CN111380077A

CN111380077A - Combustor of gas turbine

Info

Publication number: CN111380077A
Application number: CN201811628027.XA
Authority: CN
Inventors: 杨旭; 吕煊; 刘小龙; 李珊珊
Original assignee: China United Heavy Gas Turbine Technology Co Ltd
Current assignee: China United Heavy Gas Turbine Technology Co Ltd
Priority date: 2018-12-28
Filing date: 2018-12-28
Publication date: 2020-07-07
Anticipated expiration: 2038-12-28
Also published as: CN111380077B

Abstract

The invention discloses a combustor of a gas turbine, which comprises a flame tube, a flow bushing and a flow guide device, wherein the flow bushing is sleeved on the flame tube, an annular channel is formed between the flow bushing and the flame tube, a cooling hole is formed in the flow bushing, and the cooling hole extends along the axial direction of the bushing and is in a long strip shape; the flow guide device comprises a ring-shaped piece and a bottom plate, the first end of the ring-shaped piece is matched in the cooling hole, the second end of the ring-shaped piece extends into the annular channel, the ring-shaped piece is provided with an inner cavity, the first end of the ring-shaped piece is provided with an opening to be communicated with the inner cavity and the cooling hole, the bottom plate is arranged at the second end of the ring-shaped piece, the bottom plate is provided with a plurality of openings, and the openings are communicated with the inner cavity and the annular channel. The combustor of the gas turbine improves the cooling performance and reduces the flow loss.

Description

Combustor of gas turbine

Technical Field

The invention relates to the technical field of gas turbines, in particular to a combustor of a gas turbine.

Background

The gas turbine mainly comprises a gas compressor, a combustion chamber and a turbine, wherein compressed air discharged by the gas compressor cools heat components such as a flame tube, a transition section and the like outside the combustion chamber of the combustor, flows to the head of the combustion chamber to participate in combustion, and generated hot gas flows through the flame tube and the transition section in sequence and then enters the turbine to do work through expansion.

The wall surface of the combustor is mostly a double-layer wall surface, namely, the flow bushing is sleeved outside the flame tube and the transition section, so that an annular channel is formed between the flow guiding flow bushing and the flame tube and between the flow bushing and the transition section. In the related art, impingement cooling holes are formed in the flow sleeve to adjust the cooling performance of the liner and the transition section. However, existing combustors suffer from poor cooling of the liner and/or transition piece and there is a need for improvement.

Disclosure of Invention

The present invention is based on the finding that the inventors have conducted research analysis on burners in the related art, and have made the following problems and facts:

document US8677759B2 discloses a burner for a gas turbine comprising a flow guide cylinder, a flow liner surrounding the outside of the flow guide cylinder and forming an annular passage therebetween, and a plurality of flow ducts, the flow liner being provided with a plurality of rows of holes spaced apart in the axial direction of the flow liner, and a plurality of holes in each row being spaced apart in the circumferential direction of the flow liner, one end of the flow duct being within the holes, the other end of the flow duct extending into the annular passage, and each hole corresponding to one of the flow ducts, air outside the flow liner flowing through the holes and the flow ducts into the annular passage.

In the combustor disclosed in this document, cooling is enhanced by adding a plurality of the above-described flow guide pipes, but since the annular passage has a cross flow flowing from front to rear and the ratio of the cross flow rate to the total air flow rate in the combustor is large, the impingement cooling is impaired because the impingement jet flow does not reach the impingement-cooled surface due to an excessively large cross flow ratio, and thus cooling performance is impaired, and the cross flow generated by the holes in the front row is still impaired to some extent by the holes in the rear row, and the effect of enhancing cooling performance is not good. Further, the arrangement of the plurality of flow guide pipes tends to cause flow disturbance, and large flow loss tends to occur. In addition, the burner of this structure does not facilitate fine adjustment of the cooling air flow rate in response to the thermal load variation of the liner in different regions.

The present inventors have found out the above problems and have proposed a new combustor for a gas turbine, which is intended to solve at least one of the technical problems in the related art to some extent.

A combustor of a gas turbine according to an embodiment of the present invention includes a liner; the flow bushing is sleeved on the flame tube, an annular channel is formed between the flow bushing and the flame tube, so that air can flow from a first end of the annular channel to a second end of the annular channel, the flow bushing is provided with a cooling hole, and the length of the cooling hole in the axial direction of the flow bushing is greater than the length of the cooling hole in the circumferential direction of the flow bushing, so that the cooling hole is in an elongated shape; the flow guide device comprises a ring-shaped piece and a bottom plate, the ring-shaped piece is matched with the cooling hole, the first end of the ring-shaped piece is matched in the cooling hole, the second end of the ring-shaped piece extends into the annular channel, the ring-shaped piece is provided with an inner cavity, an opening at the first end of the ring-shaped piece is arranged to be communicated with the inner cavity and the cooling hole, the bottom plate is arranged at the second end of the ring-shaped piece to cover the second end of the inner cavity, a plurality of openings are formed in the bottom plate, and the openings are communicated with the inner cavity and the annular channel.

According to the combustor of the gas turbine, the flow guide device is arranged on the flow bushing, so that the cooling performance is improved, and the flow loss is reduced.

In some embodiments, the ring member includes a first curved section, a first straight section, a second curved section, and a second straight section, the first straight section and the second straight section being spaced apart from each other along the circumferential direction, the first curved section connecting a first end of the first straight section and a first end of the second straight section, the second curved section connecting a second end of the first straight section and a second end of the second straight section, and the first curved section and the second curved section both projecting outwardly of the first straight section and the second straight section.

In some embodiments, the length of the first and second curved sections in the axial direction is less than the length of the first and second straight sections in the axial direction.

In some embodiments, at least one of the first curved segment and the second curved segment is arcuate or V-shaped.

In some embodiments, the first curved section is arcuate and the second curved section is V-shaped.

In some embodiments, the height of the ring is gradually reduced in the flow direction of the air.

In some embodiments, the inner circumferential profile of the cross-section of the aperture is square, circular, arcuate, or V-shaped.

In some embodiments, a plurality of the apertures are the same shape and size.

In some embodiments, at least one of the plurality of openings has a shape and size that is different from the shape and size of the remaining openings.

In some embodiments, the cooling hole has a plurality of cooling holes, the plurality of cooling holes are arranged at intervals along the circumferential direction, the flow guide device is provided in plurality, and the plurality of flow guide devices correspond to the plurality of cooling holes one by one.

In some embodiments, the shape and size of the aperture of at least one of the deflectors is different from the shape and size of the apertures of the remaining deflectors.

In some embodiments, the second end of the annular channel communicates with the first end of the liner, and the cooling holes correspond to the second end of the liner, or the cooling holes correspond to the entire liner.

Drawings

FIG. 1 is a schematic structural view of a combustor of a gas turbine according to an embodiment of the present invention.

Fig. 2 is a schematic structural view of a deflector according to an embodiment of the present invention.

Fig. 3 is a schematic structural view of a deflector according to an embodiment of the present invention, in which the cross section of the opening of the base plate is circular.

Fig. 4 is a schematic structural view of a deflector according to an embodiment of the present invention, in which one opening of a base plate has a shape and size different from those of another opening.

Fig. 5 is a schematic structural view of a deflector according to an embodiment of the present invention, in which the plurality of openings on the base plate are different in shape and size.

Fig. 6 is a schematic structural view of a deflector according to an embodiment of the present invention, in which a first curved section has a V-shape and a second curved section has an arc shape.

Fig. 7 is a schematic structural view of a deflector according to an embodiment of the present invention, in which the first and second curved sections are each V-shaped.

Fig. 8 is a structural view of a deflector according to an embodiment of the present invention, in which the height of the ring-shaped member is gradually reduced from right to left.

FIG. 9 is a schematic flow organization of an air flow within a combustor of a gas turbine according to an embodiment of the invention.

FIG. 10 is a schematic view of a combustor of a gas turbine according to another embodiment of the present invention.

Reference numerals:

the combustor basket 1, the flow sleeve 2, the cooling holes 21, the flow guide device 3, the annular member 31, the inner cavity 310, the first curved section 311, the first straight section 312, the second curved section 313, the second straight section 314, the bottom plate 32, the opening 321 and the annular channel 4.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the invention.

As shown in fig. 1 to 10, a combustor of a gas turbine according to an embodiment of the present invention includes a combustor basket 1, a flow liner 2 and a flow guide device 3, wherein the flow liner 2 is sleeved on the combustor basket 1, and the flow liner 2 and the combustor basket 1 are spaced apart in a radial direction of the combustor basket 1 or the flow liner 2 and form an annular channel 4 therebetween, and air can flow from a first end of the annular channel 4 toward a second end (in a direction from right to left in fig. 1) of the annular channel 4, i.e., the annular channel 4 is adapted to be flowed through by air, wherein, for example, as shown by arrows in fig. 1 and 2, a cross flow can flow from the right end of the annular channel 4 to the left end of the annular channel 4 through the flow guide device 3.

The flow liner 2 is provided with cooling holes 21, the cooling holes 21 penetrate the wall thickness of the flow liner 2, and the length of the cooling holes 21 in the axial direction (the left-right direction shown in fig. 1) of the flow liner 2 is longer than the length of the cooling holes 21 in the circumferential direction of the flow liner 2 so that the cooling holes 21 are elongated. In other words, the cooling holes 21 extend in the axial direction of the flow sleeve 2 and are elongated.

The flow guiding device 3 comprises a ring-shaped member 31 and a bottom plate 32, wherein the ring-shaped member 31 is matched with the cooling hole 21. In other words, the length of the ring 31 in the axial direction of the flow sleeve 2 is larger than the length of the ring 31 in the axial direction of the flow sleeve 2, and as shown in fig. 2, the length of the ring 31 in the left-right direction is larger than the length of the ring 31 in the front-rear direction, so that the length of the ring 31 in the axial direction of the flow sleeve 2 and the length of the ring 31 in the circumferential direction of the flow sleeve 2 correspond to the length of the cooling holes 21 in the axial direction of the flow sleeve 2 and the length of the ring 31 in the circumferential direction of the flow.

A first end of the ring member 31 (the upper end of the ring member 31 shown in fig. 2) is fitted into the cooling hole 21, and a second end of the ring member 31 (the lower end of the ring member 31 shown in fig. 2) extends into the annular passage 4. In other words, as shown in fig. 2, the upper end of the ring member 31 is fitted in the cooling hole 21, and the lower end of the ring member 31 extends in the radial direction of the ring member 31 and into the annular passage 4. Specifically, the first end surface of the ring-shaped member 31 is flush with the outer circumferential surface of the flow sleeve 2, and it is understood that the present invention is not limited thereto, for example, the first end surface of the ring-shaped member 31 is located in the cooling hole 21, and the first end surface of the ring-shaped member 31 does not extend to the outer circumferential surface of the flow sleeve 2.

The ring member 31 has an inner cavity 310, and it will be appreciated that the ring member 31 is annular by having the inner cavity 310, and that a first end of the ring member 31 (the upper end of the ring member 31 shown in fig. 2) is open to communicate the inner cavity 310 with the cooling holes 21. In other words, the first end of the inner cavity 310 is open to communicate the inner cavity 310 with the cooling hole 21.

The base plate 32 is provided at a second end of the ring member 31 (a lower end of the ring member 31 shown in fig. 2) to cover the second end of the inner cavity 310, and the base plate 32 is spaced apart from the combustor basket 1. In other words, the flow guiding device 3 is annular, the upper end of the flow guiding device 3 is open, the lower end of the flow guiding device 3 is provided with a bottom plate 32, the upper end of the flow guiding device 3 is matched with the cooling hole 21, and the lower end of the flow guiding device 3 is spaced from the flame tube 1.

The bottom plate 32 is provided with a plurality of openings 321, and the openings 321 communicate the inner cavity 310 with the annular passage 4, in other words, the openings 321 penetrate through the plate thickness of the bottom plate 32 to communicate the inner cavity 310 with the annular passage 4. Thus, external air may enter the annular channel 4 through the internal cavity 310 and the plurality of openings 321 (when the first end surface of the ring-shaped member 31 is flush with the outer circumferential surface of the flow liner 2) or through the cooling hole 21, the internal cavity 310 and the plurality of openings 321 (when the first end surface of the ring-shaped member 31 is in the cooling hole 21) to impingement cool the outer circumferential surface of the liner 1, and may flow in the annular channel 4 and enter the liner 1. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.

According to the combustor of the gas turbine provided by the embodiment of the invention, the distance between the cooling hole 21 and the outer peripheral surface of the flame tube 1 is reduced through the annular and elongated flow guide device 3, and the cooling hole can reach the outer peripheral surface of the flame tube 1 to form impingement cooling on the outer peripheral surface, so that the problem that the impingement cooling jet is flushed to the downstream and mixed with cross flow (as shown in fig. 9) under the action of cross flow when the impingement cooling hole is far away from a target impingement surface, even cannot reach the target impingement cooling surface, and cannot form effective cooling is solved, the cooling performance is improved, the flow loss is reduced, and the flow rate of cooling air can be conveniently and finely adjusted according to the heat load change conditions of the flame tube in different areas.

In some embodiments, the ring member 31 includes a first curved section 311, a first straight section 312, a second curved section 313 and a second straight section 314, the first straight section 312 and the second straight section 314 are spaced apart from each other along the circumferential direction (up-down direction shown in fig. 3) of the flow bushing 2, the first curved section 311 connects a first end (left end of the first straight section 312 shown in fig. 3) of the first straight section 312 and a first end (left end of the second straight section 314 shown in fig. 3) of the second straight section 314, the second curved section 313 connects a second end (right end of the first straight section 312 shown in fig. 3) of the first straight section 312 and a second end (right end of the second straight section 314 shown in fig. 3) of the second straight section 314, and both the first curved section 311 and the second curved section 313 outwardly protrude the first straight section 312 and the second straight section 314. In the description of the present invention, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In other words, as shown in fig. 3, the first and second

straight sections

312 and 312 each extend in the left-right direction, the first and second

straight sections

312 and 312 are opposite to and spaced apart from each other in the front-rear direction, the rear end of the first curved section 311 is connected to the left end of the first straight section 312, the front end of the first curved section 311 is connected to the left end of the second straight section 314, the rear end of the second curved section 313 is connected to the right end of the first straight section 312, the front end of the second curved section 313 is connected to the right end of the second straight section 314, and the first curved section 311 extends rightward from the left end of the first straight section 312 and is curved from the rear or front, or the first curved section 311 extends rightward from the left end of the second straight section 314 and is curved forward from the rear. In some embodiments, by providing the ring member 31 in the above-described structure, air flow resistance can be reduced, and pressure loss can be reduced.

In some specific embodiments, the lengths of the first and second

curved sections

311 and 313 in the axial direction of the flow sleeve 2 are smaller than the lengths of the first and second

straight sections

312 and 314 in the axial direction of the flow sleeve 2. In other words, as shown in fig. 3, the lengths of the first and second

curved sections

311 and 313 in the left-right direction are smaller than the lengths of the first and second

straight sections

312 and 314 in the left-right direction.

Specifically, the first and second

straight sections

312 and 314 are the same length in the left-right direction.

In some embodiments, at least one of the first curved segment 311 and the second curved segment 313 is arcuate or V-shaped. In other words, the first bending section 311 and the second bending section 313 may have an arc shape or a V shape in the cross section of the ring member 3. It is understood that by providing the first bent section 311 and/or the second bent section 313 in an arc shape or a V shape, the flow resistance of the cross flow can be further reduced, reducing the pressure loss.

In some alternative embodiments, as shown in fig. 2-5, the first curved segment 311 and the second curved segment 313 are each curved. Specifically, the first and second

bent sections

311 and 311 are opposite to each other and are symmetrically disposed to each other.

In other alternative embodiments, as shown in FIG. 7, first curved section 311 and second curved section 313 are each V-shaped. Specifically, the first and second

bent sections

In still other alternative embodiments, one of the first curved segment 311 and the second curved segment 313 is arcuate and the other of the first curved segment 311 and the second curved segment 313 is V-shaped. As shown in fig. 6, the first bending portion 311 has a V shape, and the second bending portion 313 has an arc shape.

It is to be understood that, as to the specific shapes of the first and second

bent sections

311 and 313, the present invention is not limited thereto, so as to obtain the effect of reducing the flow resistance.

In some embodiments, the height of the ring 31 gradually decreases in the direction of flow of the air (in the direction from right to left as viewed in fig. 1). In other words, as shown in fig. 1 and 8, the height of the ring 31 is gradually reduced from right to left. Here, it is to be understood that the height of the ring 31 is the length of the ring 31 in the up-down direction shown in fig. 1 and 8. In some embodiments, by setting the height of the ring member 31 to be different, the impingement distance from the cooling hole 21 to the outer peripheral surface of the liner 1 can be adjusted, thereby adjusting the cooling performance.

In some embodiments, as shown in fig. 2-8, the inner peripheral profile of the cross-section of the aperture 321 is square, circular, arcuate, or V-shaped. It will be appreciated that the invention is not so limited.

In alternative embodiments, as shown in fig. 3 and 7, the plurality of openings 321 in the base plate 32 are the same shape and size.

In other alternative embodiments, as shown in fig. 4-6 and 8, at least one of the plurality of openings 321 has a shape and size that is different from the shape and size of the remaining openings 321.

It will be appreciated that the shape and size of the plurality of apertures 321 in the bottom plate 32 can be adjusted as the case may be, to facilitate adjustment of the amount of cooling air flow to further improve cooling performance in response to changes in the thermal load of the combustor basket 1 in different areas. Likewise, the number on the base plate 32 may be adjusted as the case may be.

In some embodiments, as shown in fig. 1, the cooling hole 21 has a plurality of cooling holes 21, the plurality of cooling holes 21 are arranged at intervals in the circumferential direction, the flow guide device 3 is provided in a plurality, and the plurality of flow guide devices 3 correspond to the plurality of cooling holes 21 one to one. It will be appreciated that the cross flow entering the annular channel 4 from the right end of the annular channel 4 mainly flows through the area between two adjacent flow guiding devices 3, so that the flow in the annular channel 4 is more regular, the weakening of the impingement cooling jets by the cross flow is reduced (as shown in fig. 9), and thus more efficient impingement cooling is achieved with less flow losses.

In some embodiments, the shape and size of the apertures 321 of at least one flow guiding device 3 of the plurality of flow guiding devices 3 is different from the shape and size of the apertures 321 of the remaining flow guiding devices 3. Further, the number of the openings 321 of at least one flow guiding device 3 of the plurality of flow guiding devices is different from the number of the openings 321 of the remaining flow guiding devices 3.

In other words, the shape, size and number of the openings 321 of one of the plurality of flow guiding devices 3 may be different from the shape, size and number of the openings 321 of another one of the flow guiding devices 3, wherein only the shape and size may be different, only the number may be different, and the shape, size and number may also be different, and the specific arrangement may be adjusted according to actual requirements when the shapes are the same, so as to further adapt to the thermal load variation of the flame tube 1 in different areas.

It will be appreciated that the invention is not limited thereto, for example, the openings 321 may be of the same shape, size and number in the plurality of deflectors 3.

In some embodiments, the second end of the annular channel 4 (the left end of the annular channel 4 shown in FIG. 1) communicates with the first end of the liner 1 (the left end of the liner 1 shown in FIG. 1), and the cooling holes 21 correspond to the second end of the liner 1 (the right end of the liner 1 shown in FIG. 1). In other words, as shown in FIG. 1, the cross flow flows from the right end of the annular channel 4 toward the left end of the annular channel 4 and into the combustor basket 1 at the left end of the annular channel 4, wherein elongated cooling holes 21 are provided at the right end of the flow sleeve 2 and correspond to the right end of the combustor basket 1.

It will be appreciated that the invention is not limited thereto, for example, the cooling holes 21 correspond to the entire liner 1. In other words, as shown in fig. 10, the cooling holes 21 extend rightward from a position of the flow sleeve 2 adjacent to the left end thereof to a position adjacent to the right end thereof such that the cooling holes 21 correspond to substantially the entire combustor basket 1.

A combustor of a gas turbine according to an embodiment of the present invention is described below with reference to fig. 1 to 9.

As shown in fig. 1 to 9, the combustor of the gas turbine according to the embodiment of the present invention includes a combustor basket 1, a flow liner 2 and a plurality of flow guiding devices 3, wherein the flow liner 2 is sleeved on the combustor basket 1, and the flow liner 2 and the combustor basket 1 are spaced apart in a radial direction of the combustor basket 1 or the flow liner 2 and form an annular channel 4 therebetween, and air can flow from a right end of the annular channel 4 toward a left end of the annular channel 4, i.e., the annular channel 4 is adapted to be flowed through by air, for example, as shown by arrows in fig. 1 and 2, and a cross flow can flow from the right end of the annular channel 4 to the left end of the annular channel 4 through the flow guiding devices 3.

The right end of the flow liner 2 is provided with a plurality of cooling holes 21, the cooling holes 21 correspond to the right end of the flame tube 1, the cooling holes 21 are uniformly arranged at intervals in the circumferential direction of the flow liner 2, each cooling hole 21 penetrates through the wall thickness of the flow liner 2, and the length of each cooling hole 21 in the axial direction (the left and right direction shown in fig. 1) of the flow liner 2 is greater than that in the circumferential direction of the flow liner 2, so that the cooling holes 21 are in a long strip shape.

The flow guide device 3 includes a ring member 31 and a bottom plate 32, the length of the ring member 31 in the left-right direction is larger than the length of the ring member 31 in the front-rear direction so that the length of the ring member 31 in the axial direction of the flow sleeve 2 is matched to the length of the cooling hole 21 in the axial direction of the flow sleeve 2, and the length of the ring member 31 in the circumferential direction of the flow sleeve 2 is matched to the length of the cooling hole 21 in the circumferential direction of the flow sleeve 2. As shown in fig. 2, the upper end of the ring member 31 is fitted in the cooling hole 21 with the upper end face of the ring member 31 flush with the outer peripheral surface of the flow sleeve 2, and the lower end of the ring member 31 extends in the radial direction of the ring member 31 and into the annular passage 4.

The ring member 31 has an inner cavity 310 so that the ring member is annular, and an upper end of the ring member 31 is open to communicate the inner cavity 310 with the cooling hole 21. The base plate 32 is provided at the lower end of the ring member 31 and the base plate 32 is spaced apart from the combustor basket 1. The bottom plate 32 is provided with a plurality of openings 321, and the openings 321 communicate the inner cavity 310 and the annular channel 4, so that external air can enter the annular channel 4 through the inner cavity 310 and the plurality of openings 321 to impact cool the outer peripheral surface of the combustor basket 1, and can flow in the annular channel 4 and enter the combustor basket 1.

The first and second

straight sections

312 and 312 extend in the left-right direction, the first and second

straight sections

312 and 312 are opposite to and spaced apart from each other in the front-rear direction, the rear end of the first curved section 311 is connected to the left end of the first straight section 312, the front end of the first curved section 311 is connected to the left end of the second straight section 314, the rear end of the second curved section 313 is connected to the right end of the first straight section 312, the front end of the second curved section 313 is connected to the right end of the second straight section 314, and the first curved section 311 extends rightward from the left end of the first straight section 312 and is curved from the rear or front, or the first curved section 311 extends rightward from the left end of the second straight section 314 and is curved forward from the rear.

The first and second

straight sections

312 and 314 have the same length in the left-right direction, and the first and second

curved sections

311 and 313 have a length in the left-right direction smaller than the lengths of the first and second

straight sections

312 and 314 in the left-right direction.

The shapes of the first bending section 311 and the second bending section 313 and the shapes, the sizes and the number of the holes 321 can be designed and determined according to specific practical situations so as to adjust the cooling air flow rate according to the heat load change conditions of different areas of the flame tube 1.

Regarding the shapes of the first and second

bent segments

311 and 313, as shown in fig. 2-5, for example, the first and second

bent segments

311 and 313 are each arc-shaped, and the first and second

bent segments

311 and 311 are disposed opposite to each other and symmetrically to each other. For example, as shown in fig. 6, the first curved section 311 has a V-shape and the second curved section 313 has an arc shape. For example, as shown in fig. 7, each of the first bending portion 311 and the second bending portion 313 has a V shape, and the first bending portion 311 and the second bending portion 311 are opposite to each other and are symmetrically disposed.

Regarding the shape, size and number of the openings 321, for example, as shown in fig. 2, 6 and 7, the openings 321 have two openings 321, and the two openings 321 are opposite and symmetrically disposed, wherein one of the openings 321 is disposed adjacent to the first bending section 311, and the cross-sectional shape of the opening 321 is adapted to the cross-sectional shape of the first bending section 311, and the other opening 321 is disposed adjacent to the second bending section 313, and the cross-sectional shape of the opening 321 is adapted to the cross-sectional shape of the second bending section 313, wherein the two openings 321 are arc-shaped in fig. 2; in FIG. 6, one opening 321 is V-shaped and one opening 321 is arcuate; both openings 321 are V-shaped in fig. 7.

Also, as shown, for example, in fig. 3-4, the opening 321 has a plurality, wherein at least one opening 321 of the plurality of openings 321 has a shape and size different from the shape and size of the remaining openings 321.

Further, the height of the ring member 31 is gradually reduced from right to left, and by setting the height of the ring member 31 to be different, the impingement distance from the cooling hole 21 to the outer peripheral surface of the liner 1 can be adjusted, thereby adjusting the cooling performance.

The plurality of flow guiding devices 3 correspond to the plurality of cooling holes 21 one by one, that is, one end of one flow guiding device 3 is fitted in one cooling hole 21, wherein the shape, size and/or number of the openings 321 in the plurality of flow guiding devices 3 may be the same or different, and are designed and determined according to specific practical situations.

A combustor of a gas turbine according to another embodiment of the present invention is described below with reference to fig. 10. As shown in fig. 2, a combustor of a gas turbine according to an embodiment of the present invention includes a combustor basket 1, a flow sleeve 2, and a plurality of flow guiding devices 3, wherein the flow sleeve 2 is fitted over the combustor basket 1, and the flow sleeve 2 and the combustor basket 1 are spaced apart in a radial direction of the combustor basket 1 or the flow sleeve 2 and form an annular passage 4 therebetween.

The flow liner 2 is provided with a plurality of cooling holes 21, and each cooling hole 21 corresponds to substantially the whole combustor basket 1, namely, the left end of the cooling hole 21 is adjacent to the left end of the flow liner, and the right end of the cooling hole 21 is adjacent to the right end of the flow liner, so that the length of the cooling hole 21 in the axial direction of the flow liner 2 is relatively long, and the outer peripheral surface of the combustor basket 1 is better cooled.

The other structure and operation of the combustor of the gas turbine shown in fig. 10 may be the same as the embodiment shown in fig. 1-9 and will not be described in detail herein.

In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.

In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; may be mechanically coupled, may be electrically coupled or may be in communication with each other; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

In the present invention, unless otherwise expressly stated or limited, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.

Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.

Claims

1. A combustor for a gas turbine, comprising:

a flame tube;

the flow bushing is sleeved on the flame tube, an annular channel is formed between the flow bushing and the flame tube, so that air can flow from a first end of the annular channel to a second end of the annular channel, the flow bushing is provided with a cooling hole, the cooling hole penetrates through the wall thickness of the flow bushing, and the length of the cooling hole in the axial direction of the flow bushing is greater than that in the circumferential direction of the flow bushing, so that the cooling hole is in an elongated shape;

the flow guide device comprises a ring-shaped piece and a bottom plate, the ring-shaped piece is matched with the cooling hole, the first end of the ring-shaped piece is matched in the cooling hole, the second end of the ring-shaped piece extends into the annular channel, the ring-shaped piece is provided with an inner cavity, an opening at the first end of the ring-shaped piece is arranged to be communicated with the inner cavity and the cooling hole, the bottom plate is arranged at the second end of the ring-shaped piece to cover the second end of the inner cavity, the bottom plate is spaced apart from the flame tube, a plurality of holes are formed in the bottom plate, and the holes are communicated with the inner cavity and the annular channel.

2. The gas turbine combustor of claim 1, wherein the annulus includes a first curved section, a first straight section, a second curved section, and a second straight section, the first and second straight sections being spaced apart from each other along the circumferential direction, the first curved section connecting a first end of the first straight section and a first end of the second straight section, the second curved section connecting a second end of the first straight section and a second end of the second straight section, and the first and second curved sections each outwardly projecting the first and second straight sections.

3. The gas turbine combustor of claim 2, where the first and second curved sections are shorter in length in the axial direction than the first and second straight sections.

4. The gas turbine combustor of claim 2, where at least one of the first curved section and the second curved section is arcuate or V-shaped.

5. The gas turbine combustor of claim 4, where one of the first curved section and the second curved section is arcuate and the other of the first curved section and the second curved section is V-shaped.

6. The gas turbine combustor of claim 1, wherein the ring has a height that gradually decreases in a flow direction of the air.

7. The gas turbine combustor of claim 1, wherein the cross-sectional inner peripheral profile of the opening is square, circular, arcuate, or V-shaped.

8. The gas turbine combustor according to claim 1, wherein a plurality of said openings are identical in shape and size.

9. The gas turbine combustor according to claim 1, wherein at least one of the openings has a shape and size different from the remaining openings.

10. The combustor of a gas turbine according to any one of claims 1 to 9, wherein the cooling hole has a plurality of cooling holes arranged at intervals in the circumferential direction, and the flow guide device is provided in plurality in one-to-one correspondence with the plurality of cooling holes.

11. The gas turbine combustor of claim 10, wherein the shape and size of the opening of at least one of the flow guides is different from the shape and size of the openings of the remaining flow guides.

12. The gas turbine combustor according to any one of claims 1 to 9, wherein the second end of the annular passage communicates with the first end of the liner, and the cooling hole corresponds to the second end of the liner, or the cooling hole corresponds to the entire liner.