Combustor with flow guide in double pipe type liner, and gas turbine having same

Abstract

A combustor includes a flow guide installed in an air channel to simultaneously implement collision cooling and convection cooling of a combustor liner and a transition piece. The air channel is formed by an inner casing and an outer casing which are spaced apart from each other by a predetermined distance, through which combustion air is introduced to the combustor in order to produce a fuel-air mixture. The flow guide is attached to an inner surface of the outer casing and extending a predetermined length towards the inner casing so as to guide the combustion air flowing through the air channel toward a surface of the inner casing. The flow guide includes a channel inlet formed on an upstream side; a channel outlet formed on a lower surface facing the inner casing; and a guide channel communicating with each of the channel inlet and the channel outlet.

Claims

1. A combustor comprising: an air channel formed by an inner casing and an outer casing which are spaced apart from each other by a predetermined distance, through which combustion air is introduced to the combustor in order to produce a fuel-air mixture; and a flow guide attached to an inner surface of the outer casing and extending a predetermined length towards the inner casing so as to guide the combustion air flowing through the air channel toward an outer surface of the inner casing, the flow guide including: a channel inlet formed so as to face in a direction of the combustion air flowing through the air channel; a channel outlet formed on a lower surface of the flow guide facing the inner casing, the lower surface having a curved structure recessed by a predetermined depth towards the outer casing, the curved structure including an upstream end, a downstream end, and a concave surface extending between the upstream and downstream ends and facing the outer surface of the inner casing; and a guide channel communicating with each of the channel inlet and the channel outlet, wherein the curved structure is disposed such that the upstream and downstream ends are arranged in the direction of the combustion air flowing through the air channel and is configured to pass the combustion air along the concave surface, and wherein the channel outlet of the flow guide communicates with the concave surface of the curved structure and is configured to generate swirl along the curved structure when the combustion air flowing in the guide channel collides with the combustion air passing the curved structure.

2. The combustor of claim 1, wherein the guide channel has a curved shape with a predetermined radius of curvature connecting the channel inlet and the channel outlet with each other.

3. The combustor of claim 1, wherein the channel outlet is comprised of two or more channel outlets respectively communicating with the guide channel.

4. The combustor of claim 1, wherein the guide channel is comprised of two or more guide channels, and wherein the channel inlet is comprised of two or more channel inlets communicating with the two or more guide channels, respectively.

5. The combustor of claim 1, wherein the channel outlet is comprised of a plurality of channel outlets, and the channel inlet is comprised of a plurality of channel inlets; and wherein the plurality of channel outlets and the plurality of channel inlets communicate with each other, respectively.

6. The combustor of claim 1, wherein the lower surface of the flow guide has a structure corresponding to the outer surface of the inner casing and is spaced apart from the outer surface of the inner casing by a predetermined distance.

7. The combustor of claim 1, wherein the channel outlet is comprised of a plurality of micro-channels respectively communicating with the guide channel.

8. The combustor of claim 7, wherein the channel outlet occupies 50% to 90% of the lower surface of the flow guide.

9. The combustor of claim 1, wherein the flow guide is detachably mounted on the inner surface of the outer casing.

10. The combustor of claim 1, wherein the flow guide is mounted on the inner surface of the outer casing and is configured to rotate at a predetermined angle about a hinge.

11. The combustor of claim 10, wherein the flow guide has a cross-sectional structure formed as an airfoil structure extending in a direction corresponding to the direction of the combustion air flowing through the air channel.

12. The combustor of claim 1, wherein the flow guide has a cross-sectional structure formed as any one of a circular, oval, or airfoil structure extending in a direction corresponding to the direction of the combustion air flowing through the air channel.

13. A gas turbine comprising a compressor to compress air introduced from an outside; a combustor to produce combustion gas by combusting a mixture of fuel and the compressed air; and a turbine to produce power using the combustion gas, wherein the combustor comprises: an air channel formed by an inner casing and an outer casing which are spaced apart from each other by a predetermined distance, through which the compressed air is introduced to the combustor; and a flow guide attached to an inner surface of the outer casing and extending a predetermined length towards the inner casing so as to guide the compressed air flowing through the air channel toward an outer surface of the inner casing, the flow guide including: a channel inlet formed so as to face in a direction of the compressed air flowing through the air channel; a channel outlet formed on a lower surface of the flow guide facing the inner casing, the lower surface having a curved structure recessed by a predetermined depth towards the outer casing, the curved structure including an upstream end, a downstream end, and a concave surface extending between the upstream and downstream ends and facing the outer surface of the inner casing; and a guide channel communicating with each of the channel inlet and the channel outlet, wherein the curved structure is disposed such that the upstream and downstream ends are arranged in the direction of the compressed air flowing through the air channel and is configured to pass the compressed air along the concave surface, and wherein the channel outlet of the flow guide communicates with the concave surface of the curved structure and is configured to generate swirl along the curved structure when compressed air flowing in the guide channel collides with the compressed air passing the curved structure.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) FIG. 1 is a cutaway perspective view of a gas turbine to which may be applied a combustor according to the present invention;

(2) FIG. 2 is a cross-sectional view of a combustor shown in FIG. 1;

(3) FIG. 3 is a perspective view of a flow guide of a combustor according to the present invention;

(4) FIG. 4 is a sectional view of the flow guide shown in FIG. 3;

(5) FIG. 5 is a sectional view along line A-A of FIG. 4;

(6) FIG. 6 is a sectional view of a flow guide of a combustor according to another embodiment of the present invention;

(7) FIG. 7 is a sectional view of a flow guide of a combustor according to another embodiment of the present invention;

(8) FIG. 8 is a sectional view of a flow guide of a combustor according to another embodiment of the present invention;

(9) FIG. 9 is a side view of a flow guide of a combustor according to another embodiment of the present invention;

(10) FIG. 10 is a side view of a flow guide of a combustor according to another embodiment of the present invention; and

(11) FIG. 11 is a sectional view of a flow guide of a combustor according to another embodiment of the present invention.

DETAILED DESCRIPTION OF THE INVENTION

(12) Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings. It should be noted that terms used in this specification and claims should not be limited to a common meaning or a dictionary definition, but should be construed as the meanings and concepts according to technical spirits of the present invention.

(13) It will be understood that when an element is referred to as being on another element, it can be directly on the other element or intervening elements may be present therebetween. Further, it will be understood that the term comprising or including specifies the presence of stated elements, but does not preclude the presence or addition of one or more other elements, unless the context clearly indicates otherwise.

(14) Referring to FIGS. 3-5, the combustor according to the present embodiment includes an inner casing 101 and an outer casing 102 which are spaced apart from each other by a predetermined distance to form an air channel, through which air is introduced so that fuel is mixed with the introduced air to generate a fuel-air mixture, which is then injected into a combustion chamber through a central nozzle and a main nozzle.

(15) Here, the combustor according to the present embodiment is provided with a flow guide 110 disposed between the inner casing 101 and the outer casing 102. The flow guide 110 is provided with a guide channel 111 having a specific structure capable of simultaneously implementing collision cooling and convection cooling for cooling the combustor liner and the transition piece.

(16) Specifically, the flow guide 110 according to the present embodiment is attached to an inner surface of the outer casing 102 and extends a predetermined length towards the inner casing 102. Here, combustion air flow through the space between the inner casing 101 and the outer casing 102, and the flow guide 110 may guide the flowing combustion air toward the surface of the inner casing 101.

(17) FIG. 5 shows a horizontal cross-section of the flow guide 110 taken along line A-A of FIG. 4. As illustrated in FIG. 5, the structure of the flow guide 110 has an airfoil shape extending in a direction corresponding to the direction of combustion air flowing through the space between the inner casing 101 and the outer casing 102. The structure of the flow guide 110 may have a circular, oval, or airfoil shape according to the present invention. In some cases, the cross-sectional structure of the flow guide may have a triangular structure, a trapezoidal structure, or a fan-shaped structure similarly extending in the direction of the flowing combustion air. Here, the flow guide 110 has an upstream side and a downstream side according to the direction of the combustion air flowing through the space between the inner casing 101 and the outer casing 102.

(18) As illustrated in FIG. 4, the guide channel 111 of the flow guide 110 may include a channel inlet 112 and a channel outlet 113 communicating with each other. Specifically, the channel inlet 112 is preferably formed on the upstream side of the flow guide 110, so as to face in the direction of the combustion air flowing through the air channel, and the channel outlet 113 is preferably formed on a lower surface of the flow guide 110 facing the inner casing 101. Further, a cross-sectional structure of the flow guide 110 may be differently positioned by specific distance (d) from a surface of the inner casing 101.

(19) Here, as illustrated in FIG. 4, the guide channel 111 may have a curved shape with a predetermined radius of curvature connecting the channel inlet 112 and the channel outlet 113 with each other.

(20) FIGS. 6 to 8 respectively illustrate a flow guide according to further embodiments of the present invention.

(21) As illustrated in FIG. 6, the flow guide 110 may have a structure in which two or more channel outlets 113 respectively communicate with the guide channel 111.

(22) In some cases, as illustrated in FIG. 7, the flow guide 110 may have a structure in which a plurality of channel inlets 112 and a plurality of channel outlets 113 respectively communicating with each other. That is, the flow guide 110 may have a structure in which the channel guide 111 consists of two or more channel guides each of which includes a channel inlet 112 and a channel outlet 113 communicating with each other. Alternatively, the flow guide of the present invention may have a structure in which two or more channel inlets 112 respectively communicate with the guide channel 111.

(23) It is preferred that the number and position of the channel inlets 112 and the channel outlets 113 are appropriately selected in consideration of a flow speed and a flow rate of the combustion air flowing through the space between the inner casing 101 and the outer casing 102.

(24) Referring to FIG. 8, the guide channel 111 may include a plurality of micro-channels 114. Here, the channel outlet 113 may consist of the plurality of micro-channels, which respectively communicate with the guide channel 111. At this time, the channel outlet 113 preferably has a large-area structure occupying 50 to 90% of the lower surface of the flow guide 110.

(25) FIGS. 9 and 10 respectively illustrate a flow guide according to other embodiments of the present invention.

(26) Referring to FIGS. 9 and 10, the lower surface of the flow guide 110 has a structure corresponding to the outer surface of the inner casing 101, and may be spaced apart from the outer surface of the inner casing 101 by a predetermined distance.

(27) In some cases, as illustrated in FIG. 10, the lower surface of the flow guide 110 facing the outer surface of the inner casing 101 may have a curved structure recessed by a predetermined depth towards the outer casing 102.

(28) In this case, air introduced through the channel inlet 112 is injected onto the outer surface of the inner casing 101 through the channel outlet 113. At this time, swirl may be generated along the curved structure when the injected air collides with air passing there. The swirl can maximize the collision cooling effect.

(29) FIG. 11 illustrate a flow guide according to still another embodiment of the present invention.

(30) Referring to FIG. 11, the flow guide 110 may be rotatably mounted on the inner surface of the outer casing 102 such that the flow guide is rotatable by a predetermined angle by means of a hinge structure 115. Optionally, the flow guide 110 may be detachably mounted on the inner surface of the outer casing 102.

(31) In this case, the cross-sectional structure of the flow guide 110 preferably has an airfoil structure extending in a direction corresponding to the direction of the combustion air flowing through the space between the inner casing 101 and the outer casing 102.

(32) The mounting direction of the flow guide 110 having such a structure can be intrinsically changed according to the flow of the combustion air through the space between the inner casing 101 and the outer casing 102. Here, the flow guide 110 in which the mounting direction is varied according to the flow direction of the combustion air can introduce a large amount of air through the channel inlet 112 so that a greater amount of air can be discharged through the channel outlet 113. As a result, the collision cooling effect can be maximized.

(33) The present invention can provide a gas turbine including the above-described combustor in which the difference between the direction of the air flow and the direction of the fuel flow is reduced so that the fuel is supplied to a desired region, thereby improving the fuel-air mixing ratio and thus the performance of the combustor.

(34) Specifically, a gas turbine according to the present embodiment includes a compressor 1100 to compress air introduced from an outside; a combustor 1200 to produce combustion gas by combusting a mixture of fuel and the compressed air; and a turbine 1300 to produce power using the combustion gas. Here, the combustor 1200 may include the combustor according to any one of the above-described embodiments of the present invention.

(35) As described before, the combustor of the present invention is provided with the flow guide in which the guide channel having a specific structure is installed, thereby providing a structure capable of simultaneously implementing collision cooling and convection cooling for cooling the combustor liner and the transition piece.

(36) While the exemplary embodiments of the present invention have been described in the detailed description, the present invention is not limited thereto, but should be construed as including all of modifications, equivalents, and substitutions falling within the spirit and scope of the invention defined by the appended claims.

(37) That is, the present invention is not limited to the above-mentioned embodiments and the description thereof, and it will be appreciated by those skilled in the art that various modifications and equivalent embodiments are possible without departing from the scope and spirit of the invention defined by the appended claims and that the present invention covers all the modifications and equivalents falling within the spirit and the scope of the present invention as defined by the appended claims.