embodiment, the depression 10 is provided on the outer surface 4a of the tail cylinder 4, but in the manufacturing process, for example, a reamer 12 (or a drill or the like) may be used as shown in FIGS. It is sufficient to provide the depression 10 in the base material flat plate 4A. Thereby, since the amount of machining can be remarkably reduced as compared with the comparative example, the time required for manufacturing can be greatly reduced. In addition, since the complicated work of scraping the surface of the base metal plate 4A along the complicated three-dimensional curved surface as in the case of providing the ribs 11 is not required, the working work can be extremely facilitated. Further, in terms of processing accuracy, the second manufacturing method described above, that is, the depression 10 is formed in advance on the base material flat plate 4A, and then the upper and lower base material flat plates 4A are pressed and welded. If there is no member protruding from the base material flat plate like the rib 11, there is no situation where the recess 10 is deformed and the cooling performance is deteriorated. Moreover, it is possible to prevent the pressing mold from being damaged.
[0042]
As described above, according to the present embodiment, the production work of the transition piece 4 can be facilitated, so that the production period can be shortened, and as a result, the production cost can be reduced. Therefore, it is possible to improve manufacturability while maintaining a cooling performance equal to or higher than that of a structure in which ribs are provided on the outer surface of the tail tube as in the prior art to perform turbulent flow enhanced cooling.
[0043]
Next, a second embodiment of the gas turbine combustor according to the present invention will be described below with reference to FIGS. In the present embodiment, the tail cylinder is cooled by convection cooling in the first embodiment described above, but is cooled by impingement cooling.
8 is a side sectional view showing a detailed structure in the vicinity of the transition piece 4 in the present embodiment, and FIG. 9 is a sectional view taken along a section IX-IX in FIG. In FIGS. 8 and 9, the same parts as those in FIGS. 2 and 3 in the first embodiment of the present invention described above are denoted by the same reference numerals, and description thereof is omitted.
[0044]
8 and 9, reference numeral 15 denotes an impingement cover provided so as to wrap almost the entire outer surface 4 a of the tail cylinder 4, and the impingement cover 15 has a plurality of cooling air holes 16 formed therein. In the present embodiment, the high-pressure air compressed by the compressor 110 becomes a blown air flow f2 from the casing 130 through the plurality of cooling air holes 16 provided in the impingement cover 15, and the outer surface 4a of the tail cylinder. And the tail cylinder 4 that is exposed to a high-temperature combustion gas and receives a heat load is impingement cooled.
[0045]
Also in the present embodiment having such a configuration, since the plurality of depressions 10 are provided on the outer surface 4a of the transition piece 4, the heat transfer area is increased, the heat radiation amount is increased, and the flow gap S1 flows. As a result, the convective heat transfer coefficient of the cooling air is increased, and as a result, the cooling performance is equal to or higher than that of a structure (not shown) that impinges cools the surface of the tail cylinder provided with ribs, for example. Therefore, it is possible to improve manufacturability while maintaining the cooling performance as in the first embodiment described above.
[0046]
In the present embodiment, the installation position of the depression 10 on the outer surface 4a of the tail tube may be matched with the cooling air hole 16 provided in the impingement cover 15. In this case, the cooling performance can be further improved.
[0047]
Next, a third embodiment of the gas turbine combustor of the present invention will be described below with reference to FIG. In this embodiment, in addition to the convection cooling in the first embodiment described above, the tail tube is further cooled by film cooling.
FIG. 10 is a side sectional view showing the detailed structure of the turbine side end portion of the transition piece in the present embodiment. In FIG. 10, parts similar to those in FIG. 2 in the first embodiment of the present invention described above are denoted by the same reference numerals and description thereof is omitted.
[0048]
In FIG. 10, reference numeral 20 denotes a plurality of air introduction holes that communicate with the inside and outside of the tail cylinder 4 provided in a portion of the tail cylinder 4 that is not covered with the turbine sleeve on the turbine side. With this configuration, in the present embodiment, cooling air is introduced into the transition piece 4 from the air introduction hole 20 to form a cooling air layer between the combustion gas and the inner surface 4b of the transition piece 4. The turbine side end portion of the transition piece 4 is film-cooled. Thereby, it is possible to effectively cool the turbine side end portion of the tail cylinder 4 whose convection cooling performance is lowered because it is not covered with the tail cylinder flow sleeve 5.
[0049]
Also in the present embodiment having such a configuration, it is possible to improve manufacturability while maintaining the cooling performance as in the first and second embodiments described above.
[0050]
In the present embodiment, the air introduction hole 20 is provided in the structure for performing the convection cooling as in the first embodiment described above to perform the film cooling. However, the present invention is not limited to this. The film cooling may be performed by providing the air introduction hole 20 in the structure for impingement cooling as in the embodiment.
[0051]
Here, in the first, second, and third embodiments of the present invention described above, the depressions 10 having the same shape are provided on the outer surface 4a of the tail cylinder at a uniform installation interval. Since the heat load that the tail cylinder 4 receives from the combustion gas differs depending on the part, the required cooling performance also differs depending on the part. Therefore, it is preferable to change the diameter of the recess 10 (that is, the diameter of the opening of the recess 10), the depth, and the installation interval according to the site so as to satisfy the cooling performance required at each site of the tail tube 4. The following embodiment is an example in which at least one of the diameter, depth, and installation interval of the recess 10 is changed in accordance with the part of the transition piece 4.
[0052]
Next, a fourth embodiment of the gas turbine combustor of the present invention will be described below with reference to FIG. In the present embodiment, the convection cooling of the transition piece is performed as in the first embodiment, and the installation interval of the depressions 10 is changed according to the position of the transition piece 4.
FIG. 11 is a side view showing a detailed structure near the transition piece 4 in the present embodiment. In FIG. 11, the same parts as those in FIG. 2 in the first embodiment of the present invention described above are denoted by the same reference numerals, and description thereof is omitted.
[0053]
As shown in FIG. 11, in this embodiment, the installation interval in the circumferential direction and the axial direction (whichever is sufficient) of the recess 10 provided on the outer surface 4 a of the tail tube with respect to the tail tube 4 is set from the liner 2 side to the turbine 150. The structure is narrower toward the side. That is, in general, the flow velocity of the combustion gas flowing in the transition piece 4 is larger because the flow passage area is narrowed on the turbine 150 side, which is the outlet side, than the liner 2 side, which is the inlet side. The heat load received from the combustion gas is also larger on the turbine 150 side. In the present embodiment, as described above, the installation interval of the depressions 10 is narrowed from the liner 2 side toward the turbine 150 side. Therefore, the number of depressions 10 installed on the turbine 150 side with a large thermal load is compared with that on the liner 2 side. Can do a lot. Thereby, the cooling performance on the turbine side of the transition piece 4 can be partially improved. As a result, according to the present embodiment, the ease of manufacture can be improved while maintaining the cooling performance as in the first, second and third embodiments described above, and the entire tail cylinder 4 can be improved. Can be made uniform, and the occurrence of local thermal stress can be suppressed.
[0054]
Next, a fifth embodiment of the gas turbine combustor of the present invention will be described below with reference to FIG. In the present embodiment, the installation distance of the depressions 10 is changed according to the portion of the tail cylinder 4 in the fourth embodiment described above, but in addition, the diameter of the depressions 10 is changed. .
FIG. 12 is a side view showing a detailed structure near the transition piece 4 in the present embodiment. In FIG. 12, the same parts as those in FIG. 2 in the first embodiment of the present invention described above are denoted by the same reference numerals, and description thereof is omitted.
[0055]
As shown in FIG. 12, in this embodiment, the diameter of the recess 10 (opening) provided on the outer surface 4a of the tail cylinder is reduced from the liner 2 side toward the turbine 150 side. By doing in this way, the number of installation of the hollow 10 in the turbine 150 side with a large heat load can be increased compared with the liner 2 side. Thereby, the cooling performance on the turbine side of the transition piece 4 can be partially improved. Therefore, in the same manner as in the above-described fourth embodiment, the ease of manufacture can be improved while maintaining the cooling performance, and the temperature distribution of the entire tail tube 4 can be made uniform to generate local thermal stress. Can be suppressed.
[0056]
In the first to fifth embodiments of the present invention described above, the opening shape of the recess 10 is circular. However, the shape is not limited to this, and may be, for example, an elliptical shape. Further, the cross-sectional shape of the recess 10 is an arc shape (semicircular shape) as shown in FIG. 6, but is not limited to this. For example, as shown in FIG. 13, a reamer 12 'having a substantially conical tip is used. You may provide the hollow 10 'dented in the substantially cone shape. Further, for example, as shown in FIG. 14, a reamer 12 ″ may be used to provide a recess 10 ″ having a substantially trapezoidal cross section.
[0057]
Moreover, in the said 4th and 5th embodiment of this invention, although it changed about the installation space | interval and diameter of the hollow 10, for example, as the depth of the hollow 10 goes to the turbine 150 side from the liner 2 side, it changes. A deeper structure may be used. That is, by deepening the recess 10, the surface area can be increased, the heat transfer area can be increased, and the effect of promoting turbulence can be strengthened. By deepening, the cooling performance on the turbine side of the transition piece 4 can be partially improved, and the occurrence of local thermal stress can be suppressed.
[0058]
【The invention's effect】
According to the present invention, by providing a plurality of depressions on the outer surface of the transition piece, it is possible to have a cooling performance equal to or higher than that in the case of providing a rib on the outer surface of the transition piece and performing turbulent flow enhanced cooling. . In addition, the amount of shaving during production can be significantly reduced compared to the case of providing ribs, and the outer surface of the tail tube is scraped along a complicated three-dimensional curved surface as in the case of providing ribs. Therefore, the machining work can be facilitated. Thereby, the production period of the transition piece can be shortened, and as a result, the production cost can be reduced. Therefore, according to the present invention, it is possible to improve manufacturability while maintaining the cooling performance.
[Brief description of the drawings]
FIG. 1 is a schematic configuration diagram schematically showing an overall configuration of a gas turbine including a first embodiment of a gas turbine combustor according to the present invention.
FIG. 2 is a side sectional view showing a detailed structure in the vicinity of a transition piece constituting the first embodiment of the gas turbine combustor of the present invention.
FIG. 3 is a cross-sectional view taken along the line III-III in FIG. 2, showing a detailed structure in the vicinity of the transition piece constituting the first embodiment of the gas turbine combustor of the present invention.
FIG. 4 is a side sectional view showing the structure of a comparative example used for explaining the ease of manufacture of the first embodiment of the gas turbine combustor of the present invention.
FIG. 5 is a perspective view showing the overall structure of a base material flat plate used for manufacturing a comparative example used for explaining the ease of manufacturing of the first embodiment of the gas turbine combustor of the present invention.
FIG. 6 is a view showing a method of processing a recess in a base material flat plate of a tail tube constituting the first embodiment of the gas turbine combustor of the present invention.
FIG. 7 is a perspective view showing the overall structure of the base plate of the tail cylinder constituting the first embodiment of the gas turbine combustor of the present invention.
FIG. 8 is a side sectional view showing a detailed structure in the vicinity of a transition piece constituting a second embodiment of a gas turbine combustor according to the present invention.
FIG. 9 is a cross-sectional view taken along the line IX-IX in FIG. 8 showing a detailed structure in the vicinity of the transition piece constituting the second embodiment of the gas turbine combustor of the present invention.
FIG. 10 is a side sectional view showing a detailed structure of a turbine side end portion of a transition piece constituting a third embodiment of a gas turbine combustor of the present invention.
FIG. 11 is a side view showing a detailed structure in the vicinity of a transition piece constituting a fourth embodiment of a gas turbine combustor of the present invention.
FIG. 12 is a side view showing a detailed structure in the vicinity of a transition piece constituting a fifth embodiment of a gas turbine combustor of the present invention.
FIG. 13 is a view showing a modification of the shape of the recess provided in the base plate of the tail cylinder constituting the gas turbine combustor according to the embodiment of the present invention.
FIG. 14 is a view showing a modified example of the shape of the recess provided in the base plate of the tail tube constituting the embodiment of the gas turbine combustor of the present invention.
[Explanation of symbols]
2 liner
4 tail pipe
4a outer surface
5 Tail tube flow sleeve (flow sleeve)
10 depression
15 Impinge cover
16 Cooling air hole
20 Air introduction hole
110 Compressor
140 Combustor (gas turbine combustor)
150 turbine

Claims (8)

In a gas turbine combustor that mixes and burns high-pressure air compressed by a compressor and fuel, and supplies the generated combustion gas to a turbine.
A cylindrical liner for generating the combustion gas therein;
A plurality of depressions on the outer surface, and a transition piece that guides the combustion gas generated by the liner to the turbine;
A gas turbine combustor comprising: a flow sleeve provided so as to wrap at least a part of an outer surface of the tail tube. In a gas turbine combustor that mixes and burns high-pressure air compressed by a compressor and fuel, and supplies the generated combustion gas to a turbine.
A cylindrical liner for generating the combustion gas therein;
A plurality of depressions on the outer surface, and a transition piece that guides the combustion gas generated by the liner to the turbine;
A gas turbine combustor comprising: an impingement cover provided with a plurality of cooling air holes, and provided so as to wrap at least a part of an outer surface of the transition piece. 3. The gas turbine combustor according to claim 1, wherein a plurality of air introduction holes that communicate the inside and outside of the tail cylinder are provided in a portion of the tail cylinder that is not covered with the flow sleeve or the impingement cover. Gas turbine combustor. The gas turbine combustor according to any one of claims 1 to 3, wherein at least one of an opening area, a depth, and an installation interval of the recess is changed according to a portion of the tail tube. Gas turbine combustor. 5. The gas turbine combustor according to claim 4, wherein an interval between the depressions provided on an outer surface of the transition piece is narrowed from the liner side toward the turbine side. 6. 6. The gas turbine combustor according to claim 4, wherein an opening area of the recess provided on an outer surface of the tail tube is reduced from the liner side toward the turbine side. . The gas turbine combustor according to any one of claims 1 to 6, wherein an opening shape of the recess is circular. The gas turbine combustor according to any one of claims 1 to 7, wherein an opening shape of the recess is an ellipse.

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