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A Laminar Cooling Structure Using Polygonal Spoiler Columns

A technology of cooling structure and spoiler column, which is applied to the supporting elements of blades, engine elements, machines/engines, etc., can solve the problem of increased thermal load of turbine components, and achieves reduction of flow loss, flow resistance loss, and replacement. good thermal effect

Active Publication Date: 2021-06-04
DALIAN UNIV OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] At present, in order to increase the thrust of the aero-engine and the power of the gas turbine, the method of increasing the temperature before the turbine is generally adopted, which brings about the increase of the heat load of the turbine components.

Method used

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  • A Laminar Cooling Structure Using Polygonal Spoiler Columns
  • A Laminar Cooling Structure Using Polygonal Spoiler Columns
  • A Laminar Cooling Structure Using Polygonal Spoiler Columns

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Embodiment 1

[0032] The present invention conducts a comparative study of the flow state of the internal cooling air between the conventional laminate structure and the interior cavity of the polygonal spoiler column laminate in the present invention through three-dimensional numerical simulation, as shown in Figure 2(a) and Figure 2(b), it can be It is known that the spiral cavity and the air inlet / outlet hole are smoothly connected and the turning angle is small, and there is no obvious change in cross-sectional area, so that the airflow will not appear sudden expansion and throttling, as well as mutual impact interference, and also make the laminate resistance smaller. The structure of the present invention is calculated and analyzed through numerical simulation, and its flow resistance is about 13% smaller than that of the conventional laminate structure, which confirms the above conclusion.

Embodiment 2

[0034] Such as figure 1 As shown, the present invention is a laminar cooling structure suitable for gas turbine engines, wherein the structure of the spoiler column 3 and the spiral cavity 4 is the main feature different from the existing laminar structure. Each spiral cavity is approximately circular and can be regarded as a relatively independent minimum unit body. The spoiler column 3 at the center of the unit body is a polygon, such as a triangle, a quadrangle, a pentagon, etc. (such as Figure 6 shown). The cavity structure around the spoiler column in the unit body is smoothly connected with the air inlet / outlet holes and generally presents a spiral shape. The air inlet hole 2 and the air outlet hole 5 which are spatially adjacent but do not interfere with each other have a parallelogram in section. The projections of the air inlet centerline 10 and the air outlet centerline 11 of the air inlet 2 and the air outlet 5 in each unit body in the horizontal plane are respe...

Embodiment 3

[0038] The present invention is a laminar cooling structure suitable for gas turbine engines, in which the structure of the spoiler column 3 and the spiral cavity 4 is the main feature different from the existing laminar structure. Each spiral cavity is approximately circular and can be regarded as a relatively independent minimum unit body, and the spoiler column 3 at the center of the unit body is hexagonal. The cavity structure around the spoiler column in the unit body is smoothly connected with the air inlet / outlet holes and generally presents a spiral shape. The air inlet 2 and the air outlet 5, which are spatially adjacent but do not interfere with each other, have a cross-section approximately parallelogram. The projections of the air inlet centerline 10 and the air outlet centerline 11 of the air inlet 2 and the air outlet 5 in each unit body are located in the horizontal plane, which are respectively parallel to the adjacent two sides of the spoiler column, and the a...

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Abstract

The invention belongs to the technical field of turbine cooling for aero-engines and gas turbines, and relates to a laminate cooling structure using polygonal spoiler columns. The laminate cooling structure includes an air inlet hole on the air inlet plate, an air outlet hole on the air outlet plate, a spoiler column and a spiral cavity, the spoiler column is located at the center of the spiral cavity and forms a cold air passage, and the number of sides is 3 , 4, 5, 6...any one of the items; the cross-sectional shape of the air inlet hole and the air outlet hole is a parallelogram, and the air inlet hole and the air outlet hole are connected with the channel in the spiral cavity smoothly with an arc-shaped slideway. And extend outward from two adjacent sides of the polygonal spoiler column. The angles formed by the centerline of the inlet hole and the centerline of the outlet hole and the horizontal plane are the incident angle ∠A1 and the exit angle ∠A2, both of which are acute angles. In the present invention, the spiral cavities that are spatially adjacent but do not interfere with each other avoid the impact and mixing of the cooling airflow inside the laminate, reduce flow resistance and flow loss, and greatly reduce the flow resistance loss.

Description

technical field [0001] The invention belongs to the technical field of turbine cooling for aero-engines and gas turbines, and relates to a laminate cooling structure using polygonal spoiler columns. Background technique [0002] At present, in order to increase the thrust of the aero-engine and the power of the gas turbine, the method of increasing the temperature before the turbine is generally adopted, which brings about the increase of the heat load of the turbine components. In addition, these turbine components working in a high-temperature environment also bear loads caused by factors such as high speed, high pressure, and large vibration. In such a harsh working environment, to ensure the normal, reliable and long-term operation of the turbine, it is necessary to effectively cool the turbine components to keep them in a reliable working temperature range. The principle of cooling is to use the least amount of cold air to remove as much heat as possible, keep the comp...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/18F01D25/12
CPCF01D5/186F01D5/187F01D25/12
Inventor 吕东王楠周亦胄朱剑琴孔星傲
Owner DALIAN UNIV OF TECH