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Turbine cooling cascade with vortex structure

A turbine cooling and trapped vortex technology, which is applied in the combustion method, combustion chamber, combustion equipment, etc., can solve the problems of easy burnout of the leading edge end wall of the blade, affecting the performance of the blade cascade, and significant heat transfer characteristics, reducing the amount of cold air. The effect of utilization, reduction of mixing loss, and improvement of air-conditioning utilization rate

Inactive Publication Date: 2010-09-08
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to solve the problem of flow loss and mixing loss caused by the existence of the horseshoe vortex structure in the existing cascade, which affects the performance of the cascade, and the heat transfer characteristics near the end wall of the blade and the surface of the blade are significant, and the front of the blade The problem that the wall surface of the edge and the leading edge end wall of the blade is extremely easy to burn out, and then a turbine cooling blade cascade with a vortex structure is provided.

Method used

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  • Turbine cooling cascade with vortex structure
  • Turbine cooling cascade with vortex structure
  • Turbine cooling cascade with vortex structure

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specific Embodiment approach 1

[0009] Specific Embodiment 1: This embodiment is described with reference to FIGS. 4 to 7. The turbine cooling cascade with a vortex structure in this embodiment includes a wall 1 and blades 2. The blades 2 are arranged on the wall 1. The blades 2 On the pressure surface 2-2 close to the blade leading edge 2-1, on the suction surface 2-3 of the blade 2 close to the blade leading edge 2-1, and on the blade leading edge end wall 1-1 of the wall 1, there are rows of A plurality of long grooves 3 arranged, each long groove 3 on the pressure surface 2-2 of the blade 2 close to the blade leading edge 2-1 and each long groove 3 on the suction surface 2-3 of the blade 2 close to the blade leading edge 2-1 Each long groove 3 is opened along the height direction of the blade 2, and each long groove 3 on the blade leading edge end wall 1-1 of the wall 1 is all opened along the width direction of the wall 1, and one side of each long groove 3 A plurality of cold air injection holes 4 are ...

specific Embodiment approach 2

[0010] Specific Embodiment 2: This embodiment is described in conjunction with FIGS. 4 to 7. In this embodiment, the pressure surface 2-2 of the blade 2 close to the blade trailing edge 2-4 and the suction surface 2- of the blade 2 close to the blade trailing edge 2-4 3 are provided with a plurality of long grooves 3 arranged in a row, each long groove 3 on the pressure surface 2-2 of the blade 2 close to the blade trailing edge 2-4 and the suction force of the blade 2 close to the blade trailing edge 2-4 Each long groove 3 on the surface 2-3 is opened along the height direction of the blade 2. Such setting can effectively avoid burning out of the pressure surface, suction surface and high-temperature area of ​​the trailing edge, and effectively improve the overall performance of the blade. Other compositions and connections are the same as in the first embodiment.

specific Embodiment approach 3

[0011] Specific Embodiment 3: This embodiment is described with reference to FIGS. 4 to 7 . The cross section of the long groove 3 in this embodiment is square, trapezoidal or semicircular. With such a setting, the overall blade has diversity, and the coverage effect of the strength of the standing vortex and the thin layered air film is better. Other compositions and connections are the same as those in the second embodiment.

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Abstract

A turbine cooling cascade with a vortex structure relates to a turbine cooling cascade. The invention settles the problems of flowing loss, blending loss and easy burning of blade leading edge and endwall surface of blade leading edge caused by the existence of horse shoe vortex structure in the prior blade cascade. According to the blade (2) of the invention, a pressure surface (2-2) next to theblade leading edge (2-1), a suction surface (2-3) of blade (2) next to the blade leading edge (2-1) and the blade leading edge (1-1) of wall (1) are respectively provided with a plurality of elongated slots (3) which are distributed in row. One side wall of each elongated slot (3) is provided with a plurality of cold air injection openings (4). Furthermore the positions of cold air injection opening (4) are next to the base of elongated slot (3). The turbine cooling cascade with vortex structure according to the invention reduces the flowing loss at the inner part of flow passage, reduces thebigger blending loss of air currents with different flowing velocities, provides better thermal protection function for the end wall of blade and the blade surface, effectively protects the end walladjacent with the blade leading edge and the high-temperature area on the surface of blade, and increases the usage factor of cold air.

Description

technical field [0001] The invention relates to a turbine cooling cascade. Background technique [0002] Natural eddies can be seen on the sheltered surface of exposed ridges in nature, and similar eddies can also be seen near sand dunes. When the fluid flows through a concave cavity, due to the effect of viscosity, a dwelling vortex will also be generated in the cavity. For different blowing positions before and after the concave cavity, two different structures of double vortex and single vortex can be formed (as shown in Figure 1 and Figure 2). Vortex is also called secondary vortex. The characteristic of the double vortex structure is that the large vortex at the bottom of the concave cavity is very stable, and the secondary vortex at the upper part of the cavity can make the gas in the vortex and the mainstream air mix better and faster. [0003] Internationally, the trapped vortex structure has been well used in the design of the combustion chamber, and concepts suc...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/14F23R3/58
Inventor 黄洪雁王振峰王松涛周逊韩万金
Owner HARBIN INST OF TECH
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