JP7396945B2 - Heat exchanger - Google Patents

Description

The present invention relates to a heat exchanger, and particularly to a heat exchanger including a core portion.

Conventionally, a heat exchanger including a core portion is known (for example, see Patent Document 1).

The above-mentioned Patent Document 1 discloses a heat exchanger including a heat exchanger core. The heat exchanger core includes a tube length having a plurality of fluid conduits for communicating refrigerant and corrugated fin segments for communicating air. The heat exchanger core is configured to exchange heat between refrigerant flowing through the tube length fluid conduit and air flowing through the corrugated fin segments. Moreover, this heat exchanger core is deformed into a bow shape by a bending process of bending a planar heat exchanger core.

Special table 2017-516660 publication

Although not specified in Patent Document 1, the heat exchanger may be formed into an appropriate shape depending on the installation environment in order to appropriately arrange it in the installation environment. However, unlike the fin-and-tube type heat exchanger described in Patent Document 1, when a plate-fin type heat exchanger is used as a heat exchanger, the core part of the plate-fin type heat exchanger is usually Since it is formed into a rectangular parallelepiped shape, there is a problem in that it is difficult to form the core part into a curved shape depending on the installation environment.

This invention was made to solve the above-mentioned problems, and one object of the invention is to make the core part compatible with the installation environment even when using a rectangular plate-fin type heat exchange part. It is an object of the present invention to provide a heat exchanger that can be formed into a curved shape as required.

In order to achieve the above object, a heat exchanger according to the present invention includes a core section that performs heat exchange, and the core section has a first flow path through which a first fluid flows and a second flow path through which a second fluid flows. a plurality of rectangular parallelepiped-shaped plate-fin type heat exchange parts each having a passage and performing heat exchange between a first fluid flowing through the first flow passage and a second fluid flowing through the second flow passage; A connection part provided between the plurality of heat exchange parts and connecting the plurality of heat exchange parts at different angles , the connection part allowing one of the first fluid and the second fluid to flow. The core part has a third flow path, and the core part is adjacent to one of the first fluid and the second fluid flowing through the third flow path of the connection part and the connection part of the plurality of heat exchange parts. The heat exchanger is configured to perform heat exchange with the other of the first fluid and the second fluid flowing through the heat exchange section .

As described above, the heat exchanger according to the present invention includes a plurality of rectangular parallelepiped plate-fin type heat exchange sections and a connection section that connects the plurality of heat exchange sections at different angles. This allows multiple plate-fin type heat exchange parts to be connected at different angles using the connection part, so even when using a rectangular plate-fin type heat exchange part, the connection part and multiple heat exchange parts can be connected at different angles. The core portion as a whole including the portion can be formed into a curved shape depending on the installation environment. In addition, by using a plate-fin type heat exchanger, the heat transfer area per volume can be increased compared to when using other types of heat exchangers such as fin-and-tube heat exchangers. The core portion including the core portion can be made smaller and lighter.
Further, the connecting portion has a third flow path through which one of the first fluid and the second fluid flows, and the core portion has the first fluid and the second fluid flowing through the third flow path of the connecting portion. Heat exchange is performed between one of the first fluid and the second fluid flowing through the heat exchange section adjacent to the connection section of the plurality of heat exchange sections. It is configured as follows. With this configuration, heat exchange can be performed in the third flow path of the connection portion, unlike when the connection portion does not have a third flow path and only has a connection function, so heat transfer in the core portion is improved. Performance can be further improved. In addition, since a hollow part (reduced part) can be provided as a third flow path in the connection part, the weight of the connection part and the core part can be reduced compared to the case where the third flow path is not provided in the connection part. can do. Note that being able to reduce the weight of the core portion is very effective when using a heat exchanger for an aircraft engine, where weight reduction is important for improving fuel efficiency.

In the heat exchanger according to the above invention, preferably, the connection part has a first connection surface and a second connection surface forming a predetermined angle with the first connection surface, and the plurality of heat exchange parts are connected to the first connection surface. and the second connection surface, the plurality of heat exchange parts are connected at different angles. With this configuration, simply connecting the plurality of heat exchange parts to the first connection surface and the second connection surface allows the connections to be made at different angles. As a result, the core portion can be easily formed into a curved shape depending on the installation environment.

In this case, preferably, the connecting portion is formed into a wedge shape by the first connecting surface and the second connecting surface. With this configuration, the connecting portion can be formed in a simple shape, so the structure of the connecting portion can be simplified, and the manufacturing of the connecting portion can be facilitated. As a result, it is possible to connect a plurality of heat exchange parts at different angles through the connection part, while simplifying the structure of the connection part and facilitating the manufacture of the connection part. Note that the wedge shape is a broad concept that includes trapezoidal shapes, triangular shapes, and the like.

In the configuration in which the connecting portion has a wedge shape, preferably, a plurality of wedge-shaped connecting portions are provided, and the core portion has heat exchange portions and wedge-shaped connecting portions arranged alternately. It is formed into a curved shape. With this configuration, the core portion can be easily formed into a curved shape depending on the installation environment due to the alternate arrangement structure of the heat exchange portions and the wedge-shaped connecting portions. As a result, when there is a curved surface in the installation environment, the curved core portion can be appropriately arranged along the curved surface of the installation environment.

In the heat exchanger according to the above invention, preferably , in the core part, a flow path through which the other of the first fluid and the second fluid of the heat exchange part flows is arranged adjacent to the connection part. ing .

In this case, preferably the connection part is a multi-hole pipe including a plurality of through holes as the third flow path. With this configuration, the connecting portion having the third flow path can be formed in a simple shape, so the structure of the connecting portion having the third flow path can be simplified, and the third flow path can be formed in a simple shape. It is possible to facilitate the manufacture of a connection portion having the following characteristics. As a result, heat exchange can be performed in the third flow path of the connecting portion while simplifying the structure of the connecting portion and facilitating manufacturing of the connecting portion.

The heat exchanger according to the above invention is preferably a heat exchanger for an aircraft engine, and the core part connects a plurality of heat exchange parts at different angles by connecting parts, so that the core part can be attached to a curved surface in the aircraft engine. It is formed in a curved shape. With this configuration, the curved core portion can be appropriately disposed along the curved surface within the aircraft engine.

According to the present invention, as described above, there is provided a heat exchanger in which the core part can be formed into a curved shape depending on the installation environment even when using a rectangular parallelepiped plate-fin type heat exchange part. can do.

FIG. 1 is a schematic perspective view showing a heat exchanger according to an embodiment. FIG. 2 is a schematic perspective view showing a plate-fin type heat exchange part of a heat exchanger according to an embodiment. FIG. 2 is a schematic perspective view showing a connection part of a heat exchanger according to an embodiment. FIG. 2 is a schematic front view showing a heat exchanger according to an embodiment.

Embodiments of the present invention will be described below based on the drawings.

The configuration of a heat exchanger 100 according to this embodiment will be described with reference to FIGS. 1 to 4.

(Configuration of heat exchanger)
The heat exchanger 100 according to this embodiment is a heat exchanger for an aircraft engine. Specifically, the heat exchanger 100 is installed in an aircraft engine and is provided as an air-cooled heat exchanger (cooler) that exchanges heat using airflow within the aircraft engine. Further, the aircraft engine is a type of engine, such as a gas turbine engine, that generates propulsive force by using air taken in from the outside into a cylindrical casing. Therefore, a high-speed airflow is generated within the casing of the aircraft engine.

In the following description, the axial direction of the aircraft engine will be referred to as the A direction, the circumferential direction of the aircraft engine will be referred to as the B direction, and the radial direction of the aircraft engine will be referred to as the C direction.

As shown in FIG. 1, the heat exchanger 100 includes a core section 10 and a header section 20. The core portion 10 is configured to allow fluid to flow therethrough and perform heat exchange. Specifically, the core section 10 is configured to exchange heat between a first fluid 101 and a second fluid 102 different from the first fluid 101. The core portion 10 is configured to allow the first fluid 101 and the second fluid 102 to flow therethrough. The first fluid 101 is an air flow (air) for propulsion of an aircraft engine. Further, the second fluid 102 is oil such as lubricating oil for an aircraft engine or lubricating oil for a generator driven by the aircraft engine. In the core section 10, a second fluid 102, which is a fluid to be cooled (high temperature fluid), is cooled by a first fluid 101, which is a cooling fluid (low temperature fluid). Further, the core portion 10 is configured such that the first fluid 101 flows along the axial direction (direction A) of the aircraft engine, and the second fluid 102 flows along the radial direction (direction C) of the aircraft engine. has been done. Further, since the axial direction and the radial direction of the aircraft engine are substantially orthogonal to each other, the first fluid 101 and the second fluid 102 flow in the core portion 10 so as to be substantially orthogonal to each other.

The header section 20 is configured to supply a heat exchange fluid to the core section 10. Specifically, the header section 20 is configured to supply the second fluid 102, which is the fluid to be cooled, to the core section 10. For this reason, the header section 20 includes an inlet section 20a for taking in the second fluid 102. The second fluid 102 before heat exchange in the core section 10 flows into the header section 20 through the inlet section 20a. Further, the header section 20 is configured to discharge the second fluid 102 that has passed through the core section 10. For this reason, the header section 20 includes an outlet section 20b for taking out the second fluid 102. The second fluid 102 after heat exchange in the core section 10 flows out of the header section 20 via the outlet section 20b. Furthermore, a partition plate (not shown) is provided in the header section 20 to partition a flow path for the second fluid 102 flowing in through the inlet portion 20a and a flow path for the second fluid 102 flowing out through the outlet portion 20b. It is being

Note that in this embodiment, the first fluid 101, which is an air flow, is directly supplied to the core portion 10. Therefore, while the header section 20 for the second fluid 102 is provided, the header section for the first fluid 101 is not provided. Further, the header portion 20 is provided inside the core portion 10 in the radial direction (direction C), but is not provided outside the core portion 10 in the radial direction. This is because, in this embodiment, the second fluid 102 flows into the core section 10 and the second fluid 102 flows out from the core section 10 on the same side (radially inside the aircraft engine).

(Detailed configuration of core part)
Next, the detailed configuration of the core section 10 will be described with reference to FIGS. 1 to 4.

As shown in FIG. 1, the core section 10 includes a plurality (six) of heat exchange sections 11 and a plurality (five) of connection sections 12. Note that the plurality of heat exchange units 11 have substantially the same configuration. Further, the plurality of connecting portions 12 have substantially the same configuration.

The heat exchange section 11 is a rectangular parallelepiped plate-fin type heat exchanger. The heat exchange section 11 has a structure in which plates and fins are alternately stacked. Specifically, as shown in FIG. 2, the heat exchange section 11 includes a first flow path 11a having heat transfer fins 111a described below, a second flow path 11b having heat transfer fins 112a described below, and a partition section. 11c. The heat exchange section 11 includes a first flow path 11a, a partition portion 11c, a second flow path 11b, a partition portion 11c, a first flow path 11a, and so on. It has a structure in which the partitions 11c and 11c are regularly and repeatedly arranged in the stacking direction (direction D). Further, the heat exchange section 11 is provided so that the stacking direction is substantially perpendicular to the axial direction (direction A) and the radial direction (direction C) of the aircraft engine.

The first flow path 11a is a flow path through which the first fluid 101 flows. The first flow path 11a is configured to allow the first fluid 101 to flow along the axial direction (direction A) of the aircraft engine. Further, the first flow path 11a is provided with heat transfer fins 111a that divide the first flow path 11a into a plurality of flow paths (channels) and allow the first fluid 101 to flow therethrough. The heat transfer fins 111a are configured with corrugated corrugated fins that extend along the axial direction of the aircraft engine and wave along the radial direction (direction C) of the aircraft engine. Due to the corrugated fins, the first fluid 101 flows linearly in the first flow path 11a. Further, side bars 111b and 111c are arranged at both ends of the heat transfer fin 111a in the radial direction of the aircraft engine, respectively. The side bars 111b and 111c constitute the ends of the first flow path 11a in the radial direction of the aircraft engine. Side bars 111b and 111c are provided to extend along the axial direction of the aircraft engine.

The second flow path 11b is a flow path through which the second fluid 102 flows. The second flow path 11b is configured to allow the second fluid 102 to flow along the radial direction (direction C) of the aircraft engine that is orthogonal to the axial direction (direction A) of the aircraft engine. Further, the second flow path 11b is provided with heat transfer fins 112a that divide the second flow path 11b into a plurality of flow paths (channels) and allow the second fluid 102 to flow therethrough. The heat transfer fins 112a are corrugated fins that extend along the radial direction of the aircraft engine and wave along the axial direction of the aircraft engine. It consists of two types of corrugated fins: corrugated fins that wave along the corrugated fins, and corrugated fins that wave along the corrugated fins. These corrugated fins cause the second fluid 102 to flow in a U-shape (like a U-turn) in the second flow path 11b. Note that the second flow path 11b may be configured to allow the second fluid 102 to flow linearly, similarly to the first flow path 11a.

Further, side bars 112b and 112c are arranged at both ends of the heat transfer fin 112a in the axial direction (direction A) of the aircraft engine, respectively. Furthermore, a side bar 112d is arranged at the end of the heat transfer fin 112a on the outside in the radial direction (direction C) of the aircraft engine. The side bars 112b, 112c and 112d constitute the ends of the second flow path 11b on both axial sides and radially outer side of the aircraft engine. Side bars 112b and 112c are provided to extend along the radial direction of the aircraft engine. Further, the side bar 112d is provided so as to extend along the axial direction of the aircraft engine. Furthermore, the side bars 112b, 112c, and 112d are integrally provided in a U-shape. Further, the second flow path 11b is provided with a partition bar 112e for forming a U-shaped flow of the second fluid 102. The partition bar 112e is provided so as to extend along the radial direction of the aircraft engine.

The partition portion 11c is a partition plate (brazing sheet) that partitions the first flow path 11a and the second flow path 11b. The partition portion 11c is provided between the first flow path 11a and the second flow path 11b and at both ends of the heat exchange portion 11 in the stacking direction (direction D). The partition part 11c between the first flow path 11a and the second flow path 11b partitions the first flow path 11a and the second flow path 11b, and also serves as a partition for the first fluid 101 flowing through the first flow path 11a. and the second fluid 102 flowing through the second flow path 11b. Moreover, the partition parts 11c at both ends of the heat exchanger 11 in the stacking direction are configured to partition the first flow path 11a or the second flow path 11b arranged at the end in the stacking direction. In the example shown in FIG. 2, the partition parts 11c at both ends of the heat exchanger 11 in the stacking direction partition the second flow path 11b arranged at the end in the stacking direction. Further, the first flow path 11a, the second flow path 11b, and the partition portion 11c have a rectangular shape when viewed in the stacking direction, and are formed in a planar shape. The heat exchange section 11 is formed in a rectangular parallelepiped shape (box shape) by stacking a rectangular and planar first channel 11a, second channel 11b, and partition section 11c. .

Here, in this embodiment, as shown in FIG. 1, connecting portions 12 are provided between the plurality of heat exchange portions 11. The connecting portion 12 is configured to connect the plurality of heat exchange portions 11 at different angles. Specifically, the connection part 12 is provided adjacent to the heat exchange part 11 in the circumferential direction (direction B) of the aircraft engine, and two heat exchangers adjacent to the connection part 12 on one side and the other side in the circumferential direction are provided. The exchange parts 11 are configured to be connected at different angles along the circumferential direction.

As shown in FIG. 3, the connecting portion 12 has a first connecting surface 12a, a second connecting surface 12b, and a third flow path 12c. The first connecting surface 12a is arranged on one side of the connecting portion 12 in the circumferential direction (direction B) of the aircraft engine. The first connection surface 12a is configured to be connected to the heat exchange section 11 adjacent to the connection section 12 on one side in the circumferential direction. Specifically, the first connection surface 12a is in contact with the partition portion 11c of the heat exchanger 11 facing in the circumferential direction on one side in the circumferential direction, and is connected (joined) to the abutted partition portion 11c. It is composed of The first connection surface 12a has the same substantially rectangular shape as the partition portion 11c of the heat exchange section 11 when viewed in the circumferential direction.

The second connection surface 12b is arranged on the other side of the connection portion 12 in the circumferential direction (direction B) of the aircraft engine. The second connection surface 12b is configured to be connected to the heat exchange section 11 adjacent to the connection section 12 on the other side in the circumferential direction. Specifically, the second connection surface 12b is in contact with the partition portion 11c of the heat exchanger 11 facing in the circumferential direction on the other side in the circumferential direction, and is connected (joined) to the abutted partition portion 11c. It is composed of The second connection surface 12b has the same substantially rectangular shape as the partition portion 11c of the heat exchange section 11 when viewed in the circumferential direction.

Further, in this embodiment, the first connection surface 12a and the second connection surface 12b are formed to form a predetermined angle θ (>0). The predetermined angle θ is formed by the first connection surface 12a and the second connection surface 12b, which are formed in a V shape when viewed in the axial direction (A direction) of the aircraft engine, in the circumferential direction (B direction) of the aircraft engine. It's an angle. The predetermined angle θ is not particularly limited, but may be less than 90 degrees, for example. By reducing the predetermined angle θ, the radius of curvature of the arc-shaped core portion 10 (see FIG. 4) can be increased, as will be described later. ). Furthermore, by increasing the predetermined angle θ, the radius of curvature of the arc-shaped core portion 10 can be decreased, so that the core portion 10 can be formed along the curved surface S having a small radius of curvature. In the example shown in FIG. 3, the predetermined angle θ is approximately 6.5 degrees. The connecting portion 12 connects the plurality of heat exchange portions 11 to the first connection surface 12a and the second connection surface 12b, thereby connecting the plurality of heat exchange portions 11 at different angles by a predetermined angle θ. It is composed of

Further, the connecting portion 12 is formed into a wedge shape by a first connecting surface 12a and a second connecting surface 12b. Specifically, the connecting portion 12 has a wedge shape (trapezoidal shape) that gradually tapers from the outside to the inside in the radial direction of the aircraft engine when viewed in the axial direction (direction A) of the aircraft engine. . Further, the connecting portion 12 has a square prism shape with a wedge shape extending uniformly along the axial direction of the aircraft engine. The connecting portion 12 is configured such that a cross section perpendicular to the axial direction of the aircraft engine has a wedge shape.

Furthermore, in the present embodiment, the connecting portion 12 is provided with a third flow path 12c through which the first fluid 101 flows. The third flow path 12c is configured to allow the first fluid 101 to flow along the axial direction (direction A) of the aircraft engine. The third flow path 12c extends along the axial direction (direction A) of the aircraft engine and is constituted by a plurality of through holes that penetrate the connecting portion 12 in the axial direction. The plurality of through holes allow the first fluid 101 to flow linearly in the third flow path 12c. Further, the connecting portion 12 is provided as a multi-hole pipe including a plurality of through holes as the third flow path 12c. The connecting portion 12 as a multi-hole pipe is formed by extrusion molding of aluminum, for example. Therefore, the plurality of through holes as the third flow path 12c are provided so as to extend linearly from one end of the connecting portion 12 to the other end in the axial direction of the aircraft engine. Further, the connecting portion 12 is formed so that the shape of a cross section perpendicular to the axial direction of the aircraft engine is the same from one end to the other end in the axial direction of the aircraft engine. Further, the connecting portion 12 is made of a single member. In addition, in FIG. 3, for ease of understanding, only one of the plurality of through holes as the third flow path 12c is illustrated as penetrating the connecting portion 12 by a broken line.

The plurality of through holes serving as the third flow path 12c are arranged along the radial direction of the aircraft engine. Specifically, the plurality of through holes as the third flow paths 12c extend radially from near the end of the outer connecting portion 12 in the radial direction of the aircraft engine to near the end of the inner connecting portion 12. It is provided so as to be arranged along the direction. Further, since the connecting portion 12 has a wedge shape, the plurality of through holes serving as the third flow path 12c are provided so that the opening width in the circumferential direction gradually decreases from the outside to the inside in the radial direction of the aircraft engine. It is being Further, the plurality of through holes as the third flow path 12c have a substantially rectangular opening shape.

In the present embodiment, the core section 10 (see FIG. 1) connects the first fluid 101 flowing through the third flow path 12c of the connection section 12 and the plurality of heat exchange sections 11 (see FIG. 2). The second fluid 102 (see FIG. 2) flowing through the heat exchange section 11 adjacent to the section 12 is configured to exchange heat with the second fluid 102 (see FIG. 2). That is, in the core part 10, the connecting part 12 and the second flow path 11b (see FIG. 2) through which the second fluid 102 of the heat exchange part 11 flows, with the partition part 11c in between, are arranged in the circumferential direction ( They are arranged adjacent to each other in the direction B). The partition part 11c between the connecting part 12 and the second flow path 11b of the heat exchange part 11 is configured to separate the first fluid 101 flowing through the third flow path 12c and the second fluid 102 flowing through the second flow path 11b. Acts as a heat transfer surface that transfers heat between

Further, in this embodiment, as shown in FIG. 4, the core part 10 is curved along the curved surface S in the aircraft engine by connecting the plurality of heat exchange parts 11 at different angles by the connecting parts 12. It is formed in the shape of Specifically, the core portion 10 is formed in an arcuate and curved shape along the circumferential direction (B direction) of the aircraft engine when viewed in the axial direction (A direction) of the aircraft engine. The core part 10 is formed into an arcuate and curved shape by alternately arranging rectangular parallelepiped-shaped heat exchange parts 11 and wedge-shaped connection parts 12. Note that the curved surface S in the aircraft engine may be any part of the aircraft engine as long as it is exposed to airflow, and may be, for example, the inner circumferential surface of the fan casing of the aircraft engine.

Further, the core portion 10 is formed into a curved shape having a substantially constant radius of curvature so as to correspond to the curved surface S having a substantially constant radius of curvature. Specifically, the core portion 10 has heat exchange portions 11 having substantially the same shape and connecting portions 12 having substantially the same shape arranged alternately along the circumferential direction (direction B) of the aircraft engine, so that the core portion 10 is curved. It is formed into a curved shape having a substantially constant radius of curvature corresponding to the surface S.

(Effects of this embodiment)
In this embodiment, the following effects can be obtained.

In this embodiment, as described above, a plurality of rectangular plate-fin type heat exchange parts 11 and a connection part 12 that connects the plurality of heat exchange parts 11 at different angles are provided. A plurality of plate-fin type heat exchange parts 11 can be connected at different angles. As a result, even when using the rectangular plate-fin type heat exchange section 11, the core section 10 as a whole including the connection section 12 and the plurality of heat exchange sections 11 can be formed into a curved shape according to the installation environment. can do. Furthermore, by using the plate-fin type heat exchanger 11, the heat transfer area per volume can be increased compared to when using other types of heat exchangers such as fin-and-tube heat exchangers. The core portion 10 including the portion 11 can be made smaller and lighter.

Further, in this embodiment, as described above, the connecting portion 12 has the first connecting surface 12a and the second connecting surface 12b forming a predetermined angle θ with the first connecting surface 12a, and has a plurality of heat exchangers. By connecting the section 11 to the first connection surface 12a and the second connection surface 12b, the plurality of heat exchange sections 11 are connected at different angles, so it is possible to simply connect the plurality of heat exchange sections 11. Connection can be made by changing the angle simply by connecting to the first connection surface 12a and the second connection surface 12b. As a result, the core portion 10 can be easily formed into a curved shape depending on the installation environment.

Furthermore, in this embodiment, as described above, the connecting portion 12 is formed in a wedge shape by the first connecting surface 12a and the second connecting surface 12b, so that the connecting portion 12 can be formed into a simple shape. It can be formed by Thereby, the structure of the connecting portion 12 can be simplified, and the manufacturing of the connecting portion 12 can be facilitated. As a result, the plurality of heat exchange parts 11 can be connected by the connecting part 12 at different angles while simplifying the structure of the connecting part 12 and facilitating the manufacture of the connecting part 12.

Further, in this embodiment, as described above, a plurality of wedge-shaped connecting portions 12 are provided. Further, since the core portion 10 is formed into a curved shape by alternately arranging the heat exchange portions 11 and the wedge-shaped connecting portions 12, the heat exchange portions 11 and the wedge-shaped connecting portions 12 are The alternate arrangement structure allows the core portion 10 to be easily formed into a curved shape depending on the installation environment. As a result, when there is a curved surface S in the installation environment, the curved core portion 10 can be appropriately arranged along the curved surface S in the installation environment.

Furthermore, in this embodiment, as described above, the connecting portion 12 has the third flow path 12c through which the first fluid 101 flows. The core part 10 also includes a first fluid 101 that flows through the third flow path 12c of the connection part 12 and a second fluid that flows through the heat exchange part 11 adjacent to the connection part 12 of the plurality of heat exchange parts 11. 102, unlike the case where the connection part 12 does not have the third flow path 12c and only has a connection function, the third flow path 12c of the connection part 12 Heat exchange can be performed. Thereby, the heat transfer performance of the core portion 10 can be further improved. Further, since a hollow portion (reduced portion) can be provided in the connecting portion 12 as the third flow path 12c, the weight of the connecting portion 12 can be reduced compared to a case where the third flow path 12c is not provided in the connecting portion 12. The weight of the core portion 10 can be reduced. Note that being able to reduce the weight of the core portion 10 is very effective when the heat exchanger 100 is used for an aircraft engine, where weight reduction is important for improving fuel efficiency.

Furthermore, in this embodiment, as described above, the connecting portion 12 is configured to be a multi-hole pipe including a plurality of through holes as the third flow path 12c, so that it has the third flow path 12c. The connecting portion 12 can be formed with a simple shape. Thereby, the structure of the connecting portion 12 having the third flow path 12c can be simplified, and the manufacturing of the connecting portion 12 having the third flow path 12c can be facilitated. As a result, heat exchange can be performed in the third flow path 12c of the connecting portion 12 while simplifying the structure of the connecting portion 12 and facilitating manufacturing of the connecting portion 12.

Furthermore, in this embodiment, as described above, the heat exchanger 100 is a heat exchanger for an aircraft engine. In addition, since the core part 10 is formed in a curved shape along the curved surface S in the aircraft engine by connecting the plurality of heat exchange parts 11 at different angles by the connecting parts 12, The curved core portion 10 can be appropriately arranged along the curved surface S.

(Modified example)
Note that the embodiments disclosed this time should be considered to be illustrative in all respects and not restrictive. The scope of the present invention is indicated by the claims rather than the description of the embodiments described above, and further includes all changes (modifications) within the meaning and range equivalent to the claims.

For example, in the above embodiment, an example was shown in which the present invention is applied to a heat exchanger for an aircraft engine, but the present invention is not limited to this. The present invention may be applied to heat exchangers other than those for aircraft engines, such as heat exchangers for automobiles.

Further, in the above embodiment, an example is shown in which the first fluid is an air flow and the second fluid is oil, but the present invention is not limited to this. In the present invention, the types of the first fluid and the second fluid are not particularly limited. The first fluid and the second fluid may be any fluid.

Further, in the above embodiment, an example is shown in which the first fluid is a cooling fluid and the second fluid is a fluid to be cooled, but the present invention is not limited to this. In the present invention, the first fluid may be the fluid to be cooled, and the second fluid may be the cooling fluid.

Further, in the above embodiment, an example in which six plate-fin type heat exchange sections are provided is shown, but the present invention is not limited to this. In the present invention, a plurality of plate fin type heat exchange parts other than six may be provided.

Further, in the above embodiment, an example is shown in which five connection parts are provided, but the present invention is not limited to this. In the present invention, the number of connection parts may be provided in accordance with the number of heat exchange parts. That is, a plurality of connections other than one or five may be provided.

Further, in the above embodiment, an example was shown in which the connecting portion is constituted by a single member, but the present invention is not limited to this. In the present invention, the connection part between the two heat exchange parts may be configured by connecting two or more divided members that are divided from each other.

Further, in the above embodiment, an example in which the connecting portion has a wedge shape is shown, but the present invention is not limited to this. In the present invention, the connecting portion may have a shape other than a wedge shape as long as the plurality of heat exchange portions can be connected at different angles.

Further, in the above embodiment, an example is shown in which the core part is formed into a curved shape having a substantially constant radius of curvature by alternately arranging heat exchange parts of the same shape and connection parts of the same shape. However, the present invention is not limited to this. In the present invention, the core portion may be formed in a curved shape having a radius of curvature that is not constant. In this case, by using heat exchange parts or connection parts of different shapes, the core part can be formed into a curved shape having a non-uniform radius of curvature. Further, in this case, the core portion may be formed into a complicated curved shape such as an S-shape. The plurality of heat exchange parts may not have the same shape, and the plurality of connection parts may not have the same shape.

Further, in the embodiment described above, an example was shown in which the connecting portion has a third flow path through which the first fluid flows, but the present invention is not limited to this. In the present invention, the connection portion may have a third flow path through which the second fluid flows. In this case, the core part is used for heat exchange between the second fluid flowing through the third flow path of the connection part and the first fluid flowing through the heat exchange part adjacent to the connection part among the plurality of heat exchange parts. It can be configured to do this. Further, in the present invention, the connecting portion may have a third flow path through which both the first fluid and the second fluid flow. Further, in the present invention, the connecting portion does not need to have a flow path through which the first fluid or the second fluid flows.

Further, in the above embodiment, an example is shown in which the connecting portion is a multi-hole pipe including a plurality of through holes as the third flow path, but the present invention is not limited to this. In the present invention, the connection portion may have a configuration in which only one through hole is formed as the third flow path.

Further, in the embodiment described above, an example was shown in which the plurality of through holes serving as the third flow path had a substantially rectangular opening shape, but the present invention is not limited to this. In the present invention, the plurality of through holes serving as the third flow path may have an opening shape other than a substantially rectangular shape, as long as the fluid can flow through the third flow path.

Further, in the above embodiment, an example was shown in which a header section for the second fluid is provided but a header section for the first fluid is not provided, but the present invention is not limited to this. In the present invention, both the header section for the second fluid and the header section for the first fluid may be provided.

Further, in the above embodiment, an example is shown in which the header section for the second fluid is provided inside the core section in the radial direction, but is not provided outside the core section in the radial direction. However, the present invention is not limited to this. In the present invention, when the second fluid flows into the core part and the second fluid flows out from the core part on opposite sides, the header part for the second fluid is arranged radially inside and inside the core part. It may be provided on both the outside.

Further, in the above embodiment, an example was shown in which the first flow path and the second flow path are alternately stacked in the heat exchange section, but the present invention is not limited to this. In the present invention, as long as the first flow path and the second flow path are adjacent to each other in the heat exchange section, they do not necessarily need to be stacked alternately. For example, in the heat exchange section, the first flow path and the second flow path may be arranged as follows: first flow path, first flow path, second flow path, first flow path... However, the first flow path and the second flow path may be arranged such as a first flow path, a second flow path, a second flow path, a first flow path, and so on.

Further, in the above embodiment, an example was shown in which the heat exchange section is configured as a cross-flow type heat exchanger in which the first fluid and the second fluid flow substantially perpendicularly to each other. It is not limited to this. In the present invention, the heat exchange section may be configured as a counterflow type heat exchanger in which the first fluid and the second fluid flow in substantially parallel and opposite directions, or the first fluid and the second fluid may flow in opposite directions. The heat exchanger may be configured as a parallel flow type heat exchanger in which the fluids flow substantially parallel to each other and in the same direction.

Further, in the embodiment described above, an example was shown in which the connection part was provided between a plurality of heat exchange parts, but the present invention is not limited to this. In the present invention, the connection part may be provided not only between the plurality of heat exchange parts but also at the end of the core part (outside of the endmost heat exchange part).

10 core part 11 heat exchange part 11a first flow path 11b second flow path 12 connection part 12a first connection surface 12b second connection surface 12c third flow path 100 heat exchanger 101 first fluid 102 second fluid S curved surface θ predetermined angle

Claims (7)

Equipped with a core part that performs heat exchange,
The core portion is
The first fluid flows through the first flow path and the second fluid flows through the second flow path. a plurality of rectangular plate-fin type heat exchange parts that exchange heat with the second fluid;
a connection part provided between the plurality of heat exchange parts and connecting the plurality of heat exchange parts at different angles ,
The connecting portion has a third flow path through which one of the first fluid and the second fluid flows,
The core portion is adjacent to one of the first fluid and the second fluid flowing through the third flow path of the connection portion and the connection portion of the plurality of heat exchange portions. A heat exchanger configured to perform heat exchange with the other of the first fluid and the second fluid flowing through the heat exchange section. The connecting portion has a first connecting surface and a second connecting surface forming a predetermined angle with the first connecting surface, and the plurality of heat exchange portions are connected to the first connecting surface and the second connecting surface. The heat exchanger according to claim 1, wherein the heat exchanger is configured to connect the plurality of heat exchange parts at different angles by connecting to the heat exchanger. The heat exchanger according to claim 2, wherein the connection portion is formed in a wedge shape by the first connection surface and the second connection surface. A plurality of the wedge-shaped connecting portions are provided,
The heat exchanger according to claim 3, wherein the core portion is formed into a curved shape by alternately arranging the heat exchange portions and the wedge-shaped connection portions. Claim 1: In the core part, a flow path through which the other of the first fluid and the second fluid of the heat exchange part flows is arranged so as to be adjacent to the connection part. The heat exchanger according to any one of items 1 to 4. The heat exchanger according to claim 1 , wherein the connecting portion is a multi-hole tube including a plurality of through holes as the third flow path. A heat exchanger for aircraft engines,
The core portion is formed into a curved shape along a curved surface within the aircraft engine by connecting the plurality of heat exchange portions at different angles by the connecting portion. The heat exchanger according to item 1.

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