Patent Description:
Generally, a gas turbine is a power engine which combusts fuel and compressed air generated from a compressor, generates high-temperature gas, and rotates a turbine using the high-temperature gas. Such gas turbines are used for combined cycle power generation, thermal cogeneration, etc..

A gas turbine is roughly divided into a compressor, a combustor, and a turbine. The compressor functions to draw air and compress the air to a high pressure using some of the power generated by the rotation of the turbine. Compressed air is transmitted to the combustor.

The combustor mixes the compressed air with fuel, generates a flow of high-temperature combustion gas by burning the mixture, and discharges the combustion gas toward the turbine. The discharged combustion gas rotates the turbine to generate rotating force. A combustor for an industrial gas turbine includes a plurality of fuel nozzle modules arranged in an annular configuration. The mixing of air and fuel is performed in the fuel nozzle modules.

Air compressed by the compressor is drawn into the combustor. Fuel is injected through a vane disposed in each of the fuel nozzle modules and then mixed with air. A mixture of fuel and air is combusted in a plurality of combustion chambers respectively disposed at a downstream side of each of the fuel nozzle modules. Combustion gas is discharged through a passage extending to the turbine.

High-temperature combustion gas is drawn from the combustion chamber into the turbine through a transition piece and thus drives the turbine. During a process in which combustion gas flows toward the turbine, heat is transferred from the combustion gas to the transition piece because of the high temperature of the combustion gas. To prevent damage to the transition piece or a casing that encloses the transition piece the transition piece casing, which may be caused by overheating, the transition piece and its casing must be cooled.

<CIT> presents a support between a transition piece and an impingement sleeve in a combustor. The support includes a resilient portion, the resilient portion configured to provide dampening between the transition piece and the impingement sleeve. The support further includes a mount portion configured for mounting the support to one of the transition piece or the impingement sleeve. The support further includes a contact portion configured for contacting the other of the transition piece or the impingement sleeve.

<CIT> presents aerodynamic devices for enhancing side panel cooling on an impingement cooled transition duct and related method. A transition piece assembly for a gas turbine includes a transition duct having one end adapted for connection to a gas turbine combustor and an opposite end adapted for connection to a first turbine stage, and a pair of side panels. The assembly also includes an impingement sleeve surrounding the transition duct and establishing a cooling path therebetween. The impingement sleeve is formed with a plurality of rows of cooling holes therein; and a plurality of flow catcher devices on an external surface of the impingement sleeve, each flow catcher device at least partially surrounding one of the cooling holes.

<CIT> presents a turbine combustion system cooling scoop. A scoop over a coolant inlet hole in an outer wall of a double-walled tubular structure of a gas turbine engine component is provided. The scoop redirects a coolant flow into the hole. The leading edge of the scoop has a central projection or tongue that overhangs the coolant inlet hole, and a curved undercut on each side of the tongue between the tongue and a generally C-shaped or generally U-shaped attachment base of the scoop. A partial scoop may be cooperatively positioned with the scoop.

An object of the present invention is to provide a transition piece assembly, a transition piece module, and a combustor and a gas turbine including the same, which can increase the amount of compressed air flowing to a transition piece and a transition piece casing.

Other objects and advantages of the present invention can be understood by the following description, and become apparent with reference to the embodiments of the present invention.

Also, it will be clear to those skilled in the art to which the present invention pertains that the objects and advantages of the present invention can be realized by the means as claimed and combinations thereof.

The object is solved by invention set out by the features of the independent claim(s).

Hereinafter, embodiments of the present disclosure will be described with reference to the accompanying drawings. In addition, when an element described herein is referred to as "comprising" or "including" a component, the description does not preclude the inclusion of another component unless the context clearly indicates otherwise.

Referring to <FIG>, the gas turbine <NUM> includes a compressor <NUM>, a combustor <NUM>, and a turbine <NUM>, and is a power engine configured to mix compressed air output from the compressor <NUM> with fuel in the combustor <NUM>, combust the mixture of the air and the fuel, and thus rotate the turbine <NUM>. The transition piece assembly in accordance with the present disclosure is included in the combustor <NUM>.

Referring to <FIG>, the transition piece assembly includes a transition piece <NUM> through which passes high-temperature combustion gas that is ignited and combusted in a combustion chamber <NUM> (<FIG>). The high-temperature combustion gas that has passed through the transition piece <NUM> is drawn into the turbine <NUM>.

To allow the combustion gas to pass through the transition piece <NUM>, the transition piece <NUM> includes an inlet into which the combustion gas is drawn, and an outlet from which the combustion gas is discharged toward a turbine inlet port. A passage, along which the combustion gas can flow, is formed between the inlet and the outlet. As illustrated in <FIG>, the inlet of the transition piece <NUM> is larger than its outlet, but the relative sizes of the inlet and the outlet are not particularly limited.

In addition, as illustrated in <FIG>, the transition piece <NUM> includes a portion formed toward the inlet to be coupled with a cylindrical liner <NUM> (<FIG>) and a portion formed toward the outlet to be coupled to a turbine inlet port <NUM> (<FIG>). The inlet-side portion of the transition piece <NUM> may have a circular shape, and the outlet-side portion may have a quadrangular shape approximating a rectangle with rounded corners, but these shapes are not particularly limited. The quadrangular shape corresponds to the shape of the turbine inlet port <NUM>, wherein the longer sides of the approximate rectangle formed by the outlet side portion of the transition piece <NUM> extend in the circumferential direction of the gas turbine <NUM>, and the longer sides extend in the radial direction of the gas turbine <NUM>.

As shown in the sectional view of <FIG>, the transition piece <NUM> includes a lower portion and an upper portion, each of which extends from the inlet to the outlet of the transition piece <NUM>. The transition piece <NUM> is configured such that the lower (radially inward) portion is curved to enable the transition piece <NUM> to be coupled with the turbine inlet port <NUM>, and the upper (radially outward) portion is also curved to enable the coupling. Here, since a difference in height between the upper portion of the transition piece <NUM> and the turbine inlet port <NUM> is greater than that of the lower portion of the transition piece <NUM>, the degree to which the upper portion is curved is greater than that of the lower portion. The upper portion of the transition piece <NUM> includes a second curvature occurring toward the turbine inlet port <NUM>. In the embodiment of the present disclosure, the curvatures of the transition piece <NUM> enable a precise coupling with the turbine inlet port <NUM> to prevent the combustion gas from leaking out.

Referring again to <FIG>, a transition piece casing <NUM> is spaced apart from the transition piece <NUM> and encloses the transition piece <NUM>. The transition piece casing <NUM> is configured to enable compressed air to effectively flow over the entire area of an outer circumferential surface of the transition piece <NUM>. The transition piece casing <NUM> forms a cylindrical hollow space so that the transition piece <NUM> can be inserted into the transition piece casing <NUM>. Thus, the transition piece casing <NUM> may have a shape corresponding, or similar, to that of the transition piece <NUM> so that the distance between the inner circumferential surface of the transition piece casing <NUM> and the outer circumferential surface of the transition piece <NUM> can remain constant over the entirety of the outer circumferential surface of the transition piece <NUM>. However, the shape of the transition piece casing <NUM> is not particularly limited.

When the transition piece <NUM> is inserted into the hollow space of the transition piece casing <NUM>, the transition piece <NUM> is spaced apart from an inner circumferential surface of the transition piece casing <NUM> so that an annular interspace is formed between the transition piece casing <NUM> and the transition piece <NUM>. The transition piece casing <NUM> is seated on a support member <NUM> which will be described below.

At least one support member <NUM> is inserted into the annular interspace formed between the inner circumferential surface of the transition piece casing <NUM> and the outer circumferential surface of the transition piece <NUM> so that the transition piece casing <NUM> that encloses the transition piece <NUM> can be spaced apart from and supported on the transition piece <NUM>. The support member <NUM> includes a convexly curved portion protruding in one direction (e.g., outwardly from the transition piece <NUM>) and approximating a U shape. Thus, the support member <NUM> is a member having elasticity.

When the support member <NUM> is inserted into the annular interspace, the support member <NUM> is seated on the outer circumferential surface of the transition piece <NUM>, and the convexly curved portion comes into contact with the inner circumferential surface of the transition piece casing <NUM> so that the support member <NUM> can support the transition piece casing <NUM>. To support the transition piece <NUM>, a plurality of support members <NUM> may be arranged in an annular configuration along the outer circumferential surface of the transition piece <NUM>, as shown in <FIG>, but this configuration is not particularly limited.

The transition piece casing <NUM> may include a plurality of cooling holes through which compressed air can be drawn into the transition piece casing <NUM>. The size and the shape of any of the cooling holes are not limited. The cooling holes are formed in the transition piece casing <NUM> such that compressed air drawn from the compressor <NUM> can flow toward the outer circumferential surface of the transition piece <NUM> so as to cool the transition piece <NUM> heated by high-temperature combustion gas. Compressed air drawn through the cooling holes absorbs heat from the transition piece <NUM> while flowing toward the liner <NUM> through the annular interspace, thus preventing the transition piece <NUM> from being damaged by temperature rise.

Referring to <FIG>, the embodiment of the present disclosure includes a guide member <NUM> which guides compressed air flowing over the outer circumferential surface of the transition piece casing and toward an upper portion of the turbine casing <NUM> (<FIG>) and redirects the flow (i.e., changes the flow direction) of the compressed air toward the transition piece <NUM>. The present embodiment may be comprised of one or more guide members <NUM> each of which is fixed with respect to the transition piece casing <NUM> and includes an axially perpendicular structure for redirecting and guiding the compressed air flowing over the outer circumferential surface of the transition piece casing <NUM>. The axially perpendicular structure, which may include one or more curvatures, extends generally in a direction perpendicular to the axis of the transition piece casing <NUM>. The axially perpendicular structure of the guide member <NUM> extends between opposite end portions 601a and 601b, which are separated from each other in the direction perpendicular to the axis of the transition piece casing <NUM>.

In addition to the axially perpendicular structure, the guide member <NUM> may further include a guide support <NUM> having one end fixed to the transition piece casing <NUM> so that the guide member <NUM> can be fixed in position with respect to the transition piece casing <NUM>. The guide support <NUM> may be fixed to the outer circumferential surface of the transition piece casing <NUM> in a manner that is not limited.

The extending direction and configuration of the guide support <NUM> is not particularly limited. The guide support <NUM> is configured such that the axially perpendicular structure of the guide support <NUM> can be spaced apart from the transition piece casing <NUM>. More particularly, a predetermined distance (space) is established between the axially perpendicular structure, more specifically, a guide surface <NUM> of a single guide <NUM> (described below), and the outer circumferential surface of the transition piece casing <NUM>. The guide support <NUM> extends from the transition piece casing <NUM> by a distance enabling compressed air flowing over an upper side portion of the outer circumferential surface of the transition piece casing <NUM> can be effectively collected and guided by the guide surface of the axially perpendicular structure toward the transition piece casing <NUM>. The distance from the transition piece casing <NUM> further enables compressed air flowing upward from the upper side portion of the outer circumferential surface of the transition piece casing <NUM> toward the turbine casing <NUM> can be similarly collected and guided.

The single guide <NUM> may be fixed to one end of the guide support <NUM>. The fixing method may include welding, bolt coupling, or the like, but is not particularly limited. The single guide <NUM> may have opposite end portions 601a and 601b oriented downward (radially inward) for collection of compressed air, as illustrated in <FIG>, so that the single guide <NUM> can effectively collect compressed air that flows along opposite side portions of the outer circumferential surface of the transition piece casing <NUM> toward the upper portion of the turbine casing <NUM> and change the flow direction of the compressed air toward the transition piece <NUM>.

With regard to a method of orienting the opposite end portions 601a and 601b of the single guide <NUM> downward, the opposite end portions 601a and 601b may be oriented downward by curving or bending a portion of the single guide <NUM>. The method of forming the downwardly oriented end portions 601a and 601b of the single guide <NUM> is not particularly limited, provided that the opposite end portions 601a and 601b are oriented so as to guide compressed air colliding with the single guide <NUM> into the transition piece casing <NUM> without flowing out of the single guide <NUM>. Since the opposite end portions 601a and 601b are formed in an inwardly curved manner or the like, the compressed air that collides with the guide member <NUM> is collected to be guided into the transition piece casing <NUM>.

In the embodiment of the present disclosure, an inner guide <NUM> may be provided on one surface of the single guide <NUM> so that the single guide <NUM> can more smoothly guide the flow of compressed air toward the transition piece casing <NUM>. The shape of the inner guide <NUM> is not decided to a particular shape. <FIG> illustrates an example in which the inner guide <NUM> has a thin plate shape curved in one direction.

One end of the inner guide <NUM> is oriented toward the transition piece casing <NUM> so that compressed air, which moves upward along the opposite side portions of the outer circumferential surface of the transition piece casing <NUM> and is collected toward a predetermined portion of the single guide <NUM> along the opposite ends of the single guide <NUM>, can flow toward the transition piece casing <NUM>. The one end of the inner guide <NUM> may be bent or curved toward the transition piece casing <NUM>, and the method of orienting the one end of the inner guide <NUM> is not particularly limited.

To allow compressed air to more intensively flow toward the transition piece casing <NUM> through the inner guide <NUM>, at least one pair of inner guides <NUM> are fixed to one surface of the single guide <NUM> that faces the transition piece casing <NUM>. The fixing method may be a welding method, a bolt coupling method, or a sliding coupling method, and the fixing method is not particularly limited.

In the case where the one pair of inner guides <NUM> are fixed on one surface of the single guide <NUM>, the one pair of inner guides <NUM> may be installed taking into account the fact that compressed air is drawn from the opposite ends of the single guide <NUM> toward the inner guides <NUM>. To allow the thus drawn compressed air to efficiently flow toward the transition piece casing <NUM>, the one pair of inner guides <NUM> may be installed on the single guide <NUM> such that, as illustrated in <FIG>, the inner guides <NUM> are symmetrical with each other based on an imaginary plane drawn between the inner guides <NUM>.

In the transition piece assembly in accordance with the embodiment of the present disclosure, the distance between the opposite end portions 601a and 601b of the perpendicular structure is greater than the distance between the opposite side portions of the transition piece casing <NUM>. Hence, the amount of compressed air that can be collected may be increased. In detail, in the case where the transition piece casing <NUM> is cylindrical, the distance between the opposite side portions of the transition piece casing <NUM> refers to a distance on the outer circumferential surface of the transition piece casing <NUM>, in other words, an outer diameter or width of the transition piece casing <NUM>. To guide compressed air collected by the axially perpendicular structure <NUM> and guided toward the transition piece casing <NUM>, the opposite end portions 601a and 601b may be formed by creating a curve or bend in the guide surface <NUM> in a radially inward direction, that is, toward the outer circumferential surface of the transition piece casing <NUM>.

In this embodiment, the axially perpendicular structure of the guide member <NUM> is formed by the single guide <NUM>. To increase the amount of collected compressed air, the single guide <NUM> may include a central protrusion <NUM> which extends in the axial direction, i.e., downstream, to have a partially protruding shape, as illustrated in <FIG>. Thus, the central protrusion <NUM> extends from a downstream edge of the axially perpendicular structure (<NUM>). The shape of the central protrusion <NUM> is not particularly limited but may be formed in an approximately triangular shape (<FIG>) or an approximately trapezoidal shape (<FIG>) to increase an amount of compressed air that collides with the single guide <NUM> to be guided into the transition piece casing <NUM>.

In a modification of the embodiment of the present disclosure, the transition piece assembly may include dual guides <NUM>. That is, the axially perpendicular structure of the guide member <NUM> may be formed by the dual guides <NUM> each of which is fixed to one end of the guide support <NUM>. The opposite end portions of each of the dual guides <NUM> may be bent or curved toward the transition piece casing <NUM> in a manner the same as or similar to that described above with respect to the axially perpendicular structure (<NUM>).

Each of the dual guides <NUM> may be individually fixed by the guide support <NUM> that is fixed to and extends from the transition piece casing <NUM>. Alternatively, the dual guides <NUM> may be fixed by a guide support <NUM> having a width large enough to accommodate both guides <NUM>. The form of supporting either of the dual guides <NUM> is not particularly limited.

As illustrated in <FIG>, the guide support <NUM> that supports the dual guides <NUM> may be fixed to two portions of an end of the transition piece casing <NUM> and extend from the two portions. In this case, the guide support <NUM> is formed as if the ends of the guide support <NUM> that extend from the two portions of the transition piece casing <NUM> are connected to each other by a connector, whereby the guide support <NUM> is formed into a single body. In the case of the guide support <NUM> having the foregoing configuration, the dual guides <NUM> are seated on and fixed to the surface of the connector and thus may guide compressed air toward the transition piece casing <NUM>.

The dual guides <NUM> seated on the guide support <NUM> may form a symmetrical structure so that each guide <NUM> can uniformly guide compressed air toward the transition piece casing <NUM>. The symmetry of the symmetrical structure is established about an imaginary plane drawn between the dual guides <NUM>. Thus, the dual guides <NUM> may be symmetrically arranged with respect to each other and may be respectively configured to guide a portion of the compressed air into the transition piece casing <NUM>.

The guide support <NUM> included in the transition piece assembly in accordance with the embodiment of the present disclosure may include a mount <NUM> and a rotatable arm <NUM>. The mount <NUM> may be seated on and fixed to the transition piece casing <NUM>, and the rotatable arm <NUM> may be rotatably provided to allow the guides <NUM> to be changed in position. The mount <NUM> and rotatable arm <NUM> configuration may be equally applied to the embodiments of <FIG> and <FIG>. In other words, the axially perpendicular structure <NUM> may be provided with the mount <NUM> and rotatable arm <NUM> to allow the structure <NUM> to be changed in position in the same manner as shown in <FIG>.

The mount <NUM> includes a distal end portion extending from the transition piece casing <NUM>, enabling the rotatable arm <NUM> to be coupled to the mount <NUM> by a bolt coupling method or the like to allow the rotatable arm <NUM> to rotate about the distal end portion of the mount <NUM>. The rotatable arm <NUM> is preferably coupled the mount <NUM> at the distal end portion, which may have one surface making contact with and facing a corresponding surface of a lower end of the rotatable arm <NUM>. Provided the rotatable arm <NUM> is rotatable, its coupling method is not particularly limited.

Although not specifically illustrated, the mount <NUM> may have a cuboidal shape in which, among four side surfaces, an upper surface and two opposite side surfaces are open. In this case, the rotatable arm <NUM> is inserted into the mount <NUM> through the open upper surface of the mount <NUM> so that the rotatable arm <NUM> is rotatable within the open opposite side surfaces.

Since the guide support <NUM> includes the rotatable arm <NUM>, the position of the single guide <NUM> or dual guides <NUM> can be changed taking into account the size of the transition piece casing <NUM> or the position at which the guide member <NUM> is installed.

Referring to <FIG>, a transition piece assembly in accordance the present invention includes a transition piece <NUM>, a transition piece casing <NUM>, and a support member <NUM> as in the case of the embodiments of <FIG>, and the transition piece assembly further includes a turbine casing <NUM>. In this case, a guide member <NUM> having an axially perpendicular structure is substituted for the guide member <NUM> having an axially perpendicular structure. In any event, a guide member <NUM> is fixed with respect to the transition piece casing <NUM> and is configured to guide the compressed air toward the transition piece casing. To do so, the guide member <NUM> is provided with a turbine casing guide <NUM> that is fixed to the inner wall of the turbine casing <NUM> and includes a guide surface <NUM>, which faces the outer circumferential surface of the transition piece casing <NUM> so that the compressed air is guided into the transition piece casing <NUM>. Here, the compressed air being guided by the guide surface <NUM> includes compressed air that flows over the outer circumferential surface of the transition piece casing <NUM> and toward an upper portion of the turbine casing <NUM>.

The turbine casing <NUM> is spaced apart from the transition piece casing <NUM> and encloses the transition piece casing <NUM> to prevent compressed air drawn from the compressor <NUM> from leaking out. Compressed air through the turbine casing <NUM> may flow to the liner <NUM> through the cooling holes formed in the transition piece casing <NUM> without leaking out.

As illustrated in <FIG>, the guide member <NUM> is seated on and fixed to an inner wall of the turbine casing <NUM>, and includes a coupling crosspiece <NUM> which is coupled to a sidewall of the turbine casing <NUM> and fixes the guide member <NUM> to the turbine casing <NUM>, and the turbine casing guide <NUM> which guides compressed air to the transition piece casing <NUM>. <FIG> schematically illustrates a location of the guide member <NUM> coupled to the inner wall of the turbine casing <NUM> but does not illustrate structural details such as its curvature.

The turbine casing guide <NUM> collects compressed air and guides the compressed air to the transition piece casing <NUM>, and has a structure similar to that of the single guide <NUM> described in the foregoing embodiment; therefore, repetitive explanation will be omitted. For example, the turbine casing guide <NUM> may be provided with features of the single guide <NUM>, including the opposite end portions 601a and 601b.

Compressed air that flows on one surface of the turbine casing guide <NUM> is not subjected to resistance.

The turbine casing guide <NUM> is coupled to the inner wall of the turbine casing <NUM> so that the turbine casing guide <NUM> can be fixed at a position facing the transition piece casing <NUM>. Therefore, compressed air that moves upward in the turbine casing <NUM> may be changed in direction by the turbine casing guide <NUM> and focused onto the transition piece casing <NUM>.

In another embodiment of the present disclosure, as illustrated in <FIG>, the coupling crosspiece <NUM> may have a flat plate shape. One side of the coupling crosspiece <NUM> may have a shape corresponding to that of one side of the turbine casing guide <NUM> so that the coupling crosspiece <NUM> can be joined with the turbine casing guide <NUM>. A plurality of coupling holes (not shown) through which the coupling crosspiece <NUM> can be coupled to the sidewall of the turbine casing <NUM> by bolting may be formed in a surface of the coupling crosspiece <NUM> that is exposed after the coupling crosspiece <NUM> is joined with the turbine casing guide <NUM>. However, the shape or the coupling method of the coupling crosspiece <NUM> is not particularly limited so long as the coupling crosspiece <NUM> can be coupled to the sidewall of the turbine casing <NUM> and thus fix and support the guide member <NUM>.

In another embodiment of the present disclosure, as illustrated in <FIG>, the guide member <NUM> may further include at least one rib <NUM> to prevent the turbine casing guide <NUM> and the coupling crosspiece <NUM> from being separated from each other by the flow of compressed air and to reinforce the support of the turbine casing guide <NUM> by the coupling crosspiece <NUM>.

One side of each of the ribs <NUM> is joined with and fixed to one surface of the coupling crosspiece <NUM>. Another side of the rib <NUM> is joined with and fixed to one surface of the turbine casing guide <NUM>. Thereby, the turbine casing guide <NUM> may be prevented from being dislodged.

In another embodiment of the present disclosure, a length of the junction of the rib <NUM> with the coupling crosspiece <NUM> and the turbine casing guide <NUM> is similar to a width of the coupling crosspiece <NUM> and the turbine casing guide <NUM>, and the shape of the rib <NUM> may be similar to an approximately trapezoidal shape. However, the shape of the rib <NUM> is not particularly limited.

Opposite end portions of the turbine casing guide <NUM> may be curved in the same manner as that described in the foregoing embodiment of the present disclosure so that compressed air can be more efficiently guided to the transition piece casing <NUM>. As described in the foregoing embodiment of the present disclosure, an inner guide <NUM> may be provided on one surface of the turbine casing guide <NUM> that faces the transition piece casing <NUM>. Furthermore, as described above, the distance between the opposite ends of the turbine casing guide <NUM> is greater than the distance between the opposite side portions of the transition piece casing <NUM>, so that compressed air can be more efficiently collected and guided to the transition piece casing <NUM>. Characteristics of the turbine casing guide <NUM> are similar to that of the embodiments of <FIG>; therefore, repetitive explanation will be omitted.

In another embodiment of the present disclosure, a transition piece module including a plurality of transition piece assemblies arranged in an annular shape may be implemented. Each of the plurality of transition piece assemblies may include a transition piece <NUM>, a transition piece casing <NUM>, and a support member <NUM> consistent with those of the above-described embodiments. For example, the transition piece <NUM> may include an inlet into which high-temperature combustion gas is drawn and an outlet from which the combustion gas is discharged toward a turbine inlet port <NUM>; the transition piece casing <NUM> may be spaced apart from the transition piece <NUM> and enclose the transition piece <NUM>, and the support member <NUM> may be inserted into space formed by spacing the transition piece <NUM> apart from the transition piece casing <NUM> and seated on an outer circumferential surface of the transition piece <NUM> to support the transition piece <NUM>. The transition piece module may also include at least one guide member <NUM> or <NUM> which guide compressed air that flows along the outer circumferential surface of the transition piece casing <NUM> toward the transition piece casings <NUM> and are disposed between the adjacent transition piece casings <NUM>. Each of the guide members <NUM> or <NUM> includes a single guide <NUM> or turbine casing guide <NUM> to guide compressed air, and a guide support <NUM> to fix the guide <NUM>, <NUM>.

As illustrated in <FIG>, in another embodiment of the present disclosure, the single guides <NUM> are disposed between the transition piece casings <NUM>. The single guides <NUM> may be designed to be seated at a position higher than the transition piece casings <NUM> so that compressed air that rises upward can efficiently flow onto upper surfaces of the transition piece casings <NUM>. A scheme of seating the single guide <NUM> is not particularly limited.

The guide support <NUM> is seated on an end portion of each transition piece casing <NUM>, extends in one direction, and is coupled with the corresponding guide <NUM>. Thereby, the guide <NUM> may be fixed between the transition piece casings <NUM>. The shape of the guide support <NUM> is not particularly limited so long as the guide support <NUM> extends in one direction so that the guide <NUM> can be spaced apart from the transition piece casing <NUM>. Although the guide support <NUM> may have various shapes, as illustrated in <FIG>, the guide support <NUM> is fixed to the end portion of the transition piece casing <NUM> and extends in at least one direction so that the guide <NUM> can be spaced apart from the transition piece casing <NUM>. In general, the guides <NUM> or <NUM> of the embodiment of <FIG> may be structured as described in the embodiments of <FIG>, including opposite end portions 601a and 601b.

As shown in <FIG>, the opposite end portions of the guides <NUM> or <NUM> include a first end portion curved inwardly toward a first transition piece casing <NUM> of an adjacent pair of transition piece assemblies and a second end portion curved inwardly toward a second transition piece casing <NUM> of the adjacent pair of transition piece assemblies. The opposite end portions are configured to collect the compressed air that collides with the guide member <NUM> or <NUM> and to guide the collected compressed air into the first and second transition piece casings.

The guide member <NUM> included in the transition piece module in accordance with another embodiment of the present disclosure may include a turbine casing guide <NUM> which guides compressed air to the transition piece casing <NUM>, and a coupling crosspiece <NUM> which couples the turbine casing guide <NUM> to the inner wall of the turbine casing <NUM>. As illustrated in <FIG>, the coupling crosspiece <NUM> may extend in one direction from an end portion of the turbine casing guide <NUM>, be formed in an approximately plate shape, and be fixed to the inner wall of the turbine casing <NUM> by a method such as a welding method or a bolt coupling method.

As illustrated in <FIG>, the guide <NUM>, <NUM> may include a central protrusion <NUM> which extends in one direction to collect a comparatively large amount of rising compressed air and guide the compressed air to the transition piece casing <NUM>. The central protrusion <NUM> extends in one direction from one surface of the guide <NUM>, <NUM> and has a protruding shape, as illustrated in <FIG>.

The guide <NUM>, <NUM> is disposed between adjacent transition piece casings <NUM>. Hence, to prevent the guide <NUM>, <NUM> from coming into contact with the transition piece casing <NUM> that is curved upward as illustrated in <FIG>, the central protrusion <NUM> may protrude in an approximately triangular or trapezoidal shape from the guide <NUM>, <NUM> by cutting away opposite side portions of a downstream edge of the guide <NUM>, <NUM>, as illustrated in <FIG>. However, the protruding shape is not particularly limited.

The amount of rising compressed air that flows toward the transition piece casing <NUM> may be increased by the protrusion that extends in one direction from one surface of the guide <NUM>, <NUM>, whereby the efficiency of cooling the transition piece casing <NUM> can be effectively increased.

Another embodiment of the present disclosure may include a combustor <NUM> provided with the above-described transition piece assembly. The combustor <NUM> may include a fuel nozzle module <NUM>' which includes a plurality of fuel nozzle assemblies <NUM> configured to supply fuel, a casing <NUM> which encloses the fuel nozzle module <NUM>', a liner <NUM> which is coupled with the fuel nozzle module <NUM>' and has internal space in which a fuel-air mixture is ignited and combusted, a liner casing <NUM> which encloses the liner <NUM>, and a transition piece assembly which is coupled with the liner <NUM> and the liner casing <NUM>. The transition piece assembly may include all of the characteristics described above.

Another embodiment of the present disclosure may include a gas turbine <NUM> provided with the above-described transition piece assembly. The gas turbine <NUM> may include a compressor <NUM> which draws air thereinto and forms compressed air, a combustor <NUM> which combusts a fuel-air mixture formed by mixing the compressed air with fuel and thus forms high-temperature combustion gas, and a turbine <NUM> which is driven by the combustion gas. Here, the combustor <NUM> is consistent with the above-mentioned combustor <NUM> and thus refers to a combustor <NUM> including the transition piece assembly described above in this specification.

Claim 1:
A transition piece assembly for a gas turbine, comprising:
a transition piece (<NUM>) including an inlet into which high-temperature combustion gas is drawn, and an outlet from which the combustion gas is discharged to a turbine inlet port (<NUM>);
a transition piece casing (<NUM>) disposed so as to be spaced apart from the transition piece (<NUM>), the transition piece casing (<NUM>) enclosing the transition piece (<NUM>) to form an annular interspace between an inner circumferential surface of the transition piece casing (<NUM>) and an outer circumferential surface of the transition piece (<NUM>), the transition piece casing (<NUM>) including an outer circumferential surface over which compressed air flows to cool the transition piece (<NUM>);
a support member (<NUM>) for supporting the transition piece casing (<NUM>), the support member (<NUM>) inserted into the annular interspace and seated on the outer circumferential surface of the transition piece (<NUM>); and
a turbine casing (<NUM>) spaced apart from the transition piece casing (<NUM>) and configured to enclose the transition piece casing (<NUM>), the turbine casing (<NUM>) having an inner wall facing the transition piece casing (<NUM>);
characterized in that the transition piece assembly further comprises:
a guide member (<NUM>) that includes an axially perpendicular structure, extending generally in a direction perpendicular to an axis of the transition piece casing (<NUM>), and configured to guide the compressed air toward the transition piece casing (<NUM>);
wherein the guide member (<NUM>) is fixed with respect to the inner wall of the turbine casing (<NUM>); and
wherein the axially perpendicular structure of the guide member (<NUM>) comprises a turbine casing guide (<NUM>) that is fixed to the inner wall of the turbine casing (<NUM>) and includes a guide surface (<NUM>) facing the outer circumferential surface of the transition piece casing (<NUM>) so that the compressed air, which flows over the outer circumferential surface of the transition piece casing (<NUM>) and toward the turbine casing (<NUM>), is guided into the transition piece casing (<NUM>).