Gas turbine turbine blade and method incorporating a double-wall and oscillating jet structure

Abstract

This invention discloses a gas turbine blade and method with a coupled double-walled and oscillating jet structure, including a blade body having a leading edge and a trailing edge. The leading edge has a main intake cavity and is connected to a cold air input. A cooling interlayer is provided between the main intake cavity and the outer wall of the blade body, and the cooling interlayer and the inner wall of the blade body are supported by multiple side plates. The cold air is obliquely injected into the cooling interlayer through film vents on the wall between the main intake cavity and the cooling interlayer, and is injected into the outside through the heat exchange cavity and the corresponding film vents. The cold air injected into the cooling interlayer is processed by several first jet oscillators to generate high-frequency oscillating jet cold air until it is ejected from the outside of the blade body to form a cold air film covering. The formed cold air film mixes with the high-temperature mainstream above the blade body, thereby achieving the purpose of reducing the surface temperature of the blade body.

Description

Technical Field

[0001] This invention belongs to the field of gas turbine blade technology, specifically relating to gas turbine blades and methods with coupled double-walled and oscillating jet structures. Background Technology

[0002] Gas turbines are widely used in aviation, marine, power generation, military and other fields. The first-stage guide vanes of the high-pressure turbine in a 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 use cooling technology. Currently, the commonly used cooling methods are internal blade 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 purpose of this invention is to provide a gas turbine blade and method with a coupled double-walled and oscillating jet structure to solve the above-mentioned problems.

[0004] To achieve the above objectives, the present invention provides the following technical solution: a gas turbine blade with a coupled double-walled and oscillating jet structure, comprising a blade body having a leading edge and a trailing edge, a main intake cavity being formed inside the leading edge and connected to an external cold air input, a cooling interlayer being provided between the main intake cavity and the outer wall of the blade body, and the cooling interlayer being supported by multiple side plates to provide strength between the inner wall of the blade body and the inner wall of the blade body, a plurality of inclined air film holes being formed on the outer wall of the main intake cavity connecting the cooling interlayer, and a plurality of first jet oscillators being provided on the wall between the leading edge and the cooling interlayer, and the cold air input into the main intake cavity enters the cooling interlayer through the air film holes and is then output inclinedly to the outer side of the blade body by the first jet oscillators to form a cooling air film;

[0005] A secondary air intake chamber is also provided on the blade body at the bottom of one side of the main air intake chamber. Several second jet oscillator groups are provided on the wall between the secondary air intake chamber and the main air intake chamber. Air film holes are provided between the secondary air intake chamber and the cooling jacket, and between the cooling jacket and the outer side of the blade body for outputting cold air.

[0006] Preferably, the first air film hole, the second air film hole, and the first jet oscillator group are all inclined towards the tail edge position, and the first air film hole and the first jet oscillator group have the same inclination angle and the corresponding first jet oscillator group and the first air film hole are on the same inclined line.

[0007] Preferably, the blade body is further provided with several heat exchange cavities for internal heat exchange in areas not covered before the formation of the air film through the external air film pores, thereby creating a composite cooling effect.

[0008] Preferably, an air film hole for connecting the heat exchange cavity to the outside is provided on the wall between the heat exchange cavity and the cooling jacket and the wall between the cooling jacket and the outside.

[0009] The cooling method for gas turbine blades with arbitrary coupled double-walled and oscillating jet structures comprises the following steps:

[0010] Step 1: Cold air intake. Use the external cold air output port to directly inject cold air into the main intake chamber. The cold air is then injected into the cooling jacket through the air film holes on the wall between the main intake chamber and the cooling jacket, and into the outside through the heat exchange chamber and the corresponding air film holes.

[0011] Step 2: Film cooling. The cold air rushing into the cooling interlayer is processed by several first jet oscillators to generate high-frequency oscillating jets until it is ejected from the outside of the blade body to form a cold air film covering it. The cold air film formed mixes 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 characteristics of high-frequency oscillating jets are also formed by the setting of the second jet oscillator group. The cold air is then ejected from the second air film hole to form a cold air film covering the outside of the blade body. The cold air film formed mixes with the high-temperature mainstream below the blade body, thereby achieving the purpose of cooling.

[0013] Step 3: Formation of composite cooling. At the beginning of the formation of the air film formed by the external airflow, there may be situations where there is no cold airflow or the flow is relatively weak at the intersection. At this time, through several heat exchange chambers, heat exchange can be formed with the blade body to make up for the cooling effect at the weak points and achieve a more reasonable and uniform composite cooling effect.

[0014] The technical effects and advantages of this invention are as follows: Cold air is directly injected into the main intake chamber through an external cold air outlet. The cold air then flows obliquely into the cooling jacket through film vents on the wall between the main intake chamber and the cooling jacket, and into the outside through film vents in the heat exchange chamber and corresponding locations. The cold air injected into the cooling jacket is processed by several first jet oscillator groups to generate high-frequency oscillating jets of cold air until it exits the outer side of the blade body, forming a cold air film covering it. This cold air film mixes with the high-temperature mainstream above the blade body, thereby reducing the surface temperature of the blade body. Similarly, a second jet oscillator group is used to generate high-frequency oscillating jets of cold air, which then exits the outer side of the blade body through film vents, forming a cold air film covering it. This cold air film mixes with the high-temperature mainstream below the blade body, further achieving cooling. This invention couples oscillating jet film cooling, oscillating jet impact cooling, and film cooling into a double-wall structure. Under the action of high-frequency oscillating jet, the coverage of film cooling and impact cooling is increased, which greatly improves the overall cooling efficiency and reduces the amount of cooling gas used. Ultimately, this helps to improve the thermal efficiency of the gas turbine system and achieve the goal of energy saving and carbon reduction. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the structure of the present invention;

[0016] Figure 2 This is a three-dimensional structural diagram of the present invention.

[0017] In the figure: 1. Side plate; 3. Cooling jacket; 4. Leading edge; 5. Main intake chamber; 6. Blade body; 7. Trailing edge; 8. Secondary intake chamber; 9. Second jet oscillator group; 10. Heat exchange chamber; 11. Film oscillator three; 12. First jet oscillator group; 13. Film oscillator one. Detailed Implementation

[0018] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0019] This invention provides a gas 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 chamber 5 is provided inside the leading edge 4 and externally connected to the input of cold air, a cooling interlayer 3 is provided between the main air intake chamber 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 plates 1, forming a double-wall structure using the cooling interlayer 3, a number of inclined air film holes 13 are provided on the wall connecting the cooling interlayer 3 on the outer side of the main air intake chamber 5, a number 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 chamber 5 enters the cooling interlayer 3 through the air film holes 13, and is then output inclinedly to the outer side of the blade body 6 by the first jet oscillator groups 12 to form a cooling air film;

[0020] A secondary air intake chamber 8 is also provided on the blade body 6 at the bottom of one side of the main air intake chamber 5. Several second jet oscillator groups 9 are provided on the wall between the secondary air intake chamber 8 and the main air intake chamber 5. Air film holes are provided between the secondary air intake chamber 8 and the cooling jacket 3, and between the cooling jacket 3 and the outer side of the blade body 6 for outputting cold air.

[0021] Specifically, the tilting directions of the first air film hole 13, the second air film hole, and the first jet oscillator group 12 are all tilted towards the tail edge 7. The tilting angle of the first air film hole 13 and the first jet oscillator group 12 are the same, and the corresponding first jet oscillator group 12 and the first air film hole 13 are on the same tilting line.

[0022] Specifically, the blade body 6 is also provided with several heat exchange chambers 10 for internal heat exchange in areas not covered before the formation of the air film through the external air film holes, forming a composite cooling effect.

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

[0024] The cooling method for gas turbine blades with coupled double-walled and oscillating jet structures comprises the following steps:

[0025] Working principle: Cold air is directly injected into the main intake chamber 5 through the external cold air outlet 2. The cold air then flows obliquely into the cooling jacket 3 through film vents on the wall between the main intake chamber 5 and the cooling jacket 3, and is expelled into the outside through the heat exchange chamber 10 and corresponding film vents. The cold air injected into the cooling jacket 3 is processed by several first jet oscillator groups 12 to generate high-frequency oscillating jets until it exits the outer side of the blade body 6, forming a cold air film covering it. This cold air film mixes with the high-temperature mainstream above the blade body 6, thereby reducing the surface temperature of the blade body 6. During this process, a second... Similarly, the jet oscillator group 9 is set up to form a high-frequency oscillating jet. The cold air is then ejected from the outer side of the blade body 6 through the second air film hole to form a cold air film covering it. The cold air film formed mixes with the high-temperature mainstream below the blade body 6, thereby achieving the purpose of cooling. At the beginning of the formation of the air film formed by the external airflow, there may be situations where there is no cold air flow at the intersection or the flow is relatively weak. At this time, the air film is connected to each other through the third air film hole (11) of several heat exchange chambers 10 and finally flows out from the tail edge. During this period, heat exchange can be formed with the blade body 6 to make up for the cooling effect at the weak point and achieve a more reasonable and uniform composite cooling effect.

[0026] Finally, it should be noted that the above description 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 foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A gas turbine blade with a coupled double-walled and oscillating jet structure, comprising a blade body (6), wherein the blade body (6) has a leading edge (4) and a trailing edge (7), wherein the leading edge (4) is further provided with a main air intake cavity (5) and externally connected to a cooling air input, characterized in that: A cooling interlayer (3) is provided between the outer wall of the main air intake cavity (5) and the blade body (6), and the cooling interlayer (3) and the inner wall of the blade body (6) are supported by multiple side plates (1). The cooling interlayer 3 forms a double-wall structure. Several inclined air film holes (13) are opened on the wall between the main air intake cavity (5) and the cooling interlayer (3). Several first jet oscillator groups (12) are provided on the wall between the leading edge (4) and the cooling interlayer (3). 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 to the outside of the blade body (6) by the first jet oscillator group (12) to form a cooling air film. A secondary air intake chamber (8) is also provided on the blade body (6) at the bottom of one side of the main air intake chamber (5). Several second jet oscillator groups (9) are provided on the wall between the secondary air intake chamber (8) and the main air intake chamber (5). The side of the secondary air intake chamber (8) near the leading edge (4) has the inner wall of the leading edge (4) as its sidewall and is provided with a second air film hole for direct output of cold air. The tilting direction of the first air film hole (13), the second air film hole and the first jet oscillator group (12) are all tilted towards the trailing edge (7). The tilting angle of the first air film hole (13) and the first jet oscillator group (12) is consistent, and the corresponding first jet oscillator group (12) and the first air film hole (13) are on the same tilting line. Several heat exchange chambers (10) are also provided inside the blade body (6) for internal heat exchange to form a composite cooling effect in areas not covered before the formation of the air film by the external air film hole.

2. The gas turbine blade with coupled double-walled and oscillating jet structure according to claim 1, characterized in that: An air film hole is provided on the wall between the heat exchange cavity (10) and the cooling jacket (3) and between the cooling jacket (3) and the outside world for connecting the heat exchange cavity (10) and the outside world.

3. The cooling method for gas turbine blades with coupled double-walled and oscillating jet structures according to claim 2, characterized in that: The specific steps are as follows: Step 1: Cold air is introduced. The cold air is connected to the external cold air through the main air intake chamber (5) and the cold air flow is directly introduced into the main air intake chamber (5). The cold air is then introduced into the cooling jacket (3) through the air film holes on the wall between the main air intake chamber (5) and the cooling jacket (3) and into the outside through the heat exchange chamber (10) and the corresponding air film holes. Step 2: Air film cooling. The cold air rushing into the cooling jacket (3) is processed by several first jet oscillator groups (12) to generate high-frequency oscillating jet cold air until it is sprayed out to the outside of the blade body (6) to form a cold air film covering it. The cold air film formed mixes 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 used to form a high-frequency oscillating jet. The cold air is then ejected from the second air film hole to the outside of the blade body (6) to form a cold air film covering. The cold air film formed mixes with the high-temperature mainstream below the blade body (6) to achieve the purpose of cooling. Step 3: Composite cooling is formed. At the beginning of the formation of the air film formed by the external airflow, there may be situations where there is no cold airflow at the intersection or the flow is relatively weak. At this time, the air film is connected to each other through the air film holes (11) of several heat exchange chambers (10) and finally flows out from the tail edge. During this period, heat exchange can be formed with the blade body (6) to make up for the cooling effect at the weak point and achieve a more reasonable and uniform composite cooling effect.

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