HONEYCOMB-LIKE HELICALLY CAVITY COOLING STRUCTURE OF TURBINE BLADE

Abstract

The present invention belongs to the technical field of turbine cooling of aero-engine and gas turbine, and relates to the honeycomb-like helically cavity cooling structure of turbine blade. The honeycomb-like helically cavity cooling structure of turbine blade includes hollow turbine blade, honeycomb-like helically cavity and pin fins. Some cooling channels are arranged inside the hollow the hollow turbine blade, the cooling gas flows through the tunnels and cools the blade. Multi-arrays of honeycomb-like helically cavity are arranged in the blade wall, for cooling gas to enter and convective cooling. A cylindrical pin fin is arranged in the center of the honeycomb-like helically cavity. In each unit, the inlet hole and film hole are located on both sides of the blade wall, and the center lines of them are parallel in the same vertical plane.

Claims

1. A honeycomb-like helically cavity cooling structure of turbine blade, comprising hollow turbine blade, honeycomb-like helically cavity and pin fins; cooling channels are arranged inside the hollow the hollow turbine blade, the cooling channels provide low-temperature cooling gas to flow inside the blade and cools the blade; multi-arrays of the honeycomb-like helically cavity are arranged in blade wall of the hollow turbine blade, for cooling gas to enter and convective cooling; the pin fin is arranged in center of the honeycomb-like helically cavity, the pin fin is cylindrical; each honeycomb-like helically cavity is a unit with a regular hexagon shape, and multi-units are arranged as hive; inlet hole and film hole are located on both sides of the blade wall, and center line of inlet hole and center line of film hole are parallel in same vertical plane; angle between the center line of inlet hole and horizontal plane is incident angle, angle between the center line of film hole and the horizontal plane is exit angle; the incident angle and exit angle are both acute.

2. The honeycomb-like helically cavity cooling structure of turbine blade according to claim 1, wherein cross sections of the inlet hole and film hole are rectangular.

3. The honeycomb-like helically cavity cooling structure of turbine blade according to claim 1, wherein both angle of the incident angle and exit angle are 20-45°.

4. The honeycomb-like helically cavity cooling structure of turbine blade according to claim 1, wherein the inlet hole and film hole are smoothly connected with passage in the honeycomb-like helically cavity by circular arc slide.

5. The honeycomb-like helically cavity cooling structure of turbine blade according to claim 3, wherein the inlet hole) and film hole are smoothly connected with passage in the honeycomb-like helically cavity by circular arc slide.

6. The honeycomb-like helically cavity cooling structure of turbine blade according to claim 3, wherein both typical angle of the incident angle and exit angle are 30°.

7. The honeycomb-like helically cavity cooling structure of turbine blade according to claim 5, wherein both typical angle of the incident angle and exit angle are 30°.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0027] FIG. 1 shows the laminate structure and conventional turbine blades.

[0028] FIG. 2(a) shows the honeycomb-like helically cavity cooling structure of turbine blade.

[0029] FIG. 2(b) shows the partial enlarged detail view of honeycomb-like helically cavity cooling structure.

[0030] FIG. 3 shows the comparison of quadrangle and hexagonal unit arrangement.

[0031] FIG. 4 shows the comparison of cooling gas flow state inside laminate structure and honeycomb-like helically cavity.

[0032] FIG. 5 shows the comparison of section shape of two kind of structures.

[0033] FIG. 6 shows the comparison of air film hole coverage area of two kinds of structures.

[0034] FIG. 7(a) shows the 3D numerical simulation result of cooling gas flow in laminate structure.

[0035] FIG. 7(b) shows the 3D numerical simulation result of cooling gas flow in honeycomb-like helically cavity structure.

[0036] In the figures: 1. Hollow turbine blade; 2. Cooling channel; 3. Honeycomb-like helical cavity; 4. Pin fin; 5. Inlet hole; 6. Film hole; 7. Incident angle ∠A1; 8. Exit angle ∠A2; 9. Center line of inlet hole; 10. Center line of film hole.

DETAILED DESCRIPTION

[0037] In order to make the content of the invention more easily and clearly understood, a further detailed description of the invention is given in accordance with the concrete embodiments and the attached figure.

EMBODIMENT 1

[0038] In the present invention, the internal cooling gas flow state is compared between the honeycomb-like helically cavity cooling structure and the laminate structure through 3D numerical simulation. According to the analysis of the FIG. 7(a) and FIG. 7(b), the cross-sectional area of passage in the invention is roughly the same along the flow, won't from flow sudden and throttling phenomenon. Furthermore, the airflow turning angle is smaller and no collide and mix between each other, so the relative resistance of the laminate structure is smaller.

EMBODIMENT 2

[0039] As shown in FIG. 2, honeycomb-like helical cavity cooling structure includes hollow turbine blade 1, honeycomb-like helical cavity 3 and pin fin 4.

[0040] Some cooling gas channels 2 are arranged inside the hollow turbine blade 1, multiple arrays of honeycomb-like helical cavity 3 are located in the blade wall of the hollow turbine blade 1. A cylindrical pin fin 4 is arranged in the center of the honeycomb-like helically cavity 3. Each honeycomb-like helically cavity 3 is a unit with a regular hexagon shape. Multi-units are arranged as a hive. In each unit, inlet hole 5 and film hole 6 were located on both sides of the blade wall, and the center line of inlet hole 9 and the center line of film hole 10 were parallel in the same vertical plane. The cross section is rectangle of inlet hole 5 and film hole 6, two holes connected with honeycomb-like helical cavity 3 by the circular arc slide. The angle between the center line of inlet hole 9 and the horizontal plane is incident angle ∠A1, the angle between the center line of film hole 10 and the horizontal plane is exit angle ∠A2. The incident angle ∠A1 and exit angle ∠A2 are both 20°.

EMBODIMENT 3

[0041] Some cooling gas channels 2 are arranged inside the hollow turbine blade 1, multiple arrays of honeycomb-like helical cavity 3 are located in the wall of the hollow turbine blade 1. A cylindrical pin fin 4 is arranged in the center of the honeycomb-like helically cavity 3. Each honeycomb-like helically cavity 3 is a unit with a regular hexagon shape. Multi-units are arranged as a hive. In each unit, inlet hole 5 and film hole 6 were located on both sides of the blade wall, and the center line of inlet hole 9 and the center line of film hole 10 were parallel in the same vertical plane. The cross section is rectangle of inlet hole 5 and film hole 6, two holes connected with honeycomb-like helical cavity 3 by the circular arc slide. The angle between the center line of inlet hole 9 and the horizontal plane is incident angle ∠A1, the angle between the center line of film hole 10 and the horizontal plane is exit angle ∠A2. The incident angle ∠A1 and exit angle ∠A2 are both 30°.

EMBODIMENT 4

[0042] Some cooling gas channels 2 are arranged inside the hollow turbine blade 1, multiple arrays of honeycomb-like helical cavity 3 are located in the wall of the hollow turbine blade 1. A cylindrical pin fin 4 is arranged in the center of the honeycomb-like helically cavity 3. Each honeycomb-like helically cavity 3 is a unit with a regular hexagon shape. Multi-units are arranged as a hive. In each unit, inlet hole 5 and film hole 6 were located on both sides of the blade wall, and the center line of inlet hole 9 and the center line of film hole 10 were parallel in the same vertical plane. The cross section is rectangle of inlet hole 5 and film hole 6, two holes connected with honeycomb-like helical cavity 3 by the circular arc slide. The angle between the center line of inlet hole 9 and the horizontal plane is incident angle ∠A1, the angle between the center line of film hole 10 and the horizontal plane is exit angle ∠A2. The incident angle ∠A1 and exit angle ∠A2 are both 45°.