CN-121993263-A - Turbine blade air film cooling hole type structure, turbine blade and engine

CN121993263ACN 121993263 ACN121993263 ACN 121993263ACN-121993263-A

Abstract

A turbine blade, a turbine blade and an engine comprise a gas film hole inlet, a gas film hole outlet, a gas transmission channel and a gas transmission channel, wherein the opening of the gas film hole outlet is larger than that of the gas film hole inlet, the gas transmission channel is connected with the gas film hole inlet and the gas film hole outlet and sequentially comprises a cylindrical section provided with the gas film hole inlet and a conical expansion section connected with the cylindrical section and provided with the gas film hole outlet along the flowing direction of fluid, the gas transmission channel comprises the cylindrical section and the conical expansion section arranged at the downstream of the cylindrical section, and the conical expansion section comprises a first expansion part formed at the conical expansion section and having an elliptical arc section in the cross section, and a second expansion part formed at the conical expansion section and having a circular arc section in the cross section. The turbine blade air film cooling hole type structure can enhance the adherence and transverse diffusion capacity of cooling air flow, so that the air film cooling efficiency in the working condition range of high blowing ratio is remarkably improved.

Inventors

REN JING
LI XUEYING
HUANG XINYU

Assignees

清华大学

Dates

Publication Date: 20260508
Application Date: 20260320

Claims (10)

1.A turbine blade film cooling hole pattern structure comprising: An air film hole inlet; an air film hole outlet with an opening larger than the opening of the air film hole inlet, and The gas transmission channel is connected with the gas film hole inlet and the gas film hole outlet; The gas transmission channel sequentially comprises a cylindrical section provided with the gas film hole inlet and a conical expansion section connected with the cylindrical section and provided with the gas film hole outlet along the flowing direction of fluid, wherein the conical expansion section comprises a first expansion part which extends based on one part of the circumferential direction of the circular outlet of the cylindrical section and is formed on the cross section of the conical expansion section to form an elliptical arc section, and a second expansion part which extends based on the other part of the circumferential direction of the circular outlet of the cylindrical section and is formed on the cross section of the conical expansion section to form a circular arc section, and the cross section of the conical expansion section is a plane perpendicular to the axial direction of the cylindrical section.
2. The turbine blade film cooling hole pattern structure of claim 1, wherein the first expansion portion extends and is formed based on one half of the circumferential direction of the circular outlet of the cylindrical section; In the same cross section of the conical expansion section, the minor axis of the elliptical arc section of the first expansion part is the diameter of the circular outlet of the cylindrical section, and the major axis of the elliptical arc section of the first expansion part is the diameter of the circular arc section of the second expansion part.
3. The turbine blade air film cooling hole type structure according to claim 1, wherein the air film hole inlet is elliptical, the long axis direction of the elliptical surface where the air film hole inlet is located is the X direction, the direction perpendicular to the plane where the air film hole inlet is located is the Z direction, the air film hole outlet and the air film hole inlet are parallel and are arranged in a parallel staggered mode along the Z direction and face away from each other, and the air conveying channel rises along the Z direction and inclines towards the X direction.
4. The turbine blade film cooling hole pattern structure as set forth in claim 3, wherein the peripheral side of said tapered expansion section includes a first side and a second side disposed opposite each other in said Z direction, said first side being elongated linearly continuing said cylindrical section, the remaining peripheral sides being expanded outwardly.
5. A turbine blade film cooling hole pattern structure according to claim 3, wherein the bore diameter D of the cylindrical section is a specific first discrete value comprising one of 3mm, 4mm, 5 mm; the ratio of the distance L between the air film hole outlet and the air film hole inlet along the axial direction of the cylindrical section to the aperture D of the cylindrical section is a specific second discrete value, and the second discrete value comprises one of 3.46, 3.66, 3.92, 4.24, 4.67, 5.23 and 6.
6. The turbine blade film cooling hole pattern structure of claim 5, wherein a jet angle α formed by the axis of the cylindrical section and a main flow direction of the fluid is a specific third discrete value, the third discrete value including one of 60 °, 55 °, 50 °, 45 °, 40 °,35 ° and 30 °; The second discrete values 3.46, 3.66, 3.92, 4.24, 4.67, 5.23 and 6 correspond to the third discrete values 60 °, 55 °,50 °, 45 °, 40 °, 35 ° and 30 °, respectively.
7. The turbine blade film cooling hole pattern structure of claim 1, wherein a distance L between the film hole outlet and the film hole inlet along the axial direction of the cylindrical section and a length Lp of the expansion section along the axial direction of the cylindrical section are in relation that a ratio of Lp to L is a specific fourth discrete value, and the fourth discrete value is one of 0.2, 0.3, 0.4, 0.5, 0.6, 0.7 and 0.8.
8. The turbine blade film cooling hole pattern structure according to claim 3, wherein the minor axis direction of the elliptical surface where the film hole inlet is located is the Y direction, and the conical angle β formed by the expansion edges of the two sides of the conical expansion section along the Y direction and the axis of the cylindrical section is a specific fifth discrete value, and the fifth discrete value is one of 6 °, 8 °,10 °, 12 ° and 14 °.
9. A turbine blade comprising a main flow passage, a cold air chamber, and a film cooling hole pattern structure according to any one of claims 1 to 8 connecting the main flow passage and the cold air chamber.
10. An engine according to claim 9, comprising turbine blades.

Description

Turbine blade air film cooling hole type structure, turbine blade and engine Technical Field The application relates to the technical field of air engine and gas turbine air film cooling, in particular to a turbine blade air film cooling hole type structure, a turbine blade and an engine. Background With the continuous development of the gas turbine technology towards high efficiency, the inlet temperature of the turbine is continuously increased and is far higher than the high temperature resistant limit of metal materials, and the development of the new generation of heavy-duty gas turbine technology needs to break through the higher inlet temperature of the gas. According to the existing research, the concept of integrated design of a combustion chamber and a turbine (hereinafter referred to as a "combustion-jet combination") breaks through the conventional design configuration of the combustion engine, and the two large-temperature hot end parts of the combustion chamber and the turbine are cooperatively considered to form the key technology of integrated gas-heat design of the combustion chamber and the turbine, so that the cooling efficiency is further improved, and the cold air consumption is reduced. Under the concept of integrated design of a combustion chamber and a turbine, the application of the combustion-injection combination component has more complex flow and heat exchange characteristics matched with the turbine, and the working condition of downstream turbine movable blades is more severe. First, the downstream turbine blades are in the region of strong vortices at the combustor outlet and first stage vane wake, which requires that the cooling jet must have sufficient momentum to penetrate the main flow to establish an effective protective layer. Secondly, stress concentration is easy to occur around the air film hole under the environment of extreme thermal mechanical load, so that cracks and component failure are caused. Finally, the downstream conditions under the integrated configuration are complex and changeable, so that the hole patterns need to be ensured to have good performance under the multi-objective of cold effect and wide working condition adaptability. In the prior art, the main flow hole pattern is more suitable for the working condition that the blowing ratio is not more than 2. And under the high blowing ratio, the main flow hole pattern can generate kidney-shaped vortex pairs in the downstream flow process, so that the coverage of cooling gas in the flow direction and the expanding direction is insufficient, and the cooling efficiency of a gas film is reduced under the high blowing ratio. In addition, the main flow hole type such as a cat-ear hole, a hyacinth bean hole, a pentagram hole and the like has complex structures, and stress concentration is easy to occur around the air film hole under the actual flow condition, so that the hole type and the blade structure are damaged, and the cooling fails. Disclosure of Invention The embodiment of the application provides a turbine blade air film cooling hole type structure, a turbine blade and an engine, which can enhance the adherence and transverse diffusion capacity of cooling air flow, thereby remarkably improving the air film cooling efficiency in a working condition range with high blowing ratio. The embodiment of the application provides a turbine blade air film cooling hole type structure, which comprises the following steps: An air film hole inlet; an air film hole outlet with an opening larger than the opening of the air film hole inlet, and The gas transmission channel is connected with the gas film hole inlet and the gas film hole outlet; The gas transmission channel sequentially comprises a cylindrical section provided with the gas film hole inlet and a conical expansion section connected with the cylindrical section and provided with the gas film hole outlet along the flowing direction of fluid, wherein the conical expansion section comprises a first expansion part which extends based on one part of the circumferential direction of the circular outlet of the cylindrical section and is formed on the cross section of the conical expansion section to form an elliptical arc section, and a second expansion part which extends based on the other part of the circumferential direction of the circular outlet of the cylindrical section and is formed on the cross section of the conical expansion section to form a circular arc section, and the cross section of the conical expansion section is a plane perpendicular to the axial direction of the cylindrical section. In one exemplary embodiment, the first expansion extends and is formed based on half of the circumference of the circular outlet of the cylindrical section; the second expansion part extends and is formed based on the other half of the circular outlet circumference of the cylindrical section; In the same cross section of the conical expansion section, the minor a