Suction surface cooling structure with bionic turbulent flow columns

Abstract

The invention discloses a suction surface cooling structure with bionic turbulent flow columns, relates to the technical field of aero-engine turbine blades, and solves the problem that the cold air cooling effect is affected by shock wave loss. The blade comprises a flow channel and a plurality of flow disturbing columns, wherein the flow channel is arranged in the blade; a runner inlet is communicated with a blade internal cold air cavity, and a runner outlet is formed in the upstream of a blade suction surface reflection shock wave point; the flow channel is of an S-shaped structure, and a plurality of flow disturbing columns are arranged in the flow channel. The turbulent flow columns comprise the first turbulent flow columns and the third turbulent flow columns, the first turbulent flow columns are arranged on the upstream of the flow channel in a staggered mode, and the third turbulent flow columns are arranged on the downstream of the flow channel in a staggered mode. The first turbulent flow column and the third turbulent flow column are of a gill cover-shaped structure. The parts, facing the concave side of the flow channel, of the first turbulent flow column and the third turbulent flow column are of an arc-shaped structure. The cooling structure is located on the upstream of the blade suction surface reflection shock waves and is specifically used for weakening the reflection shock waves and enhancing cold air sprayed out of the cooling structure, the better covering effect is achieved, and the heat exchange effect is improved.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft engine turbine blades, in particular to a suction surface cooling structure with a bionic spoiler column. Background Art

[0002] Gas turbines, characterized by excellent maneuverability, compact size, and high power output, are now widely used in aerospace, aviation, marine, and industrial power generation. Gas turbine engines are the most widely used engines in aviation, representing a country's comprehensive scientific and technological capabilities. The design and development of gas turbines and aircraft engines are focused on improving specific output power, enhancing thermal efficiency, reducing fuel consumption, and achieving lightweight design. Increasing turbine inlet temperature is the most effective technical approach to improving output power and thrust-to-weight ratio. To enhance turbine efficiency and power, increasing the turbine expansion ratio and inlet total temperature is a pressing issue. However, a large expansion ratio places the turbine in the transonic operating range, increasing the Mach number of the airflow, causing severe shock wave losses and degrading turbine performance. Regulating the shock wave intensity of the transonic turbine blades and reducing aerodynamic losses are key to achieving lightweight and high-load turbines.

[0003] The inlet temperature of gas turbines increases at an average rate of approximately 25K per year, which is much higher than the annual growth rate of about 10K of the melting point of high-temperature materials. Therefore, in the future, in addition to promoting the application of new material component manufacturing technologies such as high-temperature composite materials, the research and development of more efficient turbine component cooling technologies will be of great significance for improving the operating life of turbines and the overall design level of gas turbines.

[0004] For turbine blades with high inlet temperatures and high aerodynamic loads, the cold air jet on the blade surface is affected by the complex shock wave system within the flow channel. This in turn affects aerodynamic performance, such as shock wave intensity and blade cascade losses. External cooling technology offers the advantages of high cooling efficiency, long flight time, and reusability. Among external cooling technologies, film cooling offers excellent thermal protection and is widely used in aircraft engine thermal protection. The technology is relatively mature. Summary of the Invention

[0005] To address the aforementioned issue of shock wave losses affecting the cooling efficiency of cold air, this invention proposes a suction surface cooling structure with biomimetic spoiler columns. This cooling structure is designed to enhance and weaken the reflected shock waves from turbine blades. Located upstream of the blade's suction surface, this cooling structure specifically weakens the reflected shock waves and enhances the cooling air's coverage, improving heat exchange.

[0006] The present invention proposes a suction surface cooling structure with bionic spoiler columns, which specifically includes a flow channel and some spoiler columns. The flow channel is arranged inside the turbine blade; the flow channel inlet is connected to the cold air cavity inside the blade, and the outlet is arranged upstream of the reflection shock wave point of the blade suction surface; the flow channel is an S-shaped structure, and some spoiler columns are arranged inside; the spoiler columns include spoiler column 1 and spoiler column 3, if the spoiler column 1 is staggered and arranged upstream of the flow channel, if the spoiler column 3 is staggered and arranged downstream of the flow channel; spoiler column 1 and spoiler column 3 are fish gill cover-like structures; the parts of spoiler column 1 and spoiler column 3 facing the concave side of the flow channel are arc-shaped structures.

[0007] Furthermore, the arc-shaped structures of the spoiler column 1 and the spoiler column 3 facing the concave side of the flow channel are concave toward the inside of the spoiler column.

[0008] Furthermore, a second spoiler column is provided in the middle of the flow channel, and the second spoiler column is a long strip structure.

[0009] Furthermore, the second spoiler column has an S-shaped structure and matches the direction of the flow channel.

[0010] Furthermore, the bottom surface of the flow channel outlet is inclined.

[0011] Furthermore, the angle between the bottom surface at the flow channel outlet and the blade surface is 15°-30°.

[0012] The beneficial effects of the suction surface cooling structure with bionic spoiler columns described in the present invention are: (1) The suction surface cooling structure with a bionic spoiler column described in the present invention solves the problem of the impact of shock wave loss on the cooling effect of cold air. A cold air flow channel is set inside the blade, the channel inlet is connected to the cold air cavity inside the blade, and the channel outlet is set upstream of the reflected shock wave on the blade suction surface. It is used to specifically weaken the reflected shock wave and enhance the coverage effect of the cold air ejected from the cooling structure, thereby improving the heat exchange effect. Slotting the suction surface for tangential cold air injection can minimize the tendency of the cold air jet to separate from the wall surface and maximize the cooling effect of the air film on the blade surface. Under normal working conditions, it can enhance the coverage effect and cooling efficiency of the air film, weaken the intensity of the reflected shock wave on the blade suction surface, and weaken the intensity of the adverse pressure gradient caused by the reflected shock wave.

[0013] (2) The suction surface cooling structure with a bionic spoiler column described in the present invention has several spoilers arranged in the flow channel, including fish gill cover-shaped spoilers and streamlined spoilers. The wake generated by the spoiler columns can increase the turbulence. In addition, the horseshoe vortex generated upstream of the column bottom surrounds the spoiler column, causing more disturbances, thereby improving the heat transfer coefficient. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The illustrative embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute improper limitations on the present invention.

[0015] In the attached figure: Figure 1 This is a schematic structural diagram of a suction surface cooling structure with a bionic spoiler column according to the present invention; Figure 2 This is a cross-sectional view of a suction surface cooling structure with a bionic spoiler column according to the present invention; Among them: 1-flow channel, 2-spoiler column 1, 3-spoiler column 2, 4-spoiler column 3, 5-groove bank, 6-blade. DETAILED DESCRIPTION

[0016] The following will clearly and completely describe the technical solutions of the present invention in conjunction with the accompanying drawings. Obviously, the embodiments described are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative efforts shall fall within the scope of protection of the present invention.

[0017] In the description of the present invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," "outer," and the like, indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate the description of the present invention and simplify the description. They do not indicate or imply that the devices or components referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limitations on the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0018] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "installed," "connected," and "connected" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on the specific circumstances.

[0019] In addition, the technical features involved in different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0020] Specific implementation method 1: See Figure 1-Figure 2The embodiment of the present invention is described in detail. The suction surface cooling structure with bionic spoiler columns described in the embodiment specifically includes a flow channel 1 and some spoiler columns. The flow channel 1 is arranged inside the blade 6; the flow channel 1 inlet is connected to the cold air cavity inside the blade 6, and the outlet is arranged upstream of the shock wave reflection point on the suction surface of the blade 6, which is used to increase the turbine inlet temperature of the gas turbine, enhance the film cooling efficiency, and improve the efficiency of the combustion engine; the flow channel 1 is an S-shaped structure, and some spoiler columns are arranged inside; the spoiler columns include spoiler column 1 2 and spoiler column 3 4. If the spoiler column 1 2 is arranged upstream of the flow channel 1, the spoiler column 3 is arranged upstream of the spoiler column 3. Flow column three 4 is arranged at the downstream of flow channel 1, and spoiler column one 2 and spoiler column three 4 are arranged in rows, with adjacent rows staggered; spoiler column one 2 and spoiler column three 4 are fish gill cover-like structures, with one end being an angular structure and the other end being an arc-shaped structure, and the whole is approximately fan-shaped, minimizing the convection area as much as possible; the edge part of spoiler column one 2 and spoiler column three 4 on the S-shaped concave side facing the flow channel 1 is an arc-shaped structure, and the arc structure is concave toward the inside of the spoiler column, and the other side is a straight structure, so that spoiler column one 2 and spoiler column three 4 are mirror-symmetrical in structure.

[0021] A spoiler column 2 3 is provided in the middle of the flow channel 1. The spoiler column 2 3 is a long S-shaped structure and is flat as a whole. The S-shaped structure of the spoiler column 2 3 matches the direction of the flow channel 1, reducing the energy lost by the cold air impacting the wall. This structure can also minimize the loss caused by the tail vortex when the cold air flows in the cold air cavity.

[0022] The bottom surface of the outlet of the flow channel 1 is inclined, and the angle between the bottom surface at the outlet and the surface of the blade 6 is 15°-30°, so that the cold air can cover the blade surface as best as possible.

[0023] The outlet of channel 1 is a groove-like structure, with banks 5 separating several outlets. When the spoiler columns have rounded corners at the contact points with the upper and lower walls of channel 1, the heat transfer pattern may change. As the distance between the spoiler columns increases, their disruptive effect gradually decreases. When the spacing reaches a certain value, the effect of the spoiler columns on the flow almost disappears.

[0024] To summarize the above implementation cases, the suction surface cooling structure with a bionic spoiler column described in the present invention solves the problem of the impact of shock wave loss on the cooling effect of cold air. A cold air flow channel is provided inside the blade 6, and the inlet of the flow channel 1 is connected to the cold air cavity inside the blade 6. The outlet of the flow channel 1 is provided upstream of the reflected shock wave on the suction surface of the blade 6, which is used to specifically weaken the reflected shock wave and enhance the cold air ejected from the cooling structure to have a better coverage effect and improve the heat exchange effect. Slotting the suction surface for tangential cold air injection can minimize the tendency of the cold air jet itself to separate from the wall, and maximize the cooling effect of the air film on the blade surface. Under normal working conditions, the coverage effect and cooling efficiency of the air film can be enhanced, the intensity of the reflected shock wave on the suction surface of the blade can be weakened, and the intensity of the adverse pressure gradient effect caused by the reflected shock wave can be weakened. The present invention describes a suction surface cooling structure with a bionic spoiler column, in which several spoilers are arranged in the flow channel 1, including fish gill cover-shaped spoiler columns and streamlined spoiler columns. The wake generated by the spoiler columns can increase the turbulence. In addition, the horseshoe vortex generated upstream of the column bottom surrounds the spoiler column, causing more disturbances, thereby improving the heat transfer coefficient.

[0025] The specific embodiments described above further illustrate the objectives, technical solutions, and beneficial effects of the present invention. It should be understood that the above description is merely a specific embodiment of the present invention and is not intended to limit the invention. Reasonable combinations of the features described in the above embodiments are also possible. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention shall be included in the scope of protection of the present invention.

Claims

1. A suction surface cooling structure with a bionic spoiler column, characterized by: The invention comprises a flow channel (1) and some interference flow columns, wherein the flow channel (1) is arranged inside the blade (6); the inlet of the flow channel (1) is connected to the cold air cavity inside the blade (6), and the outlet is arranged upstream of the reflection shock wave point of the suction surface of the blade (6); the flow channel (1) is an S-shaped structure, and some interference flow columns are arranged inside; the interference flow columns comprise a first interference flow column (2) and a third interference flow column (4), wherein the first interference flow column (2) is staggeredly arranged upstream of the flow channel (1), and the third interference flow column (4) is staggeredly arranged downstream of the flow channel (1); the first interference flow column (2) and the third interference flow column (4) are fish gill cover-like structures; the parts of the first interference flow column (2) and the third interference flow column (4) facing the concave side of the flow channel (1) are arc-shaped structures.

2. The suction surface cooling structure with bionic spoiler columns according to claim 1, characterized in that: The arc-shaped structures of the spoiler column 1 (2) and the spoiler column 3 (4) facing the concave side of the flow channel (1) are concave toward the inside of the spoiler column.

3. The suction surface cooling structure with bionic spoiler columns according to claim 1, characterized in that: A second spoiler column (3) is provided in the middle of the flow channel (1), and the second spoiler column (3) is a long strip structure.

4. The suction surface cooling structure with bionic spoiler columns according to claim 3, characterized in that: The second spoiler column (3) is an S-shaped structure and matches the direction of the flow channel (1).

5. The suction surface cooling structure with bionic spoiler columns according to claim 1, characterized in that: The bottom surface of the outlet of the flow channel (1) is arranged inclined.

6. The suction surface cooling structure with bionic spoiler columns according to claim 5, characterized in that: The angle between the bottom surface at the outlet of the flow channel (1) and the surface of the blade (6) is 15°-30°.

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