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Structure for improving air film cooling efficiency of downstream wall surface of slotted air film hole

An air film cooling and air film hole technology, which is applied to the supporting elements of blades, machines/engines, mechanical equipment, etc., can solve the problems of flow obstruction, and do not consider the superposition of air film cooling and cooling, so as to achieve improved coverage and enhanced coverage. Lateral cooling effect, simple structure effect

Active Publication Date: 2015-05-06
HEBEI UNIV OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The Chinese patent application No. 201010106756.6 discloses a structure to improve the efficiency of film cooling in discrete holes. Its disadvantage is that the structure does not consider the superimposed effect of film cooling on the cooling of transverse slots. The protrusions arranged downstream are not only One-piece structure, and it is close to the gas film hole, which will hinder the flow to a certain extent. At the same time, the elevation of the protrusion exposes a certain range downstream of the protrusion to high-temperature gas, without protecting the cooling gas.

Method used

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  • Structure for improving air film cooling efficiency of downstream wall surface of slotted air film hole
  • Structure for improving air film cooling efficiency of downstream wall surface of slotted air film hole
  • Structure for improving air film cooling efficiency of downstream wall surface of slotted air film hole

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Embodiment 1

[0032] In this embodiment, the structure (see Figure 1-3 ) includes air film hole 1, transverse slot 2, protrusion 3 and wall surface 4, protrusion 3 is located in the downstream direction of wall surface 4, protrusion 3 is two semi-bracket-shaped circular arcs, and the two arcs pass through the air film hole The center of the outlet 11 and the straight line perpendicular to the wall 4 are axisymmetrically arranged. The direction of the protrusion 3 facing the air film hole 1 is the front part, the front part is the air inlet 33, and the opposite direction is the air outlet 34. The protrusion 3 The profile of the side facing away from the air film hole is the back pressure profile 32, the profile of the side facing the air film hole 1 is the windward profile 31, and the back pressure profile 32 and the windward profile 31 are arc lines. exist figure 2 and image 3 Among them, the three flow directions are represented by coordinates X, Y, and Z respectively, X is the flow d...

Embodiment 2

[0038] The position and connection relationship of each part in the described structure of this embodiment are the same as those in Embodiment 1. In this embodiment, the protrusion 3 is two spiral protrusions, and the two spiral protrusions are arranged axisymmetrically with the center of the outlet 11 of the air film hole and perpendicular to the wall 4, and the protrusion 3 faces the air film The direction of the hole 1 is the front, the front is the air inlet 33, and the opposite direction is the air outlet 34, and the side profile of the protrusion 3 facing away from the air film hole is the back pressure profile 32, facing the air film hole One side of 1 is the windward profile 31, the back pressure profile 32 is a spiral and protrudes downstream of the wall, the windward profile 31 is an arc line and protrudes downstream of the wall, the windward profile 31 and the back pressure The spacing of the molded lines 32 is adjustable, and the spacing gradually decreases from th...

Embodiment 3

[0041] The position and connection relationship of each part in the described structure of this embodiment are the same as those in Embodiment 1. Protrusion 3 is two prism type arcs in the present embodiment (referring to Figure 9 ), the two circular arcs are axisymmetrically arranged with the center of the air film hole outlet 11 and the straight line perpendicular to the wall surface 4, the direction of the protrusion 3 facing the air film hole 1 is the front, and the front is the air inlet 33, on the contrary The direction is the air outlet 34, the side profile of the protrusion 3 facing away from the air film hole is the back pressure profile 32, the side profile facing the air film hole 1 is the windward profile 31, and the back pressure profile 32 It is an arc protruding toward the downstream direction of the wall surface, the windward profiled line 31 is a straight line, and the distance between the windward profiled line 31 and the backpressure profiled line 32 is a v...

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Abstract

The invention relates to a structure for improving the air film cooling efficiency of a downstream wall surface of a slotted air film hole. The structure comprises an air film hole, a transverse slot and a wall surface, wherein the transverse slot is formed in the upstream area of the wall surface; the air film hole is positioned in the transverse slot. The structure is characterized in that a bump is arranged on the downstream area of the wall surface, is symmetrically arranged by taking a straight line passing through the center of an outlet of the air film hole and perpendicular to the wall surface as an axis, and is provided with an air inlet in the direction leading to the air film hole and an air outlet in the opposite direction, wherein the profile of the side, back on to the air film hole, of the bump is a back pressure profile, and the profile of the side, leading to the air film hole, of the bump is a windward profile; the back pressure profile is a profile protruded towards the downstream of the wall surface; the length of the air inlet is 2 to 5 times the aperture of the air film hole, and is 1.5 to 4 times that of the air outlet; the ratio of the distance between the air inlet of the bump to the center of the outlet of the air film hole to the aperture of the air film hole is 10 to 30; the ratio of the height of the bump to the aperture of the air film hole is 0.25 to 3.

Description

technical field [0001] The invention relates to the technical field of gas turbine heat transfer and cooling, in particular to a structure for improving the gas film cooling efficiency of the downstream wall surface of a slotted gas film hole. Background technique [0002] Gas turbines are widely used in aviation, power generation, chemical industry, energy and power engineering and other fields. By increasing the inlet temperature of the turbine rotor, the thermal efficiency and power output of the gas turbine can be effectively increased. At present, the inlet temperature of advanced gas turbines has exceeded 2000K, which is more than 400K higher than the melting point of high-pressure turbine blade metal materials. The solution to the problems caused by high temperatures is mainly to develop high-performance heat-resistant alloys and adopt advanced cooling technologies. The current technological progress in metal materials is far behind the increasing trend of engine turb...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/18
Inventor 王进闵春华崔沛田丽亭陈占秀
Owner HEBEI UNIV OF TECH
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