CN218644343U - Cooling device and gas turbine stationary blade - Google Patents

Abstract

The utility model provides a cooling device and gas turbine quiet leaf, cooling device are applicable to the gas turbine quiet leaf, and the gas turbine quiet leaf includes the blade, and the blade includes the end wall, and cooling device includes: an impact plate covering the first side of the end wall; the first groove is formed in the first side face of the end wall and forms a cold air cavity together with the impact plate; the impact hole is formed in the impact plate, so that cold air enters the cold air cavity through the impact hole to cool the bottom surface and the side surface of the first groove; the streamline rib is arranged on the bottom surface of the first groove and used for changing the flowing direction of the cold air in the cold air cavity. The cooling device provided by the utility model is provided with the streamline ribs in the cold air cavity, thereby disturbing the air flow in the cold air cavity and improving the heat transfer enhancement of the end wall; meanwhile, the streamline ribs can reduce the vortexes behind the ribs, reduce the flow resistance, reduce the pressure loss, reduce the pressure requirement of cold air incoming flow, effectively reduce the temperature of the end wall and improve the operation stability of the stationary blade of the gas turbine.

Description

Cooling device and gas turbine stationary blade

Technical Field

The utility model relates to an aeroengine, gas turbine, steam turbine technical field especially relate to a cooling device and gas turbine quiet leaf.

Background

Along with the development of science and technology, the inlet air temperature of the blades of the gas turbine is continuously improved and is far beyond the melting point of the blade materials, and in order to ensure the safe and reliable operation of the gas turbine, the blades of the gas turbine need to be cooled so that the temperature and stress distribution of the blades of the gas turbine are kept reasonable. For the stator blade endwalls, impingement cooling and air film cooling are generally adopted, wherein after cold air flows into the impingement plate from a cold air hole, the cold air impacts the endwalls, and the impacted exhaust air flows into endwall air film holes or blade bodies to form air film covers or cool the blade bodies on the surfaces of the endwalls. The impact target surface of the end wall is a plane, and the end wall on the cold air cavity side is only subjected to impact cooling and is not provided with other enhanced heat exchange devices; or the column ribs are arranged, but the flow loss is large, and the requirement on the pressure of the cold air inlet is high; in addition, the cross flow of spent air after impingement affects the downstream impingement effect.

SUMMERY OF THE UTILITY MODEL

In view of the above, the present invention provides a cooling device and a gas turbine stationary blade.

According to an aspect of the utility model, a cooling device is provided, is applicable to the gas turbine quiet leaf, and the gas turbine quiet leaf includes the blade, and the blade includes the end wall, and cooling device includes:

an impact plate covering the first side of the end wall;

the first groove is formed in the first side face of the end wall and forms a cold air cavity together with the impact plate;

the impact holes are formed in the impact plate, so that cold air enters the cold air cavity through the impact holes to cool the bottom surface and the side surface of the first groove;

the streamline rib is arranged on the bottom surface of the first groove and used for changing the flowing direction of the cold air in the cold air cavity.

Alternatively, in the horizontal direction, the streamlined ribs alternate with the impingement holes.

Optionally, the cross section and the longitudinal face of the streamlined rib are both streamlined, the cross section of the streamlined rib includes a drop shape, and the longitudinal face of the streamlined rib includes a half-core shape.

Optionally, one end of the streamline rib is a blunt end, and the other end of the streamline rib is a pointed end, the blunt end faces the flow direction of the cold air in the cold air cavity, and the pointed end faces away from the flow direction of the cold air in the cold air cavity.

Optionally, the impingement holes are arranged on the impingement plate in a uniform or non-uniform, array or non-array form;

the cross-section of the impingement holes comprises a circular shape.

Optionally, the height of the streamlined rib is less than the depth of the first groove.

Optionally, the method further comprises: the air film hole is formed in the bottom face of the first groove and used for enabling cold air to flow out of the cold air cavity, so that the outer side of the end wall and the blades are cooled by the cold air.

Optionally, a blade cavity is formed in the blade, an end wall vent hole is further formed in the bottom of the first groove, and the air film hole penetrates through the bottom of the first groove, so that the cold air flows out of the cold air cavity and enters the blade body outer flow field of the blade, and the cold air enters the blade cavity through the end wall vent hole to cool the blade.

Optionally, the axis of the film hole and the bottom surface of the first groove form a preset angle, and an included angle between the flowing direction of the cold air flowing out through the film hole and the direction of the fuel gas passing through the surface of the blade is an acute angle.

According to a second aspect of the present invention, there is provided a gas turbine stationary blade using the above-mentioned cooling device, the gas turbine stationary blade including blades, the end walls of the blades all being provided with the cooling device.

The utility model provides a cooling device is applicable to the quiet leaf of gas turbine, and the quiet leaf of gas turbine includes the blade, and the blade includes the end wall, and cooling device includes: an impingement plate covering the first side of the end wall; the first groove is formed in the first side face of the end wall and forms a cold air cavity together with the impact plate; the impact hole is formed in the impact plate, so that cold air enters the cold air cavity through the impact hole to cool the bottom surface and the side surface of the first groove; the streamline rib is arranged on the bottom surface of the first groove and used for changing the flowing direction of the cold air in the cold air cavity. The cooling device provided by the utility model is provided with the streamline ribs in the cold air cavity, thereby disturbing the air flow in the cold air cavity and improving the heat transfer enhancement of the end wall; meanwhile, the streamline ribs can reduce the vortexes behind the ribs, reduce the flow resistance, reduce the pressure loss, reduce the pressure requirement of cold air incoming flow, effectively reduce the temperature of the end wall and improve the operation stability of the stationary blade of the gas turbine.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.

Fig. 1 schematically illustrates a cross-sectional view of a cooling device according to an embodiment of the present invention;

fig. 2 schematically illustrates a top view of a cooling device according to an embodiment of the present invention;

fig. 3 schematically illustrates a cross-sectional view and a top view of a streamlined rib of a cooling apparatus provided by an embodiment of the present invention;

fig. 4A schematically illustrates a flow of cool air in a cooling device according to an embodiment of the present invention;

fig. 4B schematically illustrates a schematic view of a streamlined rib turbulent air flow in a cooling device according to an embodiment of the present invention; and

fig. 5 schematically illustrates a top view of an impingement plate of a cooling device according to an embodiment of the present invention.

Description of reference numerals:

1 impacting the hole; 2 streamline ribs; 3, air film hole; 4, impacting a plate; 5 end walls; 6 a cold air cavity; 7, blades; 8 a first groove; and 9, end wall vent holes.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in detail with reference to the accompanying drawings. It is to be understood that the embodiments described are only some of the embodiments of the present invention, and not all of them. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art on the premise of each creative work belong to the protection scope of the present invention.

The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The terms "comprises," "comprising," and the like, as used herein, specify the presence of stated features, steps, operations, and/or components, but do not preclude the presence or addition of one or more other features, steps, operations, or components.

In the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," "fixed," and the like are to be construed broadly, e.g., as meaning a fixed connection, a removable connection, or an integral part; can be mechanically connected, electrically connected or can communicate with each other; either directly or indirectly through intervening media, either internally or in any other suitable relationship. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.

All terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs, unless otherwise defined. It is noted that the terms used herein should be interpreted as having a meaning that is consistent with the context of this specification and should not be interpreted in an idealized or overly formal sense.

It should be noted that, in the drawings or the description of the specification, the same drawing numbers are used for similar or identical parts to indicate that the parts have the same or similar components, and the components have the same or similar functions in each embodiment. Furthermore, implementations not shown or described in the drawings are of a form known to those of ordinary skill in the art. Additionally, although examples may be provided herein of parameters including particular values, it should be appreciated that the parameters need not be exactly equal to the respective values, but may approximate the respective values within acceptable error margins or design constraints.

In the description of the present invention, it should be noted that the terms "directly above", "directly below", "both ends", "both sides", and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation.

Hereinafter, examples will be provided to explain embodiments of the present invention in detail. The advantages and effects of the present invention will be more apparent through the disclosure of the present invention. The drawings attached hereto are simplified and serve as illustrations. The number, shape, and size of the components shown in the drawings may be modified depending on the actual situation, and the arrangement of the components may be more complicated. The present invention can be practiced or applied in other ways without departing from the spirit and scope of the present invention, and various changes and modifications can be made.

Fig. 1 to 5 respectively show a schematic structural diagram of a cooling device according to an embodiment of the present invention. It is understood that the structure of a cooling device and its components in fig. 1 to 5 is only schematic for helping those skilled in the art to understand the technical content of the present invention, but it is not meant to limit the implementation of the present invention. The layout, shape and the like of a cooling device and its components can be adapted according to actual needs.

Fig. 1 schematically shows a cross-sectional view of a cooling device according to an embodiment of the present invention. Fig. 5 schematically illustrates a top view of an impingement plate of a cooling device according to an embodiment of the present invention.

As shown in fig. 1 and 5, in an embodiment of the present invention, the cooling device is applied to a gas turbine stationary blade, the gas turbine stationary blade includes a blade 7, the blade 7 includes an endwall 5, and the cooling device includes: a striking plate 4 covering a first side surface of the end wall 5; a first groove 8, which is arranged on the first side surface of the end wall 5 and forms a cold air cavity 6 with the impact plate 4; the impact hole 1 is formed in the impact plate 4, so that cold air enters the cold air cavity 6 through the impact hole 1 to cool the bottom surface and the side surface of the first groove 8; and the streamline rib 2 is arranged on the bottom surface of the first groove 8 and is used for changing the flowing direction of the cold air in the cold air cavity 6.

In the embodiment, a first groove 8 is formed on an end wall 5 of a blade 7 of a gas turbine stator blade, and an impact plate 4 is covered on the upper portion of the first groove 8, so that a cold air cavity 6 is formed between the impact plate 4 and the first groove 8, impact holes 1 for allowing cold air to enter the cold air cavity 6 are formed on the impact plate 4, the impact holes 1 are formed on the impact plate 4 in a uniform or non-uniform, array or non-array manner, and the cross section of the impact holes 1 can be circular. Make air conditioning get into air conditioning cavity 6 through impact hole 1 and cool off endwall 5 of blade 7 of gas turbine quiet leaf, when cooling endwall 5, air conditioning is impacted to endwall 5 after getting into air conditioning cavity 6 through impact hole 1, the air conditioning after the impact is called exhaust in this embodiment, exhaust can form the crossing current, influence air conditioning and to impact cooling effect, consequently, be provided with streamlined rib 2 in the bottom of first recess 8 in this embodiment, the height of streamlined rib 2 is less than the degree of depth of first recess 8, in order to utilize streamlined rib 2 to disturb the air current in air conditioning cavity 6, the intensive heat transfer in the air conditioning cavity 6 has been improved, thereby the cooling effect to endwall 5 has been improved.

It should be understood that the number of the streamlined ribs, the number and shape of the impingement holes, and the dimensional relationship among the components of the cooling device in fig. 1 are merely illustrative to help those skilled in the art understand the technical content of the present invention, and in particular, the number of the streamlined ribs, the number and shape of the impingement holes, and the dimensional relationship among the components of the cooling device may be selected according to the actual needs of the user, and are not limited thereto.

Fig. 2 schematically illustrates a top view of a cooling device according to an embodiment of the present invention.

As shown in fig. 2, in an embodiment of the present invention, the streamline ribs 2 and the impingement holes 1 are alternately arranged in the horizontal direction.

Referring to fig. 2, in the present embodiment, the position of the streamline rib 2 does not correspond to the position of the impact hole 1, but the streamline rib 2 is disposed downstream of the impact hole 1, where downstream refers to the downstream of the flow direction of the gas after the cold air enters the cold air cavity 6 through the impact hole 1, and the streamline rib 2 is disposed downstream of the impact hole 1 to guide the exhaust gas to directly impact the streamline rib 2, so that the streamline rib 2 is used to guide the exhaust gas to flow, change the exhaust gas flow direction, disturb the flow of the gas in the cooling cavity 6, and improve heat exchange. In addition, the streamline ribs 2 can reduce pressure loss to the maximum extent and improve heat exchange, and guide exhaust gas, so that the exhaust gas is prevented from directly impacting downstream impact airflow (the impact airflow refers to cold air entering the cold air cavity 6 through the impact holes 1), and the effect of downstream impact cooling is improved.

As shown in fig. 2, the angle of the streamline ribs 2 adjacent to the blades 7 is changed with the change of the streamline angle, so that the pressure loss of the flow can be reduced.

Fig. 3 schematically illustrates a cross-sectional view and a top view of a streamlined rib of a cooling device provided by an embodiment of the present invention.

As shown in fig. 3, in an embodiment of the present invention, the cross section and the longitudinal surface of the streamline rib 2 are streamline, the cross section of the streamline rib 2 includes a drop shape, and the longitudinal surface of the streamline rib 2 includes a half-heart shape.

In order to further promote the heat exchange, in the present embodiment, both the cross section and the longitudinal plane of the streamlined rib 2 are set to be streamlined, and referring to fig. 3, the cross section of the streamlined rib 2 is set to be in a drop shape, and the longitudinal plane of the streamlined rib 2 is set to be in a half-heart shape, it should be understood that the examples of the cross section and the longitudinal plane of the streamlined rib in the present embodiment are only schematic, so as to help those skilled in the art understand the technical content of the present invention, and specifically, the shape of the cross section and the longitudinal plane of the streamlined rib can be selected according to the actual needs of the user, and is not limited herein.

Fig. 4A schematically illustrates a schematic flow of cool air in a cooling device according to an embodiment of the present invention. Fig. 4B schematically illustrates a schematic view of a streamline rib disturbing airflow in a cooling device according to an embodiment of the present invention.

As shown in fig. 4A and 4B, in an embodiment of the present invention, one end of the streamline rib 2 is a blunt end, and the other end is a pointed end, the blunt end faces the flow direction of the cold air in the cold air cavity 6, and the pointed end faces away from the flow direction of the cold air in the cold air cavity 6.

In the present embodiment, in order to better utilize the streamline rib 2 to disturb the airflow in the cold air cavity 6, the streamline rib 2 is configured in a shape that one end is blunt and the other end is pointed, and at the same time, the blunt end of the streamline rib 2 faces upstream and the pointed end faces downstream, referring to fig. 4B, so as to reduce the swirl behind the streamline rib 2, reduce the flow resistance, reduce the pressure loss, and reduce the pressure requirement of the incoming cold air flow.

As shown in fig. 3, one end of the streamline rib 2 is a blunt end, the other end is a pointed end, the blunt end is a round ball structure, the ratio of the height H to the diameter D of the round ball is H/D = 1-2, and the ratio of the length S of the pointed end to the diameter D of the round ball is S/D = 1-2.

As shown in fig. 1, in an embodiment of the present invention, the cooling device further includes: and the air film hole 3 is formed in the bottom surface of the first groove 8, and the air film hole 3 is used for enabling cold air to flow out of the cold air cavity 6, so that the cold air can cool the outer side of the end wall 5 and the blade 7.

In this embodiment, a film hole 3 is opened at the bottom of the first groove 8, the gas in the cold air cavity 6 flows out of the cold air cavity 6 through the film hole 3, a film is formed on the outer side of the end wall 5, and the end wall 5 is further cooled.

The utility model discloses an in the embodiment, be provided with the blade cavity in the blade 7, the bottom of first recess 8 still is provided with end wall air vent 9, and air film hole 3 link up the bottom of first recess 8 to make air conditioning follow the outer flow field of blade body that air conditioning cavity 6 flows out entering blade 7, and so that air conditioning warp end wall air vent 9 gets into the blade cavity and cools off blade 7. In the present embodiment, the cool air portion in the cool air cavity 6 flows out from the film hole 3 into the flow field outside the blade body of the blade 7. Furthermore, the utility model provides a cooling device sets up the end wall 5 at the blade 7 of the quiet leaf of gas turbine, and is provided with the blade cavity in the blade 7, consequently, the air conditioning in the air conditioning cavity 6 can also get into the blade cavity through the end wall air vent 9 of first recess 8 bottom, cools off blade 7.

As shown in fig. 1, in an embodiment of the present invention, the axis of the film hole 3 is a predetermined angle with the bottom surface of the first groove 8, and the included angle between the flowing direction of the cool air flowing out through the film hole 3 and the direction of the gas passing through the surface of the blade 7 is an acute angle.

As shown in fig. 1, the axis of the film hole 3 in this embodiment is not perpendicular to the bottom surface of the first groove 8, but is at a predetermined angle, and the included angle between the flowing direction of the cool air flowing out through the film hole 3 and the flowing direction of the gas passing through the surface of the vane 7 is an acute angle, which can be referred to in fig. 1, and thus the flowing of the gas passing through the surface of the vane 7 is not affected. And the specific inclination in air film hole 3 can be set for according to actual demand, the utility model discloses do not do the restriction to this.

Based on above-mentioned cooling device, the utility model also provides an adopt above-mentioned cooling device's quiet leaf of gas turbine, this quiet leaf of gas turbine includes blade 7, all is provided with cooling device on the end wall 5 of blade 7.

With reference to fig. 1, in the present embodiment, the cooling device provided by the present invention is provided on both endwalls 5 of the blades 7 of the gas turbine stator blades, so as to cool all endwalls 5 of the blades 7.

In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed or operated in a specific orientation, and thus, should not be construed as limiting the present invention. Throughout the drawings, like elements are represented by like or similar reference numerals. Conventional structures or constructions will be omitted when they may cause confusion as to the understanding of the present invention. And the shapes, sizes and positional relationships of the components in the drawings do not reflect the actual sizes, proportions and actual positional relationships.

Similarly, in the above description of exemplary embodiments of the invention, various features of the invention are sometimes grouped together in a single embodiment, figure, or description thereof for the purpose of streamlining the disclosure and aiding in the understanding of one or more of the various disclosed aspects. Reference to the description of the terms "one embodiment," "some embodiments," "an example," "a specific example" or "some examples" or the like means 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 do not necessarily refer to the same embodiment or example. Rather, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

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

It will be appreciated by a person skilled in the art that various combinations and/or combinations of the features recited in the various embodiments and/or claims of the invention are possible, even if such combinations or combinations are not explicitly recited in the invention. In particular, various combinations and/or combinations of the features recited in the various embodiments and/or claims of the present invention may be made without departing from the spirit and teachings of the invention. All such combinations and/or associations fall within the scope of the present invention.

The above-mentioned embodiments further describe the objects, technical solutions and advantages of the present invention in detail, it should be understood that the above-mentioned embodiments are only examples of the present invention, and are not intended to limit the present invention. While the invention has been shown and described with reference to certain exemplary embodiments thereof, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims and their equivalents. Accordingly, the scope of the present invention should not be limited to the above-described embodiments, but should be defined not only by the appended claims, but also by equivalents thereof.

Claims (10)

1. A cooling device, adapted for a gas turbine vane, said gas turbine vane comprising a blade (7), said blade (7) comprising an endwall (5), said cooling device comprising:

an impact plate (4) covering a first side of the end wall (5);

a first groove (8) which is arranged on a first side surface of the end wall (5) and forms a cold air cavity (6) with the impact plate (4);

the impact hole (1) is formed in the impact plate (4) so that cold air enters the cold air cavity (6) through the impact hole (1) to cool the bottom surface and the side surface of the first groove (8);

the streamline rib (2) is arranged on the bottom surface of the first groove (8) and is used for changing the flowing direction of the cold air in the cold air cavity (6).

2. A cooling arrangement according to claim 1, characterised in that the streamlined ribs (2) alternate with the impingement holes (1) in the horizontal direction.

3. The cooling device according to claim 2,

the cross section and the longitudinal surface of the streamline rib (2) are streamline, the cross section of the streamline rib (2) comprises a water drop shape, and the longitudinal surface of the streamline rib (2) comprises a half-heart shape.

4. A cooling arrangement according to claim 1, characterised in that the streamlined rib (2) has a blunt end at one end and a pointed end at the other end, the blunt end facing in the direction of flow of the cold air in the cold air cavity (6) and the pointed end facing away from the direction of flow of the cold air in the cold air cavity (6).

5. The cooling device according to claim 1, characterized in that the impingement holes (1) open onto the impingement plate (4) in a uniform or non-uniform, arrayed or non-arrayed manner;

the cross section of the impact hole (1) comprises a circular shape.

6. A cooling device according to claim 1, characterized in that the height of the streamlined rib (2) is smaller than the depth of the first groove (8).

7. The cooling device of claim 1, further comprising: the air film hole (3) is formed in the bottom face of the first groove (8), and the air film hole (3) is used for enabling the cold air to flow out of the cold air cavity (6) so that the cold air is opposite to the outer side of the end wall (5) and the blades (7) are cooled.

8. A cooling device according to claim 7, characterized in that a blade cavity is arranged in the blade (7), the bottom of the first groove (8) is further provided with an end wall vent hole (9), the film hole (3) penetrates through the bottom of the first groove (8) to make the cool air flow out from the cool air cavity (6) into the blade body external flow field of the blade (7), and to make the cool air flow into the blade cavity through the end wall vent hole (9) to cool the blade (7).

9. A cooling device according to claim 7, characterized in that the axis of the film hole (3) is at a predetermined angle to the bottom surface of the first groove (8), and the angle between the direction of flow of the cold air flowing out through the film hole (3) and the direction of the combustion gas passing over the surface of the blade (7) is acute.

10. A gas turbine vane employing a cooling device according to any one of claims 1-9, characterized in that the gas turbine vane comprises blades (7), the endwalls (5) of which blades (7) are each provided with said cooling device.

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