Pressure side leading edge cutback cove structured turbine blade

Abstract

The application discloses a pressure side front edge cutaway groove structure turbine blade, which comprises a head-to-tail pressure surface and a suction surface, wherein a circular-arc groove is arranged on the pressure surface near a blade tip end surface, a tail cut structure is arranged at a tail edge of the pressure surface, and a pressure side rib wall and a suction side rib wall form a groove on a blade tip. The application can reduce the size of vortex structure in the blade tip front edge cavity, improve the flow loss of the blade tip front edge cavity region, control the heat exchange between the front edge vortex structure and the bottom of the blade tip cavity, improve the heat load region of the blade tip cavity front edge, and achieve the purpose of improving the blade tip heat exchange performance.

Description

Technical Field

[0001] This utility model relates to a technology in the field of aero-engines, specifically a turbine blade with a grooved structure for pressure-side leading edge cut-off to suppress tip thermal load. Background Technology

[0002] In modern turbines, a clearance is required between the rotating blade tip and the stationary casing to allow for relative motion. However, under pressure gradients, the mainstream gas flows through this clearance as it passes the pressure side, creating tip leakage. This high-temperature, high-pressure mainstream gas flows over the blade tip surface, causing ablation and severely impacting turbine blade life. Existing turbine blade trailing edge cooling structures are inadequate to address the high heat load in the leading edge region of blades with tip groove configurations. Utility Model Content

[0003] To address the aforementioned shortcomings of existing technologies, this invention proposes a turbine blade with a grooved structure cut off at the pressure side leading edge. This reduces the size of the vortex structure within the blade tip leading edge cavity, improves flow losses in the region within the blade tip leading edge cavity, controls heat exchange between the leading edge vortex structure and the bottom of the blade tip cavity, and improves the condition of the blade tip cavity leading edge being in a heat-loaded region, thereby achieving the goal of improving the blade tip heat exchange performance.

[0004] This utility model is achieved through the following technical solution:

[0005] This utility model relates to a turbine blade with a groove structure with a pressure side leading edge cut off, comprising: a pressure surface and a suction surface connected end to end, wherein: an arc-shaped groove is provided on the side of the pressure surface near the blade tip, and a tail-cutting structure is provided at the tail edge of the pressure surface, and the pressure side rib wall and the suction side rib wall form a groove located on the blade tip.

[0006] The width of the pressure-side rib wall from the front edge to the rear edge of the pressure surface, i.e., the rib width, is half the height of the pressure-side rib wall from the front edge to the rear edge of the pressure surface, i.e., the rib height.

[0007] The length of the arc-shaped groove is the axial chord length of the outer contour line of the pressure side rib wall from 10% to 25% of the distance from the leading edge point.

[0008] The arc-shaped groove is shaped to meet the outer contour line perpendicular to the 18% axial chord length of the pressure-side rib wall, with the maximum depth located at the outer contour line of the 18% axial chord length of the pressure-side rib wall, and the maximum depth w = h, where h is the height of the pressure side rib wall from the leading edge to the trailing edge of the pressure surface.

[0009] The termination point of the pressure-side rib wall, i.e. the starting point of the tail section, is located at 90% of the axial chord length of the outer contour line of the pressure-side rib wall.

[0010] The tail-cut structure and the inner contour line of the rib wall are right-angled. Attached Figure Description

[0011] Figure 1 This is a schematic diagram of the structure of this utility model;

[0012] Figure 2 for Figure 1 A top-down view;

[0013] Figure 3 for Figure 1 A cross-sectional view of the grooved blade configuration with the pressure-side leading edge cut off along line AA, where line AA is located at the maximum depth of the pressure-side leading edge cut off;

[0014] In the figure: 1 pressure surface, 2 suction surface, 3 pressure side rib wall, 4 suction side rib wall, 5 groove, 6 leading edge point, 7 trailing edge point, 8 casing, 9 pressure side rib wall cut-off, 10 pressure side tail cut-off, s pressure side rib wall width, w pressure side cut-off structural depth, h rib height, Cx axial chord length, A pressure side rib wall termination point. Detailed Implementation

[0015] like Figures 1-3 As shown, this embodiment relates to a turbine blade with a groove structure with a pressure side leading edge cut-off, including: a pressure surface 1 and a suction surface 2 connected end to end, wherein: an arc-shaped groove 9 is provided on the side of the pressure surface 1 near the blade tip, a tail-cutting structure 10 is provided at the tail edge of the pressure surface 1, and the pressure side rib wall 3 and the suction side rib wall 4 form a groove 5 located on the blade tip.

[0016] like Figure 3 As shown, the width of the pressure-side rib wall 3 from the leading edge to the trailing edge of the pressure surface 1, i.e., the rib width s = h, where h is the rib height, i.e., the distance from the bottom of the groove 5 to the tip of the blade.

[0017] The bottom of the groove 5 is a flat bottom surface, which connects to the pressure side rib wall 3 and the suction side rib wall 4 at right angles to form a groove with a rectangular cross section.

[0018] like Figure 2 and Figure 3 As shown, the length of the arc-shaped groove 9 is the range of axial chord length Cx from 10% to 25% of the distance from the leading edge point of the outer contour line of the pressure side rib wall 3.

[0019] like Figure 3 As shown, the shape of the arc-shaped groove 9 satisfies the outer contour line at a position perpendicular to the 18% axial chord length of the pressure-side rib wall 3, and the maximum depth position is located at the outer contour line at 18% axial chord length of the pressure-side rib wall, with a maximum depth w= h, where h is the rib height.

[0020] The termination point of the pressure side rib wall 3, i.e. the starting point of the tail-cut structure 10, is located at 90% of the axial chord length of the outer contour line of the pressure side rib wall 3.

[0021] The tail-cut structure 10 and the inner contour line of the rib wall are perpendicular lines.

[0022] Through specific practical experiments, the steady-state Reynolds time-averaged equation was solved and analyzed using the commercial CFD calculation software Ansys 24.1 CFX. Compared with the existing tip groove configuration technology, the area of ​​the region with a heat transfer coefficient greater than 1500 W / m²K in the tip and tip region cavity within the first 50% axial chord length range was reduced by 2.99%, and the area of ​​the region with a heat transfer coefficient greater than 1800 W / m²K was reduced by 1.72%. In addition, the total pressure loss coefficient at the 50% axial chord length position was reduced by 1.66%. This utility model improves the flow loss in the leading edge region and effectively reduces the heat load in the tip leading edge region.

[0023] The above-described specific implementations can be partially adjusted by those skilled in the art in different ways without departing from the principles and purpose of this utility model. The scope of protection of this utility model is determined by the claims and is not limited to the above-described specific implementations. All implementation schemes within its scope are bound by this utility model.

Claims

1. A turbine blade with a grooved structure on the pressure side leading edge, characterized in that, include: The pressure surface and suction surface are connected end to end. The pressure surface has an arc groove on the side near the blade tip, and the tail edge of the pressure surface has a tail-cutting structure. The pressure side rib wall and the suction side rib wall form a groove on the blade tip.

2. The turbine blade with a grooved structure cut off at the pressure side leading edge according to claim 1, characterized in that, The width of the pressure-side rib wall from the front edge to the rear edge of the pressure surface, i.e., the rib width, is half the height of the pressure-side rib wall from the front edge to the rear edge of the pressure surface, i.e., the rib height.

3. The turbine blade with a grooved structure cut off at the pressure side leading edge according to claim 1, characterized in that, The length of the arc-shaped groove is the axial chord length of the outer contour line of the pressure side rib wall from 10% to 25% of the distance from the leading edge point.

4. The turbine blade with a grooved structure cut off at the pressure side leading edge according to claim 1, characterized in that, The arc-shaped groove is shaped to meet the outer contour line perpendicular to the 18% axial chord length of the pressure-side rib wall, with the maximum depth located at the outer contour line of the 18% axial chord length of the pressure-side rib wall, and the maximum depth w = h, where h is the rib height, i.e., the distance from the bottom of the groove to the tip of the blade.

5. The turbine blade with a grooved structure cut off at the pressure side leading edge according to claim 1, characterized in that, The termination point of the pressure-side rib wall, i.e. the starting point of the tail section, is located at 90% of the axial chord length of the outer contour line of the pressure-side rib wall.

6. The turbine blade with a grooved structure cut off at the pressure side leading edge according to claim 1, characterized in that, The tail-cut structure and the inner contour line of the rib wall are right-angled.

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