Laminate cooling structure adopting polygonal turbulent flow columns

A technology of cooling structure and spoiler column, applied in the direction of supporting elements of blades, engine elements, machines/engines, etc., can solve the problems of increased heat load of turbine components, reduce flow resistance and flow loss, and achieve good heat exchange effect , Avoid the effects of backflow and streaming

Active Publication Date: 2020-05-12
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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  • Laminate cooling structure adopting polygonal turbulent flow columns
  • Laminate cooling structure adopting polygonal turbulent flow columns
  • Laminate cooling structure adopting polygonal turbulent flow columns

Examples

Experimental program
Comparison scheme
Effect test

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 aero-engine and gas turbine cooling, and relates to a laminate cooling structure adopting polygonal turbulent flow columns. The laminate cooling structure comprises an air inlet hole positioned in an air inlet plate, an air outlet hole positioned in an air outlet plate, the turbulent flow columns and a spiral cavity, wherein the turbulent flow columns are positioned in the center of the spiral cavity and form a cold air channel, and the number of the edges of the turbulent flow columns is any one of 3, 4, 5, 6 to n; the cross sections of the airinlet hole and the air outlet hole are in a parallelogram shape, the air inlet hole and the air outlet hole are smoothly connected with the channel in the spiral cavity through an arc-shaped sliding way, and the air inlet hole and the air outlet hole extend outwards from the two adjacent edges of the polygonal turbulent flow columns; and the included angles between the center line of the air inlethole and the horizontal plane and between the center line of the air outlet hole and the horizontal plane are an incident angle A1 and an emergent angle A2 correspondingly, and the incident angle A1and the emergent angle A2 are acute angles. According to the laminate cooling structure, the spiral cavities which are adjacent in space but do not interfere with each other avoid impact and mixing ofcooling airflow in a laminate, so that the flow resistance and the flow loss can be reduced, and the flow resistance loss is greatly reduced.

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 Applications(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
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