Gas turbine blade coupled with double-layer wall and oscillating jet structure and method

Abstract

The invention discloses a gas turbine blade of a coupled double-layer wall and oscillating jet structure and a method, the gas turbine blade comprises a blade body, the blade body is provided with a front edge and a tail edge, the front edge is internally provided with a main air inlet cavity and is externally connected with a cold air input, and the tail edge is provided with an air outlet. A cooling interlayer is arranged between the main air inlet cavity and the outer wall of the blade body, and strength supporting is conducted between the cooling interlayer and the inner wall of the blade body through a plurality of side plates. Cold air is obliquely injected into the cooling interlayer through the air film holes in the wall between the main air inlet cavity and the cooling interlayer and injected into the outside through the heat exchange cavity and the air film holes in the corresponding positions, and the cold air injected into the cooling interlayer is treated by the multiple first jet flow oscillator sets; characteristic cold air generating high-frequency oscillation jet flow is sprayed out of the outer side of the blade body to form cold air film covering, the formed cold air film and high-temperature main flow above the blade body generate a mixing effect, and then the purpose of reducing the surface temperature of the blade body is achieved.

Description

Technical Field

[0001] The invention belongs to the technical field of gas turbine turbine blades, and in particular relates to a gas turbine turbine blade and a method for coupling a double-wall and oscillating jet structure. Background Art

[0002] Gas turbines are widely used in aviation, navigation, power generation, military and other fields. The first-stage guide vanes of the high-pressure turbine in the gas turbine need to withstand the highest gas temperature and the most complex stress environment. In order to protect the first-stage guide vanes of the high-pressure turbine, the conventional method is to adopt cooling technology. Currently, the cooling methods commonly used are blade internal impact cooling and blade surface film cooling. Traditional film cooling technology faces the defect of insufficient lateral heat transfer coverage. Summary of the invention

[0003] The object of the present invention is to provide a gas turbine blade and method having a coupled double-wall and oscillating jet structure to solve the above-mentioned problems.

[0004] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a gas turbine turbine blade coupled with a double-wall and oscillating jet structure, comprising a blade body, the blade body having a leading edge and a trailing edge, a main air intake cavity being provided inside the leading edge and connected to an external cold air input, a cooling interlayer being provided between the main air intake cavity and the outer wall of the blade body, and the cooling interlayer and the inner wall of the blade body being supported in strength by a plurality of side plates, a plurality of inclined air film holes 1 being provided on the wall outside the main air intake cavity connected to the cooling interlayer, a plurality of first jet oscillator groups being provided on the wall between the leading edge position and the cooling interlayer, and the cold air input into the main air intake cavity enters the cooling interlayer through the air film hole 1, and is then outputted obliquely by the first jet oscillator group to the outside of the blade body to form a cooling air film;

[0005] An auxiliary air intake cavity is also provided on the blade body at the bottom of one side of the main air intake cavity, a plurality of second jet oscillator groups are arranged on the wall between the auxiliary air intake cavity and the main air intake cavity, and air film holes 2 are provided between the auxiliary air intake cavity and the cooling interlayer, and between the cooling interlayer and the outer side of the blade body for outputting cold air.

[0006] Preferably, the inclination directions of the air film hole 1, the air film hole 2 and the first jet oscillator group are all inclined toward the trailing edge position, the air film hole 1 has the same inclination angle as the first jet oscillator group and the corresponding first jet oscillator group and the air film hole 1 are on the same inclined line.

[0007] Preferably, a plurality of heat exchange cavities are further provided inside the blade body for performing internal heat exchange on the areas not involved before the air film is formed by the external air film holes to form a composite cooling effect.

[0008] Preferably, air film holes for connecting the heat exchange cavity with the outside are provided on the wall between the heat exchange cavity and the cooling interlayer and between the wall between the cooling interlayer and the outside.

[0009] A method for cooling a gas turbine blade having an arbitrary coupled double-wall and oscillating jet structure, the specific steps are as follows:

[0010] Step 1: cold air is charged, and the cold air flow is directly charged into the main air intake cavity through the external cold air outlet, and is obliquely charged into the cooling interlayer through the air film holes on the wall between the main air intake cavity and the cooling interlayer, and is charged into the outside through the air film holes at the corresponding positions of the heat exchange cavity;

[0011] Step 2: Air film cooling, the cold air rushing into the cooling interlayer is processed by a plurality of first jet oscillator groups to generate characteristic cold air of high-frequency oscillating jet until it is sprayed out to form a cold air film covering the outer side of the blade body. The formed cold air film is mixed with the high-temperature mainstream above the blade body, thereby achieving the purpose of reducing the surface temperature of the blade body;

[0012] During this period, the second jet oscillator group is also used to form a high-frequency oscillating jet. The cold air is then ejected from the second air film hole to form a cold air film covering the outer side of the blade body. The formed cold air film is mixed with the high-temperature mainstream under the blade body, thereby achieving the purpose of cooling.

[0013] Step 3: Compound cooling is formed. At the beginning of its formation, the air film formed by the external airflow is prone to have no cold air flow or weak flow at the staggered positions. At this time, several heat exchange cavities can be used to form heat exchange with the main body of the blade to compensate for the cooling effect at the weak points and achieve a more reasonable and uniform compound cooling effect.

[0014] The technical effects and advantages of the present invention are as follows: cold air is directly filled into the main air intake cavity through an external cold air outlet, and obliquely rushed into the cooling interlayer through the air film holes on the wall between the main air intake cavity and the cooling interlayer, and rushed into the outside through the heat exchange cavity and the air film holes at the corresponding positions. The cold air rushed into the cooling interlayer is processed by a plurality of first jet oscillator groups to generate characteristic cold air of a high-frequency oscillating jet until it is ejected out of the outer side of the blade body to form a cold air film covering the outer side. The formed cold air film is mixed with the high-temperature mainstream above the blade body, thereby achieving the purpose of lowering the surface temperature of the blade body. During this period, the second jet oscillator group is used to similarly form the characteristic cold air of the high-frequency oscillating jet, and then ejected out of the outer side of the blade body through the second air film hole to form a cold air film covering the outer side of the blade body. The formed cold air film is mixed with the high-temperature mainstream below the blade body, thereby achieving the purpose of cooling. This invention couples oscillating jet film cooling, oscillating jet impingement cooling and film cooling in a double-wall structure, which increases the coverage of film cooling and impingement cooling under the action of high-frequency oscillating jets, greatly improves the overall cooling efficiency and reduces the amount of cold air used, ultimately helping to improve the thermal efficiency of the gas turbine system and achieve the goal of energy conservation and carbon reduction. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a structural schematic diagram of the present invention;

[0016] Figure 2 It is a schematic diagram of the three-dimensional structure of the present invention.

[0017] In the figure: 1. side panel; 3. cooling interlayer; 4. leading edge; 5. main air intake cavity; 6. blade body; 7. trailing edge; 8. secondary air intake cavity; 9. second jet oscillator group; 10. heat exchange cavity; 11. air film hole three; 12. first jet oscillator group; 13. air film hole one. DETAILED DESCRIPTION

[0018] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0019] The present invention provides a gas turbine turbine blade with a coupled double-wall and oscillating jet structure as shown in the figure, including a blade body 6, a leading edge 4 and a trailing edge 7 on the blade body 6, a main air intake cavity 5 is opened inside the leading edge 4 and is externally connected to cold air input, a cooling interlayer 3 is arranged between the main air intake cavity 5 and the outer wall of the blade body 6, and the cooling interlayer 3 and the inner wall of the blade body 6 are supported by multiple side panels 1, a double-wall structure is formed by the cooling interlayer 3, a plurality of obliquely arranged air film holes 13 are opened on the wall outside the main air intake cavity 5 connected to the cooling interlayer 3, a plurality of first jet oscillator groups 12 are arranged on the wall between the leading edge 4 and the cooling interlayer 3, and the cold air input into the main air intake cavity 5 enters the cooling interlayer 3 through the air film holes 13, and is then output obliquely to the outside of the blade body 6 by the first jet oscillator group 12 to form a cooling air film;

[0020] An auxiliary air intake cavity 8 is also provided on the main body of the blade body 6 at the bottom of one side of the main air intake cavity 5, and a plurality of second jet oscillator groups 9 are arranged on the wall between the auxiliary air intake cavity 8 and the main air intake cavity 5, and air film holes 2 are provided between the auxiliary air intake cavity 8 and the cooling interlayer 3, and between the cooling interlayer 3 and the outer side of the blade body 6 for outputting cold air.

[0021] Specifically, the inclination directions of the air film hole 13, the air film hole 2 and the first jet oscillator group 12 are all inclined toward the trailing edge 7, the air film hole 13 and the first jet oscillator group 12 have the same inclination angle and the corresponding first jet oscillator group 12 and the air film hole 13 are on the same inclined line.

[0022] Specifically, a plurality of heat exchange cavities 10 are further provided inside the blade body 6 for performing internal heat exchange on the areas not involved before the air film is formed by the external air film holes to form a composite cooling effect.

[0023] Specifically, air film holes for connecting the heat exchange cavity 10 with the outside are provided on the wall between the heat exchange cavity 10 and the cooling interlayer 3 and between the wall between the cooling interlayer 3 and the outside.

[0024] The cooling method of the gas turbine blade coupled with the double-wall and oscillating jet structure comprises the following specific steps:

[0025] Working principle: The cold air flow is directly filled into the main air intake cavity 5 by using the external cold air outlet 2, and is obliquely rushed into the cooling interlayer 3 through the air film holes on the wall between the main air intake cavity 5 and the cooling interlayer 3, and is rushed into the outside through the heat exchange cavity 10 and the air film holes at the corresponding positions. The cold air rushed into the cooling interlayer 3 is processed by a plurality of first jet oscillator groups 12 to generate characteristic cold air of high-frequency oscillating jets until it is sprayed out to form a cold air film covering the outer side of the blade body 6. The formed cold air film is mixed with the high-temperature mainstream above the blade body 6, thereby achieving the purpose of reducing the surface temperature of the blade body 6. During this period, the second The setting of the jet oscillator group 9 is similar to the formation of the characteristic high-frequency oscillating jet. The cold air is then ejected from the air film hole 2 to form a cold air film covering the outer side of the blade body 6. The formed cold air film is mixed with the high-temperature mainstream under the blade body 6, thereby achieving the purpose of cooling. The air film formed by the external airflow is prone to no cold air flowing through the staggered positions or weak flow at the beginning of its formation. At this time, several heat exchange cavities 10 are interconnected by using the air film hole 3 (11) and finally flow out from the tail edge. During this period, heat exchange can be formed with the main body of the blade body 6 to compensate for the cooling effect at the weak points, thereby achieving a more reasonable and uniform composite cooling effect.

[0026] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, it is still possible for those skilled in the art to modify the technical solutions described in the aforementioned embodiments or to make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A gas turbine turbine blade coupled with a double-wall and oscillating jet structure, comprising a blade body (6), the blade body (6) having a leading edge (4) and a trailing edge (7), the leading edge (4) also having a main air intake cavity (5) formed therein and connected to an external cold air input, characterized in that: A cooling interlayer (3) is provided between the main air intake cavity (5) and the outer wall of the blade body (6), and the cooling interlayer (3) and the inner wall of the blade body (6) are supported by a plurality of side panels (1), and a double-wall structure is formed by the cooling interlayer 3. A plurality of inclined air film holes (13) are provided on the wall between the outer side of the main air intake cavity (5) and the cooling interlayer (3). A plurality of first jet oscillator groups (12) are provided on the wall between the leading edge (4) and the cooling interlayer (3), and the cold air input into the main air intake cavity (5) enters the cooling interlayer (3) through the air film holes (13), and is then outputted obliquely by the first jet oscillator group (12) to the outer side of the blade body (6) to form a cooling air film. An auxiliary air intake cavity (8) is also provided on the main body of the blade body (6) at the bottom of one side of the main air intake cavity (5), and a plurality of second jet oscillator groups (9) are arranged on the wall between the auxiliary air intake cavity (8) and the main air intake cavity (5), and the side of the auxiliary air intake cavity (8) close to the front edge (4) uses the inner wall of the front edge (4) as the side wall and is provided with an air film hole 2 for directly outputting cold air.

2. The gas turbine blade with coupled double-wall and oscillating jet structure according to claim 1, characterized in that: The inclination directions of the air film hole 1 (13), the air film hole 2 and the first jet oscillator group (12) are all inclined toward the trailing edge (7) position, the air film hole 1 (13) and the first jet oscillator group (12) have the same inclination angle, and the corresponding first jet oscillator group (12) and the air film hole 1 (13) are on the same inclined line.

3. The gas turbine blade with coupled double-wall and oscillating jet structure according to claim 1, characterized in that: A plurality of heat exchange cavities (10) are also arranged inside the blade body (6) for performing internal heat exchange on areas not involved before the air film is formed by the external air film holes to form a composite cooling effect.

4. The gas turbine blade coupled with a double-wall and oscillating jet structure according to claim 3, characterized in that: Air film holes for connecting the heat exchange cavity (10) with the outside are provided on the wall between the heat exchange cavity (10) and the cooling interlayer (3) and between the wall between the cooling interlayer (3) and the outside.

5. The cooling method of a gas turbine blade according to any coupled double-wall and oscillating jet structure according to claims 1 to 4, characterized in that: The specific steps are as follows: Step 1: cold air is charged, the main air inlet cavity (5) is connected to the external cold air and the cold air flow is directly charged into the main air inlet cavity (5), and is obliquely charged into the cooling interlayer (3) through the air film holes on the wall between the main air inlet cavity (5) and the cooling interlayer (3) and is charged into the outside through the air film holes at the corresponding positions of the heat exchange cavity (10); Step 2: air film cooling, using the cold air that rushes into the cooling interlayer (3) to be processed by a plurality of first jet oscillator groups (12) to generate characteristic cold air of high-frequency oscillating jets until it is ejected outward from the outside of the blade body (6) to form a cold air film covering the blade body (6). The formed cold air film is mixed with the high-temperature mainstream above the blade body (6), thereby achieving the purpose of reducing the surface temperature of the blade body (6); During this period, the second jet oscillator group (9) is also used to form a high-frequency oscillating jet with the characteristics of the cold air, which is then ejected from the second air film hole to form a cold air film covering the outer side of the blade body (6). The formed cold air film is mixed with the high-temperature mainstream below the blade body (6), thereby achieving the purpose of cooling; Step three: Compound cooling is formed. When the air film formed by the external airflow is first formed, it is easy for no cold air to flow through or the cold air to flow through the staggered positions. At this time, several heat exchange cavities (10) are interconnected through air film holes three (11) and finally flow out from the tail edge. During this period, heat exchange can be formed with the main body of the blade body (6) to compensate for the cooling effect at the weak points, thereby achieving a more reasonable and uniform compound cooling effect.

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