KR20100055012A - Cooling device for gas turbine combustor protect and method of embody same - Google Patents

Abstract

PURPOSE: A cooling device for protecting a gas turbine combustor and a transfer pipe and a method of embodying the same are provided to reduce damage to the joint between a combustor liner and an guide pipe by relieving the radial expansion pressure. CONSTITUTION: A cooling device for protecting a gas turbine combustor comprises a combustor liner(100), an guide pipe(200) and a cooling member(300). The guide pipe conducts high-temperature combustion gas provided from the combustor liner to a turbine space. The cooling member is interposed between the outer end of the combustor liner and the inner end of the guide pipe to form a plurality of unit paths. The combustor liner and the guide pipe have a double pipe structure in which outer tubes(120,220) cover inner tubes(110,210). In the double pipe structure, air inlet holes(122,222) are formed between the inner and outer tubes.

Description

Cooling device for gas turbine combustor protect and method of embody same}

The present invention relates to a cooling apparatus and an implementation method for protecting a gas turbine combustion chamber, and more particularly, to introducing a high temperature combustion gas generated from a gas turbine combustion chamber into a turbine device, and to a combustion gas flow path connecting the turbine space and the combustion chamber. The present invention relates to a cooling device and a method for implementing the cooling device for protecting a gas turbine combustion chamber which is applied for the cooling implementation.

In general, the combustion chamber installed in the gas turbine burns the high pressure air supplied from the compressor to generate a high temperature and high pressure combustion gas and supplies it to the turbine. Therefore, the combustion chamber installed in the gas turbine receives a very large heat load. Various cooling methods and various inner wall structures of the combustion chamber have been developed to protect the combustion chamber from heat load.

Typical cooling methods for cooling the combustion chamber include a collision jet cooling method and a membrane cooling method. The impingement jet cooling method is a method of reducing the temperature of the contact surface in contact with the combustion gas by injecting a jet (classification) of a cooling fluid into the contact surface in contact with the hot combustion gas. In the membrane cooling method, a slot or a plurality of holes are formed in a contact surface where hot combustion gas is contacted to provide cooling air to a desired cooling part through the hole, thereby providing a kind of cooling air between the contact surfaces which are in contact with the hot combustion gas. It is a method of protecting the contact surface by forming the used heat insulating film.

1 is a view schematically showing a conventional turbine combustion chamber structure. As shown in FIG. 1, a conventional turbine combustion chamber is configured to deliver a combustion chamber liner (hereinafter, referred to as “CL”) and a high temperature combustion gas from the combustion chamber liner 1 substantially to form a combustion chamber wall. It is composed of an introduction tube (Transition Piece; 2, hereinafter referred to as 'TP'), the CL (1) and TP (2), respectively, the outer tube 12, 22 outside the inner tube (10, 20) It has a double tube structure wrapped around it.

A plurality of air inlets 14 and 24 are formed in the outer tubes 12 and 22 so that external cooling air can be introduced therein. Therefore, cooling air is continuously supplied from the outside to the flow paths 16 and 26 formed between the outer tubes 12 and 22 and the inner tube 10 and 20, and introduced into the flow paths 16 and 26. The cooled air is moved along the flow path while maintaining a regular or irregular pattern of flow while the inner tube 10 and 20 are in direct contact with the combustion gas and the outer tube 12 is not in direct contact with the combustion gas. An air layer is formed between the 22 to protect the CL 1 and the TP 2 from the hot gas.

FIG. 2 is an exploded perspective view of a combustion chamber for illustrating a configuration of a joint portion in which a combustion chamber liner CL and an introduction pipe TP are interconnected in the conventional turbine combustion chamber. In the case of a conventional gas turbine combustion chamber as shown in FIG. 2, a spring seal 3 as shown in FIG. 2 is used to connect the CL 1 and the TP 2. The spring seal 3 has a convex rounded shape as shown in the figure to enable elastic expansion in the radial direction, and thus, when the spring seal 3 is interposed between the CL 1 and the TP 2, It may be in close contact with the inner end of the inlet side.

The joint between CL (1) and TP (2) interconnected via the spring seal 3 is not directly protected by cooling air using the cooling method described with reference to FIG. Separate cooling means are required to protect the joint from combustion gases. Conventionally, a separate cooling channel 4 is formed at the outer end of the CL 1 discharge side to protect the joint from hot combustion gas.

The cooling channel 4 forms a separation partition 4a through mechanical processing, and covers a cooling cover 4b thereon to form a cooling flow path. Conventionally, the joint between the CL (1) and the TP (2) is protected from the hot combustion gas by using a direct cooling method through the cooling passage of the structure.

In the cooling of CL (1) and TP (2) joints through the prior art adopting the above-described cooling method, the cooling cover (4b) is located outside the cooling flow path and relatively high temperature combustion gas and The temperature is low because it is not in direct contact. On the other hand, the discharge end of the CL (1) is substantially exposed to high temperature combustion gas and the temperature is high. In such a relationship, the temperature deviation between the cooling cover 4b and the discharge end of the CL 1 positioned below it is severely generated.

The temperature deviation between the cooling cover 4b and the discharge stage of the CL 1 as described above causes a significant thermal expansion difference therebetween. This, in turn, causes the occurrence of cracks in the cooling cover 4b as shown in the photograph shown in FIG. 3 (areas shown by ellipses), and further causes a huge loss in equipment maintenance. In order to solve this problem, a method of removing the cooling cover may be considered. However, since the cooling system itself is not substantially implemented when the cooling cover is removed, it is urgent to supplement the situation.

The technical problem to be solved by the present invention is to provide a cooling device and a cooling device for the gas turbine combustion chamber protection method that can implement a cooling system for the joint section in which the combustion chamber liner and the transfer pipe are interconnected without a cooling cover. Is in.

Another technical problem to be solved by the present invention is a cooling device and a cooling device for protecting the gas turbine combustion chamber that can express a more effective cooling performance with a simple configuration that does not require a separate mechanical processing (forming a cooling channel) as in the prior art To provide an implementation method.

Another technical problem to be solved by the present invention, even if the temperature of the discharge end of the combustion chamber liner and the introduction end of the transfer pipe to be assembled in a form surrounding the discharge end is different in the expandability of the combustion chamber liner or the transfer pipe in the section in contact with each other It is an object of the present invention to provide a cooling device and a method of implementing the cooling device for protecting a gas turbine combustion chamber, which can significantly reduce the damage rate of the gas turbine.

According to an aspect of the present invention for solving the above technical problem, a hollow combustion chamber liner; A hollow inlet tube connected to the combustion chamber liner and introducing a high temperature combustion gas provided from the combustion chamber liner into the turbine space; And a unit interposed between the outlet side outer end of the combustion chamber liner and the inlet side inner end of the introduction tube connected to the outlet side outer end of the combustion chamber liner, the plurality of units being parallel to the connection direction of the introduction tube to the combustion chamber liner. And a cooling member forming a flow path, wherein the combustion chamber liner and the introduction pipe each have a double tube structure in which an outer tube surrounds an outer tube, and the outer tube is formed from an outer channel formed between the inner tube and the outer tube. It has an air inlet for introducing the cooling air, the cooling air introduced through the air inlet of the introduction tube outer tube of the outer tube forms an air layer for protecting the introduction tube between the introduction tube inner tube and the outer tube and the cooling member By way of cooling, it is possible to realize cooling of the joint portion where the combustion chamber liner and the inlet pipe are interconnected. It provides a cooling apparatus for a gas turbine combustion chamber, characterized in that protection.

According to another aspect of the present invention for solving the above technical problem, a hollow combustion chamber liner; A hollow inlet tube connected to the combustion chamber liner and introducing a high temperature combustion gas provided from the combustion chamber liner into the turbine space; A heat dissipation cover having one end fixed to the outlet side end step surface of the combustion chamber liner by welding, and having one side formed a cooling hole for introducing cooling air into a space spaced from the outlet side outer end; A plurality of spring seals installed on the outer circumference of the heat dissipation cover; And a cooling member interposed between the heat dissipation cover and the outlet side outer end of the combustion chamber liner and forming a plurality of unit flow paths in a direction parallel to the connection direction of the inlet pipe to the combustion chamber liner. And an introduction tube, each having a double tube structure in which an outer tube surrounds an outer tube, and the outer tube has an air inlet for introducing cooling air from the outside in a flow path formed between the inner tube and the outer tube. The cooling air introduced through the air inlet of the introduction tube outer tube forms an air layer for protecting the introduction tube between the tube tube inner tube and the outer tube and passes through the cooling hole and the cooling member formed in the heat dissipation cover. Cooling for the joint portion is connected to the introduction pipe and characterized in that It provides a cooling system for gas turbine combustion chamber protection.

According to a preferred aspect of the present invention, the cooling member is provided with an effective cooling function, even though mutual thermal expansion difference occurs due to a temperature difference between the outlet side of the combustion chamber liner and the inlet side of the inlet pipe, the cooling intervening therebetween. In order to compensate for the difference in thermal expansion while the member contracts in a radial direction within a predetermined range, it is preferable that a plurality of unit flow paths having polygonal partitions are formed in a honeycomb type in which a flow path in a honeycomb form is crowded with each other. Polygonal sections are suitable for sections with hexagonal cross sections.

Preferably, the turbulence forming means is installed in the unit flow passage adjacent to the hot end portion of the plurality of unit flow passages formed in the cooling member to increase air flowability so that the cooling effect can be maintained for a longer time.

At this time, as the turbulence forming means, a straight or curved uneven surface continuously formed in the longitudinal direction of the unit flow passage on the inner wall surface of the unit flow passage, a groove surface formed in a regular pattern from the inner wall surface of the unit flow passage, the inner wall surface of the unit flow passage It can be any one selected from the configuration in which the ridges raised in a regular pattern from, the configuration in which the wing of the plate is vertically or inclined in an alternating pattern on the inner wall surface of the unit flow path.

As the material of the cooling member applied to the present invention, any material satisfying the mechanical properties required in a high temperature environment is applicable. Preferably, nickel (Ni) and chromium (Cr) having excellent corrosion resistance and heat resistance are mainly composed of carbon. Metal alloys based on nickel-chromium alloy steel to which (C), silicon (Si), manganese (Mn), phosphorus (P), and sulfur (S) are added in small amounts are preferable.

According to an aspect of the present invention, there is provided a cooling apparatus including: cutting a cooling member into a length corresponding to a circumferential length of an outlet side outer end of a combustion chamber liner; Wrap the outer end of the combustion chamber liner in the circumferential direction as the cut cooling member; Welding both ends of the cooling member and the cooling member surrounding the outer end of the combustion chamber liner outlet side in the circumferential direction so that the cooling member is fixed to the outlet side in an annular ring shape; Provides a method for implementing a cooling apparatus for protecting a gas turbine combustion chamber, characterized in that by connecting the inlet side of the inlet pipe for introducing a high temperature combustion gas into the turbine space on the outlet side of the combustion chamber liner with the cooling member therebetween. do.

In addition, the present invention for implementing a cooling device according to another aspect of the above cooling device, the cooling member is cut to a length corresponding to the circumferential length of the outer end of the outlet side of the combustion chamber liner; Wrap the outer end of the combustion chamber liner in the circumferential direction as the cut cooling member; Welding both ends of the cooling member and the cooling member surrounding the outer end of the combustion chamber liner outlet side in the circumferential direction so that the cooling member is fixed to the outlet side in an annular ring shape; Fixing one side of the heat dissipation cover to the step surface formed at the outlet side outer end of the combustion chamber liner by welding so that the cooling member is located between the heat dissipation cover and the outlet side outer end of the combustion chamber liner; Welding and fixing the spring seal along the outer circumference of the heat dissipation cover; It provides a cooling device for the gas turbine combustion chamber protection method characterized in that is implemented by connecting the inlet side of the inlet pipe for the introduction of high temperature combustion gas into the turbine space to the outlet side of the combustion chamber liner with the spring seal in between. do.

According to the above-described apparatus for cooling a combustion gas discharge pipe joint of a gas turbine combustion chamber according to the present invention, a plurality of unit flow paths are crowded with each other to form a honeycomb-type cooling member to discharge a high temperature part. Combine the stage with the low temperature introduction stage. When the honeycomb type is formed, the cooling member has a plurality of flow paths for introducing cooling air in a horizontal direction while having elasticity in the vertical direction.

Accordingly, it is possible to implement a device having a more effective cooling function without a separate mechanical processing (forming a cooling channel) to implement a cooling system, and the difference in thermal expansion between the outlet end of the combustion chamber liner and the inlet end of the inlet pipe Even if occurs, the cooling member intervened therebetween is absorbed / alleviated that the expansion force is transmitted to the low temperature introduction portion while the radial contraction within a predetermined range. Due to the difference in thermal expansion rate, breakage that may occur in the joint portion between the combustion chamber liner and the introduction pipe can be significantly reduced.

In addition, in the case of the honeycomb type, the flow developed in the flow path therein has a high momentum, and thus the cooling effect is enhanced by the continuous cooling for a longer time in more areas than the area protected by the conventional cooling method. In addition, the effect of improving the efficiency of the slot membrane cooling is also expected to extend the life of the device.

In addition, the cooling device proposed in the present invention, while expressing an effective cooling function, the configuration is simple, more than the gas turbine illustrated in the present invention, as well as throughout the industrial field that requires a slot membrane cooling system, such as rockets and ramjets. The advantage is that it can be widely applied.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings.

In the following description of the present invention, if it is determined that a detailed description of a related known function or configuration may unnecessarily obscure the subject matter of the present invention, the detailed description thereof will be omitted. In addition, terms to be described below are terms defined in consideration of functions within the present invention, and may be changed according to a user's or operator's intention or custom. Therefore, the definition should be made based on the contents throughout the specification.

The present invention provides a high temperature combustion gas generated from a gas turbine combustion chamber to a turbine apparatus, and is a cooling apparatus for protecting a gas turbine combustion chamber which is applied for cooling the combustion gas flow path connecting the turbine space and the combustion chamber. Embodiments of the present invention will be described in detail through examples.

First embodiment

4 is an exploded perspective view schematically illustrating a configuration of a cooling apparatus for protecting a gas turbine combustion chamber according to a first embodiment of the present invention, FIG. 5 is a cross-sectional view of the cooling apparatus of FIG. 4 is a longitudinal cross-sectional view of a joint portion in which a combustion chamber liner and an introduction tube are coupled to each other according to the cooling device coupling of FIG. 4.

4 to 6, the cooling apparatus according to the first embodiment of the present invention is connected to the combustion chamber liner (100) and the combustion chamber liner (100) substantially forming the wall of the turbine combustion chamber; And a hollow transition tube 200 for introducing a high temperature combustion gas provided from the combustion chamber liner 100 into the turbine space, and the outer end and the introduction tube of the hollow combustion chamber liner 100 connected to each other ( The cooling member 300 is interposed between the inlet side inner end of the 200. Hereinafter, for convenience of description, the combustion chamber liner 100 and the introduction tube 200 will be referred to as "CL" and "TP", respectively.

The CL 100 and the TP 200 have a double tube structure in which outer tubes 120 and 220 surround an inner tube 110 and 210, and the outer tubes 120 and 220 are inner tubes. The air inlets 122 and 222 for introducing cooling air from the outside are provided in the flow paths 130 and 230 formed between the 110 and 210. The cooling air introduced through the air inlet 222 of the outer tube 220 constituting the TP 200 among the outer tubes constituting the CL 100 and the TP 200 is an inner tube of the TP 200. Flowing through the flow path 230 between the 210 and the outer tube 220 to form an air layer for protecting the TP (200).

Cooling air introduced through the air inlet 222 of the outer tube 220 constituting the TP 200 cools the TP 200 via the flow path 230, and the CL 100 and TP ( 200) When coupled, the inner tube 210 of the TP (200) outer side and the outer end of the TP (200) in the direction is changed while passing through the gap existing in front of the end of the inner tube 210 of the inlet side of the TP (200) Pass through the cooling member 300 interposed between the inner end of the side. Cooling air passing through the cooling member 300 passes through the cooling member to cool the CL 100 and the TP 200 joint, and then flows into the TP 200 to be mixed with the combustion gas.

The cooling member 300 is configured to form a plurality of unit flow paths 320 in a direction parallel to the direction in which the inlet side of the TP 200 is coupled to the outlet side of the CL (100), and directly to the hot gas When the thermal expansion of the exit side of the CL (100) exposed and relatively high temperature has elasticity elastically stretchable against the radial thermal expansion of the exit side of the CL (100) between the inlet side of the TP (200) Suitable. According to a preferred embodiment, as shown in FIG. 4, a plurality of unit flow paths 320 having polygonal partitions may be densely formed to form a honey comb-type in which honeycomb-shaped flow paths are formed.

Although the honeycomb type is slightly different depending on the material, the honeycomb type has a sufficient rigidity in the direction of the flow path formation, while having a flexible elasticity in the direction orthogonal to the flow path formation direction. Accordingly, the inner end of the inlet side of the TP 200 is fitted to the outlet side outer end of the CL 100 so as to be interconnected, and the inlet side of the TP 200 is connected to the outlet side of the CL 100. On the contrary, even if the displacement due to thermal expansion is relatively large, the expansion force due to the thermal expansion of the outlet side of the CL 100 is absorbed / mitigated while being compressed vertically within a predetermined range therebetween. have.

The cooling member 300 may be adopted a variety of different materials depending on the application environment. The cooling member 300 is applicable to any material as long as the material satisfies the required mechanical properties in a high temperature environment. As a non-limiting example of the material, the main components are nickel (Ni) and chromium (Cr), which have excellent corrosion resistance and heat resistance, and include carbon (C), silicon (Si), manganese (Mn), phosphorus (P), and sulfur ( For example, a metal alloy made of nickel-chromium alloy steel added with a small amount of S) or an alloy made of steel, a refractory metal such as titanium (Ti), nickel (Ni), cobalt (Co) or iron-based superalloy mixed in an appropriate ratio. I can lift it.

When the cooling air passes through the plurality of unit flow paths 320 formed in the cooling member 300, when the flow path walls forming the unit flow paths 320 are non-flat, the cooling air is non-linear turbulence in the flow path as a whole. It has a flow. In the case of the turbulent flow, the cooling air can be improved by the cooling air because the cooling air is dispersed in an irregular pattern in the unit flow channel in comparison with the laminar flow which maintains the linear flow. .

Therefore, in the unit flow passage located in the area adjacent to the outlet side outer end of the CL 100 in direct contact with the hot combustion gas of each unit flow channel 320, which requires more effective cooling, means for forming turbulence as described above are provided. By providing, it is preferable to make cooling to the exit side of CL 100 more efficient. The turbulence forming means 340 for forming the turbulence is not limited to a specific shape and pattern as long as it can guide the cooling air introduced into the unit flow passage to have a non-linear flow.

By way of example, the turbulence forming means 340 is a straight or curved uneven surface continuously formed in the longitudinal direction of the unit flow path on the inner wall surface of the unit flow path as shown in FIG. A recessed surface formed in a regular pattern from the inner wall surface of the unit flow passage as shown in FIG. 7 (c) or a ridge raised in a regular pattern from the inner wall surface of the unit flow passage as shown in FIG. 7 (c), or as shown in FIG. For example, a configuration in which the wings of the plate extend vertically or inclined in an alternating pattern on the inner wall surface.

8 is a view showing a process of implementing the cooling apparatus according to the first embodiment of the present invention described above. In implementing the cooling apparatus according to the first embodiment of the present invention, first, the cooling member 300 is cut to a length corresponding to the circumferential length of the outer end of the outlet side of the CL (100), and then as the cut cooling member The outer end of the exit side of the CL 100 is wrapped in the circumferential direction.

Then, both ends of the cooling member 300 surrounding the outer end of the CL 100 in the circumferential direction, and the peripheral edge of the cooling member 300 and the outer end of the CL 100 100 are welded to each other to allow the cooling member to exit the outlet. After being fixed in the form of an annular ring on the outer side, in this state of the TP (200) for introducing a high temperature combustion gas into the turbine space on the outlet side of the CL (100) with the cooling member 300 in between When assembled in the form of fitting the inlet side, the implementation of the above-mentioned cooling device is simply completed.

According to the first embodiment of the present invention, a plurality of unit flow paths 320 are densely packed with each other to form a honeycomb-type cooling member 300 having a honeycomb-shaped flow path between the CL (100) The inlet of the TP (200) is connected to the outlet side of the) to form a cooling device. When the cooling member 300 is implemented as a honeycomb type, the cooling member has a flexible elasticity in the vertical direction while forming a plurality of flow paths for introducing the cooling air in the horizontal direction.

Accordingly, to implement a cooling system, a device having a more effective cooling function can be realized without separate mechanical processing (forming of a cooling channel) and components (spring seals and cooling covers) as in the prior art, and the outlet side of the CL 100 and Even if a difference in thermal expansion rate occurs due to a temperature deviation between the inlets of the TP 200, the cooling member 300 intervened therebetween is contracted in a radial direction within a predetermined range and transferred to the inlet end of the TP 200. Since the radial expansion force is absorbed / relaxed, it is possible to significantly reduce the damage that may occur in the joint portion of the CL (100) and TP (200).

In the case of the honeycomb type, the flow developed in the flow path therein has a high momentum. Therefore, there is an advantage in that the cooling effect can be improved by continuous cooling for a longer time over more areas than the area protected by the conventional cooling method, and consequently increases the efficiency of the slot membrane cooling to improve the device life. Extendable effects are also expected.

Second embodiment

9 is a schematic cross-sectional view showing the configuration of a cooling apparatus for protecting a gas turbine combustion chamber according to a second embodiment of the present invention. In describing the present embodiment, the same reference numerals and names will be used for the same components as those of the above-described first embodiment, and detailed description thereof will be omitted.

Referring to FIG. 9, the cooling apparatus according to the second embodiment includes a cooling member 300 and a cooling member 300 interposed between the CL 100 and the TP 200, which are connected to each other, and these joints. While covering, the CL 100 includes a heat dissipation cover 400 for fixing the cooling member 300 to an outer side of the outlet side and a plurality of spring seals 500 fixed by welding to the outer circumference of the heat dissipation cover 400.

In the second embodiment, the CL 100 and the TP 200 are the same as the CL and the TP of the first embodiment. Accordingly, the CL (100) and the TP (200) has a double tube structure in which the outer tube (120, 220) is wrapped around the inner tube (110, 210), the outer tube (120, 220) Has an air inlet 122 and 222 for introducing cooling air from the outside in the flow paths 130 and 230 formed between the inner tubes 120 and 220.

In the second embodiment, the heat dissipation cover 400 is installed in a form in which one end is fixed by welding on the outer end step surface of the CL 100. The heat dissipation cover 400 has a cooling hole 410 for introducing cooling air to one side of the cooling member 300 through a space spaced from the outer end of the CL 100 at one side thereof. Therefore, the cooling air introduced through the air inlet 222 of the outer tube 220 on the TP 200 side passes through the flow path 230 between the inner tube 210 and the outer tube 220 of the TP 200. Forming an air layer for protecting the TP (200) and at the same time, the CL (100) and the TP 200 is connected to each other via the cooling hole 410 and the cooling member 300 formed in the heat dissipation cover 400 Cool the part.

The cooling member 30 in the second embodiment is the same as the cooling member in the first embodiment. Accordingly, the honeycomb has a honeycomb-shaped flow path in which a plurality of unit flow paths 320 having polygonal partitions are concentrated in a direction parallel to a direction in which the inlet side of the TP 200 is coupled to the exit side of the CL 100. Comb type (Honey comb-Type).

In the case of the honeycomb type, as mentioned above, it has a characteristic of having sufficient rigidity in the direction of the flow path formation while having elasticity in the direction perpendicular to the flow path formation direction. Therefore, even if the displacement due to thermal expansion is relatively larger on the outlet side of the CL 100 than the heat dissipation cover, since the compression is within a predetermined range therebetween, the expansion force due to the outlet thermal expansion of the CL 100 is increased. Absorption / relaxation of the transmission to the heat dissipation cover 400 may be prevented.

10 is a view showing a process for implementing a cooling device according to a second embodiment of the present invention described above.

Referring to FIG. 10, in implementing the cooling apparatus according to the second embodiment of the present invention, first, the cooling member 300 is cut to a length corresponding to the circumferential length of the outer end of the outlet side of the CL 100. The cut cooling member 300 is installed to surround the outer end of the outlet side of the CL 100 in the circumferential direction.

Then, both ends of the cooling part ash 300 surrounding the outer end of the CL 100 outlet side and the cooling member 300 and the outer circumference of the outer end end of the CL 100 are welded to each other. The other end of the heat dissipation cover 400 and the CL (by fixing one side of the heat dissipation cover to the stepped surface formed on the outer end of the CL (100) by welding by fixing to the outer end of the exit side). The cooling member 300 is located between the outlet side outer ends of the 100.

Next, the spring seal 500 is welded and fixed along the outer circumference of the heat dissipation cover 400, and high temperature combustion gas is introduced into the turbine space at the outlet side of the CL 100 with the spring seal 500 interposed therebetween. When assembled in the form of fitting the inlet side of the TP 200 for, the implementation of the cooling device is simply completed.

According to the second embodiment of the present invention described above, unlike the first embodiment, the heat dissipation cover 400 is further provided between the cooling member 300 and the inner end of the inlet side of the TP 200. Compared to the CL 100 and the TP 200, the cooling performance can be further improved. Accordingly, a high performance cooling device may be implemented to protect the joints of the CL 100 and the TP 200 from high temperature combustion gas.

In the above described and described with respect to a specific embodiment with respect to the present invention, the present invention will be variously modified and changed without departing from the spirit or scope of the present invention provided by the claims below. It will be appreciated that one of ordinary skill in the art can readily understand that the present invention can be used.

1 is a view schematically showing a conventional turbine combustion chamber structure.

FIG. 2 is an exploded perspective view of a combustion chamber for showing a configuration of a joint portion in which a combustion chamber liner and an introduction tube are interconnected in a conventional turbine combustion chamber according to FIG. 1.

Figure 3 is a photograph for showing a crack generated in the exit end of the combustion chamber liner to which the introduction pipe is connected in the conventional turbine combustion chamber.

Figure 4 is an exploded perspective view schematically showing the configuration of a cooling device for protecting the gas turbine combustion chamber according to the first embodiment of the present invention.

Figure 5 is a cross-sectional view of the combination of the cooling device of FIG.

6 is a longitudinal cross-sectional view of a joint portion in which a combustion chamber liner and an introduction tube are coupled to each other according to the cooling device coupling of FIG. 4.

Figure 7 is a view for showing various embodiments of the flow path formed in the cooling member applied to the present invention.

8 is a view showing a process for implementing a cooling device according to a first embodiment of the present invention.

9 is a schematic cross-sectional view schematically showing the configuration of a cooling apparatus according to a second embodiment of the present invention.

10 is a view showing a process for implementing a cooling device according to a second embodiment of the present invention.

<Description of the symbols for the main parts of the drawings>

100.Combustion chamber liner

200 ... Introduction

300 ... cooling member

320 ... Euros

340.Measuring turbulence

400 ... heat cover

Claims (12)

Hollow combustion chamber liners; A hollow inlet tube connected to the combustion chamber liner and introducing a high temperature combustion gas provided from the combustion chamber liner into the turbine space; And A plurality of unit flow paths are interposed between the outlet side outer end of the combustion chamber liner and the inlet side inner end of the inlet tube connected to the outlet side outer end of the combustion chamber liner, and parallel to the connection direction of the inlet tube to the combustion chamber liner. It comprises a cooling member; The combustion chamber liner and the introduction tube, respectively, It has a double tube structure that wraps the outer tube outside the inner tube, The outer tube has an air inlet for introducing cooling air from the outside in the flow path formed between the inner tube, The cooling air introduced through the air inlet of the introduction tube outer tube of the outer tube forms an air layer for protecting the introduction tube between the introduction tube inner tube and the outer tube and passes through the cooling member, Cooling apparatus for protecting the gas turbine combustion chamber, characterized in that for cooling the interconnected joints. Hollow combustion chamber liners; A hollow inlet tube connected to the combustion chamber liner and introducing a high temperature combustion gas provided from the combustion chamber liner into the turbine space; A heat dissipation cover having one end fixed to the outlet side end step surface of the combustion chamber liner by welding, and having a cooling hole at one side to introduce cooling air into a space spaced from the outlet side outer end; A plurality of spring seals installed on the outer circumference of the heat dissipation cover; And a cooling member interposed between the heat dissipation cover and the outlet side outer end of the combustion chamber liner and forming a plurality of unit flow paths in a direction parallel to the connection direction of the inlet pipe to the combustion chamber liner. The combustion chamber liner and the introduction tube, respectively, It has a double tube structure that wraps the outer tube outside the inner tube, The outer tube has an air inlet for introducing cooling air from the outside in the flow path formed between the inner tube, The cooling air introduced through the air inlet of the introduction tube outer tube of the outer tube forms an air layer for protecting the introduction tube between the introduction tube inner tube and the outer tube and passes through the cooling hole and the cooling member formed in the heat dissipation cover. Cooling apparatus for protecting the gas turbine combustion chamber, characterized in that for implementing the cooling for the joint portion in which the combustion chamber liner and the introduction pipe are interconnected. The method according to claim 1 or 2, The cooling member, Cooling apparatus for protecting a gas turbine combustion chamber, characterized in that the honeycomb type consisting of a plurality of unit flow paths having a polygonal partition are densely formed to form a honeycomb flow path. The method of claim 3, wherein The polygonal compartment, Cooling device for gas turbine combustion chamber protection, characterized in that the section having a hexagonal cross section. The method of claim 3, wherein Cooling apparatus for a gas turbine combustion chamber protection further comprising; turbulent flow forming means formed in the unit flow channel is located in close proximity to the outer end of the combustion chamber liner of the plurality of unit flow paths formed in the cooling member. The method of claim 5, The turbulence forming means, A cooling device for protecting a gas turbine combustion chamber, characterized by a straight or curved uneven surface formed continuously in the longitudinal direction of the unit flow passage on the inner wall surface of the unit flow passage. The method of claim 5, The turbulence forming means, Cooling device for protecting the gas turbine combustion chamber, characterized in that the groove surface formed recessed in a regular pattern from the inner wall surface of the unit flow path. The method of claim 5, The turbulence forming means, Cooling device for gas turbine combustion chamber protection, characterized in that the ridge raised in a regular pattern from the unit wall inner wall surface. The method of claim 5, The turbulence forming means, Cooling apparatus for protecting the gas turbine combustion chamber, characterized in that the configuration in which the wings in the form of a plate alternately extends vertically or inclined in the pattern of the inner channel surface. The method according to claim 1 or 3, The cooling member, Metal-based material based on nickel-chromium alloy steel containing nickel (Ni) and chromium (Cr) as main components, and a small amount of carbon (C), silicon (Si), manganese (Mn), phosphorus (P), and sulfur (S) Cooling apparatus for protecting the gas turbine combustion chamber, characterized in that the alloy. Cutting the cooling member into a length corresponding to the circumferential length of the outlet side outer end of the combustion chamber liner; Wrap the outer end of the combustion chamber liner in the circumferential direction as the cut cooling member; Welding both ends of the cooling member and the cooling member and the outer circumference of the outer end of the combustion chamber liner outlet side in the circumferential direction so that the cooling member is fixed to the outlet side in an annular ring shape; Implementing a cooling apparatus for protecting the gas turbine combustion chamber, characterized in that by connecting the inlet side of the inlet pipe for introducing a high temperature combustion gas into the turbine space on the outlet side of the combustion chamber liner with the cooling member between. Cutting the cooling member into a length corresponding to the circumferential length of the outlet side outer end of the combustion chamber liner; Wrap the outer end of the combustion chamber liner in the circumferential direction as the cut cooling member; Welding both ends of the cooling member and the cooling member and the outer circumference of the outer end of the combustion chamber liner outlet side in the circumferential direction so that the cooling member is fixed to the outlet side in an annular ring shape; Fixing one side of the heat dissipation cover to the step surface formed at the outlet side outer end of the combustion chamber liner by welding so that the cooling member is located between the heat dissipation cover and the outlet side outer end of the combustion chamber liner; Welding and fixing the spring seal along the outer circumference of the heat dissipation cover; And a spring seal between the inlet side of the introduction pipe for introducing high temperature combustion gas into the turbine space at the outlet side of the combustion chamber liner.

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