JP2016056792A - Aircraft heat exchanger - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide an aircraft heat exchanger that can lower a rise in temperature of a seal member in a fire disaster to secure fire resistance.SOLUTION: The aircraft heat exchanger 10 includes: an auxiliary flow passage 60a branching from a main flow passage; a valve 70 for opening and closing the auxiliary flow passage 60a; the seal member 63 for sealing between members forming the auxiliary flow passage 60a; and a relief flow passage 71a for connecting an upstream side to a downstream side of the valve 70. A transverse section area of the relief flow passage 71a is smaller than that of the auxiliary flow passage 60a.SELECTED DRAWING: Figure 5

Description

  The present invention relates to an aircraft heat exchanger including an auxiliary flow path that branches from a main flow path, a valve that opens and closes the auxiliary flow path, and a seal member that seals between members that form the auxiliary flow path.

  In an aircraft, a heat exchanger is used for cooling engine oil and generator oil, for example. Aircraft heat exchangers include, for example, a plate fin type, a shell and tube type, a surface type, and the like, and these have different structures of a main body (core) that performs heat exchange.

  The main body of the plate fin type heat exchanger is formed by alternately stacking a high-temperature fluid channel and a low-temperature fluid channel, for example. In both the hot fluid passage and the cold fluid passage, plate-like fins are arranged, and the plate-like fins are called corrugated fins.

  The main body of the shell-and-tube heat exchanger includes a cylindrical shell and a plurality of heat transfer tubes arranged side by side in the shell. In this case, while the 1st fluid distribute | circulates between a shell and a heat exchanger tube, a 2nd fluid distribute | circulates in each heat exchanger tube, and heat exchange is performed via a heat exchanger tube.

  The main body of the surface type heat exchanger has, for example, a belt shape, and a fluid circulates in the inside thereof. Further, the outside of the main body is exposed to an air current. Plate-like fins (corrugated fins) are arranged inside the main body, and heat radiating fins are provided outside the main body. In this case, heat exchange is performed between the fluid inside the main body and the external airflow via the plate-like fins and the heat radiating fins.

  Such an aircraft heat exchanger may include an auxiliary flow path that branches from a main flow path through which a fluid to be used for heat exchange flows, and a valve that opens and closes the auxiliary flow path. The auxiliary flow path corresponds to, for example, a bypass flow path for omitting a part of the main flow path. Hereinafter, among the valves that open and close the auxiliary flow path, the valve that opens and closes the bypass flow path is also particularly referred to as a “bypass valve”.

  When providing a valve for opening and closing the auxiliary flow path, a seal member that seals between the members forming the auxiliary flow path may be disposed. For example, in the surface type heat exchanger proposed in Patent Document 1, a bypass flow path and a bypass valve that opens and closes the bypass flow path are provided. By providing such a bypass flow path, for example, when the temperature of the fluid to be cooled is lower than the melting point in a cryogenic environment, the fluid to be cooled passes through a part of the flow path of the heat exchanger. Can be omitted. In addition, although description is abbreviate | omitted in patent document 1, a seal member is arrange | positioned with providing a bypass valve with a bypass flow path. This seal member is disposed, for example, between a lid of the bypass valve and a member that mainly forms a bypass flow path and houses the valve main body, and seals the gap therebetween.

Patent No. 5442916

  As described above, in an aircraft heat exchanger, a seal member may be disposed on an auxiliary flow path along with a valve capable of opening and closing the auxiliary flow path. Moreover, in the surface type heat exchanger described in Patent Document 1, a bypass valve capable of opening and closing the bypass flow path is provided. In this case, a gap between the bypass valve lid and a member that mainly forms the bypass flow path is provided. A sealing member (for example, an O-ring) to be sealed is disposed.

  By the way, in an aircraft heat exchanger, it is required to hold the fluid inside without leaking the fluid to the outside even in the event of a fire. Specifically, the aircraft heat exchanger is required to pass a predetermined flame test. This flame test is performed, for example, as defined in ISO 2685, by placing the heat exchanger in an environment of about 1100 ° C. for 15 minutes. In the flame test, it passes if there is no external leakage of fluid.

  In Patent Document 1, it is described that a bypass valve is provided in the bypass flow path, but there is no description regarding fire resistance. For example, if a seal member is arranged between the bypass valve lid and the member that mainly forms the bypass flow path, the seal member is heated and damaged during the flame test, and the fluid leaks to the outside. .

  This invention is made | formed in view of such a condition, and it aims at providing the heat exchanger for aircraft which can reduce the temperature rise of the sealing member in the case of a fire, and can ensure fire resistance.

  An aircraft heat exchanger according to an embodiment of the present invention includes an auxiliary flow path that branches from a main flow path, a valve that opens and closes the auxiliary flow path, and a seal member that seals between members that form the auxiliary flow path. The aircraft heat exchanger further includes an escape passage that connects the upstream side and the downstream side of the valve, and the cross-sectional area of the escape passage is It is smaller than the cross-sectional area of the auxiliary flow path.

  The ratio of the cross-sectional area of the relief flow channel to the cross-sectional area of the auxiliary flow channel may be 0.1 to 5%. Moreover, it is preferable that the said escape flow path consists of a through-hole provided in the valve body of the said valve. The aircraft heat exchanger may be a surface type.

  The aircraft heat exchanger of the present invention includes an escape passage that connects the upstream side and the downstream side of the valve. For this reason, even when the flow of the fluid in the auxiliary channel is blocked by the valve, the fluid in the auxiliary channel slightly flows. Thereby, when a fire occurs, a high-temperature fluid heated by the flame flows out from the auxiliary flow path, and a low-temperature fluid flows into the auxiliary flow path. As a result, the temperature rise of the sealing member can be reduced to prevent the sealing member from being damaged, and the heat resistance of the heat exchanger can be ensured.

FIG. 1 is a front view showing a configuration example of an aircraft heat exchanger. FIG. 2 is an exploded perspective view showing a configuration example of an aircraft heat exchanger. Drawing 3 is a front view showing the 1st member with which the example of composition of the heat exchanger for airplanes is provided. FIG. 4 is a cross-sectional view taken along the line AA showing an example of the configuration of an aircraft heat exchanger. FIG. 5 is a cross-sectional view taken along the line B-B showing a configuration example of an aircraft heat exchanger.

  Below, the heat exchanger for aircrafts of this embodiment is explained, referring to drawings.

  1-5 is a figure which shows the structural example of the heat exchanger for aircrafts. Of these, FIG. 1 is a front view of the heat exchanger, FIG. 2 is an exploded perspective view of the heat exchanger, FIG. 3 is a front view of the first member, FIG. FIG. 4 is a cross-sectional view of the heat exchanger taken along the line BB.

  The aircraft heat exchanger 10 (hereinafter also simply referred to as “heat exchanger”) shown in FIGS. 1 to 5 is a surface type and is not shown in the figure, but is mounted on an aircraft engine (for example, a gas turbine engine). . The shape of the heat exchanger 10 is a belt shape. Since the heat exchanger 10 is disposed along, for example, a curved surface (for example, an inner peripheral surface or an outer peripheral surface) of the engine, the heat exchanger 10 is also curved along the arrangement surface.

  When the heat exchanger is disposed on a curved surface of the engine, the outside of the heat exchanger 10 is exposed to an airflow along the axial direction of the engine (see the hatched arrows in FIGS. 1, 4, and 5). Inside the heat exchanger 10, for example, engine oil or generator oil driven by the engine flows as a fluid. At that time, heat exchange is performed between the external airflow and the internal oil, and the internal oil is cooled.

  The inner curved surface 10a and the outer curved surface 10b of the heat exchanger 10 are tapered as shown in FIGS. 4 and 5, and the diameter increases toward the downstream side of the airflow along the axial direction of the fan casing. . 4 and 5 are lines parallel to the center lines of the inner curved surface 10a and the outer curved surface 10b of the heat exchanger 10.

  The main body of the heat exchanger 10 is configured by overlapping the first member 20 and the second member 30 in the thickness direction. A plurality of plate-like fins (corrugated fins) 40 are arranged in the main body. These members are joined together by brazing, for example.

  The 1st member 20 is a strip | belt-shaped board | plate material, and has the hollow part 20a in the curved surface of the outer side. The second member 30 is also a belt-like plate material, and becomes a lid that covers the recessed portion 20 a of the first member 20 by overlapping the first member 20. The main flow path 11 is formed inside the main body by the recess 20a of the first member and the curved surface inside the second member 30 (see FIG. 3).

  The main flow path 11 inside the main body is divided into an outward path 11a and a return path 11b by a partition portion 20b of the first member. The partition part 20b extends from one end (upper end in FIG. 3) to the other end (lower end in FIG. 3) at the center position in the axial direction of the curved surface in the recess 20a of the first member.

  Next, the configuration of the inflow header 12 and the outflow header 13 for flowing fluid into and out of the main flow path 11 inside the main body will be described with reference mainly to FIG. In the hollow portion 20a of the first member, two concave grooves (20c, 20d) are provided side by side in the axial direction of the curved surface across the partition portion 20b at one end in the circumferential direction thereof. The concave grooves (20c, 20d) respectively extend in the axial direction of the curved surface and are deeper than the concave portion 20a. Further, at the position corresponding to the concave grooves (20c, 20d) of the first member, convex bulge portions 30a are provided on the outer curved surface of the second member 30, and two on the inner curved surface. Concave grooves (30c, 30d) are provided side by side in the axial direction.

  The concave groove 20c on the forward path 11a side of the first member, together with the concave groove 30c of the second member 30, constitutes an inflow header 12 that allows fluid to flow into the main flow path 11 (outward path 11a) inside the main body. Further, the recessed groove 20d on the return path 11b side of the first member constitutes an outflow header 13 that causes the fluid to flow out from the main flow path 11 (return path 11b) inside the main body together with the recessed groove 30d of the second member 30.

  A port mounting portion 50 is provided outside the bulging portion 30a of the second member. The port attachment portion 50 and the bulging portion 30a are provided with a fluid supply port 14 to the inflow header 12, and the supply port 14 includes a through-hole communicating with the port attachment portion 50 and the bulging portion 30a. Further, the port attachment portion 50 and the bulging portion 30a are provided with a discharge port 15 for fluid from the outflow header 13, and the discharge port 15 includes a through-hole communicating with the port attachment portion 50 and the bulge portion 30a.

  A plurality of radiating fins 20 e are provided on the inner curved surface of the first member 20 substantially perpendicularly to the inner curved surface. The plurality of heat radiation fins 20e extend along the axial direction of the curved surface, and are arranged side by side in the circumferential direction of the curved surface. In FIG. 2, a region where the radiation fins 20 e are provided is indicated by a two-dot chain line, and illustration of some of the radiation fins 20 e is omitted.

  On the outer curved surface of the second member 30, a plurality of heat radiation fins 30e are provided substantially perpendicular to the outer curved surface. The plurality of heat radiation fins 30e extend along the axial direction of the curved surface, and are arranged side by side in the circumferential direction of the curved surface. In FIG. 2, a region where the radiation fins 30 e are provided is indicated by a two-dot chain line, and illustration of some of the radiation fins 30 e is omitted.

  In addition, although the heat exchanger 10 shown in FIGS. 2-6 provides a radiation fin (20e, 30e) in both the curved surface inside the 1st member 20, and the curved surface outside the 2nd member 30, You may employ | adopt the structure which provides a radiation fin only in either. What is necessary is just to set suitably the curved surface which provides a radiation fin according to the arrangement surface (for example, inner peripheral surface or outer peripheral surface) of a heat exchanger, and the required heat exchange efficiency.

  The corrugated fin 40 is accommodated in the recessed portion 20 a of the first member, and abuts on the bottom surface of the recessed portion 20 a of the first member and the curved surface inside the second member 30. With such a corrugated fin 40, the main channel 11 inside the main body is partitioned and subdivided, and a plurality of small channels are formed in the main channel 11.

  As shown in FIG. 2, the corrugated fin 40 is divided and includes a plurality of members. As shown in FIGS. 4 and 5, the corrugated fin 40 is arranged in the main body except for the inflow header 12, the outflow header 13, the bypass inflow header 16, and the bypass outflow header 17. More specifically, as shown in FIG. 2, the corrugated fin 40 includes a concave groove 20 c constituting the inflow header 12, a concave groove 20 d constituting the outflow header 13, a concave groove 20 f constituting the bypass inflow header 16, and It is arranged excluding the concave groove 20g constituting the bypass outlet header 17.

  In the heat exchanger 10 having such a configuration example, fluid is supplied to the inflow header 12 through the supply port 14. The fluid is distributed to a plurality of small flow paths of the main flow path 11 in the inflow header 12, flows in order through the forward path 11 a and the return path 11 b of the main flow path 11, and reaches the outflow header 13. In the process of flowing through the main flow path 11 inside the main body, heat exchange is performed between the fluid inside the main body and the external airflow via the corrugated fins 40, the first member heat dissipating fins 20e, and the second member heat dissipating fins 30e. . The fluid that has circulated through the plurality of small flow paths of the main flow path 11 and reached the outflow header 13 joins at the outflow header 13 and flows out from the discharge port 15.

  The aircraft heat exchanger of the present embodiment includes an auxiliary flow path that branches from the main flow path 11 and a valve that opens and closes the auxiliary flow path. This auxiliary flow path can be a bypass flow path 60a for omitting a part of the main flow path, and a valve for opening and closing the auxiliary flow path can be a bypass valve 70. The configuration of such an auxiliary flow path and a valve for opening and closing the auxiliary flow path will be described with reference to FIG. 5 mainly using the bypass flow path 60a and the bypass valve 70 as an example.

  Similarly to the concave grooves (20c, 20d) constituting the inflow header 12 or the outflow header 13 in the recessed portion 20a of the first member, the concave grooves (20f, 20g) are also formed in the intermediate portion in the circumferential direction of the curved surface. Are provided. In addition, a convex bulge 30b is provided on the outer curved surface of the second member 30 at a position corresponding to the groove (20f, 20g) in the intermediate portion of the first member, and the inner curved surface. The two concave grooves (30f, 30g) are provided side by side in the axial direction of the curved surface.

  The concave groove 20f on the forward path 11a side of the first member constitutes the bypass inflow header 16 capable of allowing fluid to flow into the bypass flow path 60a together with the concave groove 30f of the second member. The concave groove 20g on the return path 11b side of the first member, together with the concave groove 30g of the second member 30, constitutes a bypass outflow header 17 capable of allowing fluid to flow out of the bypass flow path 60a.

  The bulging portion 30b of the second member is provided with a through hole 30h leading to the concave groove 30f so that fluid can flow from the bypass inflow header 16 into the bypass flow path 60a. Further, the bulging portion 30b of the second member is provided with a through hole 30i leading to the concave groove 30g so that the fluid can flow out from the bypass flow path 60a to the bypass outflow header 17.

  The bulging portion 30b of the second member is provided with a valve mounting portion 60, and the valve mounting portion 60 is provided with a bypass flow path 60a. The bypass flow path 60 a is a flow path that connects the bypass inflow header 16 and the bypass outflow header 17.

  A bypass valve 70 is disposed in the bypass flow path 60a. The bypass valve 70 shown in the figure is a differential pressure on-off valve, and opens and closes the bypass flow path 60a according to the differential pressure between the bypass inflow header 16 and the bypass outflow header 17.

  In order to provide this bypass valve 70, the valve mounting portion 60 is divided into a valve body housing member 61 and a lid member 62. Since the bypass valve 70 is provided in the bypass flow path 60 a, the seal member 63 is disposed to seal between the valve body housing member 61 and the lid member 62. The seal member 63 shown in the figure is an O-ring and is disposed in the ring groove. The ring groove is provided on the inner peripheral surface of the hole into which the bypass valve 70 is inserted. The seal member 63 seals a gap between the inner peripheral surface of the hole into which the bypass valve 70 is inserted and the outer peripheral surface of the columnar protrusion of the lid member 62.

  If the bypass flow path 60a and the bypass valve 70 are provided, when the bypass flow path 60a is blocked by the bypass valve 70, the fluid flows in order through the forward path 11a and the return path 11b of the main flow path 11 as described above. To do. On the other hand, when the bypass flow path 60a is opened by the bypass valve 70, most of the fluid flows into the bypass flow path 60a when passing through the bypass inflow header 16 in the middle of the forward path 11a, and the bypass outflow header 17 To return to the middle of the return path 11b. For this reason, a fluid distribute | circulates, omitting some main flow paths 11 inside a main body.

  According to such a bypass function, it is omitted that the cooling-symmetric fluid flows through a part of the main flow path 11 inside the main body of the heat exchanger 10, so that the temperature of the fluid after passing through the heat exchanger is increased. Can be maintained. This bypass function can be used, for example, when the temperature of the fluid to be cooled is rapidly increased when the temperature of the fluid to be cooled is lower than the melting point in a cryogenic environment.

  The aircraft heat exchanger of the present embodiment further includes an escape passage 71a. The relief flow path 71a will be described by taking as an example a case where the auxiliary flow path is the bypass flow path 60a and the valve that opens and closes the auxiliary flow path is the bypass valve 70.

  In the heat exchanger 10 shown in the figure, the escape passage 71 a is provided in the bypass valve 70, and specifically, the escape passage 71 a is formed of a through hole provided in the valve body 71 of the bypass valve 70. The diameter of the opening of the valve seat 72 shown in the figure is 20 mm. In this case, the diameter of the through hole of the escape passage 71 a is 1 mm, for example. Such an escape passage 71a connects the upstream side (bypass inflow header 16 side) and the downstream side (bypass outflow header 17 side) of the bypass valve.

  When the escape passage 71a is not provided, the sealing member is heated and damaged in the event of a fire, and the fluid leaks to the outside for the following reason. In a state where the flow of the fluid in the bypass channel 60a is blocked by the bypass valve 70, the fluid stays in the bypass channel 60a. When a fire occurs in this state, the fluid staying in the surrounding members and the bypass flow path 60a is heated together with the seal member 63. As a result, the seal member 63 made of rubber or the like breaks due to deformation or alteration as the temperature rises, and the sealing performance is impaired, and the fluid inside the main body of the heat exchanger 10 leaks.

  On the other hand, the aircraft heat exchanger of the present embodiment includes an escape passage 71a. In this case, even when the flow of the fluid in the bypass flow path 60a is blocked by the bypass valve 70, the fluid flows in the escape flow path 71a, so that the fluid in the bypass flow path 60a slightly flows without staying completely. To do. Specifically, the fluid flows from the upstream side (bypass inflow header 16 side) to the downstream side (bypass outflow header 17 side). Accordingly, the fluid flows from the bypass inflow header 16 into the bypass flow path 60a, and the fluid flows out from the bypass flow path 60a to the bypass outflow header 17.

  When a fire occurs, the surrounding members and the fluid in the bypass flow path 60a are heated together with the seal member 63. At this time, due to the action of the above-described escape flow path 71a, the high-temperature fluid heated in the bypass flow path 60a flows out to the bypass outflow header 17, and the cooling target fluid flows from the bypass inflow header 16 to the bypass flow path 60a. Flow into. Since the fluid to be cooled is, for example, about 80 ° C., as a result, the high temperature fluid flows out from the bypass flow path 60a and the low temperature fluid flows into the bypass flow path 60a. As a result, the seal member 63 and its surrounding members are removed, so that the temperature rise of the seal member 63 can be reduced and damage can be prevented. For this reason, fire resistance can be ensured in the event of a fire.

  The area of the cross section of the escape flow path 71a is smaller than the area of the cross section of the auxiliary flow path such as the bypass flow path 60a. When the area of the cross section of the escape flow path 71a is the same as the area of the cross section of the auxiliary flow path, or when the area of the cross section of the escape flow path 71a is larger than the area of the cross section of the auxiliary flow path, the bypass valve 70 The original function of opening and closing the auxiliary flow path is lost by such a valve, and the original performance of the heat exchanger 10 cannot be exhibited.

If the cross-sectional area of the escape passage 71a is excessive, the original function of opening and closing the auxiliary passage by the valve is lost, and the performance of the heat exchanger 10 may not be exhibited. For this reason, the area (mm ² ) of the cross section of the escape flow path 71a is such that the function of the valve that blocks the flow of the fluid in the auxiliary flow path can be maintained as compared with the area (mm ² ) of the cross section of the auxiliary flow path. It is preferable to set a small value. For example, exposure is set as the ratio of the area of the cross section of the relief channel 71a (mm ^2), it occupies the area of the cross section of the auxiliary passage (mm ²⁾ is 5% or less, preferably 1% or less What is necessary is just to set.

If the area of the cross section of the escape passage 71a is too small, the effect of the heat removal of the seal member 63 by the above-described escape passage 71a is insufficient, and the seal member 63 may be damaged. Therefore, the area of the cross section of the relief channel 71a (mm ²⁾ as compared to the area of the cross section of the auxiliary passage (mm ^2), to set small enough to prevent damage of the seal member 63 in a fire Is preferred. For example, the area of the cross section of the relief channel 71a (mm ^2), a percentage of the area of the cross section of the auxiliary passage (mm ²⁾ may be set to be 0.1% or more.

  In the present invention, the “area of the cross section of the relief flow path” and the “area of the cross section of the auxiliary flow path” mean a cross-sectional area at a position where the flow rate per unit time of the flow path is determined. Usually, the position for determining the flow rate per unit time of the flow path is the position having the smallest cross-sectional area. The reason for defining the cross-sectional area of the flow path in this way is that the flow rate per unit time of the flow path increases as the cross-sectional area of the flow path increases. Therefore, the fact that the cross-sectional area of the escape flow path is smaller than the cross-sectional area of the auxiliary flow path is that the flow rate per unit time of the escape flow path is substantially smaller than the flow rate per unit time of the auxiliary flow path. Means that. In the case of the escape flow path 71a shown in FIG. 5, the “area of the cross section of the escape flow path” is the cross-sectional area of the through hole constituting the escape flow path 71a, and the “area of the cross section of the auxiliary flow path” is the valve seat 72. The cross-sectional area of the opening is.

  The escape flow path 71a is not limited to the structure including the through hole of the valve body 71 of the valve such as the bypass valve 70 as shown in FIG. In other words, various configurations can be adopted as long as the effect of removing heat from the seal member 63 is exerted by the escape passage 71a. For example, a configuration in which a protrusion is provided on a valve body 71 or a valve seat 72 of a valve such as the bypass valve 70 can be employed. In this configuration, even when the valve is in a closed state, a gap is formed between the valve element 71 and the valve seat 72 by the protrusion, and the gap functions as a relief flow path. Further, a relief flow path may be appropriately formed in the valve mounting portion 60.

  From the viewpoint of processing cost and durability, it is preferable that the escape passage 71a adopts a configuration including a through hole provided in the valve body of the valve as shown in FIG.

  Although the aircraft heat exchanger of the present embodiment has been described with reference to the configuration example of the surface type heat exchanger, the aircraft heat exchanger of the present embodiment is not limited to the surface type. That is, provided with an auxiliary flow path that branches from the main flow path, a valve that is disposed in the path of the auxiliary flow path, opens and closes the auxiliary flow path, and a seal member that seals between the members that form the auxiliary flow path The aircraft heat exchanger of the present embodiment can also be applied to a plate fin type heat exchanger, a shell and tube type heat exchanger, and other heat exchangers.

  In the present invention, the “main channel” means a channel through which a fluid to be heat exchanged flows. The main flow path is not limited to a flow path inside the main body of the heat exchanger, but includes a flow path outside the main body of the heat exchanger. As the main flow path outside the main body of the heat exchanger, for example, a flow path through which the fluid supplied to the inside of the heat exchanger circulates or a flow path through which the fluid discharged from the inside of the heat exchanger flows. In the case of a plate fin type heat exchanger, for example, a high-temperature fluid flow path inside and outside the main body and a low-temperature fluid flow path inside and outside the main body correspond to the main flow path.

  Further, the auxiliary flow path can be, for example, a bypass flow path. In this case, the bypass channel is not limited to the configuration in which a part of the main channel 11 inside the main body is omitted and the fluid is circulated as shown in FIGS. That is, the bypass channel may be configured such that the fluid does not flow through the entire main channel 11 inside the main body of the heat exchanger 10. When the latter configuration is employed, a bypass flow path and a bypass valve may be provided in the port mounting portion 50.

  The valve that can open and close the auxiliary flow path is not limited to the differential pressure open / close valve, and any valve that can block or open the flow of the fluid in the auxiliary flow path may be used. For example, a temperature detection type on-off valve may be employed. Further, the differential pressure release valve is not limited to the pressure detection type on / off valve of the type incorporating the coil spring as shown in FIG. 5 but may be another type of pressure detection type on / off valve.

  The aircraft heat exchanger of the present invention can reduce the temperature rise of the sealing member in the event of a fire, and can ensure fire resistance. For this reason, it can be effectively used in a heat exchanger used for cooling engine oil of an aircraft or cooling generator oil.

10: Aircraft heat exchanger, 10a: Curved surface inside heat exchanger,
10b: a curved surface outside the heat exchanger,
11: main flow path inside the main body, 11a: forward path, 11b: return path,
12: Inflow header, 13: Outflow header, 14: Supply port, 15: Discharge port,
16: Bypass inflow header, 17: Bypass outflow header,
20: 1st member, 20a: hollow part, 20b: partition part,
20c: concave groove of the inflow header, 20d: concave groove of the outflow header, 20e: radiating fin,
20f: concave groove of the header for bypass inflow, 20g: concave groove of the header for bypass inflow,
30: 2nd member, 30a, 30b: bulging part, 30c: concave groove of inflow header,
30d: Groove of the outflow header, 30e: Radiation fin,
30f: a groove in the header for bypass inflow, 30g: a groove in the header for bypass inflow,
30h, 30i: through hole,
40: Plate fin (corrugated fin), 50: Port mounting part,
60: Valve mounting portion, 60a: Bypass channel (auxiliary channel),
61: Valve body housing member, 62: Lid member, 63: Seal member,
70: Bypass valve, 71: Valve body, 71a: Escape passage (through hole), 72: Valve seat

Claims (4)

An aircraft heat exchanger comprising: an auxiliary flow path that branches from a main flow path; a valve that opens and closes the auxiliary flow path; and a seal member that seals between members that form the auxiliary flow path,
The aircraft heat exchanger is
A relief passage connecting the upstream side and the downstream side of the valve;
The aircraft heat exchanger, wherein an area of a cross section of the escape passage is smaller than an area of a cross section of the auxiliary passage. The aircraft heat exchanger according to claim 1,
The aircraft heat exchanger, wherein an area of a cross section of the escape passage is 0.1 to 5% of an area of a cross section of the auxiliary passage. The aircraft heat exchanger according to claim 1 or 2,
The escape passage is an aircraft heat exchanger comprising a through hole provided in a valve body of the valve. The heat exchanger for aircraft according to any one of claims 1 to 3,
The aircraft heat exchanger is a surface heat exchanger.

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