Double-wall target rectifier and turbine blade with anisotropic flow resistance

Abstract

The present invention relates to the field of heat exchange technology for aircraft engines and gas turbine blades, specifically a double-wall target rectifier and turbine blade with anisotropic flow resistance. It comprises an inner impact plate and an outer air film plate; the inner impact plate is provided with a plurality of impact holes; the outer air film plate is provided with a plurality of rectifier units; each rectifier unit is provided with a plurality of first guide grooves; and the ends of adjacent rectifier units are provided with air film holes. The airflow passes through the inner impact plate and reaches the rectifier unit, where it is rectified by the first guide grooves to complete the heat exchange; the airflow that impacts the target surface is adjusted, and the gas originally flowing to the downstream impact area is diverted to the nearest air film hole, thereby avoiding the adverse effect of the exhaust gas generated in the upstream impact area on the downstream impact heat exchange, and eliminating the cumulative effect of the cross flow; the problem that the comprehensive heat exchange capacity of the double-walled structure rectifier is low and cannot meet the current heat exchange requirements of aircraft engines and gas turbine blades is solved.

Description

Technical Field

[0001] The present invention relates to the technical field of heat exchange of turbine blades of aviation engines and gas turbines, and in particular to a double-wall target surface rectifier and turbine blade with anisotropic flow resistance. Background Art

[0002] To achieve higher cycle efficiency and output power, the inlet temperature of modern gas turbine and aircraft engine turbine blades continues to rise. The inlet temperature of the most advanced aircraft engines and gas turbines has exceeded 2100K, far exceeding the temperature limit of metal. This poses a significant challenge to protecting hot-end components and ensuring stable and efficient operation in high-temperature environments. Common cooling technologies for turbine blades include convection cooling, impingement cooling, swirl cooling, and film cooling. With the development of additive manufacturing technology, double-wall structures based on impingement and film cooling have become possible.

[0003] The double-wall structure is one of the most efficient internal cooling technologies for turbine blades. This structure consists of two inner and outer wall surfaces, a turbulent column rib between them, and microstructured units on the inner side of the outer wall. Gas passes through the impact holes on the inner wall surface and impacts the inner side of the outer wall surface. After exchanging heat with the microstructured units on the inner side of the outer wall surface and the turbulent column rib between the inner and outer walls, it flows out through the air film holes or cross-flow outlets arranged on the outer wall surface. To suppress the adverse effects of cross-flow on heat transfer in the downstream impact area, many researchers have developed a series of cross-flow prevention devices, such as installing a cross-flow suppressor between the two impact areas, reducing the distance from the impact plate to the impact target surface, or other devices to prevent the adverse effects of upstream cross-flow on heat transfer in the downstream impact area.

[0004] This type of double-wall structure has the following problems: First, the impact holes are usually arranged in rows on the inner solid wall of the double-wall. The gas (also called exhaust gas) generated after the impact of the upstream impact hole usually affects the downstream impact area, resulting in deterioration of the heat exchange in the downstream impact area and failure to achieve the designed heat exchange efficiency; second, the existing anti-cross flow device usually only focuses on how to reduce the impact of the cross flow in the upstream impact area on the downstream, but often ignores the impact of the cross flow cumulative effect, channel resistance, and channel pressure drop on the comprehensive heat exchange capacity of the double-wall channel. Summary of the Invention

[0005] In view of the problem that the double-walled structure rectifier in the existing technology has low comprehensive heat exchange capacity and cannot meet the heat exchange requirements of current aircraft engines and gas turbine turbine blades, the present invention provides a double-walled target surface rectifier and turbine blade with anisotropic flow resistance.

[0006] In order to achieve the above object, the present invention adopts the following technical solutions:

[0007] The present invention provides a double-wall target rectifier with anisotropic flow resistance, comprising an inner impact plate and an outer air film plate; the inner impact plate and the outer air film plate are arranged relative to each other; a plurality of impact holes are provided on the inner impact plate; a plurality of rectifier units are provided on the plate surface of the outer air film plate close to the inner impact plate; the projections of the impact holes fall on the rectifier units; a plurality of first guide grooves are provided on each rectifier unit, and the angle between the first guide grooves on adjacent rectifier units is greater than 0° and less than 180°; air film holes are provided at the ends of adjacent rectifier units; the first guide grooves are connected to the air film holes.

[0008] Preferably, the projections of the impact holes on the rectifying unit are arranged alternately with the air film holes.

[0009] Furthermore, the rectification unit is evenly divided into a plurality of rectification areas, the first guide grooves are distributed in each rectification area, and the first guide grooves of two adjacent rectification areas are connected to each other.

[0010] Furthermore, the included angle between the first guide grooves on two adjacent rectifying areas is greater than 0°.

[0011] Preferably, the number of the rectification areas is equal to the number of the air film holes around each rectification unit.

[0012] Preferably, there are four rectifying areas, and the angle between the first guide grooves on adjacent rectifying areas is 90°.

[0013] Preferably, the projection of the impact hole falls on the center of the rectification unit.

[0014] Preferably, a second guide groove is provided between adjacent rectifying units, and the second guide groove is connected to the air film holes at the ends of the adjacent rectifying units.

[0015] Preferably, the cross-sectional shape of the first guide groove is triangular, semicircular, elliptical, rectangular, shuttle-shaped or trigonometric function-shaped.

[0016] A turbine blade comprises the above-mentioned double-wall target surface rectifier.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] The present invention provides a double-walled target rectifier with anisotropic flow resistance. The target rectifier includes an inner impact plate and an outer air film plate. The inner impact plate is provided with a plurality of impact holes. The outer air film plate is provided with a plurality of rectifier units. Each rectifier unit is provided with a plurality of first guide grooves. The ends of adjacent rectifier units are provided with air film holes. The high-temperature airflow passes through the impact holes through the inner impact plate and impacts the rectifier units of the outer air film plate. The airflow is guided by the first guide grooves to the air film holes to complete the heat exchange. The adverse effect of cross flow on the heat exchange in the downstream impact area is mainly due to the fact that the heat exchange intensity generated by the cross flow is less than the intensity of the cross flow suppressing the downstream impact heat exchange. The cross flow itself also has a positive effect on the heat exchange. The present invention can rectify the airflow that impacts the target surface by setting the impact hole, the rectifying unit, the first guide groove and the air film hole, and rectify the gas that originally flows to the downstream impact area to the nearest air film hole, thereby avoiding the adverse effect of the exhaust gas generated in the upstream impact area on the downstream impact heat exchange, and eliminating the cumulative effect of the cross flow; and in this process, the mass flow rate of the cold air passing through the air film hole increases, and the target surface rectifier provided by the present invention only changes the direction of the cross flow, and does not annihilate the kinetic energy of the cross flow, which will also have a positive effect on the impact heat exchange of the double wall and reduce the pressure loss of the channel. Therefore, the comprehensive heat exchange capacity of the double-wall structure rectifier is improved as a whole. On the other hand, since the mass flow rate of the cold air passing through the air film hole increases, the target surface rectifier provided by the present invention will reduce the adverse effect of the cross flow on the heat exchange and eliminate the cumulative effect of the cross flow while also improving the air film cooling efficiency of the double-wall channel.

[0019] Furthermore, the projection of the impact hole on the rectifier unit is staggered with the air film hole, so that the high-temperature airflow from the impact hole can impact the first guide groove and conduct heat exchange through the first guide groove on the rectifier unit, further improving the comprehensive heat exchange capacity of the double-wall structure rectifier.

[0020] Furthermore, the setting of the rectification area can further enhance the anisotropy of the double-walled structure rectifier, so that the high-temperature airflow from the impact hole enters the air film hole along the first guide groove in different directions, thereby enhancing the heat exchange performance.

[0021] Furthermore, the provision of the second guide groove can enable the airflow after rectification and heat exchange of each rectification unit to converge and flow out through the air film hole, further improving the rectification performance of the target surface rectifier.

[0022] Furthermore, the cross-sectional shape of the first guide groove is triangular, semicircular, elliptical, rectangular, shuttle-shaped or trigonometric function-shaped, etc., which not only increases the disturbance of the cooling gas in the channel, but also increases the heat exchange area. Therefore, the target surface rectifier itself can also play a role in enhancing heat exchange.

[0023] The present invention also provides a turbine blade comprising the above-mentioned double-wall target surface rectifier. The turbine blade can still operate efficiently and stably when the inlet temperature exceeds 2100K. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 This is a schematic diagram of a double-wall target surface rectifier with anisotropic flow resistance according to the present invention.

[0025] Figure 2 This is a structural diagram of the outer layer air film plate of the present invention.

[0026] Figure 3 This is a structural diagram of the rectifier unit of the present invention.

[0027] Figure 4 This is a structural diagram of a rectifying unit in which the first guide groove is a shuttle-shaped rib in an embodiment of the present invention.

[0028] Figure 5 The cross-sectional views of the first guide grooves of the present invention in different shapes are given as examples.

[0029] Figure 6 This is a working principle diagram of the double-wall target rectifier with anisotropic flow resistance of the present invention.

[0030] Figure 7 This is a gas flow diagram of a double-wall rectifier in the prior art.

[0031] Figure 8 This is the gas flow diagram of the double-wall target rectifier with anisotropic flow resistance of the present invention.

[0032] Figure 9 This is a diagram of the structure of bird feathers.

[0033] Among them, 1-inner impact plate, 2-outer air film plate, 11-impact hole, 21-rectification unit, 22-air film hole, 23-second guide groove, 24-discrete guide rib, 211-first guide groove, 212-rectification area. DETAILED DESCRIPTION

[0034] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings herein can be arranged and designed in various different configurations.

[0035] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention as claimed, but rather merely represents selected embodiments of the present invention. All other embodiments derived by persons of ordinary skill in the art based on the embodiments of the present invention without creative effort shall fall within the scope of protection of the present invention.

[0036] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, it does not need to be further defined or explained in subsequent drawings.

[0037] In the description of the embodiments of the present invention, it should be noted that if the terms "upper," "lower," "horizontal," "inner," etc. appear, the orientation or positional relationship indicated is based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship in which the inventive product is typically placed when in use. These terms are merely for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or component referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limitations on the present invention. In addition, the terms "first," "second," etc. are used only to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0038] In addition, if the term "horizontal" appears, it does not mean that the component must be absolutely horizontal, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0039] In the description of the embodiments of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "disposed," "installed," "connected," and "connected" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to internal connections between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0040] The present invention will be further described in detail below with reference to specific embodiments, which are intended to explain the present invention rather than to limit it.

[0041] See also Figures 1 to 3The present invention discloses a double-wall target surface rectifier with anisotropic flow resistance, comprising an inner impact plate 1 and an outer air film plate 2; the inner impact plate 1 and the outer air film plate 2 are arranged opposite to each other; the inner impact plate 1 is provided with a plurality of impact holes 11, and the number, size, shape, spacing, etc. of the impact holes 11 can be adjusted according to the demand of heat load; the outer air film plate 2 is provided with a plurality of rectifier units 21 on the plate surface close to the inner impact plate 1; the projection of the impact hole 11 falls on the rectifier unit 21; the projection of the impact hole 11 on the rectifier unit 21 is equal to the projection of the impact hole 11 on the rectifier unit 21. The air film holes 22 are arranged in a staggered manner; a plurality of first guide grooves 211 are provided on each rectifying unit 21, and the angle between the first guide grooves 211 on adjacent rectifying units 21 is greater than 0° and less than 180°; second guide grooves 23 are provided between adjacent rectifying units 21, and the second guide grooves 23 are connected to the air film holes 22 at the ends of adjacent rectifying units 21; air film holes 22 are provided at the ends of adjacent rectifying units 21, and the number, size, shape, spacing, etc. of the air film holes 22 can be adjusted according to the requirements of the heat load; the first guide grooves 211 are connected to the air film holes 22.

[0042] See also Figures 2 to 4 The rectifying unit 21 is evenly divided into a plurality of rectifying regions 212. The first guide grooves 211 are distributed in each rectifying region 212. The first guide grooves 211 of two adjacent rectifying regions 212 are interconnected, and the angle between the first guide grooves 211 of two adjacent rectifying regions 212 is greater than 0°. The number of the rectifying regions 212 is equal to the number of the air film holes 22 around each rectifying unit 21. The first guide grooves 211 include continuous grooves and discrete guide ribs 24.

[0043] Preferably, there are four rectifying regions 212 , and the angle between the first guide grooves 211 on adjacent rectifying regions 212 is 90°. The projection of the impact hole 11 falls on the center of the rectifying unit 21 .

[0044] See also Figure 4 The discrete guide ribs 24 of the first guide groove 211 can be protrusions or pits in the shape of a spindle, a leaf, an ellipse, a teardrop, a rectangle or any other shape.

[0045] See also Figure 5Preferably, the cross-sectional shape of the first guide groove 211 and the second guide groove 23 is triangular, semicircular, elliptical, rectangular, fusiform, or trigonometric; the flow direction of the first guide groove 211 and the second guide groove 23 can be straight or curved. The depth or height of the grooves and discrete guide ribs 24 constituting the first guide groove 211 can be adjusted according to the distribution of the heat load or cross-flow intensity. In locations with high heat load or cross-flow intensity, the depth or height of the first guide groove 211 and the discrete guide ribs 24 can be designed to be larger, while in locations with low heat load or cross-flow intensity, the depth or height of the first guide groove 211 and the discrete guide ribs 24 can be designed to be smaller.

[0046] Working principle:

[0047] See also Figure 6 The fluid hits the outer air film plate 2 through the impact hole 11, and exchanges heat with the rectification unit 21 arranged on the outer air film plate 2. After being rectified by the rectification unit 21, the fluid flows out through the air film hole 22 of the outer air film plate 2 and merges with the mainstream.

[0048] Specifically: the cooling gas hits the rectification unit 21 through the upstream impact hole 11, forming convective impact heat exchange. The gas after heat exchange passes through the rectification unit 21, and part of the gas passes through the partial rectification area 212 of the rectification unit 21. Part of the gas is deflected clockwise along the flow direction, and part of the gas is deflected counterclockwise along the cross-flow direction. This means that through the rectification of the rectification unit 21, the direction of part of the gas that should have been along the adjacent or downstream impact hole is gradually deflected toward the direction of the air film hole 22, thereby avoiding the exhaust gas generated by the upstream impact heat exchange from having an adverse effect on the heat exchange of the adjacent or downstream impact area.

[0049] Part of the cooling exhaust gas generated after the upstream impact hole heat exchange should flow in the horizontal direction. Under the rectification effect of the rectification unit, the direction of part of the gas is deflected counterclockwise, and the direction of part of the gas is deflected clockwise, thus avoiding the cooling exhaust gas generated after the upstream impact hole heat exchange from having an adverse effect on the downstream impact core area;

[0050] Similarly, part of the cooling exhaust gas generated after the impact heat exchange in the upstream impact hole 11 should flow in a horizontal reverse direction opposite to the above-mentioned direction. Under the rectifying action of the rectifying unit 21, the direction of part of the gas is deflected clockwise, and the direction of part of the gas is deflected counterclockwise, thereby avoiding the cooling exhaust gas generated after the impact heat exchange in the downstream impact hole and the cooling exhaust gas generated after the impact heat exchange in the upstream impact hole from colliding head-on, thereby avoiding the annihilation of the kinetic energy of the two cooling gases and the loss of flow pressure.

[0051] After being rectified by the target surface rectifier, the cooling exhaust gas generated after the impact heat exchange from the upstream impact hole 11 and the cooling exhaust gas generated after the impact heat exchange from the downstream impact hole meet in the upper half of the second guide groove 23, and then flow into the air film hole 22 along the first guide groove 211; the cooling exhaust gas generated after the impact heat exchange from the upstream impact hole 11 and the cooling exhaust gas generated after the impact heat exchange from the downstream impact hole meet in the lower half of the second guide groove 23, and then flow into the air film hole 22 along the second guide groove 23.

[0052] After rectification by the target surface rectifier and guidance by the guide groove, the flow direction of the cross flow that has an adverse effect on the downstream impingement flow heat exchange no longer directly impacts the core area of the downstream impingement heat exchange, but is guided to the adjacent air film holes, thereby avoiding the adverse effect of the cross flow on the downstream flow heat exchange.

[0053] Since the cooling exhaust gas generated by the upstream impingement flow heat exchange no longer directly impacts the core area of the downstream impingement heat exchange, but is diverted to the adjacent air film hole 22, this means that the cross flow from the upstream impingement hole 11 does not collide head-on with the cooling exhaust gas generated by the downstream impingement flow heat exchange, thereby avoiding the annihilation of the kinetic energy of the two cooling gases and the loss of flow pressure, while increasing the cooling flow of the adjacent air film hole 22, thereby improving the air film cooling effect of the outer solid wall. This shows that after the rectification of the target surface rectifier and the guidance of the guide groove described in the present invention, the cross flow that originally had an adverse effect on the impingement heat exchange has been well utilized as the cooling flow of the air film hole, thereby improving the air film cooling effect of the outer air film plate 2.

[0054] See also Figure 7 and Figure 8 In the double-wall channel equipped with a rectifier unit 21, the intensity and size of the separation vortex generated by the mixing of the cross flow and the downstream impact area are smaller than those of the double-wall channel without a target surface rectifier. This shows that the rectification by the target surface rectifier reduces the mass flow rate of the cross flow to the downstream impact area, and the dissipation and pressure loss caused by the separation vortex are also reduced, which fully demonstrates the correctness and feasibility of the present invention.

[0055] The cumulative effect of cross flow means that, along the downstream direction, as the number of impact holes increases, the intensity of the cross flow will also increase. This is because the source of the cross flow of the second impact hole is only the first impact hole, the source of the cross flow of the third impact hole is the previous two impact holes, and the source of the cross flow of the nth impact hole is the previous n-1 impact holes. This results in the cross flow intensity of the downstream impact core area becoming larger and larger along the cross flow direction, making the heat exchange in the downstream impact core area more and more affected by the cross flow. This is the cumulative effect of cross flow; and the innovation of the target surface rectifier in suppressing cross flow in the present invention is that the target surface rectifier rectifies the cooling gas that impacts the target surface, so that most of the fluid that should have flowed along the downstream or adjacent impact hole direction flows in the direction of the adjacent air film hole. The cross flow eventually mixes with the mainstream through the adjacent air film holes, and will not accumulate along the flow direction, thereby causing the heat exchange in the downstream impact core area to deteriorate. That is, the target surface rectifier described in the present invention has the characteristic of eliminating the cumulative effect of cross flow.

[0056] Since the target surface rectifier and the guide groove have a disturbing effect on the flow heat exchange and increase the flow heat exchange area, the target surface rectifier and the guide groove can effectively suppress the cross flow while also increasing the impact flow heat exchange capacity of the double wall.

[0057] Design principle:

[0058] After the target surface rectifier is rectified, from the perspective of fluid flow, on the target surface where the target surface rectifiers are arranged in an array, the fluid impacting the target surface from the impact hole 11 has a larger flow resistance along the direction of the downstream impact hole or the adjacent impact hole, while the flow resistance along the direction of the adjacent air film hole 23 is smaller. This partial physical property of the same object changes with the change of direction, and exhibits different properties in different directions, which is called anisotropy.

[0059] In nature, single crystals have different physical and chemical properties along different directions of the lattice, which is similar to the target surface rectifier mentioned in the present invention; single crystals are composed of a large number of microscopic material units arranged in an orderly manner according to certain rules, and the target surface rectifier described in the present invention is also a combination of rectifier units 21 arranged in an array; single crystals have different physical and chemical properties along different directions of the lattice, and the target surface rectifier described in the present invention has different flow resistance along the downstream direction, the direction adjacent to the impact hole 11 and the direction adjacent to the air film hole 23. Therefore, this characteristic of the target surface rectifier described in the present invention is defined as a target surface rectifier with anisotropic flow resistance.

[0060] The biological characteristics of the target surface rectifier described in the present invention are reflected in the following aspects:

[0061] See also Figure 9The surface of bird feathers is composed of a hollow feather shaft and barbs. The barbs are arranged in a herringbone array on both sides of the hollow feather shaft and diverge at an angle along the hollow feather shaft. This structure plays a decisive role in enabling birds to better utilize air flow to achieve greater buoyancy and less air resistance during flight. Since secondary vortex pairs are generated when air flows over the surface of feathers, this has an adverse effect on bird flight. When air flows through the microstructure of feathers, some tiny vortex pairs in opposite directions are generated, which offset the secondary vortex pairs of the mainstream, thereby eliminating the adverse effects of secondary flow on bird flight.

[0062] The target surface rectifier described in the present invention is also composed of some tiny ribs and pits arranged in a herringbone array on both sides of the shaft, with a divergent angle along the axial direction. Unlike the bird feather structure, the bird feathers have only one arrangement direction, while the target surface rectifier described in the present invention has many directions. This enables the present invention to achieve a better rectification effect on the double-wall target surface of the turbine blade while having the characteristics of anisotropic flow resistance, and can make corresponding adjustments as the application scenario changes. This makes the present invention extremely robust and adaptable, and thus has very good comprehensive heat exchange performance.

[0063] A turbine blade comprises the above-mentioned double-wall target surface rectifier. The turbine blade can still operate efficiently and stably when the inlet temperature exceeds 2100K.

[0064] In summary, the present invention provides a double-wall target rectifier and turbine blade with anisotropic flow resistance. Compared with the double-wall cross-flow suppression device in the prior art, the double-wall target rectifier provided by the present invention has the characteristics of better cross-flow suppression effect, higher heat exchange effect, air film cooling effect and lower channel flow loss, which provides better thermal protection capability for the safe and efficient operation of turbine blades under extreme inlet high temperature conditions.

[0065] The above description is merely a preferred embodiment of the present invention and is not intended to impose any limitation on the technical solution of the present invention. Those skilled in the art should understand that, without departing from the spirit and principles of the present invention, the technical solution can also be subjected to several simple modifications and replacements, and these modifications and replacements are also within the scope of protection covered by the claims.

Claims

1. A double-wall target rectifier with anisotropic flow resistance, characterized in that: The invention comprises an inner impact plate (1) and an outer air film plate (2); the inner impact plate (1) and the outer air film plate (2) are arranged relative to each other; a plurality of impact holes (11) are arranged on the inner impact plate (1); a plurality of rectifier units (21) are arranged on the plate surface of the outer air film plate (2) close to the inner impact plate (1); the projection of the impact holes (11) falls on the rectifier unit (21); a plurality of first guide grooves (211) are arranged on each rectifier unit (21), and the angle between the first guide grooves (211) on adjacent rectifier units (21) is greater than 0° and less than 1°. 180°; air film holes (22) are provided at the ends of adjacent rectifying units (21); the first guide grooves (211) are connected to the air film holes (22); a second guide groove (23) is provided between adjacent rectifying units (21), and the second guide grooves (23) are connected to the air film holes (22) at the ends of adjacent rectifying units (21); the rectifying unit (21) is evenly divided into a plurality of rectifying areas (212), the first guide grooves (211) are distributed in each rectifying area (212), and the first guide grooves (211) of two adjacent rectifying areas (212) are connected to each other.

2. The double-wall target rectifier with anisotropic flow resistance according to claim 1, characterized in that: The projections of the impact holes (11) on the rectifying unit (21) and the air film holes (22) are arranged in a staggered manner.

3. The double-wall target rectifier with anisotropic flow resistance according to claim 1, characterized in that: The included angle between the first guide grooves (211) on two adjacent rectifying areas (212) is greater than 0°.

4. The double-wall target rectifier with anisotropic flow resistance according to claim 1, characterized in that: The number of the rectification areas (212) is equal to the number of the air film holes (22) around each rectification unit (21).

5. The double-wall target rectifier with anisotropic flow resistance according to claim 4, characterized in that: There are four rectifying regions (212), and the angle between the first guide grooves (211) on adjacent rectifying regions (212) is 90°.

6. The double-wall target rectifier with anisotropic flow resistance according to claim 1, characterized in that: The projection of the impact hole (11) falls on the center of the rectification unit (21).

7. The double-wall target rectifier with anisotropic flow resistance according to any one of claims 1 to 6, characterized in that: The cross-sectional shape of the first guide groove (211) is triangular, semicircular, elliptical, rectangular, shuttle-shaped or trigonometric function-shaped.

8. A turbine blade, characterized in that: A double-wall target surface rectifier comprising the double-wall target surface rectifier according to any one of claims 1 to 7.

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