CN216518159U - Gas film cooling structure for gas turbine blade - Google Patents
Gas film cooling structure for gas turbine blade Download PDFInfo
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- CN216518159U CN216518159U CN202122805716.7U CN202122805716U CN216518159U CN 216518159 U CN216518159 U CN 216518159U CN 202122805716 U CN202122805716 U CN 202122805716U CN 216518159 U CN216518159 U CN 216518159U
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Abstract
The utility model discloses an air film cooling structure for a turbine blade of a gas turbine, which comprises an air film hole and a convex structure arranged at the upstream of the air film hole on the turbine blade and an end wall, wherein the convex structure takes the axis of an outlet of the air film hole parallel to the incoming flow direction of a main flow as a symmetric axis, and the section of the convex structure consists of two sections of smoothly-transitional circular arcs
And with
And (4) forming. The utility model arranges a section at the upstream of the outlet of the air film hole and is smoothly connected by two sectionsThe convex structure formed by the connected arcs improves the air film cooling efficiency of the turbine blade on the premise of not introducing additional aerodynamic loss.
Description
Technical Field
The utility model belongs to the technical field of gas turbine blade cooling, and particularly relates to an air film cooling structure for a gas turbine blade, which can provide an efficient gas film cooling effect for the gas turbine blade.
Background
The initial temperature of the current heavy-duty gas turbine is continuously improved, and higher requirements are provided for blade design. The temperature of the gas in the turbine is far higher than the allowable temperature of the blade material, the temperature of the gas is also increased, the thermal load of the blade is increased, the thermal stress is increased, the initial temperature of the turbine inlet is increased at a speed far higher than the speed of increasing the allowable temperature of the material through the material technology, and therefore the cooling technology of the gas turbine becomes an extremely important ring in the technology of the gas turbine.
The film cooling is a common cooling method in turbine blades, cold air is injected into a main flow through a film hole or a slot structure on the surface of the turbine blade, a layer of film covering is formed on the outer surface of the blade, and a metal blade is isolated from the high-temperature main flow and mixed with the high-temperature main flow to reduce the temperature of the metal blade, so that a high-temperature part is in a temperature-resistant range. The air film cooling is related to the mixing and interaction of cold air and main flow, the flow field structure is complex and directly related to the working condition of the turbine, and the air film cooling is always a hot point problem of the design of the turbine blade cooling structure.
Analysis of the flow field structure upstream and downstream of the exit of the film hole shows that a pair of counter-rotating vortices (kidney vortex pair) are formed downstream of the exit of the film hole due to mutual mixing of the main flow and the cold air, as shown in fig. 1. By weakening the strength of the kidney-shaped vortex pair, the air film cooling effect can be significantly improved. The convex structure is arranged at the upstream of the film hole, the effect of the cold air attaching to the wall surface and the transverse covering area of the cold air can be increased by changing the shape and the height of the convex structure, and the main flow gas can form a positive secondary flow kidney-shaped vortex near the outlet of the film hole due to the turbulent action of the convex structure, so that the strength of the cooling gas flow kidney-shaped vortex pair is weakened, and the cooling efficiency of the film hole is improved. Therefore, the upstream structures of the air film holes in different shapes are provided, but although the existing structures can effectively improve the air film cooling efficiency, part of the structures are difficult to process and high in cost and are difficult to adopt in an actual turbine, and part of the structures have large influence on the main flow and bring extra aerodynamic loss.
SUMMERY OF THE UTILITY MODEL
Aiming at the defects in the prior art, the utility model provides an air film cooling structure for a turbine blade of a gas turbine, the structural section is composed of two sections of smoothly-transitional arcs, and the air film cooling efficiency of the turbine blade can be improved on the premise of not introducing extra aerodynamic loss.
The utility model is realized by adopting the following technical scheme:
the gas film cooling structure for turbine blade of gas turbine includes film holes in the turbine blade and end wall and the raised structure in the upstream of the film holes, and the raised structure has film hole outlet parallel to the main flow direction as the symmetrical axis and has two sections of smooth transition arcs
And
and (4) forming.
The utility model further improves the following steps: the first section of arc of the section of the convex structure
With O1As a center of circle, r1The intersection point of the right side of the arc and the wall surface is denoted as A, and the left end point is denoted as B.
The utility model further improves the following steps: circular arc
Center of circle O of1The distance S from the front end of the downstream air film hole ranges from 0.5D to 3D, and the center of the circle is O1The vertical distance h from the wall surface ranges from 0.5D to 2D, and the radius r1Value range ofIs 1.2 to 2.2 hours.
The utility model further improves the following steps: circular arc
Left end point B and circle center O1The connecting line of (A) intersects with the wall surface at a point D, the included angle between the BD and the direction vertical to the wall surface is theta, and the value range of theta is 0-30 degrees.
The utility model further improves the following steps: second arc of the convex profile
To be located at point O on the BD line2As the center of circle, in r2The radius is defined as the radius, and the arc intersects the wall surface at the point C.
The utility model further improves the following steps: second arc of the convex profile
Center of circle O of2At the midpoint of the BD line, radius r2Has a value of BO2Length of (d).
The utility model further improves the following steps: the width of the protruding structure in the spanwise direction is W, and the value range of W is 0.5D-1.2D.
The utility model further improves the following steps: the gas film hole outlet has a spanwise width D, and the inclination angle alpha between the cooling airflow and the main flow direction is 0-90 degrees.
The utility model has at least the following beneficial technical effects:
according to the film cooling structure for the turbine blade of the gas turbine, the convex structure with the section formed by two sections of smoothly connected arcs is arranged at the upstream of the outlet of the film hole, so that the film cooling efficiency of the turbine blade is improved on the premise of not introducing extra aerodynamic loss.
The utility model has the advantages that the structure is simple in form, obvious in effect and convenient to implement, and the pneumatic loss caused by the small size and smooth transition of the bulge is negligible.
Drawings
FIG. 1 is a schematic representation of the formation of a vortex pair downstream of a film hole.
Fig. 2 is a three-dimensional schematic of the present invention.
Fig. 3 is a top view of the present invention.
Fig. 4 is a side view of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to the accompanying drawings and examples.
The utility model provides a film cooling structure for a turbine blade of a gas turbine, which comprises a film hole and a convex structure arranged on the upstream of the film hole on the turbine blade and the end wall.
The spanwise width of the air film hole is D, and the included angle between the air film hole and the wall surface is alpha. In the present embodiment, the spanwise width D is 1mm and the angle α is 30 °.
The convex structure takes the axis of the outlet of the air film hole parallel to the incoming flow direction of the main flow as a symmetrical axis, and the section of the convex structure is formed by two sections of arcs in smooth transition
And
and (4) forming. First arc of convex section
With O1As a center of circle, r1The intersection point of the right side of the arc and the wall surface is denoted as A, and the left end point is denoted as B.
Circular arc
Center of circle O of1The distance S from the front end of the downstream air film hole ranges from 0.5D to 3D, and S is preferably 2.5mm in the embodiment.
Center of circle O1Value range of vertical distance h from wall surfaceIs 0.5D to 2D, and h is preferably 1mm in this embodiment.
Radius r1The value range of (a) is 1.2 h-2.2 h, and r is preferably selected in the embodiment1Is 1.5 mm.
Circular arc
Left end point B and circle center O1The BD and the direction perpendicular to the wall surface form an angle theta, the value range of theta is 0-30 degrees, and theta is preferably 15 degrees in the present embodiment.
Second arc of convex profile
To be located at the midpoint O on the BD line2Centered on BO2The radius is defined as the radius, and the arc intersects the wall surface at the point C.
The width of the protruding structure in the spanwise direction is W, the value range of W is 0.5D-1.2D, and W is preferably 0.8mm in the embodiment.
In the embodiment, the convex structure consisting of two sections of smoothly connected circular arcs is arranged at the upstream of the outlet of the air film hole, so that the air film cooling efficiency of the turbine blade is improved on the premise of not introducing additional aerodynamic loss.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the utility model, but rather as the subject matter of any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention.
Claims (8)
1. The gas film cooling structure for the turbine blade of the gas turbine is characterized by comprising gas film holes arranged on the turbine blade and the end wall and a convex structure at the upstream of the gas film holes, wherein the convex structure takes the axis of the outlet of the gas film holes parallel to the incoming flow direction of a main flow as a symmetrical axis, and the section of the convex structure is formed by two sections of arc in smooth transition
And
and (4) forming.
2. The film cooling structure for a turbine blade of a gas turbine according to claim 1, wherein: the first section of arc of the section of the convex structure
With O1As a center of circle, r1The intersection point of the right side of the arc and the wall surface is denoted as A, and the left end point is denoted as B.
3. The film cooling structure for a turbine blade of a gas turbine according to claim 2, wherein: circular arc
Center of circle O of1The distance S from the front end of the downstream air film hole ranges from 0.5D to 3D, and the center of the circle is O1The vertical distance h from the wall surface ranges from 0.5D to 2D, and the radius r1The value range of (A) is 1.2 h-2.2 h.
4. The film cooling structure for a turbine blade of a gas turbine according to claim 2, wherein: circular arc
Left end point B and circle center O1The connecting line of (A) intersects with the wall surface at a point D, the included angle between the BD and the direction vertical to the wall surface is theta, and the value range of theta is 0-30 degrees.
5. The film cooling structure for a turbine blade of a gas turbine according to claim 2, wherein: the second section of arc of the section of the convex structure
To be located at point O on the BD line2As the center of circle, in r2The radius is defined as the radius, and the arc intersects the wall surface at the point C.
6. The film cooling structure for a turbine blade of a gas turbine according to claim 5, wherein: the second section of arc of the section of the convex structure
Center of circle O of2At the midpoint of the BD line, radius r2Has a value of BO2Length of (d).
7. The film cooling structure for a turbine blade of a gas turbine according to claim 1, wherein: the width of the protruding structure in the spanwise direction is W, and the value range of W is 0.5D-1.2D.
8. The film cooling structure for a turbine blade of a gas turbine according to claim 1, wherein: the outlet of the film hole has a width D in the spanwise direction, and the inclination angle alpha between the cooling airflow and the main flow direction is 0-90 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122805716.7U CN216518159U (en) | 2021-11-16 | 2021-11-16 | Gas film cooling structure for gas turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122805716.7U CN216518159U (en) | 2021-11-16 | 2021-11-16 | Gas film cooling structure for gas turbine blade |
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| Publication Number | Publication Date |
|---|---|
| CN216518159U true CN216518159U (en) | 2022-05-13 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202122805716.7U Active CN216518159U (en) | 2021-11-16 | 2021-11-16 | Gas film cooling structure for gas turbine blade |
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| CN (1) | CN216518159U (en) |
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2021
- 2021-11-16 CN CN202122805716.7U patent/CN216518159U/en active Active
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