阅读说明：本技术 燃气轮机用火焰筒及燃气轮机 (Combustor liner for gas turbine and gas turbine ) 是由 李珊珊 静大亮 刘江帆 张哲铭 于 2021-08-18 设计创作，主要内容包括：本发明公开了一种燃气轮机用火焰筒及燃气轮机,包括筒体和肋片,所述筒体内设有供热燃气流通的燃气通道,所述筒体具有第一端和第二端,所述筒体的第一端适于所述热燃气流入所述燃气通道,所述筒体的第二端适于所述热燃气流出所述燃气通道；所述肋片设在所述筒体的外周壁上,所述肋片沿着从所述筒体的第一端至所述筒体的第二端的方向螺旋延伸,且所述肋片的高度尺寸H可沿所述肋片的螺旋延伸方向变化。本发明的燃气轮机用火焰筒,燃气轮机用火焰筒的肋片具有较好的冷却效果,较高的冷却效率,延长了燃气轮机的使用寿命。(The invention discloses a flame tube for a gas turbine and the gas turbine, which comprise a tube body and fins, wherein a gas channel for hot gas to flow through is arranged in the tube body, the tube body is provided with a first end and a second end, the first end of the tube body is suitable for the hot gas to flow into the gas channel, and the second end of the tube body is suitable for the hot gas to flow out of the gas channel; the fin is established on the periphery wall of barrel, the fin is along following the first end of barrel extremely the direction spiral extension of the second end of barrel, just the height dimension H of fin can be followed the spiral extending direction of fin changes. According to the flame tube for the gas turbine, the fins of the flame tube for the gas turbine have good cooling effect and high cooling efficiency, and the service life of the gas turbine is prolonged.)

1. A combustor basket for a gas turbine, comprising:

a cylinder having a gas passage for hot gas to flow through, the cylinder having a first end and a second end, the first end of the cylinder being adapted for the hot gas to flow into the gas passage and the second end of the cylinder being adapted for the hot gas to flow out of the gas passage;

the fin is arranged on the peripheral wall of the barrel, the fin extends spirally along the direction from the first end of the barrel to the second end of the barrel, and the height dimension H of the fin can be changed along the spiral extending direction of the fin.

2. The combustor basket for a gas turbine as claimed in claim 1, wherein said cylinder includes a first section and a second section, an air flow velocity of said first section outer circumferential side is smaller than an air flow velocity of said second section outer circumferential side, and a height dimension H1 of said first section outer circumferential side rib is larger than a height dimension H2 of said second section outer circumferential side rib.

3. The combustor basket for a gas turbine as claimed in claim 2, wherein said first section is plural, said second section is plural, and said first sections and said second sections are alternately arranged in a direction from said first end of said barrel to said second end of said barrel.

4. The gas turbine combustor basket of claim 2, wherein said fins on said first outer circumferential side have one or a combination of a zigzag shape, a city wall shape, and a lace shape in cross section along a spiral extending direction of said fins.

5. The combustor basket for a gas turbine as in claim 2, wherein a height dimension H1 of said first outer circumferential rib is 0.8 mm to 1.2 mm.

6. The combustor basket of claim 1, wherein the fins have a pitch angle α of greater than 60 degrees and less than 90 degrees.

7. The combustor basket for a gas turbine as in claim 1, wherein a cross section of at least some of said fins along a direction of spiral extension of said fins or a cross section of at least some of said fins is one or a combination of a zigzag shape, a city wall shape and a lace shape.

8. The combustor basket for a gas turbine as in claim 1, wherein a height dimension H of said fins is from 0.5 mm to 1.2 mm.

9. The combustor basket for a gas turbine as in claim 1, wherein a width dimension W of said ribs is between 0.5 mm and 1.5 mm.

10. The combustor basket for a gas turbine as in claim 1, wherein a pitch L of said fins is 5 mm to 20 mm.

11. The combustor basket for a gas turbine according to any one of claims 1 to 10, wherein the fins have first and second opposite side surfaces, each of the first and second side surfaces extending in a direction of a helical extension of the fins, the first side surface being angled and smoothly connected to the outer peripheral wall of the cylinder, and the second side surface being angled and smoothly connected to the outer peripheral wall of the cylinder.

12. A gas turbine engine comprising a combustor basket according to any one of claims 1 to 11.

Technical Field

The invention relates to the technical field of flame tube cooling, in particular to a flame tube for a gas turbine and the gas turbine.

Background

The combustion chamber of the gas turbine is internally provided with a fuel injection device, a flame tube, a transition section and the like, the fuel injection device is used for injecting fuel to the flame tube and mixing and burning the fuel and gas in the combustion chamber, and hot combustion gas generated by burning is conveyed to the turbine through the flame tube and the transition section. Since the liner needs to operate at high temperature conditions, the liner needs to be cooled efficiently to meet expected service life requirements. However, in the related art, the cooling effect of the flame tube has a large difference in different working states of different gas turbines, especially for a low-load point, the flow speed in the outer annular cavity of the flame tube is low, and a strong high-temperature region still exists in a part of regions, so that the cooling effect is reduced, and the service life of the gas turbine is influenced.

Disclosure of Invention

The present invention is directed to solving, at least to some extent, one of the technical problems in the related art.

Therefore, the embodiment of the invention provides the combustor basket for the gas turbine, which has a good cooling effect and high cooling efficiency and is beneficial to prolonging the service life of the gas turbine.

The embodiment of the invention also provides a gas turbine with the flame tube for the gas turbine.

A combustor basket for a gas turbine according to an embodiment of the present invention includes: a cylinder having a gas passage for hot gas to flow through, the cylinder having a first end and a second end, the first end of the cylinder being adapted for the hot gas to flow into the gas passage and the second end of the cylinder being adapted for the hot gas to flow out of the gas passage; the fin is established on the periphery wall of barrel, the fin can be followed from the first end of barrel extremely the direction spiral extension of the second end of barrel, just the height dimension H of fin is along the spiral extending direction height of fin changes.

According to the combustor basket for the gas turbine, which is disclosed by the embodiment of the invention, the combustor basket for the gas turbine has a good cooling effect and high cooling efficiency, and the service life of the gas turbine is prolonged.

In some embodiments, the cylinder includes a first section and a second section, the airflow velocity on the peripheral side of the first section is less than the airflow velocity on the peripheral side of the second section, and the height dimension H1 of the peripheral side of the first section is greater than the height dimension H2 of the peripheral side of the second section.

In some embodiments, the first section is a plurality of sections, the second section is a plurality of sections, and the plurality of first sections and the plurality of second sections alternate in a direction from the first end of the barrel to the second end of the barrel.

In some embodiments, the cross section of the fins on the outer periphery of the first section along the spiral extending direction of the fins is one or a combination of sawtooth shape, city wall shape and lace shape.

In some embodiments, the first section of peripheral side elements has a height dimension H1 of 0.8 millimeters to 1.2 millimeters.

In some embodiments, the fins have a helix angle α greater than 60 degrees and less than 90 degrees.

In some embodiments, a cross section of at least a part of the fins along a spiral extending direction of the fins or a cross section of at least a part of the fins is one or a combination of a sawtooth shape, a city wall shape and a lace shape.

In some embodiments, the fins have a height dimension H of 0.5 millimeters to 1.2 millimeters.

In some embodiments, the width dimension W of the ribs is 0.5 mm to 1.5 mm.

In some embodiments, the pitch L of the fins is 5 mm to 20 mm.

In some embodiments, the rib has a first side face and a second side face which are oppositely arranged, the first side face and the second side face both extend along the spiral extending direction of the rib, the first side face and the peripheral wall of the cylinder body form an included angle and are smoothly connected, and the second side face and the peripheral wall of the cylinder body form an included angle and are smoothly connected.

According to the embodiment of the invention, the gas turbine comprises the flame tube, and the flame tube is the flame tube according to any one of the embodiments.

Drawings

Fig. 1 is a schematic perspective view of a combustor basket according to an embodiment of the present invention.

FIG. 2 is a schematic side view of the liner of FIG. 1.

Fig. 3 is a partially enlarged schematic view at a in fig. 2.

Fig. 4 is a schematic cross-sectional view at B-B in fig. 2.

Fig. 5 is a partially enlarged schematic view at C in fig. 4.

FIG. 6 is a first segment schematic view of a liner according to an embodiment of the invention.

FIG. 7 is a schematic view of a serrated rib in accordance with an embodiment of the present invention.

FIG. 8 is a schematic view of a city wall fin according to an embodiment of the invention.

FIG. 9 is a schematic view of a lace-like rib according to an embodiment of the present invention.

FIG. 10 is a schematic diagram of a combination rib according to an embodiment of the present invention.

Reference numerals:

a cylinder body 1; a gas channel 11;

a rib 2; a first side 21; a second side 22; a spiral outer peripheral surface 23; a spiral groove 24.

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.

As shown in fig. 1 to 6, a combustor basket for a gas turbine (hereinafter, simply referred to as a combustor basket) according to an embodiment of the present invention includes a basket body 1 and fins 2.

A gas channel 11 for hot gas circulation is arranged in the cylinder body 1, the cylinder body 1 is provided with a first end and a second end, the first end of the cylinder body 1 is suitable for hot gas to flow into the gas channel 11, and the second end of the cylinder body 1 is suitable for hot gas to flow out of the gas channel 11.

Specifically, as shown in fig. 1 and fig. 2, a gas channel 11 is provided in the cylinder 1, the first end of the cylinder 1 is the front end of the cylinder 1, and the second end of the cylinder 1 is the rear end of the cylinder 1, during use, hot gas can flow into the gas channel 11 from the front end of the cylinder 1, and then flow out from the rear end of the cylinder 1.

The fins 2 are arranged on the peripheral wall of the cylinder 1, the fins 2 extend spirally along the direction from the first end of the cylinder 1 to the second end of the cylinder 1, and the height dimension H of the fins 2 can be changed along the spiral extending direction of the fins 2.

Specifically, as shown in fig. 1 and 2, the fins 2 are provided on the outer peripheral wall of the cylinder 1 and spirally wound on the outer peripheral side of the cylinder 1 in the front-to-rear direction, and it should be noted that the fins 2 may be disposed on the outer peripheral side of a part of the cylinder 1, and the outer peripheral side of the cylinder 1 may be covered with the fins 2.

As shown in fig. 5, the fins 2 have a height dimension H, which is the dimension of the fins 2 in the radial direction of the cylinder 1. The height dimension H of the fins 2 may be different along the spiral extension direction of the fins 2, for example, the height dimension H of the fins 2 may be gradually larger or smaller along the front-to-back direction, or may be first larger and then smaller.

In the present embodiment, the main flow on the outer peripheral side of the flame tube flows in the rear-to-front direction.

According to the flame tube of the embodiment of the invention, the separation vortex can be formed at the downstream of the spiral outer peripheral surface 23 of the fin 2, and the separation vortex can break the flow structure (main flow) of the outer side surface of the flame tube, so that the heat exchange at the outer peripheral side of the flame tube can be enhanced. In addition, as shown in fig. 5 and fig. 6, a spiral groove 24 is formed between the spirally wound fins 2 and the flame tube, turbulence is formed in the spiral groove 24, since the spiral groove 24 is separated by the fins 2, the turbulence in the spiral groove 24 is relatively independent and does not interfere with each other, and when a local main flow changes, the turbulence structure in the adjacent spiral groove 24 is not affected, so that the cooling effect is more stable. The spirally arranged fins 2 can increase the contact area between the fins 2 and the main flow, further increasing the cooling efficiency.

In addition, because the height dimension of the fins 2 gradually changes along with the extension direction of the fins 2, the change of the height dimension can further increase the disturbance to the main flow structure, and form disturbed flow and secondary flow vortex, thereby further improving the cooling efficiency of the flame tube. Due to the enhanced cooling effect and cooling efficiency of the combustor basket, the service life of the combustor basket is increased and the operation is more stable, thereby facilitating the extension of the service life of the gas turbine.

In some embodiments, the cylinder 1 includes a first section and a second section, the airflow velocity on the outer periphery of the first section is less than the airflow velocity on the outer periphery of the second section, and the height dimension H1 of the fins 2 on the outer periphery of the first section is greater than the height dimension H2 of the fins 2 on the outer periphery of the second section.

Specifically, as shown in fig. 1, the barrel 1 may include a first section (not shown) and a second section (not shown) in a front-to-rear direction, both of which are axial sections of the barrel 1, during use of the liner, the gas flow rate at the outer periphery of the first segment is less than the gas flow rate at the outer periphery of the second segment, it being noted that the position of the first and second segments may be determined empirically and/or by means of sensor monitoring, for example, in the design stage, the flame tube may be first installed in the combustion chamber, and then a plurality of sensors may be provided on the outer circumferential side of the flame tube, the sensors may sense the air flow velocity, and then simulating the operation condition of the gas turbine, and confirming the position of the first section on the cylinder body 1 by monitoring the air flow speed of each section of the cylinder body 1, wherein the rest positions on the cylinder body 1 except the first section can be regarded as the second section.

As shown in fig. 6, the height dimension H1 of the element 2 corresponding to the first segment is greater than the height dimension H2 of the element 2 corresponding to the second segment. The larger the height dimension of the fins 2, the more remarkable the turbulent flow effect of the fins 2, and the better the cooling effect and cooling efficiency at that point, whereby the cooling performance under the condition of the load (low flow rate) on the outer peripheral side of the cylindrical body 1 can be improved by increasing the height dimension H1 of the first-stage outer peripheral-side fins 2.

In some embodiments, the first section is plural, the second section is plural, and the plural first sections and the plural second sections are alternately arranged in a direction from the first end of the barrel 1 to the second end of the barrel 1.

Specifically, the outer peripheral side of the cylinder 1 may have a plurality of hot spot positions (low flow rate positions), and correspondingly, the cylinder 1 has a plurality of first segments arranged at intervals along the extending direction of the cylinder 1. It should be noted that, except the first section, the cylinder 1 can be regarded as the second section, and therefore, the plurality of first sections and the plurality of second sections are alternately arranged one by one along the extending direction of the cylinder 1. Therefore, each position on the outer circumferential side of the flame tube can be ensured to have a good cooling effect.

In some embodiments, the first section of peripheral side elements 2 varies in height along the helical extension of the elements 2. The fins 2 of which height varies can form turbulent flow and secondary flow vortex, whereby the cooling effect and cooling efficiency of the outer peripheral side of the first stage can be further enhanced.

In some embodiments, the cross section of the first section of the peripheral fins 2 along the spiral extension direction of the fins 2 is one or a combination of sawtooth shape, city wall shape and lace shape.

Specifically, the cross section of the first-stage outer circumferential-side fin 2 in the direction along the spiral extension of the fin 2 is the cross section of the first-stage outer circumferential-side fin 2 in the tangential direction thereof, and the cross section of the first-stage outer circumferential-side fin 2 may be serrated, as shown in fig. 7; or may be city wall shaped as shown in fig. 8; may be lace-shaped, as shown in fig. 9; a combination of zigzag and city-wall shapes, a combination of city-wall and lace shapes, and the like may be employed, as shown in fig. 10.

Therefore, the turbulent flow of the main flow structure can be further enhanced, and the cooling effect and the cooling efficiency are further enhanced.

In some embodiments, the height dimension H1 of the first peripheral rib section 2 is 0.8 mm to 1.2 mm. Specifically, as shown in fig. 6, the height dimension H1 of the fins 2 on the outer peripheral side of the first stage may be any value between 0.8 mm and 1.2 mm, for example, the height dimension H1 may be 0.8 mm, 0.9 mm, 1 mm, 1.1 mm, 1.2 mm, or the like. The height H1 is designed in the above-mentioned range to achieve a turbulent flow effect on the one hand and to avoid the situation that the fins 2 are high enough to disturb the main flow on the other hand.

In some embodiments, the helix angle α of the fins 2 is greater than 60 degrees and less than 90 degrees. Specifically, as shown in FIG. 3, the helix angle α of the fins 2 may be any value greater than 60 degrees and less than 90 degrees, for example, the helix angle α may be 65 degrees, 70 degrees, 75 degrees, 80 degrees, 85 degrees, 87 degrees, and the like. The helix angle α is designed within the above range, which on the one hand allows a higher helix density of the fins 2, which is beneficial for increasing the heat dissipation area, and on the other hand allows a larger angle between the fins 2 and the main flow direction, which is beneficial for forming turbulence.

In some embodiments, the cross-section of at least part of the fins 2 in the direction of the helical extension of the fins 2 or the cross-section of at least part of the fins 2 is one or a combination of serrated, merlony, laced.

Specifically, as shown in fig. 5, a cross section of the rib 2 is shown, a section of the rib 2 extending spirally is a section perpendicular to the cross section of the rib 2, and the section of the rib 2 extending spirally may be one of a saw-tooth shape, a city wall shape and a lace shape, or a combination of two or more of the saw-tooth shape, the city wall shape and the lace shape, as shown in fig. 7 to 10. Similarly, the cross section of the rib 2 may be one of a saw-tooth shape, a city wall shape and a lace shape, or a combination of two or more of a saw-tooth shape, a city wall shape and a lace shape, as shown in fig. 7 to 10.

Therefore, the turbulent flow of the main flow structure can be further enhanced, and the cooling effect and the cooling efficiency are further enhanced.

In some embodiments, the height dimension H of the fins 2 is between 0.5 mm and 1.2 mm. Specifically, as shown in fig. 5, the height dimension H of the fins 2 may be any value between 0.5 mm and 1.2 mm, for example, the height dimension H may be 0.5 mm, 0.6 mm, 0.7 mm, 0.8 mm, 0.9 mm, 1 mm, 1.1 mm, 1.2 mm, and the like.

In some embodiments, the width dimension W of the fins 2 is 0.5 mm to 1.5 mm. Specifically, as shown in fig. 5, the width dimension W of the rib 2 may be any value between 0.5 mm and 1.5 mm, for example, the width dimension W may be 0.5 mm, 0.6 mm, 0.7 mm, 0.8 mm, 0.9 mm, 1 mm, 1.1 mm, 1.2 mm, 1.3 mm, 1.4 mm, 1.5 mm, etc.

In some embodiments, the pitch L of the fins 2 is between 5 mm and 20 mm. Specifically, as shown in fig. 5, the pitch L of the fins 2 may be any value between 5 mm and 20 mm, for example, the pitch L may be 5 mm, 6 mm, 7 mm, 8 mm, 9 mm, 10 mm, 11 mm, 12 mm, 13 mm, 14 mm, 15 mm, 17 mm, 18 mm, 19 mm, 20 mm, and the like.

In some embodiments, the fins 2 have a first side 21 and a second side 22 arranged opposite to each other, the first side 21 and the second side 22 each extending in the direction of the helical extension of the fins 2, the first side 21 being angled and smoothly connected to the peripheral wall of the cylinder 1, and the second side 22 being angled and smoothly connected to the peripheral wall of the cylinder 1.

Specifically, as shown in fig. 6, the first side 21 is a front side of the rib 2, the second side 22 is a rear side of the rib 2, the first side 21 and the second side 22 are spirally wound on an outer circumferential side of the cylinder 1, the first side 21 is substantially perpendicular to an outer circumferential wall of the cylinder 1, the first side 21 is in rounded transition with the outer circumferential wall of the cylinder 1, the second side 22 is substantially perpendicular to the outer circumferential wall of the cylinder 1, and the second side 22 is in rounded transition with the outer circumferential wall of the cylinder 1. Therefore, on one hand, the connection strength of the fins 2 and the cylinder body 1 can be ensured, and on the other hand, the condition of dead angles generated in the spiral groove 24 is avoided, so that turbulent flow in the spiral groove 24 can smoothly flow, and the improvement of heat dissipation is facilitated.

In some embodiments, the outer circumference of the cylinder 1 may be provided with a plurality of fins 2, and the plurality of fins 2 are spirally wound on the outer circumference of the cylinder 1, and a spiral groove 24 is formed between two adjacent fins 2.

A gas turbine according to an embodiment of the present invention is described below.

According to the embodiment of the invention, the gas turbine comprises the flame tube, and the flame tube can be the flame tube described in the embodiment. Specifically, the gas turbine comprises a combustion chamber, a flame tube, a fuel injection device and a transition section, wherein the flame tube is arranged in the combustion chamber, the fuel injection device is arranged at the front end of the flame tube, the transition section is connected to the rear end of the flame tube, the transition section is a transition pipe, and the transition section is connected between the flame tube and the turbine. Part of air compressed by the air compressor flows from back to front along the peripheral side of the flame tube, exchanges heat with the tube body and the fins on the peripheral side of the flame tube, and then cools the flame tube, returns back to flow into the flame tube through the front end device of the flame tube, and is mixed with fuel sprayed by the fuel spraying device for combustion.

According to the gas turbine provided by the embodiment of the invention, the flame tube of the gas turbine has a good cooling effect and high cooling efficiency, and the service life of the gas turbine is prolonged.

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.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless explicitly specifically defined otherwise.

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.

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.

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.