An apparatus for impinging jet cooling

Abstract

A collision jet cooling device according to one embodiment comprises a jet plate having a plurality of jet holes, a collision plate parallel to the jet plate and having a plurality of outflow holes, and a fin-fin formed on the surface of the collision plate facing the jet plate, wherein the fin-fin is positioned between adjacent outflow holes and extends along a first direction or a second direction parallel to the collision plate, extends from the collision plate toward the jet plate in a third direction, and has a shape in which the cross-sectional area decreases as it goes from the collision plate toward the jet plate in the third direction, and the first direction, the second direction, and the third direction may be perpendicular to each other.

Description

Technology Field

[0001] The following embodiments relate to a collision jet cooling device. Background Technology

[0002] Recently, as the turbine inlet temperature and pressure ratio have been rapidly increasing to improve gas turbine specific fuel consumption (SFC), the efficiency of the secondary flow system cooling system is becoming important. In particular, since the gas turbine casing is exposed to high-temperature main flow, casing cooling using cooling air is required. However, at the same time, flow loss caused by the cooling air can cause a decrease in gas turbine performance, so the casing must be effectively cooled with a small amount of cooling air.

[0003] A collision jet cooling system is used to cool the conventional shroud ring segment, and in existing collision jet cooling systems, there is interaction between adjacent jets. In the case of array collision jet cooling, after the injection jet strikes the collision plate, the residual flow moves toward the outlet to form a transverse flow, and as the flow rate increases closer to the outlet, the influence of the transverse flow becomes greater. Since the effect of the collision jet is reduced by this transverse flow, an outflow hole is created in the collision plate to reduce the influence of the transverse flow.

[0004] Even if the impact jet cooling system suppresses the effect of the lateral flow generated by the impact jet through the outlet hole, a fountain effect occurs due to the collision between the injected fluids. In the case where only the outlet hole is present, there is a limitation in that the turbulent kinetic energy generated by the fountain effect cannot be fully utilized for cooling.

[0005] Registered Patent No. 10-1872856 discloses a gas turbine combustor liner with a hollow fin and impact suction structure capable of multi-layer composite impact and outflow cooling. The problem to be solved

[0006] An objective according to one embodiment is to provide a collision jet cooling device capable of performing effective cooling by reflecting the influence of turbulent kinetic energy according to the distance between the jet hole and the fin-fin through a fin-fin shape in which the cross-sectional area decreases as it goes in a third direction from the collision plate toward the jet plate.

[0007] An objective according to one embodiment is to provide a collision jet cooling device in which the average number of nacelles in the collision plate and the fin-fin can be increased through a fin-fin shape in which the cross-sectional area decreases as it goes from the collision plate toward the jet plate in a third direction. means of solving the problem

[0008] A collision jet cooling device according to one embodiment comprises a jet plate having a plurality of jet holes, a collision plate parallel to the jet plate and having a plurality of outflow holes, and a fin-fin formed on the surface of the collision plate facing the jet plate, wherein the fin-fin is positioned between adjacent outflow holes and extends along a first direction or a second direction parallel to the collision plate, extends from the collision plate toward the jet plate in a third direction, and has a shape in which the cross-sectional area decreases as it goes from the collision plate toward the jet plate in the third direction, and the first direction, the second direction, and the third direction may be perpendicular to each other.

[0009] According to one embodiment, the pin-finch has the longest length in the third direction at the central portion where the distance between the jet hole and the pin-finch is closest, and the length in the third direction may become shorter as it extends from the central portion of the pin-finch toward both ends of the pin-finch, and the distance between the jet hole and the pin-finch corresponds to the straight-line distance from the point on the collision plate where the center of the jet hole is located to the pin-finch when viewed from the surface of the jet plate.

[0010] According to one embodiment, the fin-fin can come into contact with both the jet plate and the collision plate.

[0011] According to one embodiment, when viewed from the surface of the jet plate, the jet hole, the outflow hole, and the fin-finch can be arranged so as not to overlap each other.

[0012] According to one embodiment, the pin-fine may include a first layer extending in a third direction from the surface of the collision plate and a second layer extending in a third direction from the first layer and having a smaller cross-sectional area compared to the first layer.

[0013] According to one embodiment, the pin-fine may further include a third layer that extends in a third direction from a second layer and has a smaller cross-sectional area compared to the second layer.

[0014] According to one embodiment, the cross-sectional area of ​​the fin-fin can decrease linearly as it moves in a third direction from the collision plate toward the jet plate.

[0015] According to one embodiment, the cross-sectional area of ​​the fin-fin can decrease exponentially as it moves in a third direction from the collision plate toward the jet plate. Effects of the invention

[0016] In one embodiment, an impact jet cooling device can perform effective cooling by reflecting the influence of turbulent kinetic energy according to the distance between the jet hole and the fin-fin through a fin-fin with a shape in which the cross-sectional area decreases as it goes from the impact plate toward the jet plate in a third direction.

[0017] In a collision jet cooling device according to one embodiment, the average number of nacelles in the collision plate and the fin-fin can be increased through a fin-fin shape in which the cross-sectional area decreases as it goes from the collision plate toward the jet plate in a third direction. Brief explanation of the drawing

[0018] FIG. 1 shows a perspective view of a collision jet cooling device according to one embodiment. FIG. 2 shows a projected plan view of a collision jet cooling device according to one embodiment. Figure 3 shows a perspective view of area A of Figure 2. FIG. 4 shows a perspective view of a collision jet cooling device according to one embodiment. Figure 5 illustrates the distribution of turbulent kinetic energy for regions B1, B2, and B3 of Figure 4. FIG. 6 graphs the Nusselt number according to a collision jet cooling device according to one embodiment. FIG. 7 illustrates the shape of a pin-fin according to one embodiment. FIG. 8 illustrates the shape of a pin-fin according to one embodiment. FIG. 9 illustrates the shape of a pin-fin according to one embodiment. Specific details for implementing the invention

[0019] Hereinafter, embodiments are described in detail with reference to the attached drawings. However, various modifications may be made to the embodiments, and thus the scope of the patent application is not limited or restricted by these embodiments. It should be understood that all modifications, equivalents, and substitutions to the embodiments are included within the scope of the rights.

[0020] The terms used in the embodiments are for illustrative purposes only and should not be interpreted as intended to be limiting. Singular expressions include plural expressions unless the context clearly indicates otherwise. In this specification, terms such as "comprising" or "having" are intended to indicate the existence of the features, numbers, steps, actions, components, parts, or combinations thereof described in the specification, and should be understood as not precluding the existence or addition of one or more other features, numbers, steps, actions, components, parts, or combinations thereof.

[0021] Unless otherwise defined, all terms used herein, including technical or scientific terms, have the same meaning as generally understood by those skilled in the art to which the embodiments pertain. Terms such as those defined in commonly used dictionaries should be interpreted as having a meaning consistent with their meaning in the context of the relevant technology, and should not be interpreted in an ideal or overly formal sense unless explicitly defined in this application.

[0022] In addition, when describing with reference to the attached drawings, identical components are assigned the same reference numeral regardless of drawing symbols, and redundant descriptions thereof are omitted. In describing the embodiments, if it is determined that a detailed description of related prior art could unnecessarily obscure the essence of the embodiments, such detailed description is omitted.

[0023] In addition, terms such as first, second, A, B, (a), (b), etc., may be used when describing the components of the embodiments. These terms are intended only to distinguish the components from other components, and the nature, order, or sequence of the components is not limited by the terms. Where it is stated that a component is "connected," "combined," or "connected" to another component, it should be understood that the component may be directly connected or connected to the other component, but that another component may also be "connected," "combined," or "connected" between each component.

[0024] Components included in any one embodiment and components having common functions shall be described using the same names in other embodiments. Unless otherwise stated, the description in any one embodiment may also apply to other embodiments, and specific descriptions shall be omitted to the extent of overlap.

[0025] FIG. 1 shows a perspective view of a collision jet cooling device (1) according to one embodiment. FIG. 2 shows a projected plan view of a collision jet cooling device (1) according to one embodiment. FIG. 3 shows a perspective view of area A of FIG. 2. Note that in FIG. 3, for convenience of illustration, the jet plate (10) and the collision plate (20) are omitted, and only the jet hole (10a) and the outflow hole (20a) are shown.

[0026] Referring to FIGS. 1 to 3, a collision jet cooling device (1) according to one embodiment may include a jet plate (10) having a plurality of jet holes (10a), a collision plate (20) parallel to the jet plate (10) and having a plurality of outflow holes (20a), and a fin-fin (30) formed on the surface of the collision plate (20) facing the jet plate (10).

[0027] The fin-fin (30) is positioned between adjacent outflow holes (20a) and extends along a first direction (X) or a second direction (Y) parallel to the collision plate (20), extends from the collision plate (20) toward the jet plate (10) toward a third direction (Z), and may have a shape in which the cross-sectional area decreases as it goes from the collision plate (20) toward the jet plate (10) toward the third direction (Z).

[0028] At this time, the length of the pin-fine (30) in the third direction (Z) is longest at the center part where the distance between the jet hole (10a) and the pin-fine (30) is closest, and the length in the third direction (Z) may become shorter as it moves from the center part of the pin-fine (30) toward both ends. Here, the distance between the jet hole (10a) and the pin-fine (30) may correspond to the straight-line distance from the point on the collision plate (20) where the center of the jet hole (10a) is located to the pin-fine (30) while looking at the surface of the jet plate (10).

[0029] According to one embodiment, the pin-fin (30) may include a first layer (310) extending from the surface of the collision plate (20) as shown in FIG. 3, a second layer (320) extending from the first layer (310) and having a smaller cross-sectional area compared to the first layer (310), and a third layer (330) extending from the second layer (320) and having a smaller cross-sectional area compared to the second layer (320).

[0030] Meanwhile, the first direction (X) and the second direction (Y) are directions parallel to the collision plate (10), and the first direction (X) and the second direction (Y) may be perpendicular to each other, and the third direction (Z) may be perpendicular to the first direction (X) and the second direction (Y).

[0031] Specifically, the flow entering through the jet hole (10a) of the jet plate (10) collides with the collision plate (20) to be cooled, and additional cooling occurs as the flow also collides with the fin-fin (30) formed on the collision plate (20), and the flow can exit through the outflow hole (20a) of the collision plate (20). That is, the fin-fin (30) is installed at a point where high turbulent kinetic energy is generated due to complex flow caused by the fountain effect, primary vortex, and secondary vortex resulting from the collision between adjacent jets, so that cooling performance can be improved.

[0032] Here, the first vortex may correspond to a counterclockwise vortex in the separated flow, and the second vortex may correspond to a clockwise vortex opposite to the first vortex in the separated flow.

[0033] In the jet plate (10), each jet hole (10a) may be formed at regular intervals in the first direction (X) and the second direction (Y). Additionally, in the collision plate (20), each outflow hole (20a) may be formed at regular intervals in the first direction (X) and the second direction (Y).

[0034] At this time, the jet hole (10a) and the outflow hole (20a) can be arranged so as not to overlap each other when viewed from the surface of the jet plate (10). That is, for example, as shown in FIG. 2, the jet hole (10a) can be positioned at the center of four outflow holes (20a) adjacent in the first direction (X) and the second direction (Y) when viewed from the surface of the jet plate (10). Additionally, the fin-fin (30) can be positioned between the outflow holes (20a) adjacent in the first direction (X) or the second direction (Y) so that the jet hole (10a), the outflow hole (20a), and the fin-fin (30) can be arranged so as not to overlap each other when viewed from the surface of the jet plate (10).

[0035] According to one embodiment, the fin-fin (30) may come into contact with both the jet plate (10) and the collision plate (20). That is, the fin-fin (30) extends in a third direction (Z) from the collision plate (20), and by the upper end of the fin-fin (30) coming into contact with the jet plate (10), the cooling performance can be significantly improved in the central part where the distance between the jet hole (10a) and the fin-fin (30) is closest.

[0036] Meanwhile, the fin-fin (30) contacting both the jet plate (10) and the collision plate (20) is merely one embodiment, and the fin-fin (30) may contact only the collision plate (20), and the uppermost part of the fin-fin (30) may not contact the jet plate (10).

[0037] As the distance between the jet hole (10a) and the fin-fin (30) increases, the turbulent kinetic energy reaching the fin-fin (30) may decrease. Therefore, as the distance between the jet hole (10a) and the fin-fin (30) increases, the influence of the cooling performance on the height of the fin-fin (30) (e.g., the length extended along the third direction (Z) of the fin-fin (30)) may decrease as the turbulent kinetic energy decreases.

[0038] That is, referring to FIG. 3, when the straight distance from the center of the jet hole (10a) to the part where the third layer (330) of the pin-finch (30) is located is a, the straight distance to the part where the first layer (310) and the second layer (320) are located is b, and the straight distance to the part where only the first layer (310) is located is c, when comparing the lengths, a <b<c로 나타낼 수 있다.

[0039] Accordingly, the pin-fin (30) may have a shape in which the height of the pin-fin (30) varies according to the distance from the jet hole (10a), having a maximum height in the central part that is close to the jet hole (10a) and a lower height as it moves further away from the jet hole (10a). For example, a pin-fin (30) with a shape including a first layer (310), a second layer (320) with a cross-sectional area smaller than that of the first layer (310), and a third layer (330) with a cross-sectional area smaller than that of the second layer (320) may be installed on the collision plate (20). Additionally, as described below, a pin-fin (31) with a shape in which the cross-sectional area decreases linearly, a pin-fin (32) with a shape in which the cross-sectional area decreases exponentially, and a pin-fin (33) with a shape including the first layer and the second layer may be installed.

[0040] FIG. 4 illustrates a perspective view of a collision jet cooling device (1) according to one embodiment. FIG. 5 illustrates a distribution of turbulent kinetic energy for regions B1, B2, and B3 of FIG. 4. Specifically, FIG. 5(a) illustrates a distribution of turbulent kinetic energy in region B1 of FIG. 4, FIG. 5(b) illustrates a distribution of turbulent kinetic energy in region B2 of FIG. 4, and FIG. 5(c) illustrates a distribution of turbulent kinetic energy in region B3 of FIG. 4. Note that in FIG. 4 and FIG. 5, for convenience of illustration, the jet plate (10) and the collision plate (20) are omitted, and only the jet hole (10a) and the outflow hole (20a) are illustrated.

[0041] Referring to FIGS. 4 and 5, as the distance from the jet hole (10a) to the fin-fin (30) increases, the separation of the primary vortex may occur at a relatively low point.

[0042] That is, as shown in FIG. 5(a), in region B1 of FIG. 4, separation of the primary vortex occurs at a high point in the third direction (Z); as shown in FIG. 5(b), in region B2 of FIG. 4, separation occurs at an intermediate point in the third direction (Z); and as shown in FIG. 5(c), in region B3 of FIG. 4, separation of the primary vortex occurs at a low point in the third direction (Z). Therefore, the turbulent kinetic energy is relatively high in region B1, and the turbulent kinetic energy may be relatively low as it moves toward regions B2 and B3.

[0043] Accordingly, the fin-fin (30) can perform cooling by including a first layer (310), a second layer (320), and a third layer (330) in region B1, which has high turbulent kinetic energy, including only the first layer (310) and the second layer (320) in region B2, and including only the first layer (310) in region B3, so that effective cooling can be performed.

[0044] FIG. 6 graphs the number of nacelles according to the impact jet cooling device (1) according to one embodiment.

[0045] Referring to FIG. 6(a), the white dots indicate the average number of nacelles according to the height of the pin-fin, and the black dots indicate the average number of nacelles when the pin-fin (30) according to the shape of the present invention is applied. That is, as shown in FIG. 6(b), compared to a conventional column-shaped pin-fin, it can be seen that the average number of nacelles is improved by 24.8% when the pin-fin (30) according to the shape of the present invention is applied.

[0046] Here, the Nassel number is a dimensionless temperature gradient at the surface of an object, representing the ratio of heat transfer by convection to heat transfer by conduction in the fluid layer at the object's surface. In other words, a higher Nassel number implies that heat transfer occurs more effectively via convection than via conduction.

[0047] At this time, the average number of nacelles in FIG. 6 may refer to the average number of nacelles in the collision plate (20) and the fin-fin (30), and it can be confirmed that the average number of nacelles is improved by applying the fin-fin (30) according to the shape of the present invention, thereby improving the cooling performance by the fin-fin (30).

[0048] FIG. 7 illustrates the shape of a pin-fin (31) according to one embodiment.

[0049] Referring to FIG. 7, the fin-fin (31) according to one embodiment may have a shape in which the cross-sectional area becomes linearly smaller as it moves from the collision plate (20) toward the jet plate (10) in a third direction (Z).

[0050] FIG. 8 illustrates the shape of a pin-fin (32) according to one embodiment.

[0051] Referring to FIG. 8, the fin-fin (32) according to one embodiment may have a shape in which the cross-sectional area decreases exponentially as it moves from the collision plate (20) toward the jet plate (10) in a third direction (Z).

[0052] Meanwhile, the shape of FIG. 8 is merely one embodiment, and the shape of the fin-fin (32) may have a shape in which the cross-sectional area decreases logarithmically as it moves from the collision plate (20) toward the jet plate (10) in the third direction (Z).

[0053] FIG. 9 illustrates the shape of a pin-fin (33) according to one embodiment.

[0054] Referring to FIG. 9, a pin-finch (33) according to one embodiment may include only a first layer (e.g., the first layer (310) of FIG. 3 described above) extending from the surface of the collision plate (20) and a second layer (e.g., the second layer (320) of FIG. 3 described above) extending from the first layer and having a smaller cross-sectional area compared to the first layer.

[0055] As described above, the collision jet cooling device (1) according to one embodiment can perform effective cooling by reflecting the influence of turbulent kinetic energy according to the distance between the jet hole (10a) and the fin-fin (30, 31, 32, 33) through the fin-fin (30, 31, 32, 33) which has a cross-sectional area that decreases as it goes from the collision plate (10) toward the jet plate (20) in the third direction (Z).

[0056] In addition, the collision jet cooling device (1) according to one embodiment may increase the average number of nacelles in the collision plate (20) and the fin-fin (30) through the fin-fin (30, 31, 32, 33) having a cross-sectional area that decreases as it goes from the collision plate (10) toward the jet plate (20) in a third direction (Z).

[0057] Although the embodiments have been described above with reference to the limited drawings, those skilled in the art can apply various technical modifications and variations based on the above. For example, suitable results may be achieved even if the described techniques are performed in a different order than described, and / or if the components of the described system, structure, device, circuit, etc. are combined or assembled in a form different from described, or replaced or substituted by other components or equivalents.

[0058] Therefore, other implementations, other embodiments, and equivalents to the claims also fall within the scope of the claims set forth below. Explanation of the symbols

[0059] 1: Impact jet cooling system 10 : Jet plate 10a : Jet hole 20: Collision plate 20a: Outflow hole 30 : Pin-Fin 310 : 1st Layer 320 : Layer 2 330 : Layer 3

Claims

Claim 1 A collision jet cooling device comprising: a jet plate having a plurality of jet holes; a collision plate parallel to the jet plate and having a plurality of outflow holes; and a fin-fin formed on the surface of the collision plate facing the jet plate; wherein the fin-fin is positioned between adjacent outflow holes and extends along a first direction or a second direction parallel to the collision plate, extends from the collision plate toward the jet plate in a third direction, and has a shape in which the cross-sectional area decreases as it goes from the collision plate toward the jet plate in the third direction, and the first direction, the second direction, and the third direction are perpendicular to each other; and the fin-fin comprises: a first layer extending from the surface of the collision plate in the third direction; a second layer extending from the first layer in the third direction and having a cross-sectional area smaller than that of the first layer; and a third layer extending from the second layer in the third direction and having a cross-sectional area smaller than that of the second layer. Claim 2 A collision jet cooling device according to claim 1, wherein the fin-fin has the longest length in the third direction at the central part where the distance between the jet hole and the fin-fin is closest, and the length in the third direction becomes shorter as it goes from the central part of the fin-fin to both ends of the fin-fin, and the distance between the jet hole and the fin-fin corresponds to the straight-line distance from the point on the collision plate where the center of the jet hole is located, when looking at the surface of the jet plate, to the fin-fin. Claim 3 In paragraph 2, the impact jet cooling device, wherein the fin-fin contacts both the jet plate and the impact plate. Claim 4 A collision jet cooling device according to paragraph 3, wherein, when viewed from the surface of the jet plate, the jet hole, the outflow hole, and the fin-fin are arranged so as not to overlap each other. Claim 5 delete Claim 6 delete Claim 7 delete Claim 8 delete

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