Partitioned enhanced turbine blade with oscillating jet cooling structure and method of operation

Abstract

A partitioned turbine blade with an oscillating jet cooling structure and its operating method are disclosed, belonging to the fields of energy and power engineering and turbine blade cooling. The blade includes a blade shell, a jet oscillator, a cooling airflow delivery chamber, internal impact holes, external film cooling holes, and turbulence columns. In this invention, the cooling airflow impacts and cools the inner wall of the blade through the impact holes. Utilizing the characteristic of the jet oscillator to generate a large-area high-frequency sweep without moving parts, a single row of jet oscillators is used on the suction side and leading edge of the blade. Considering that the cooling demand on the pressure side is greater than that on the suction side, the pressure side fluid oscillators are arranged in two staggered rows to generate a large-area, full cooling film on the blade surface for blade cooling.

Description

[0001] Technology Neighborhood

[0002] This invention relates to a partitioned enhanced turbine blade with an oscillating jet cooling structure and its working method, belonging to the fields of energy and power engineering and turbine blade cooling. Background Technology

[0003] With the strengthening of my country's economic power and the rise of its scientific and technological level, machinery such as aero engines, hydrogen turbines, and gas turbines are constantly increasing turbine inlet temperatures to achieve higher performance. This places higher demands on the high-temperature resistance of turbine blade materials and cooling methods. When the blades cannot withstand excessively high temperatures, cracks or even fractures will occur, seriously affecting the turbine's service life and safety. Summary of the Invention

[0004] The purpose of this invention is to provide a partitioned reinforced turbine blade with an oscillating jet cooling structure and a working method, which has better structural strength and aerodynamic performance.

[0005] A partitioned turbine blade with an oscillating jet cooling structure and its operating method are disclosed. The blade has an airfoil profile and is hollow internally, with the blade shell forming the main body. The blade is divided into a leading section, a middle section, and a trailing section from its leading edge to its trailing edge. The leading section is where the jet oscillator generates the cooling gas film. The blade is characterized by having several leading-edge impact chambers arranged along its spanwise direction, with adjacent chambers separated by baffles to prevent interference. The leading section of the blade shell also has a leading section arranged along its spanwise direction. The blade consists of a leading-edge air delivery pipe, a leading-edge suction surface air delivery pipe, and a leading-edge pressure surface air delivery pipe. A row of leading-edge suction surface jet oscillators is embedded along the blade span, with its inlet connected to the leading-edge suction surface air delivery pipe and its outlet connected to the external environment of the blade. Two rows of jet oscillators are embedded parallel and staggered along the blade span on the leading-edge pressure surface side; these are the first and second jet oscillators of the leading-edge pressure surface, with their inlets connected to the leading-edge pressure surface air delivery pipe and their outlets connected to the external environment of the blade. The inlet is connected to the external environment of the blade; a row of leading-edge jet oscillators is embedded along the blade's span at the leading edge of the leading section, with its inlet connected to the leading-edge gas delivery pipe of the leading section and its outlet connected to the corresponding leading-edge impact chamber; three rows of leading-edge film perforations are embedded along the blade's span at the leading edge, with their inlets connected to the corresponding leading-edge impact chambers and their outlets connected to the external environment; a middle section gas delivery pipe is arranged along the blade's span in the middle section of the blade shell, and the cavity between the gas delivery pipe wall and the blade shell is the middle section impact chamber region; the middle section impact chamber... The region is divided into several intermediate impact chambers along the blade span. Adjacent intermediate impact chambers are separated by baffles and do not interfere with each other. The intermediate section air delivery pipe has intermediate section impact holes embedded on both the suction and pressure surfaces of the blade. The inlet of the intermediate section impact hole is connected to the intermediate section air delivery pipe, and the outlet is connected to the intermediate section impact chamber. The tail section of the blade shell is hollow inside, and the hollow part is the trailing edge section impact chamber. The inlet of the trailing edge section impact chamber is connected to the intermediate section impact chamber, and the outlet is connected to the external environment. Two rows of turbulence columns are arranged transversely inside the cavity.

[0006] The partitioned enhanced turbine blade with oscillating jet cooling structure and its working method are as follows: In the forward section of the blade shell, the cooling airflow enters the leading edge jet oscillator from the blade root through the leading edge air inlet pipe of the forward section. The airflow enters the leading edge impact chamber of the blade to form a sweeping jet, and then leaves the blade through the leading edge film gas hole, forming a cooling gas film on the outer side of the blade leading edge; the cooling airflow enters the forward suction surface oscillator from the blade root through the forward suction surface air inlet pipe of the forward section, forming a sweeping jet on the outer surface of the blade suction surface, forming a cooling gas film; the cooling airflow enters the first jet oscillator of the forward pressure surface from the blade root through the forward pressure surface air inlet pipe of the forward section and the forward section... The second jet oscillator on the pressure surface of the blade forms a sweeping jet on the outer surface of the blade pressure surface. The cooling fluid flows along the wall to form a cooling gas film to isolate the high-temperature combustion gas and protect the blade. In the middle section of the blade shell, the cooling airflow enters the middle section impact chamber from the blade root through the middle section air supply pipe wall and the middle section impact hole, which impacts and cools the suction surface of the middle pressure surface of the blade. Then, the cooling airflow in the middle section impact chamber enters the trailing edge section impact chamber and leaves the blade after passing through the turbulence column. The internal impact chambers of the blade are separated by baffles, and each impact chamber is independent and does not interfere with each other, which allows the cooling airflow to fully contact the blade shell in a small space and enhances heat transfer.

[0007] This invention eliminates moving parts on the turbine blade, and the parts are very small, reducing the need for openings in traditional film cooling systems and ensuring the blade's structural strength and improved aerodynamic performance. Traditional film cooling methods require numerous openings on the blade surface, impacting aerodynamic performance. However, the large-area sweeping principle of jet oscillators reduces the number of openings on the blade surface. The staggered distribution compensates for the insufficient sweeping area of ​​a single jet oscillator. The internal impact chambers are separated by baffles, ensuring each chamber is independent and does not interfere with the others. This allows the cooling airflow to fully contact the blade outer shell within a small space, enhancing heat transfer. Attached Figure Description

[0008] Figure 1 It is a side cross-sectional view of a partitioned reinforced turbine blade with an oscillating jet cooling structure;

[0009] Figure 2 It is a complete three-dimensional schematic diagram of a partitioned reinforced turbine blade with an oscillating jet cooling structure;

[0010] Figure 3 yes Figure 2 A bottom view;

[0011] Figure 4 yes Figure 2 Top view;

[0012] Figure 5 This is a schematic diagram of the jet oscillator.

[0013] The labels in the diagram are as follows: 1. Blade shell; 2-1. First jet oscillator on the front pressure surface; 2-2. Second jet oscillator on the front pressure surface; 3. Leading edge film gas hole; 4. Blade leading edge impact cavity; 5. Leading edge jet oscillator; 6. Leading edge gas delivery pipe on the front section; 7. Jet oscillator on the front suction surface; 8. Gas delivery pipe on the front suction surface; 9. Gas delivery pipe on the front pressure surface; 10. Gas delivery pipe in the middle section; 11. Impact hole in the middle section; 12. Turbulence column; 13. Impact cavity on the trailing edge; 14. Impact cavity in the middle section. Detailed Implementation

[0014] The following reference Figure 1 This paper describes the working process of a partitioned turbine blade with an oscillating jet cooling structure.

[0015] In the forward section of the blade casing, cooling airflow enters the leading-edge jet oscillator from the blade root through the leading-edge gas inlet pipe. The airflow then enters the leading-edge impact chamber to form a swept jet, and exits the blade through the leading-edge film gas holes, forming a cooling film on the outer side of the blade's leading edge. Cooling airflow also enters the forward suction surface oscillator from the blade root through the forward suction surface gas inlet pipe, forming a swept jet on the outer surface of the blade's suction surface, creating a cooling film. Finally, cooling airflow enters the forward pressure surface from the blade root through the forward pressure surface gas inlet pipe. The first jet oscillator and the second jet oscillator on the front section pressure surface form a sweeping jet on the outer surface of the blade pressure surface. The cooling fluid flows along the wall to form a cooling gas film, which isolates the high-temperature combustion gases and protects the blade. In the middle section of the blade shell, the cooling airflow enters the middle section impact chamber from the blade root through the middle section air delivery pipe wall and through the middle section impact hole, impacting and cooling the suction surface of the blade's middle pressure surface. Subsequently, the cooling airflow in the middle section impact chamber enters the trailing edge impact chamber and exits the blade after passing through the turbulence column. The internal impact chambers of the blade are separated by baffles, and each impact chamber is independent and does not interfere with the others, allowing the cooling airflow to fully contact the blade shell in a small space, thus enhancing heat transfer.

Claims

1. A partitioned reinforced turbine blade with an oscillating jet cooling structure, wherein the blade profile is an airfoil structure with a hollow interior, and the blade shell (1) is the main body of the blade; the blade is divided into a leading section, a middle section, and a trailing section from the leading edge to the trailing edge, the leading section being the part where the jet oscillator generates a cooling gas film; characterized in that: Several leading-edge impact chambers (4) are arranged along the blade span on the leading edge of the blade. Adjacent leading-edge impact chambers (4) are separated by baffles and do not interfere with each other. The leading section of the blade shell (1) is arranged along the blade span with a leading-edge gas delivery pipe (6), a suction surface gas delivery pipe (8), and a pressure surface gas delivery pipe (9). A row of suction surface jet oscillators (7) is embedded along the blade span on the suction surface side of the leading section of the blade. Its inlet is connected to the suction surface gas delivery pipe (8), and its outlet is connected to the outer ring of the blade. The front section pressure surface is connected to the blade external environment; two rows of jet oscillators are embedded parallel and staggered along the blade span, namely the first jet oscillator (2-1) and the second jet oscillator (2-2) of the front section pressure surface. Their inlets are connected to the front section pressure surface gas delivery pipe (9), and their outlets are connected to the blade external environment; a row of leading edge jet oscillators (5) is embedded along the blade span at the leading edge of the front section. Their inlets are connected to the leading edge gas delivery pipe (6) of the front section, and their outlets are connected to the corresponding leading edge impact chamber (4); Three rows of leading edge air film holes (3) are embedded along the blade span at the leading edge of the blade. The inlet of the holes is connected to the corresponding leading edge impact cavity (4), and the outlet is connected to the external environment. A middle section of the blade shell (1) is provided with a middle section air pipe (10) along the blade span. The cavity between the air pipe wall and the blade shell (1) is the middle section impact chamber area. The middle section impact chamber area is divided into several intermediate section impact chambers (14) along the blade span. Adjacent intermediate section impact chambers (14) are separated by partitions and do not interfere with each other. The middle section air pipe (10) is embedded with middle section impact holes (11) on both the suction and pressure surfaces of the blade. The inlet of the middle section impact hole is connected to the middle section air pipe (10), and the outlet is connected to the middle section impact chamber (14). The blade shell (1) has a hollow interior at the tail section, which is the tail edge section impact chamber (13). The inlet of the tail edge section impact chamber (13) is connected to the middle section impact chamber (14), and the outlet is connected to the external environment. Two rows of turbulence columns (12) are arranged across the cavity.

2. The working method of the partitioned reinforced turbine blade with oscillating jet cooling structure according to claim 1 is as follows: In the front section of the blade shell (1), the cooling airflow enters the leading edge jet oscillator (5) from the blade root through the leading edge gas pipe (6) of the front section. The airflow enters the blade leading edge impact chamber (4) to form a sweeping jet, and then leaves the blade through the leading edge film hole (3), forming a cooling gas film on the outer side of the blade leading edge. The cooling airflow enters the front suction surface flow oscillator (7) from the blade root through the front suction surface gas pipe (8) to form a sweeping jet on the outer surface of the blade suction surface, forming a cooling gas film. The cooling airflow enters the first jet oscillator (2-1) and the second jet oscillator (2-2) of the front pressure surface from the blade root through the front pressure surface gas pipe (9) to form a sweeping jet on the outer surface of the blade pressure surface. The cooling fluid will flow along the wall to form a cooling gas film to isolate the high-temperature combustion gas and protect the blade. In the middle section of the blade shell (1), the cooling airflow enters the middle section impact chamber (14) through the middle section impact hole (11) from the root of the blade via the middle section air supply pipe wall (10) and the middle section impact chamber (11). The airflow then enters the trailing edge impact chamber (13) and leaves the blade after passing through the turbulence column (12). The internal impact chambers of the blade are separated by baffles, and each impact chamber is independent and does not interfere with the others. This allows the cooling airflow to fully contact the blade shell in a small space, thus enhancing heat transfer.

Images