WO2019237720A1 - 一种在基体表面产生连续气膜的方法 - Google Patents

一种在基体表面产生连续气膜的方法 Download PDF

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WO2019237720A1
WO2019237720A1 PCT/CN2018/125087 CN2018125087W WO2019237720A1 WO 2019237720 A1 WO2019237720 A1 WO 2019237720A1 CN 2018125087 W CN2018125087 W CN 2018125087W WO 2019237720 A1 WO2019237720 A1 WO 2019237720A1
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Prior art keywords
groove
substrate
groove body
gas
air film
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PCT/CN2018/125087
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English (en)
French (fr)
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张文武
郭春海
王玉峰
张天润
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中国科学院宁波材料技术与工程研究所
宁波大艾激光科技有限公司
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Publication of WO2019237720A1 publication Critical patent/WO2019237720A1/zh

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling

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  • the present application relates to the technical field of substrate surface treatment, and in particular, to a method for generating a continuous air film on the surface of a substrate.
  • a hot gas film can be used to heat the substrate, and a cooling gas film can be used to cool and protect the substrate.
  • the combustion chamber is a device that converts the chemical energy of fuel into thermal energy, and is one of the core components of engines and gas turbines.
  • the combustion process of the combustion chamber mainly occurs in the flame tube of the combustion chamber.
  • the wall surface of the flame tube must withstand the thermal stress and thermal corrosion caused by the high temperature flame.
  • the harsh use environment has brought great challenges to its service life and reliability.
  • blades are the core components of power plants such as aero-engines and gas turbines, among which turbine blades, as the key components of thermal energy conversion, need to work under high-temperature and high-pressure alternating loads and need to withstand operating temperatures higher than their own melting points.
  • turbine blades as the key components of thermal energy conversion
  • these building materials need to withstand high-temperature flames, thermal stress from gases, and thermal corrosion.
  • Such a harsh environment poses a huge challenge to the service life and reliability of the substrate. To this end, it is proposed to protect the substrate with cooling.
  • Air film cooling is one of the currently used high-efficiency cooling technologies.
  • the basic principle is to introduce cooling air from the compressor.
  • the cooling air flows out through the cooling holes densely covered on the substrate and covers the surface of the substrate to form a cold air film with a lower temperature.
  • Patent document US2010 / 0040478A1 combines discrete cooling holes with shallow grooves, and several shallow grooves are provided on one surface of the base body, and a plurality of shallow grooves are provided along the length direction of the shallow grooves at the bottom of each shallow groove.
  • Surface oblique holes.
  • the high-temperature gas acts on the side of the substrate provided with the shallow groove in the working state. After the cooling gas enters the shallow groove from the inclined hole, the cooling gas flows along the length of the groove on the one hand, because the angle with the bottom of the groove is small. It tends to tend to flow on the surface of the substrate.
  • the flow of cooling gas is restricted by the two side walls of the groove, which prevents the cooling gas from mixing with the high-temperature gas flow after it flows out of the cooling holes and hinders the A cooling gas film is formed on the surface of the substrate.
  • Patent document US2011 / 0097188A1 also combines discrete cooling holes with shallow grooves, and proposes that the cooling holes can be divided into two parts with different shapes, that is, the cooling hole structure is a special-shaped hole.
  • the groove body has a small depth and is a shallow groove.
  • patent document US2010 / 0040478A1 states that the depth of the groove is smaller than the minimum diameter of the cooling hole.
  • Such a tank can only assist the cooling gas from the cooling holes to adjust the airflow direction.
  • the initial gas film is still mainly formed by the cooling holes. Therefore, the uniformity of the gas film flowing out of the tank is still insufficient.
  • there is a problem that the cooling effect of the gas film is limited.
  • in order to form a continuous gas film more cooling holes need to be provided, which will reduce the mechanical strength of the substrate.
  • the present invention provides a method for generating a continuous air film on the surface of a substrate, and the method can be used to form a continuous and uniform air film on the surface of the substrate.
  • a method for generating a continuous air film on the surface of a substrate includes the following steps:
  • the groove structure includes the bottom of the groove and two side walls along the length of the groove.
  • a plurality of discrete holes penetrating to the other surface of the base body is provided at the bottom of each groove body, and the other surface is referred to as a B surface, and the discrete holes are generally arranged along the length direction of the groove body;
  • the depth of the groove structure be H, and set the groove body to be composed of two parts along the depth direction.
  • the part with the depth H 1 from the bottom of the groove body is the first part, which is called the middle expansion groove, and the remaining part is the second part, which is called the surface.
  • the open end of the groove body in the depth direction is optimized according to the aerodynamic needs of the air film attachment, so that the gas is modulated by the surface modulation groove, flows out from the open end, and forms a continuous uniform adherence on the A surface of the substrate. Air film.
  • at least one side wall of the surface modulation groove is formed by lateral expansion of the same side wall of the first portion.
  • the maximum diameter of the discrete holes is d and the minimum width of the groove body is D.
  • D Preferably, D ⁇ d.
  • the groove body is divided into an intermediate development groove and a surface modulation groove.
  • H ⁇ 2d more preferably H ⁇ 3d, and even more preferably H ⁇ 4d.
  • the angle between the axis of the outlet end of the groove body in the depth direction and the normal line of the A surface of the substrate is ⁇ , and preferably 10 ° ⁇ ⁇ ⁇ 90 °, more preferably 30 ° ⁇ ⁇ ⁇ 80 °, and more preferably 45 ° ⁇ 70 °.
  • two side walls of the middle development groove are two straight line segments with an interval.
  • the included angle between each straight line segment and the groove bottom is preferably 10 ° -170 °, more preferably 30 ° -150 °, and still more preferably 60 ° -120 °.
  • the two straight line segments can be parallel to each other or can form a certain angle.
  • the side wall of the surface modulation groove may be a straight line segment or an arc line segment.
  • at least one side wall of the surface modulation groove is an arc line segment.
  • the connection between at least one side wall of the middle deployment groove and the same side wall of the surface modulation groove is a chamfered transition connection or a circular arc transition connection to achieve a smooth connection.
  • the depth H 1 of the intermediate expansion tank is longer than that of the surface modulation tank, that is, H 1 > H 2 , as Preferably, H 1 : H 2 ⁇ 2: 1; further preferably H 1 : H 2 ⁇ 3: 1, and more preferably H 1 : H 2 ⁇ 4: 1.
  • the A surface of the base body and the B surface of the base body may be parallel to each other and may form a certain angle with each other.
  • the discrete holes can be straight round holes, diffuse holes, or complex three-dimensional shaped holes.
  • the included angle between the central axis of the discrete holes and the A surface of the substrate is ⁇ .
  • the included angle ⁇ and the included angle ⁇ may be different.
  • the included angle ⁇ is mainly for reducing the thickness of the hole processing, and is generally preferably 0 ° ⁇ ⁇ ⁇ 60 °, more preferably 10 ° ⁇ ⁇ ⁇ 45 °; the included angle ⁇ is mainly for ensuring good air film attachment.
  • the open end of the discrete hole is provided with a chamfered transition structure or a circular arc transition structure to avoid problems such as stress concentration caused by sharp structures and poor gas flow.
  • each groove on the surface of the substrate is not limited. According to the actual shape of the substrate surface, it can be arranged in parallel or staggered, so that the continuous air film formed by each groove covers the substrate surface.
  • the present invention provides discrete holes and grooves on the surface of the substrate, and the grooves are designed as shaped grooves formed by two parts along the depth direction of the grooves, the first part is an intermediate expansion groove, and the second part is opposite A lateral expansion is formed in the first part.
  • the gas from the discrete holes is sufficiently diffused and mixed in the middle expansion tank to form a uniform positive pressure gas, and then flows out through the open end after being modulated by the surface modulation tank, thereby forming a uniform and continuous surface on the substrate. Air film.
  • it has the following beneficial effects:
  • the cooling gas film is formed, and compared with the existing simple shallow grooves, the present invention sets the groove body as a deep groove of complex anisotropy.
  • the groove body is divided into a middle expansion groove and a surface modulation groove.
  • the discrete holes are combined with the groove body, and the groove body is designed as a shaped groove formed by two parts along the depth direction of the groove body.
  • the first part is a middle expansion groove, and the second part forms a lateral expansion relative to the first part.
  • the gas from the discrete holes is first fully diffused and mixed in the middle expansion tank to form a uniform positive pressure gas, and then flows out through the open end after being modulated by the surface modulation tank, thereby forming a uniform and continuous gas film on the surface of the substrate.
  • the trough body is a special-shaped groove formed in two sections and has a large depth.
  • the vertical cross section along the width direction of the trough body has a narrow and elongated structure. It can be expanded and mixed in the length direction, and can be diffused, mixed, and superimposed on each other along the depth of the tank. That is, it can be fully diffused and mixed in the middle expansion slot to form a continuous and uniform positive pressure gas.
  • the outflow ends, and the shape of the open end is optimized according to the aerodynamic needs of the air film attachment, so as to form a uniform, continuous, and attached air film on the surface of the substrate. And because the depth of the tank is large, the gas flowing from the open end of the tank has a strong air pressure, so a continuous and uniform air film formed on the surface of the substrate is strongly attached to the surface of the substrate.
  • FIG. 2 The aerodynamic simulation diagram of the gas in the film cooling structure of the present invention is shown in Fig. 2, which confirms that the gas in the present invention can be sprayed into the tank through discrete holes, and expanded and mixed in the tank to form a continuous, uniform positive Press the gas, and then form a continuous, continuous, uniform, adherent gas film cover on the surface of the substrate.
  • the continuous gas film generating structure of the present invention can be used to form a hot gas film on the surface of the substrate, and can also be used to form a cooling gas film on the surface of the substrate to achieve cooling protection for the substrate to prevent thermal damage to the substrate in a high temperature hot gas environment. Thermal corrosion.
  • the equivalent cooling efficiency at point C can be increased to 0.7 or more.
  • FIG. 1 is a pneumatic simulation diagram of a gas in the method of the present invention
  • FIG. 2 is a schematic diagram of a structure arrangement of a turbine blade in Embodiment 1 of the present invention
  • FIG. 3 is a schematic structural view of a horizontal section of FIG. 2;
  • FIG. 4 is a schematic structural diagram of a groove body in FIG. 3;
  • FIG. 5 is a schematic diagram of cooling gas transmission in a tank structure in FIG. 3.
  • Reference numerals in Figures 3-5 are: 100-turbine blade; 101-turbine blade A surface; 102-turbine blade B surface; 105-slot body; 106-partition line; 301-the second part of the slot body 302- the first part of the tank; 400- discrete holes; 500- the bottom of the tank; 600 and 700- both sides of the tank.
  • the base is the turbine blade 1.
  • the turbine blade 100 is a combination of the split body I and the split body II, where the split body I and the split body II are connected to form a complete turbine blade 100 at a dividing line 106.
  • One surface of the turbine blade 1, that is, the A surface 101 of the turbine blade, is provided with a plurality of groove structures 105 spaced apart from each other and parallel to each other.
  • the length of the groove body may partially or entirely penetrate the A surface 101 of the turbine blade.
  • FIG. 3 is a schematic structural view of a horizontal section of FIG. 2.
  • FIG. 4 is an enlarged structural diagram of a slot structure 105 in FIG. 3.
  • each groove body includes a groove body bottom 500 and two side walls 600 and 700 along the length of the groove body; each groove body is provided with a plurality of discrete holes 400 penetrating to the base surface 102, The discrete holes are generally aligned along the length of the slot.
  • the A surface 101 of the turbine blade is substantially parallel to the B surface 102 of the turbine blade.
  • the depth of the groove body to be H, and set the groove body in the depth direction to be composed of two parts that communicate with each other to form a special-shaped groove.
  • the depth H 1 of the intermediate development groove is slightly larger than the depth H 2 of the surface modulation groove.
  • the middle development groove is an inclined column structure, and the two side walls in the vertical section are two straight line segments spaced apart from each other. The two straight line segments are parallel to each other.
  • the angle between each straight line segment and the bottom of the groove is 70 °.
  • One side wall of the surface modulation groove is also a straight line segment, which is formed by extending the same side wall of the middle expansion groove, and the other side wall is an arc segment, which is formed by the lateral expansion of the same side wall of the first part.
  • the angle ⁇ between the axis of the open end of the surface modulation groove in the depth direction and the normal line of the A surface 101 of the turbine blade is 30 °.
  • an included angle ⁇ between the central axis of the discrete hole and the normal direction of the B surface 102 of the turbine blade is 15 °, and an arc transition structure is set at the open end of the hole to avoid the sharp structure stress concentration phenomenon.
  • FIG. 5 is a schematic diagram of the cooling gas transmission in a tank of FIG. 3.
  • the cooling gas on the B surface 102 side of the turbine blade enters the tank from the discrete hole, and then it is fully diffused and mixed in the middle expansion tank to form a uniform positive pressure gas. Then, it is modulated by the surface modulation tank to the A surface side of the turbine blade. Outflow, a uniform and continuous gas film is formed on the A surface of the turbine blade, and because the groove depth is large, the gas flowing out of the open end of the shaped groove has a strong pressure, so the continuous and uniform formation on the A surface of the turbine blade The air film is strongly attached to the A surface of the turbine blade.
  • This embodiment is basically the same as Embodiment 1, except that: H 1 : H 2 ⁇ 2: 1; the angle ⁇ between the central axis of the discrete hole and the normal direction of the B surface 102 of the turbine blade is 0 °; The angle ⁇ between the axis of the open end of the surface modulation groove in the depth direction and the normal to the A surface 101 of the turbine blade is 45 °.
  • Example 1 after the cooling gas on the B surface 102 side of the turbine blade enters the tank from the discrete holes, it is first diffused and mixed in the middle expansion tank to form a uniform positive pressure gas, and then modulated by the surface modulation tank to be biased The A-surface side of the turbine blade flows out, and a continuous and uniform air film is formed on the A-surface of the turbine blade to adhere strongly to the A-surface of the turbine blade.
  • This embodiment is basically the same as Embodiment 1, except that H 1 : H 2 ⁇ 3: 1; the included angle ⁇ between the central axis of the discrete hole and the normal direction of the B surface 102 of the turbine blade is 10 °; The two side walls of the intermediate expansion groove 302 are spaced by two parallel linear sections spaced apart from each other, and the angle between each linear section and the bottom of the groove is 65 °; the axis of the open end of the surface modulation groove in the depth direction and the A of the turbine blade The angle ⁇ between the normals of the surface 101 is 50 °.
  • Example 1 after the cooling gas on the B surface 102 side of the turbine blade enters the tank from the discrete holes, it is first diffused and mixed in the middle expansion tank to form a uniform positive pressure gas, and then modulated by the surface modulation tank to be deflected.
  • the A-surface side of the turbine blade flows out, and a continuous and uniform air film is formed on the A-surface of the turbine blade to adhere strongly to the A-surface of the turbine blade.
  • This embodiment is basically the same as Embodiment 1, except that: H 1 : H 2 ⁇ 4: 1; the included angle ⁇ between the central axis of the discrete hole and the normal direction of the B surface 102 of the turbine blade is 10 °; The two side walls of the intermediate expansion groove 302 are spaced by two mutually parallel straight line segments, and the angle between each straight line segment and the groove bottom is 75 °; the axis of the open end of the surface modulation groove in the depth direction and the A of the turbine blade The angle ⁇ between the normals of the surface 101 is 50 °.
  • Example 1 after the cooling gas on the B surface 102 side of the turbine blade enters the tank from the discrete holes, it is first diffused and mixed in the middle expansion tank to form a uniform positive pressure gas, and then modulated by the surface modulation tank to be biased The A-surface side of the turbine blade flows out, and a continuous and uniform air film is formed on the A-surface of the turbine blade to adhere strongly to the A-surface of the turbine blade.

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Abstract

一种在基体表面产生连续气膜的方法，在基体的A表面设置若干内凹的槽体结构，该槽体结构包括槽体底部，以及沿着槽体长度方向的两侧壁；在每个槽体底部设置若干贯穿至基体的另一B表面的离散孔，该离散孔大体沿着该槽体的长度方向排列；槽体结构的深度为H，槽体沿深度方向由两部分组成，自槽体底部深度为H 1的第一部分为中间展开槽，剩余部分为深度为H 2的第二部分为表面调制槽，使基体的B表面侧的冷却气体自离散孔进入槽体结构后，首先在中间展开槽内充分扩散、混合，形成均匀的正压气体，然后通过表面调制槽调制后流出，在基体的A表面形成均匀、连续、贴附的气膜。

Description

一种在基体表面产生连续气膜的方法 技术领域
本申请涉及基体表面处理技术领域，尤其涉及一种在基体表面产生连续气膜的方法。
背景技术
在基体表面形成气膜有很多用途，形成热气膜可对基体进行加热等，形成冷却气膜可对基体进行冷却保护。
在工业与航空航天等技术领域中，很多基体工作在高温燃气环境中，需要经受高温火焰引起的热应力和热腐蚀。例如，燃烧室是将燃油的化学能转变为热能的装置，是发动机和燃气轮机的核心部件之一。燃烧室的燃烧过程主要发生在燃烧室的火焰筒内，火焰筒壁面需承受高温火焰引起的热应力和热腐蚀，苛刻的使用环境对其使用寿命和可靠性提出了巨大挑战。又例如，叶片是航空发动机、燃气轮机等动力装置的核心部件，其中涡轮叶片作为热能转换的关键部件，需要工作于高温高压交变载荷下，需要承受高出自身熔点的工作温度。另外，对于某些高危环境中的建筑材料而言，当发生火灾、爆炸等意外环境时，这些建筑材料需经受高温火焰、气体的热应力和热腐蚀。这样苛刻的环境对基体的使用寿命和可靠性提出了巨大挑战，为此提出对基体进行冷却保护。
气膜冷却是当前采用的高效冷却技术之一，其基本原理是从压气机引入冷却空气，冷却空气通过密布于基体上的冷却孔流出并覆盖于基体表面形成温度较低的冷气膜，从而达到隔绝高温燃气与基体表面的目的，降低基体表面温度，实现对基体表面冷却保护的作用，保证基体长期运行的可靠性。
早期的气膜冷却是由壁面狭缝或者小孔吹出的冷流来阻隔主燃气，如美国专利US4896510A所示，具有整体机构刚性好、冷却流量可控性好等优势，但存在冷气需求量大，对火焰筒壁面冷却不均匀等问题。多斜孔气膜冷却通过斜孔结构以一定的角度射出冷气，在火焰筒壁面形成隔离气膜，起到保护壁面的作用。早期，斜孔多为直圆孔，存在单孔保护面积偏小，吹风比大时气膜剥离严重等问题，需要很密集的气膜孔。后来在气膜冷却技术中采用先进的扩散孔和复杂三维异型孔，相对于简单直圆孔可以大幅度增加单孔降温保护面积和在各种吹风比下的气膜贴附度，如美国专利US2008/0271457 A1所示。但是，使用气膜孔时，基体表面气膜的均匀度与孔的分布和形状密切相关，气膜覆盖均匀性不足，成为制约基体表面降温防护的主要技术瓶颈。
专利文献US2010/0040478A1将离散冷却孔与浅槽相结合，在基体的一个表面设置若干浅槽，在每个浅槽的槽体底部大体沿着该浅槽的长度方向设置若干贯 穿该基体另一个表面的斜孔。在该结构中，工作状态时高温燃气作用在设置浅槽的基体侧，冷却气体自斜孔进入浅槽后一方面冷却气体沿着槽体长度方向流动，由于与槽体底部的夹角较小而易倾向基体表面流动，另一方面由于浅槽的设置，冷却气体的流动受到槽体两侧壁的限制，从而防止了冷却气体自冷却孔流出后大部分与高温燃气流相混合而阻碍在基体表面形成冷却气膜。
专利文献US2011/0097188A1也将离散冷却孔与浅槽相结合，并且提出冷却孔可以分为形状不同的两部分，即冷却孔结构为异形孔。
但是，上述两项专利技术中槽体深度小，为浅槽。例如，专利文献US2010/0040478A1中指出槽体深度小于冷却孔的最小直径。这样的槽体只能对来自冷却孔的冷却气体辅助性地进行调节气流流向的作用，初始气膜仍是以冷却孔为主体形成，因此自槽体流出的气膜仍然存在均匀性不足，不能完全覆盖基体表面的问题。另外，还存在气膜冷却效果有限的问题。除此之外，这种结构中，为了形成连续气膜，需要设置较多的冷却孔，这将降低基体的力学强度。
因此，如何通过结构设计在基体表面形成连续的、均匀的气膜是科技工作者的研究课题之一，将对许多领域带来有益的技术效果。
发明内容
针对上述技术现状，本发明提供了一种在基体表面产生连续气膜的方法，利用方法可在基体表面形成连续的、均匀的气膜。
本发明的技术方案为：
一种在基体表面产生连续气膜的方法，包括如下步骤：
在基体的一个表面，称为A表面，设置若干内凹的槽体结构，所述槽体结构包括槽体底部，以及沿着槽体长度方向的两侧壁；
在每个槽体底部设置若干贯穿至基体另一表面的离散孔，该另一表面称为B表面，所述离散孔大体沿着该槽体的长度方向排列；
设槽体结构的深度为H，设置槽体沿深度方向由两部分组成，自槽体底部深度为H 1的部分为第一部分，称为中间展开槽，剩余部分为第二部分，称为表面调制槽，即，表面调制槽的深度H 2＝H-H 1，使基体的B表面侧的气体自离散孔进入槽体结构后，首先在中间展开槽内充分扩散、混合，形成均匀的正压气体，然后通过表面调制槽调制后流出，在基体的A表面形成均匀连续气膜。
作为优选，按照气膜贴附的气动需要对所述槽体沿深度方向的开口端进行优化设计，使气体经表面调制槽调制，自开口端流出，在基体的A表面形成连续的均匀贴附的气膜。作为一种优化的实现方式，所述表面调制槽的至少一侧壁是由第一部分的同侧壁横向扩张形成。
设所述离散孔的最大直径为d，所述槽体的最小宽度为D，作为优选，D≥d。
本发明中，沿着槽体深度方向，槽体分为中间展开槽与表面调制槽，作为优 选，H≥2d，进一步优选为H≥3d，更优选为H≥4d。
所述槽体沿深度方向的出口端部的轴线与基体的A表面的法线夹角为α，作为优选，10°≤α≤90°，进一步优选为30°≤α≤80°，更优选为45°≤α≤70°。
作为一种实现方式，所述槽体的沿着槽体宽度方向的垂直截面中，中间展开槽的两侧壁为存间隔的两条直线段。每条直线段与槽底夹角优选为10°-170°，进一步优选为30°-150°，更优选为60°-120°。两条直线段可以互相平行，也可以形成一定夹角。表面调制槽的侧壁可以是平直线段，也可以是弧线段，作为优选，表面调制槽的至少一侧壁为弧线段。另外，作为优选，中间展开槽的至少一侧壁与表面调制槽的同侧壁的连接处为倒角过渡连接，或者为圆弧过渡连接，以实现平滑连接。
为了使冷却气体在中间展开槽内充分扩散、混合，形成均匀的正压气体，作为优选，与表面调制槽相比，中间展开槽的深度H 1较长，即，H 1>H 2，作为优选，H 1：H 2≥2：1；进一步优选为H 1：H 2≥3：1，更优选为H 1：H 2≥4：1。
所述的基体的A表面与基体的B表面可以互相平行，与可以呈一定夹角。
所述的离散孔可以是直圆孔，也可以是扩散孔，也可以是复杂的三维异形孔。作为优选，所述的离散孔的中心轴线与基体的A表面的夹角为θ。夹角α与夹角θ可以不同。作为优选，夹角θ以减少孔加工厚度为主，一般优选为0°≤θ≤60°，更优选为10°≤θ≤45°；夹角α以保障良好气膜贴附为主。作为优选，所述的离散孔的开口端设置倒角过渡结构或者圆弧过渡结构，以避免尖锐结构造成应力集中现象，以及气体流通不畅等问题。
各个槽体在基体表面的设置不限，根据基体表面的实际形状可以是存间距平行排列，也可以是交错排列等，以使各个槽体形成的连续气膜对基体表面形成全覆盖为主。
与现有技术相比，本发明在基体表面设置离散孔与槽体，并且沿着槽体深度方向将槽体设计为由两部分形成的异形槽，第一部分为中间扩展槽，第二部分相对于第一部分形成横向扩张，来自离散孔的气体首先在中间展开槽内充分扩散、混合，形成均匀的正压气体，然后通过表面调制槽调制后经开口端流出，从而在基体表面形成均匀、连续的气膜。与现有技术相比，具有如下有益效果：
形成冷却气膜，并且与现有的简单浅槽相比，本发明设置槽体为复杂异性的深槽，沿槽体深度方向，槽体分为中间展开槽与表面调制槽，
(1)现有方法中，离散孔与浅槽相结合，气体自离散孔喷出后，表面浅槽只是起到辅助性地调节气流流向的作用，因此气膜仍是以离散孔为主体形成的，并未进行充分扩展叠加而形成连续的均匀的正压气体。
而本发明中，将离散孔与槽体结合，并且沿着槽体深度方向将槽体设计为由两部分形成的异形槽，第一部分为中间扩展槽，第二部分相对于第一部分形成横向扩张，来自离散孔的气体首先在中间展开槽内充分扩散、混合，形成均匀的正 压气体，然后通过表面调制槽调制后经开口端流出，从而在基体表面形成均匀、连续的气膜。
气体自离散孔进入槽体后，由于槽体为两段形成的异形槽，具有较大深度，沿着槽体宽度方向的垂直截面呈狭长结构，来自各离散孔的扩散气体不仅会沿槽体长度方向扩展、混合，而且能够沿着槽体深度方向扩散、混合、相互叠加，即，能够在中间展开槽充分扩散、混合，形成连续、均匀的正压气体，然后通过表面调制槽调制经开口端流出，按照气膜贴附的气动需要对开口端的形状进行优化设计，从而在基体表面形成均匀、连续、贴附的气膜。并且由于槽体深度较大，由槽体开口端流出的气体具有强大的气压，因此在基体表面形成的连续均匀的气膜强力贴附在基体表面。
(2)气体在本发明的气膜冷却结构内的气动仿真图如2所示，证实了本发明中气体可以经离散孔喷射至槽体，在槽体内扩展、混合，形成连续、均匀的正压气体，然后在基体表面形成连续、连续、均匀、贴附的气膜覆盖。
(3)本发明的连续气膜发生结构可以用于在基体表面形成热气膜，也可用于在基体表面形成冷却气膜，对基体实现冷却保护，以防止基体在高温热气环境中的热损伤与热腐蚀。实验证实，当基体处于高温热气环境中时，利用本发明的方法产生的冷却气膜具有良好的冷却效果，等效冷却效率＝(热气温度-在C点测得的温度)/(热气温度-冷却气体温度)时，在冷却气体的吹风比M＝1.5情况下，利用本发明的方法产生的冷却气膜具有等效冷却效率为0.5以上的C点距离基体的A表面十毫米以上，当冷却气体吹风比增大，C点的等效冷却效率可提高至0.7以上。
附图说明
图1是本发明的方法中气体的气动仿真图；
图2是本发明实施例1中对涡轮叶片的结构设置示意图；
图3是图2的水平截面结构示意图；
图4是图3中的一个槽体结构示意图；
图5是冷却气体在图3中的一个槽体结构中的传输示意图。
具体实施方式
下面结合实施例对本发明作进一步详细描述，需要指出的是，以下所述实施例旨在便于对本发明的理解，而对其不起任何限定作用。
图3-5中的附图标记为：100-涡轮叶片；101-涡轮叶片的A表面；102-涡轮叶片的B表面；105-槽体；106-分割线；301-槽体的第二部分；302-槽体的第一部分；400-离散孔；500-槽体底部；600、700-槽体两侧壁。
实施例1:
本实施例中，基体是涡轮叶片1。如图2所示，涡轮叶片100是由分体Ⅰ和 分体Ⅱ组合而成，其中分体Ⅰ和分体Ⅱ在分割线106处连结为一个完整涡轮叶片100。
涡轮叶片1的一个表面，即涡轮叶片的A表面101设置多个彼此存间隔互相平行的槽体结构105，槽体的长度可部分或整体贯穿涡轮叶片的A表面101。
图3是图2的水平截面的结构示意图。
图4是图3中一个槽体结构105的放大结构示意图。
从图4中可以看出，每个槽体包括槽体底部500，以及沿着槽体长度方向的两侧壁600与700；每个槽体底部设置若干贯穿至基体表面102的离散孔400，这些离散孔大体沿着该槽体的长度方向排列。本实施例中，涡轮叶片的A表面101与涡轮叶片的B表面102大体平行。
设离散孔400的最大直径为d，槽体的最小宽度为D，本实施例中D≥d。
设槽体的深度为H，设置槽体沿深度方向由互相连通的两部分组成，形成异形槽，如图4所示，自槽体底部深度为H 1的部分为槽体的第一部分302，称为中间展开槽，剩余部分为槽体的第二部分301，称为表面调制槽，即，第二部分深度为H 2＝H-H 1。本实施例中，中间展开槽的深度H 1略大于表面调制槽的深度H 2，。
本实施例中，中间展开槽呈倾斜的柱体结构，其垂直截面中两侧壁呈存间隔的两条直线段，两条直线段互相平行，每条直线段与槽底夹角为70°；表面调制槽的一个侧壁也为直线段，是由中间展开槽的同侧壁延伸形成，另一个侧壁呈弧线段，是由第一部分的同侧壁横向扩张形成。本实施例中，表面调制槽沿深度方向的开口端部的轴线与涡轮叶片的A表面101的法线之间的夹角α为30°。
本实施例中，离散孔的中心轴线与涡轮叶片的B表面102的法向之间的夹角θ为15°，并且孔的开口端设置圆弧过渡结构，以避免尖锐结构应力集中现象。
图5是冷却气体在图3的一个槽体中的传输示意图。涡轮叶片的B表面102侧的冷却气体自离散孔进入槽体后，首先在中间展开槽内充分扩散、混合，形成均匀的正压气体，然后通过表面调制槽调制后偏向涡轮叶片的A表面侧流出，在涡轮叶片的A表面形成均匀、连续的气膜，并且由于槽体深度较大，由异形槽开口端流出的气体具有强大的气压，因此在涡轮叶片的A表面形成的连续、均匀的气膜强力贴附在涡轮叶片的A表面。
实施例2：
本实施例与实施例1基本相同，所不同的是：H 1：H 2≥2：1；离散孔的中心轴线与涡轮叶片的B表面102的法向之间的夹角θ为0°；表面调制槽沿深度方向的开口端部的轴线与涡轮叶片的A表面101的法线之间的夹角α为45°。
与实施例1相同，涡轮叶片的B表面102侧的冷却气体自离散孔进入槽体后，首先在中间展开槽内充分扩散、混合，形成均匀的正压气体，然后通过表面调制槽调制后偏向涡轮叶片的A表面侧流出，在涡轮叶片的A表面形成连续、均匀的气膜强力贴附在涡轮叶片的A表面。
实施例3：
本实施例与实施例1基本相同，所不同的是：H 1：H 2≥3：1；离散孔的中心轴线与涡轮叶片的B表面102的法向之间的夹角θ为10°；中间展开槽302的两侧壁呈存间隔的两条互相平行的直线段，每条直线段与槽底夹角为65°；表面调制槽沿深度方向的开口端部的轴线与涡轮叶片的A表面101的法线之间的夹角α为50°。
与实施例1相同，涡轮叶片的B表面102侧的冷却气体自离散孔进入槽体后，首先在中间展开槽内充分扩散、混合，形成均匀的正压气体，然后通过表面调制槽调制后偏向涡轮叶片的A表面侧流出，在涡轮叶片的A表面形成连续、均匀的气膜强力贴附在涡轮叶片的A表面。
实施例4：
本实施例与实施例1基本相同，所不同的是：H 1：H 2≥4：1；离散孔的中心轴线与涡轮叶片的B表面102的法向之间的夹角θ为10°；中间展开槽302的两侧壁呈存间隔的两条互相平行的直线段，每条直线段与槽底夹角为75°；表面调制槽沿深度方向的开口端部的轴线与涡轮叶片的A表面101的法线之间的夹角α为50°。
与实施例1相同，涡轮叶片的B表面102侧的冷却气体自离散孔进入槽体后，首先在中间展开槽内充分扩散、混合，形成均匀的正压气体，然后通过表面调制槽调制后偏向涡轮叶片的A表面侧流出，在涡轮叶片的A表面形成连续、均匀的气膜强力贴附在涡轮叶片的A表面。
以上所述的实施例对本发明的技术方案进行了详细说明，应理解的是以上所述仅为本发明的具体实施例，并不用于限制本发明，凡在本发明的原则范围内所做的任何修改、补充或类似方式替代等，均应包含在本发明的保护范围之内。

Claims (10)

  1. 一种在基体表面产生连续气膜的方法，其特征是：包括如下步骤：
    在基体的一个表面，称为A表面，设置若干内凹的槽体结构，所述槽体结构包括槽体底部，以及沿着槽体长度方向的两侧壁；
    在每个槽体底部设置若干贯穿至基体另一表面的离散孔，该另一表面称为B表面，所述离散孔大体沿着该槽体的长度方向排列；
    设槽体结构的深度为H，设置槽体沿深度方向由两部分组成，自槽体底部深度为H 1的部分为第一部分，称为中间展开槽，剩余部分为第二部分，称为表面调制槽，即，表面调制槽的深度H 2＝H-H 1，使基体的B表面侧的冷却气体自离散孔进入槽体结构后，首先在中间展开槽内充分扩散、混合，形成均匀的正压气体，然后通过表面调制槽调制后流出，在基体的A表面形成均匀连续气膜。
  2. 如权利要求1所述的在基体表面产生连续气膜的方法，其特征是：按照气膜贴附的气动需要设计所述表面调制槽。
  3. 如权利要求2所述的在基体表面产生连续气膜的方法，其特征是：所述表面调制槽的至少一侧壁是由第一部分的同侧壁横向扩张形成。
  4. 如权利要求1所述的在基体表面产生连续气膜的方法，其特征是：所述槽体沿深度方向的开口端部的轴线与基体的A表面的法线夹角为α，10°≤α≤90°，优选为30°≤α≤80°，更优选为45°≤α≤70°。
  5. 如权利要求1所述的在基体表面产生连续气膜的方法，其特征是：所述槽体的沿着槽体宽度方向的垂直截面中，中间展开槽的两侧壁呈存间隔的两条直线段；
    作为优选，所述表面调制槽的至少一侧壁为的弧线段。
  6. 如权利要求5所述的在基体表面产生连续气膜的方法，其特征是：所述直线段与槽底夹角为10°-170°，优选为30°-150°，更优选为60°-120°。
  7. 如权利要求1所述的在基体表面产生连续气膜的方法，其特征是：H 1>H 2；
    作为优选，H 1：H 2≥2：1；进一步优选为H 1：H 2≥3：1，最优选为H 1：H 2≥4：1。
  8. 如权利要求1所述的在基体表面产生连续气膜的方法，其特征是：所述离散孔的最大直径为d，所述槽体的最小宽度为D，D≥d。
  9. 如权利要求1所述的在基体表面产生连续气膜的方法，其特征是：H≥2d，优选为H≥3d，更优选为H≥4d。
  10. 如权利要求1所述的在基体表面产生连续气膜的方法，其特征是：所述的离散孔的中心轴线与基体的A表面的夹角为θ，0°≤θ≤60°，优选为10°≤θ≤45°；
    作为优选，所述的离散孔的开口端设置倒角过渡结构或者圆弧过渡结构。
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CN106761947A (zh) * 2016-11-28 2017-05-31 西北工业大学 一种用于涡轮叶片的漏斗型气膜孔结构
CN108590777A (zh) * 2018-06-13 2018-09-28 中国科学院宁波材料技术与工程研究所 一种基体表面连续气膜的发生结构
CN108843403A (zh) * 2018-06-13 2018-11-20 中国科学院宁波材料技术与工程研究所 一种在基体表面产生连续气膜的方法

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