Gas turbine engine

Abstract

To reduce deterioration of cooling performance with respect to a fluid to be cooled responding to the change in an attitude of a gas turbine engine.SOLUTION: A gas turbine engine 100 includes: a casing 6 surrounding a rotation axis X; a first heat pipe 31 and a second heat pipe 32 including evaporation units 310, 320 encapsulating a working fluid and changing at least a part of the liquid-phase working fluid into gas, and condensation units 313, 323 changing the gas-phase working fluid into liquid; a first heat exchanger 41 into which a fluid to be cooled flows and which brings the fluid to be cooled into thermal contact with the evaporation unit 310 of the first heat pipe 31; and a second heat exchanger 42 into which the fluid to be cooled flows and which brings the fluid to be cooled into thermal contact with the evaporation unit 320 of the second heat pipe 32. The first heat pipe 31 and the second heat pipe 32 are provided on the casing 6, and are arranged at positions different in a circumferential direction around the rotation axis X.SELECTED DRAWING: Figure 2

Description

[Technical Field]

[0001] The technology disclosed herein relates to gas turbine engines. [Background technology]

[0002] Gas turbine engines have been known for some time and are used as power sources for aircraft, etc. For example, the gas turbine engine disclosed in Patent Document 1 includes a cooling device that cools oil supplied to components of the gas turbine engine. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] Japanese Patent Application Publication No. 2018-189091 Summary of the Invention [Problem to be solved by the invention]

[0004] In the gas turbine engine described above, the cooling device includes a heat exchanger. The heat exchanger brings an inflowing cooled fluid, such as oil, into thermal contact with a refrigerant to cool the cooled fluid. The refrigerant circulates through a refrigerant circuit that includes, for example, an evaporator and a condenser. The refrigerant changes from a liquid phase to a gas phase in the evaporator, and from a gas phase to a liquid phase in the condenser. In other words, the heat exchanger brings the cooled fluid into thermal contact with the evaporator, transferring heat from the cooled fluid to the refrigerant to cool the cooled fluid.

[0005] When a gas turbine engine is installed on an aircraft, the attitude of the aircraft changes during flight, which in turn changes the attitude of the gas turbine engine. Depending on the attitude of the gas turbine engine, gravity may make it difficult for the liquid refrigerant to flow into the evaporator. In this case, the cooled fluid is less likely to exchange heat with the refrigerant in the evaporator, resulting in a decrease in the cooling performance of the cooled fluid.

[0006] The technology disclosed herein has been made in consideration of these points, and its purpose is to reduce the deterioration of cooling performance for the cooled fluid in response to changes in the attitude of the gas turbine engine. [Means for solving the problem]

[0007] The gas turbine engine disclosed herein comprises a casing surrounding a rotating shaft, first and second heat pipes each including an evaporator that encloses a working fluid and converts at least a portion of the liquid-phase working fluid into gas, and a condenser that converts the gas-phase working fluid into liquid, a first heat exchanger into which a fluid to be cooled flows and brings the cooled fluid into thermal contact with the evaporator of the first heat pipe, and a second heat exchanger into which a fluid to be cooled flows and brings the cooled fluid into thermal contact with the evaporator of the second heat pipe, and the first and second heat pipes are provided in the casing and arranged at different positions circumferentially around the rotating shaft. [Effects of the Invention]

[0008] According to the gas turbine engine, the deterioration of the cooling performance for the fluid to be cooled can be reduced in response to changes in the attitude of the gas turbine engine. [Brief explanation of the drawings]

[0009] [Figure 1] FIG. 1 is a schematic cross-sectional view showing a gas turbine engine according to an embodiment. [Figure 2] FIG. 2 is a front view of the gas turbine engine. [Figure 3] FIG. 3 is a side view of the gas turbine engine. [Figure 4] FIG. 4 is a cross-sectional view taken along line IV-IV in FIG. [Figure 5] FIG. 5 is a schematic side view showing the state of the engine when the aircraft is in a normal vertical attitude. [Figure 6]FIG. 6 is a schematic side view showing the state of the engine when the aircraft is in an upside-down position. [Figure 7] FIG. 7 is a schematic side view showing the state of the engine when the aircraft is in a normal tilted attitude. [Figure 8] FIG. 8 is a schematic side view showing the state of the engine when the aircraft is inclined relative to the horizontal plane. [Figure 9] FIG. 9 is a side view of the gas turbine engine according to the first modification, as viewed from the side. [Figure 10] FIG. 10 is a front view of a gas turbine engine according to the second modification, as viewed from the front. [Figure 11] FIG. 11 is a cross-sectional view taken along line XI-XI in FIG. [Figure 12] FIG. 12 is a side view of a gas turbine engine according to the second modification, as viewed from the side. [Figure 13] FIG. 13 is a schematic diagram showing the flow path of the cooled fluid. DETAILED DESCRIPTION OF THE INVENTION

[0010] Exemplary embodiments will now be described in detail with reference to the drawings. FIG. 1 is a schematic cross-sectional view showing a gas turbine engine 100 according to an embodiment. Hereinafter, the gas turbine engine 100 will also be simply referred to as the engine 100. The engine 100 is a two-spool turbofan engine for an aircraft. However, the type and application of the engine 100 are not particularly limited.

[0011] In the following description, "forward" refers to the upstream side in the direction of airflow within the engine 100, and "rearward" refers to the downstream side in the direction of airflow within the engine 100. That is, "forward" refers to the side where the fan 2 is provided in the direction of the rotation axis X of the shaft 1 of the engine 100, and "rearward" refers to the side opposite the side where the fan 2 is provided in the direction of the rotation axis X of the shaft 1 of the engine 100. Specifically, the left side of the page in FIG. 1 is referred to as "forward," and the right side of the page in FIG. 1 is referred to as "rearward." "Forward" and "rearward" are expressions for convenience. "Radial direction" refers to a direction perpendicular to the rotation axis X of the shaft 1 of the engine 100. "Circumferential direction" refers to a direction around the rotation axis X of the shaft 1 of the engine 100. "Upward" simply refers to a relative upward side in the drawing unless otherwise specified as "upward in the direction of gravity," and "downward" simply refers to a relative downward side in the drawing unless otherwise specified as "downward in the direction of gravity." "Above" and "below" are terms of convenience.

[0012] The engine 100 includes a shaft 1 , a fan 2 , a compressor 3 , a combustor 4 , a turbine 5 , a casing 6 , an inner case 7 , a cooled fluid tank 8 , and a cooling device 9 .

[0013] The shaft 1 rotates around a rotation axis X. The shaft 1 extends in the front-to-rear direction of the engine 100. The fan 2, the compressor 3, the combustor 4, and the turbine 5 are arranged in this order from front to rear along the rotation axis X.

[0014] The shaft 1 has a first shaft 11 and a second shaft 12. The second shaft 12 is cylindrical with a hollow space. The first shaft 11 is inserted into the hollow space of the second shaft 12. Both ends of the first shaft 11 are rotatably supported by bearings 18. Both ends of the second shaft 12 are rotatably supported by bearings 18.

[0015] The fan 2 is connected to the front part of the first shaft 11 and rotates together with the first shaft 11. The fan 2 has a plurality of blades. As the fan 2 rotates, air is drawn into the engine 100.

[0016] The compressor 3 compresses the air supplied by the fan 2. The compressor 3 has a low-pressure compressor 13 and a high-pressure compressor 14 arranged rearward of the low-pressure compressor 13. The low-pressure compressor 13 is connected to a first shaft 11, and the high-pressure compressor 14 is connected to a second shaft 12. For example, the low-pressure compressor 13 is an axial compressor that takes in air from the front, compresses it, and sends it rearward, and the high-pressure compressor 14 is a centrifugal compressor that takes in air from the front, compresses it, and sends it radially outward. However, the types of the low-pressure compressor 13 and the high-pressure compressor 14 are not limited to this. Furthermore, the low-pressure compressor 13 may be omitted. The air compressed by the compressor 3 is supplied to the combustor 4 rearward of the compressor 3.

[0017] The combustor 4 combusts fuel by spraying it into the air compressed by the compressor 3. There are no particular restrictions on the fuel used in the engine 100, and there are no particular restrictions on the type of combustor 4. In the combustor 4, the fuel is combusted to generate high-temperature, high-pressure combustion gas, which is supplied to the turbine 5 located downstream of the combustor 4.

[0018] The turbine 5 is rotationally driven by the energy of the combustion gas generated in the combustor 4. The turbine 5 has a low-pressure turbine 15 and a high-pressure turbine 16 arranged in front of the low-pressure turbine 15. The low-pressure turbine 15 and the high-pressure turbine 16 may each be an axial-flow turbine in which the combustion gas flows in from the front and flows rearward, or may be a centrifugal turbine in which the combustion gas flows in from the front and flows radially outward.

[0019] The low-pressure turbine 15 is connected to the first shaft 11. That is, the low-pressure turbine 15 is connected to the fan 2 and the low-pressure compressor 13 via the first shaft 11. Therefore, when the low-pressure turbine 15 is rotationally driven by the combustion gas, the fan 2 and the low-pressure compressor 13 rotate accordingly.

[0020] The high-pressure turbine 16 is connected to the second shaft 12. In other words, the high-pressure turbine 16 is coupled to the high-pressure compressor 14 via the second shaft 12. Therefore, when the high-pressure turbine 16 is rotationally driven by the combustion gas, the high-pressure compressor 14 rotates accordingly.

[0021] The casing 6 surrounds the rotation axis X. Specifically, the casing 6 houses the fan 2, the compressor 3, the combustor 4, and the turbine 5. The casing 6 is cylindrical. More specifically, the casing 6 includes a cylindrical wall portion 60. The axis of the wall portion 60 coincides with the rotation axis X. The wall portion 60 has a small diameter portion 61, a large diameter portion 62 provided rearward of the small diameter portion 61, and a connecting portion 63 connecting the small diameter portion 61 and the large diameter portion 62. The small diameter portion 61 has a smaller diameter than the large diameter portion 62. The connecting portion 63 gradually expands in diameter toward the rear. The small diameter portion 61 is provided at a position corresponding to at least the fan 2 and the low-pressure compressor 13 in the front-rear direction. The large diameter portion 62 is provided at a position corresponding to at least the combustor 4 in the front-rear direction.

[0022] The inner case 7 is disposed inside the casing 6. The inner case 7 is a cylindrical case whose axis coincides with that of the casing 6. The inner case 7 houses the compressor 3, the combustor 4, and the turbine 5, excluding the fan 2. An annular bypass passage 17 is formed between the casing 6 and the inner case 7. Air drawn in by the fan 2 flows through the bypass passage 17 and is discharged rearward.

[0023] The cooled fluid tank 8 stores the cooled fluid. The cooled fluid is, for example, oil that lubricates the bearings 18, but it may also be oil that cools other components such as a generator. The cooled fluid may also be a fluid other than oil.

[0024] The cooled fluid is supplied from the cooled fluid tank 8 to the bearing 18 by a pump. For example, the cooled fluid is supplied to the bearing 18 in the form of a mist, and then sucked by the pump and collected in the cooled fluid tank 8. In this way, the cooled fluid is reused in a circulating manner. However, the cooled fluid does not have to be reused in a non-circulating manner.

[0025] The cooled fluid tank 8 is arranged on the outer peripheral surface of the casing 6. Specifically, the cooled fluid tank 8 is arranged on the outer peripheral surface of the small diameter portion 61 of the wall portion 60. The cooled fluid tank 8 is arranged radially inward from the outer peripheral surface of the large diameter portion 62 when viewed from the front. Note that a portion of the cooled fluid tank 8 may protrude radially outward from the outer peripheral surface of the large diameter portion 62 when viewed from the front. The cooled fluid tank 8 may also be arranged on the outer peripheral surface of the large diameter portion 62.

[0026] The cooling device 9 cools the cooled fluid. Specifically, the cooling device 9 cools the cooled fluid after it is delivered from the cooled fluid tank 8 and before it is supplied to the bearing 18. The cooling device 9 is provided in the casing 6. Specifically, the cooling device 9 is disposed on the outer circumferential surface of the casing 6, more specifically, on the outer circumferential surface of the small diameter portion 61 of the wall portion 60. The cooling device 9 is disposed radially inward of the outer circumferential surface of the large diameter portion 62 when viewed from the front. This allows the cooling device 9 to be disposed at a position that does not overlap with the combustor 4 in the radial direction, making it less susceptible to the heat of the combustor 4 and suppressing a reduction in the cooling effect of the cooling device 9. Furthermore, because the cooling device 9 is disposed at the small diameter portion 61, the frontal projection area of ​​the engine 100 can be reduced. Note that a portion of the cooling device 9 may protrude radially outward from the outer circumferential surface of the large diameter portion 62 when viewed from the front. Alternatively, the cooling device 9 may be disposed on the outer circumferential surface of the large diameter portion 62. Alternatively, the cooling device 9 may cool the cooled fluid at another location. For example, the cooling device 9 may cool the cooled fluid after it has been supplied to the bearings 18 and before it is collected in the cooled fluid tank 8 .

[0027] Fig. 2 is a front view of the gas turbine engine 100 as seen from the front. Fig. 3 is a side view of the gas turbine engine 100 as seen from the side. Components inside the casing 6 are omitted in Fig. 2. The cooling device 9 has a first heat pipe 31, a second heat pipe 32, a first heat exchanger 41, and a second heat exchanger 42.

[0028] The first heat pipe 31 and the second heat pipe 32 are arranged at different positions in the circumferential direction around the rotation axis X. Specifically, the first heat pipe 31 and the second heat pipe 32 face each other when viewed from the direction of the rotation axis X. More specifically, the first heat pipe 31 is located above the rotation axis X, and the second heat pipe 32 is located below the rotation axis X.

[0029] The first heat pipe 31 and the second heat pipe 32 are provided in the casing 6. Specifically, the first heat pipe 31 and the second heat pipe 32 are arranged on the outer peripheral surface of the casing 6. More specifically, the first heat pipe 31 and the second heat pipe 32 are arranged on the outer peripheral surface of the small diameter portion 61 of the wall portion 60 of the casing 6. The first heat pipe 31 and the second heat pipe 32 each have a flat shape that curves along the casing 6.

[0030] The first heat pipes 31 and the second heat pipes 32 are arranged in the circumferential direction such that the central angles about the rotation axis X are equally spaced.

[0031] Here, the first heat pipe 31 and the second heat pipe 32 are arranged so that the central angles around the rotation axis X are equally spaced apart means that when a plurality of reference lines are defined that extend radially from the rotation axis X so that the central angles around the rotation axis X are equally spaced apart and the same number as the number of heat pipes 31, 32, each heat pipe 31, 32 intersects with each reference line corresponding to each heat pipe 31, 32.

[0032] Specifically, when the first reference line K1 and the second reference line K2 are defined so that the central angle is 180°, the first heat pipe 31 intersects with the first reference line K1, and the second heat pipe 32 intersects with the second reference line K2. For example, the first reference line K1 passes through the circumferential center of the first heat pipe 31, and the second reference line K2 passes through the circumferential center of the second heat pipe 32.

[0033] When viewed from the direction of the rotation axis X, at the circumferentially opposing ends of the first heat pipe 31 and the second heat pipe 32, the angle formed by the line connecting the circumferential end of the first heat pipe 31 to the rotation axis X and the line connecting the circumferential end of the second heat pipe 32 to the rotation axis X is approximately 30°.

[0034] The first heat exchanger 41 is connected to the first heat pipe 31. The second heat exchanger 42 is connected to the second heat pipe 32. The first heat exchanger 41 and the second heat exchanger 42 are arranged side by side along the rotation axis X. The first heat exchanger 41 is arranged forward of the second heat exchanger 42. Note that the first heat exchanger 41 may also be arranged rearward of the second heat exchanger 42.

[0035] The first heat exchanger 41 and the second heat exchanger 42 are disposed on the outer peripheral surface of the casing 6. Specifically, the first heat exchanger 41 and the second heat exchanger 42 are disposed on the outer peripheral surface of the small diameter portion 61 of the wall portion 60 of the casing 6.

[0036] The first heat exchanger 41 and the second heat exchanger 42 are each located between the first heat pipe 31 and the second heat pipe 32 in the circumferential direction. Specifically, the engine 100 has two sets of first heat exchangers 41 and second heat exchangers 42. The first heat exchanger 41 and the second heat exchanger 42 of one of the two sets are located between the first heat pipe 31 and the second heat pipe 32 in the circumferential direction on the right side with respect to the rotation axis X when viewed from the front. The first heat exchanger 41 and the second heat exchanger 42 of the other of the two sets are located between the first heat pipe 31 and the second heat pipe 32 in the circumferential direction on the left side with respect to the rotation axis X when viewed from the front.

[0037] When the engine 100 is placed so that the first heat pipe 31 is located higher in the direction of gravity than the second heat pipe 32, the first heat exchanger 41 and the second heat exchanger 42 are each located lower than the first heat pipe 31 and higher than the second heat pipe 32. Here, "the first heat exchanger 41 is located lower than the first heat pipe 31 and higher than the second heat pipe 32" does not necessarily mean that the entire first heat exchanger 41 is located lower than the first heat pipe 31 and higher than the second heat pipe 32, but rather that at least a portion of the first heat exchanger 41 is located lower than the first heat pipe 31 and higher than the second heat pipe 32. The same applies to the second heat exchanger 42.

[0038] Fig. 4 is a cross-sectional view taken along line IV-IV in Fig. 2. As shown in Figs. 2, 3, and 4, the first heat pipe 31 includes an evaporator 310 that encloses a working fluid and converts at least a portion of the liquid-phase working fluid L into gas, and a condenser 313 that converts the gas-phase working fluid into liquid. The first heat pipe 31 circulates the working fluid between the evaporator 310 and the condenser 313. In Fig. 4, the liquid-phase working fluid L is indicated by dots. The working fluid is, for example, pure water, but may be another fluid.

[0039] The evaporation section 310 includes a first evaporation section 311 and a second evaporation section 312 arranged side by side along the rotation axis X. The first evaporation section 311 is arranged forward of the second evaporation section 312. When there is no need to distinguish between the first evaporation section 311 and the second evaporation section 312, they will be simply referred to as the "evaporation section 310."

[0040] Specifically, the first heat pipe 31 has a main body portion 315, and a first cylindrical portion 316 and a second cylindrical portion 317 connected to the main body portion 315. The main body portion 315 includes a condenser portion 313. The first cylindrical portion 316 includes a first evaporation portion 311. The second cylindrical portion 317 includes a second evaporation portion 312.

[0041] The main body 315 is disposed on the outer peripheral surface of the casing 6. The main body 315 is located above the rotation axis X. The main body 315 has a flat shape that curves along the outer peripheral surface of the casing 6. The main body 315 is a hollow member having a cavity inside.

[0042] The first cylindrical portion 316 and the second cylindrical portion 317 are arranged on the outer peripheral surface of the casing 6. The first cylindrical portion 316 and the second cylindrical portion 317 are curved along the outer peripheral surface of the casing 6. The first cylindrical portion 316 is arranged forward of the second cylindrical portion 317.

[0043] The first cylindrical portion 316 and the second cylindrical portion 317 each extend in the circumferential direction from the main body portion 315 toward the second heat pipe 32. Specifically, the engine 100 has two sets of the first cylindrical portion 316 and the second cylindrical portion 317. The first cylindrical portion 316 and the second cylindrical portion 317 of one of the two sets extend from the right end of the main body portion 315 toward the second heat pipe 32 when viewed from the front. The first cylindrical portion 316 and the second cylindrical portion 317 of the other of the two sets extend from the left end of the main body portion 315 toward the second heat pipe 32 when viewed from the front.

[0044] The first cylindrical portion 316 and the second cylindrical portion 317 are hollow members having cavities therein. The interior of the first cylindrical portion 316 is in communication with the interior of the main body portion 315. The interior of the second cylindrical portion 317 is in communication with the interior of the main body portion 315. A working fluid is contained inside the interior of the main body portion 315, the interior of the first cylindrical portion 316, and the interior of the second cylindrical portion 317.

[0045] The second heat pipe 32 includes an evaporator 320 that encloses a working fluid and converts at least a portion of the liquid-phase working fluid L into gas, and a condenser 323 that converts the gas-phase working fluid into liquid. The second heat pipe 32 circulates the working fluid between the evaporator 320 and the condenser 323. The evaporator 320 includes a first evaporator 321 and a second evaporator 322 that are arranged side by side along the rotation axis X. The first evaporator 321 is arranged forward of the second evaporator 322. When the first evaporator 321 and the second evaporator 322 are not distinguished from each other, they will be simply referred to as the "evaporator 320."

[0046] Specifically, the second heat pipe 32 has a main body portion 325, and a first cylindrical portion 326 and a second cylindrical portion 327 connected to the main body portion 325. The main body portion 325 includes a condenser portion 323. The first cylindrical portion 326 includes a first evaporation portion 321. The second cylindrical portion 327 includes a second evaporation portion 322.

[0047] The main body 325 is disposed on the outer circumferential surface of the casing 6. The second heat pipe 32 is positioned below the rotation axis X of the main body 325. The main body 325 has a flat shape that curves along the outer circumferential surface of the casing 6. The main body 325 is a hollow member having a cavity therein.

[0048] The first cylindrical portion 326 and the second cylindrical portion 327 are arranged on the outer peripheral surface of the casing 6. The first cylindrical portion 326 and the second cylindrical portion 327 are curved along the outer peripheral surface of the casing 6. The first cylindrical portion 326 is arranged forward of the second cylindrical portion 327.

[0049] The first cylindrical portion 326 and the second cylindrical portion 327 each extend in the circumferential direction from the main body portion 325 toward the second heat pipe 32. Specifically, the engine 100 has two sets of the first cylindrical portion 326 and the second cylindrical portion 327. The first cylindrical portion 326 and the second cylindrical portion 327 of one of the two sets extend from the right end of the main body portion 325 toward the first heat pipe 31 when viewed from the front. The first cylindrical portion 326 and the second cylindrical portion 327 of the other of the two sets extend from the left end of the main body portion 325 toward the first heat pipe 31 when viewed from the front.

[0050] The first cylindrical portion 326 and the second cylindrical portion 327 are hollow members having cavities therein. The interior of the first cylindrical portion 326 is in communication with the interior of the main body portion 325. The interior of the second cylindrical portion 327 is in communication with the interior of the main body portion 325. A working fluid is contained inside the interior of the main body portion 325, the interior of the first cylindrical portion 326, and the interior of the second cylindrical portion 327.

[0051] The evaporation section 310 of the first heat pipe 31 and the evaporation section 320 of the second heat pipe 32 are each located between the condensation section 313 of the first heat pipe 31 and the condensation section 323 of the second heat pipe 32 in the circumferential direction. Specifically, the first cylindrical section 316 and the second cylindrical section 317 of the first heat pipe 31 and the first cylindrical section 326 and the second cylindrical section 327 of the second heat pipe 32 are each located between the main body section 315 of the first heat pipe 31 and the main body section 315 of the second heat pipe 32 in the circumferential direction.

[0052] When the engine 100 is placed so that the first heat pipe 31 is located higher in the direction of gravity than the second heat pipe 32, the evaporation section 310 of the first heat pipe 31 and the evaporation section 320 of the second heat pipe 32 are each located lower than the condensation section 313 of the first heat pipe 31 and higher than the condensation section 323 of the second heat pipe 32. Specifically, the first cylindrical section 316 and the second cylindrical section 317 of the first heat pipe 31 and the first cylindrical section 326 and the second cylindrical section 327 of the second heat pipe 32 are each located lower than the main body section 315 of the first heat pipe 31 and higher than the main body section 325 of the second heat pipe 32.

[0053] The first heat exchanger 41 receives the fluid to be cooled and brings the fluid into thermal contact with the evaporator section 310 of the first heat pipe 31. As a result, the first heat exchanger 41 transfers heat from the fluid to the working fluid in the evaporator section 310, thereby cooling the fluid to be cooled.

[0054] The second heat exchanger 42 receives the fluid to be cooled and brings the fluid into thermal contact with the evaporator section 320 of the second heat pipe 32. As a result, the second heat exchanger 42 transfers heat from the fluid to the working fluid in the evaporator section 320, thereby cooling the fluid to be cooled.

[0055] Specifically, the first heat exchanger 41 and the second heat exchanger 42 have a cooled fluid flow path 50 through which the cooled fluid passes. The cooled fluid flow path 50 is a U-shaped flow path that is continuously formed inside the first heat exchanger 41 and the second heat exchanger 42. The cooled fluid flow path 50 is connected to the cooled fluid supply line 51. The cooled fluid supply line 51 is a flow path that supplies the cooled fluid from the cooled fluid tank 8 to components such as the bearing 18. The cooled fluid flow path 50 may be provided separately for each of the first heat exchanger 41 and the second heat exchanger 42. The cooled fluid flow path 50 may be a linear flow path or a bellows-shaped (zigzag) flow path, and the shape of the cooled fluid flow path 50 is not limited. Furthermore, the connection position of the cooled fluid flow path 50 may be elsewhere. For example, the cooled fluid flow path 50 may be connected midway along a cooled fluid return line, which is a flow path from a component such as the bearing 18 to the cooled fluid tank 8 for collection of the cooled fluid.

[0056] The first heat exchanger 41 is thermally connected to the first cylindrical portion 316 and the second cylindrical portion 317 of the first heat pipe 31. Specifically, the first cylindrical portion 316 and the second cylindrical portion 317 are inserted into the cooled fluid flow path 50, and the first cylindrical portion 316 and the second cylindrical portion 317 come into contact with the cooled fluid flowing through the cooled fluid flow path 50. In other words, the first heat exchanger 41 has a shell-and-tube structure. This allows the cooled fluid flowing through the cooled fluid flow path 50 to exchange heat with the working fluid inside the first cylindrical portion 316 and the second cylindrical portion 317.

[0057] The second heat exchanger 42 is thermally connected to the first cylindrical portion 326 and the second cylindrical portion 327 of the second heat pipe 32. Specifically, the first cylindrical portion 326 and the second cylindrical portion 327 are inserted into the cooled fluid flow path 50, and the first cylindrical portion 326 and the second cylindrical portion 327 come into contact with the cooled fluid flowing through the cooled fluid flow path 50. In other words, the second heat exchanger 42 has a shell-and-tube structure. This allows the cooled fluid flowing through the cooled fluid flow path 50 to exchange heat with the working fluid inside the first cylindrical portion 326 and the second cylindrical portion 327.

[0058] Next, heat exchange between the working fluid in the first heat pipe 31 and the fluid to be cooled in the first heat exchanger 41 will be described.

[0059] 4, when the engine 100 is placed so that the first heat pipe 31 is upward in the direction of gravity, the first cylindrical portion 316 and the second cylindrical portion 317 are located in the lower portion of the first heat pipe 31 in the direction of gravity, and therefore the liquid-phase working fluid L is located inside the first cylindrical portion 316 and the second cylindrical portion 317 due to gravity. At this time, when the fluid to be cooled passes through the cooled fluid flow path 50 of the first heat exchanger 41 in the direction shown by the arrow, the liquid-phase working fluid L absorbs heat from the cooled fluid and cools it.

[0060] Meanwhile, the liquid-phase working fluid L absorbs heat from the fluid to be cooled and changes into a gas. The gas-phase working fluid moves from the first cylindrical portion 316 and the second cylindrical portion 317 to the main body portion 315. Because the main body portion 315 is thermally exposed to the outside air, the temperature of the main body portion 315 is lower than the temperatures of the first cylindrical portion 316 and the second cylindrical portion 317. As a result, the gas-phase working fluid absorbs heat in the main body portion 315 and changes into a liquid. The liquid-phase working fluid L returns to the inside of the first cylindrical portion 316 and the inside of the second cylindrical portion 317 due to gravity. In this way, the working fluid circulates between the first cylindrical portion 316, the second cylindrical portion 317, and the main body portion 315, thereby cooling the fluid to be cooled.

[0061] Furthermore, when the engine 100 is placed so that the second heat pipe 32 is upward in the direction of gravity, the same applies to heat exchange between the working fluid in the second heat pipe 32 and the fluid to be cooled in the second heat exchanger 42.

[0062] Next, the state of engine 100 when an aircraft in flight changes its attitude in the circumferential direction around its direction of travel will be described. When the aircraft changes its attitude, the attitude of engine 100 changes along with the aircraft's attitude. Fig. 5 is a schematic side view showing the state of engine 100 when the aircraft's vertical attitude is normal. Fig. 6 is a schematic side view showing the state of engine 100 when the aircraft's vertical attitude is upside down. In Figs. 5 and 6, the cooled fluid flow path 50 is simply indicated by an arrow. In Figs. 5 and 6, the first heat exchanger 41 and the second heat exchanger 42 are indicated by two-dot chain lines.

[0063] As shown in FIG. 5 , when the aircraft has a normal vertical attitude, the engine 100 also has a normal vertical attitude. In the normal attitude of the engine 100, the first heat pipe 31 is located above the direction of gravity, and the second heat pipe 32 is located below the direction of gravity. Under the influence of gravity, the liquid-phase working fluid L in the first heat pipe 31 is located in the first cylindrical portion 316 and the second cylindrical portion 317 of the first heat pipe 31, i.e., in the evaporator portion 310 of the first heat pipe 31. Meanwhile, the liquid-phase working fluid L in the second heat pipe 32 is located in the main body portion 325 of the second heat pipe 32, i.e., in the condenser portion 323 of the second heat pipe 32, under the influence of gravity. This allows the fluid to exchange heat with the working fluid in the evaporator portion 310 of the first heat pipe 31 in the first heat exchanger 41, thereby cooling the fluid to be cooled.

[0064] As shown in FIG. 6 , when the aircraft is in an upside-down position, the engine 100 is also in an upside-down position. When the engine 100 is in an upside-down position, the first heat pipe 31 is positioned downward in the direction of gravity, and the second heat pipe 32 is positioned upward in the direction of gravity. In other words, the aircraft is in an upside-down flight position, and the engine 100 is rotating 180° around the rotation axis X. At this time, the liquid-phase working fluid L in the second heat pipe 32 is affected by gravity and is located in the first cylindrical portion 326 and the second cylindrical portion 327 of the second heat pipe 32, i.e., in the evaporation section 320 of the second heat pipe 32. Meanwhile, the liquid-phase working fluid L in the first heat pipe 31 is affected by gravity and is located in the main body 315 of the first heat pipe 31, i.e., in the condensation section 313 of the first heat pipe 31. This allows the fluid to be cooled to exchange heat with the working fluid in the evaporator section 320 of the second heat pipe 32 in the second heat exchanger 42, thereby cooling the fluid to be cooled.

[0065] In this way, even if the attitude of the engine 100 changes in the circumferential direction around the rotation axis X, the fluid to be cooled can be cooled.

[0066] Even if the attitude of the engine 100 changes by a rotation angle of less than 180° in the circumferential direction around the rotation axis X, the liquid-phase working fluid L is located in at least one of the evaporator section 310 of the first heat pipe 31 and the evaporator section 320 of the second heat pipe 32. This allows the fluid to exchange heat with the working fluid in at least one of the evaporator section 310 and the evaporator section 320, thereby cooling the fluid to be cooled.

[0067] Next, the state of the engine 100 when an aircraft changes its tilt attitude relative to the horizontal plane during flight will be described. When the aircraft changes its attitude, the attitude of the engine 100 changes along with the aircraft's attitude. FIG. 7 is a schematic side view showing the state of the engine 100 when the aircraft's tilt attitude is a normal attitude, not tilted relative to the horizontal plane. FIG. 8 is a schematic side view showing the state of the engine 100 when the aircraft's tilt attitude is tilted relative to the horizontal plane. In FIGS. 7 and 8, the second heat pipe 32 and the second heat exchanger 42 are omitted. In FIGS. 7 and 8, the cooled fluid flow path 50 is simply indicated by an arrow. In FIGS. 7 and 8, the first heat exchanger 41 is indicated by a two-dot chain line.

[0068] As shown in Figure 7, when the aircraft is in a normal tilted position, the engine 100 is also in a normal tilted position. In other words, because the aircraft is not tilted relative to the horizontal plane, the rotation axis X of the engine 100 is not tilted relative to the horizontal plane. At this time, the liquid-phase working fluid L in the first heat pipe 31 is affected by gravity and is located in the first cylindrical portion 316 and the second cylindrical portion 317, i.e., the first evaporator portion 311 and the second evaporator portion 312. This allows the cooled fluid to exchange heat with the working fluid in the first evaporator portion 311 and the second evaporator portion 312 in the first heat exchanger 41, thereby cooling the cooled fluid.

[0069] As shown in Figure 8, when the aircraft tilts with respect to the horizontal plane, the rotation axis X of the engine 100 also tilts with respect to the horizontal plane. Specifically, because the aircraft is tilted so that the front of the aircraft is located upward in the direction of gravity, the engine 100 is tilted so that the front of the engine 100 is located upward in the direction of gravity. At this time, the liquid-phase working fluid L in the first heat pipe 31 is affected by gravity and is located mainly in the second cylindrical portion 317, which is located rearward of the first cylindrical portion 316, i.e., the second evaporator 312. This allows the cooled fluid to exchange heat with the working fluid in the second evaporator 312 mainly in the first heat exchanger 41, thereby cooling the cooled fluid.

[0070] In this way, even if the tilt angle of the rotation axis X of the engine 100 with respect to the horizontal plane changes, the liquid-phase working fluid L is located at least in the second cylindrical portion 317, and therefore the fluid to be cooled can be cooled.

[0071] When the aircraft tilts so that the front of the aircraft is positioned downward in the direction of gravity, the engine 100 also tilts so that the front of the engine 100 is positioned downward in the direction of gravity. At this time, the liquid-phase working fluid L in the first heat pipe 31 is affected by gravity and is mainly located in the first cylindrical portion 316, which is disposed forward of the second cylindrical portion 317, i.e., the first evaporator 311. This allows the cooled fluid to exchange heat mainly with the working fluid in the first evaporator 311 in the first heat exchanger 41, thereby cooling the cooled fluid.

[0072] Furthermore, even if the tilt angle of the rotation axis X of the engine 100 relative to the horizontal plane changes when the aircraft is in an upside-down position, the fluid to be cooled can be cooled by at least one of the first evaporator 321 and the second evaporator 322 of the second heat pipe 32, depending on the tilt angle of the rotation axis X (hereinafter also referred to as the tilt attitude of the engine 100). This makes it possible to reduce the deterioration of the cooling performance for the fluid to be cooled in response to changes in the tilt attitude of the engine 100.

[0073] According to the engine 100 described above, the first heat pipe 31 and the second heat pipe 32 are arranged at different positions in the circumferential direction around the rotation axis X. Therefore, when the engine 100 is mounted on an aircraft, even if the attitude of the engine 100 changes in the circumferential direction in accordance with a change in the attitude of the aircraft, the fluid to be cooled can be cooled by both or either one of the first heat pipe 31 and the second heat pipe 32 depending on the circumferential attitude of the engine 100. This makes it possible to reduce a decrease in the cooling performance for the fluid to be cooled in response to a change in the circumferential attitude of the engine 100.

[0074] More specifically, when engine 100 is mounted on an aircraft, the attitude of the aircraft changes during flight, and therefore the attitude of engine 100 also changes. For example, when the attitude of engine 100 changes in the circumferential direction about rotation axis X, the liquid-phase working fluid L in the heat pipe is affected by gravity, causing the position of liquid-phase working fluid L within the heat pipe to change. For this reason, when there is one heat pipe, depending on the circumferential attitude of engine 100, the liquid-phase working fluid L may not be located in the evaporation section. In this case, even if the cooled fluid comes into contact with the evaporation section, the cooled fluid cannot exchange heat with the working fluid, and the cooled fluid cannot be cooled.

[0075] In contrast, in the present disclosure, the first heat pipe 31 and the second heat pipe 32 are arranged at different positions in the circumferential direction, and therefore, depending on the circumferential attitude of the engine 100, even if the liquid-phase working fluid L is not located in the evaporation section of one of the first heat pipe 31 and the second heat pipe 32, the liquid-phase working fluid L may be located in the evaporation section of the other of the first heat pipe 31 and the second heat pipe 32. In this case, even if the cooled fluid cannot exchange heat with the working fluid in the evaporation section of one of the first heat pipe 31 and the second heat pipe 32, it can exchange heat with the working fluid in the evaporation section of the other of the first heat pipe 31 and the second heat pipe 32, and the cooled fluid can be cooled.

[0076] Furthermore, because the first heat pipe 31 and the second heat pipe 32 are used to cool the fluid to be cooled, the first heat pipe 31 and the second heat pipe 32 are small, allowing the engine 100 to be made smaller. Specifically, the protrusion of the first heat pipe 31 and the second heat pipe 32 radially outward from the casing 6 is reduced, thereby reducing the frontal projection area of ​​the engine 100. This allows the air resistance of the engine 100 to be reduced when the engine 100 is installed on an aircraft.

[0077] Furthermore, since the first heat pipe 31 and the second heat pipe 32 are arranged on the outer peripheral surface of the casing 6, the first heat pipe 31 and the second heat pipe 32 do not interfere with the intake of the engine 100. This ensures the amount of intake air for the engine 100.

[0078] Furthermore, since the first heat pipe 31 and the second heat pipe 32 each have a flattened shape that curves along the casing 6, the protrusion of the first heat pipe 31 and the second heat pipe 32 radially outward from the casing 6 is reduced, and the engine 100 can be made smaller.

[0079] Furthermore, the first heat pipes 31 and the second heat pipes 32 are arranged in the circumferential direction so that the central angles around the rotation axis X are equally spaced, so that even if the attitude of the engine 100 changes in the circumferential direction, the fluid to be cooled can be cooled by at least one of the first heat pipes 31 and the second heat pipes 32. This makes it possible to reduce the deterioration of the cooling performance for the fluid to be cooled in response to changes in the attitude of the engine 100 in the circumferential direction.

[0080] Specifically, depending on the circumferential orientation of the engine 100, even if the liquid-phase working fluid L is not located in the evaporation section of one of the first heat pipe 31 and the second heat pipe 32, the liquid-phase working fluid L may be located in the evaporation section of the other of the first heat pipe 31 and the second heat pipe 32. In this case, even if the fluid to be cooled cannot exchange heat with the working fluid in the evaporation section of one heat pipe, it can exchange heat with the working fluid in the evaporation section of the other heat pipe, and the fluid to be cooled can be cooled.

[0081] Furthermore, since the first heat exchanger 41 and the second heat exchanger 42 are respectively located between the first heat pipe 31 and the second heat pipe 32 in the circumferential direction, even if the attitude of the engine 100 changes in the circumferential direction, the fluid to be cooled can be cooled by both or either of the first heat exchanger 41 and the second heat exchanger 42, depending on the circumferential attitude of the engine 100. This makes it possible to reduce a decrease in the cooling performance for the fluid to be cooled in response to changes in the circumferential attitude of the engine 100.

[0082] Specifically, depending on the circumferential orientation of the engine 100, even if the liquid-phase working fluid L in the first heat pipe 31 is not positioned toward the first heat exchanger 41 due to the influence of gravity, the liquid-phase working fluid L in the second heat pipe 32 may be positioned toward the second heat exchanger 42 due to the influence of gravity. In this case, even if the cooled fluid cannot exchange heat with the working fluid in the first heat exchanger 41, it can exchange heat with the working fluid in the second heat exchanger 42, thereby cooling the cooled fluid. Alternatively, depending on the circumferential orientation of the engine 100, even if the liquid-phase working fluid L in the second heat pipe 32 is not positioned toward the second heat exchanger 42 due to the influence of gravity, the liquid-phase working fluid L in the first heat pipe 31 may be positioned toward the first heat exchanger 41 due to the influence of gravity. In this case, even if the cooled fluid cannot exchange heat with the working fluid in the second heat exchanger 42, it can exchange heat with the working fluid in the first heat exchanger 41, thereby cooling the cooled fluid.

[0083] Furthermore, the evaporator section 310 of the first heat pipe 31 and the evaporator section 320 of the second heat pipe 32 are each located between the condenser section 313 of the first heat pipe 31 and the condenser section 323 of the second heat pipe 32 in the circumferential direction, so even if the attitude of the engine 100 changes in the circumferential direction, the cooled fluid can be cooled by both or either one of the evaporator section 310 of the first heat pipe 31 and the evaporator section 320 of the second heat pipe 32, depending on the circumferential attitude of the engine 100. This makes it possible to reduce a decrease in cooling performance for the cooled fluid in response to changes in the circumferential attitude of the engine 100.

[0084] Specifically, depending on the circumferential orientation of the engine 100, even if the liquid-phase working fluid L in the first heat pipe 31 is not located in the evaporator 310 of the first heat pipe 31 due to the influence of gravity, the liquid-phase working fluid L in the second heat pipe 32 may be located in the evaporator 320 of the second heat pipe 32 due to the influence of gravity. In this case, even if the fluid to be cooled cannot exchange heat with the working fluid in the evaporator 310 of the first heat pipe 31, the fluid to be cooled can exchange heat with the working fluid in the evaporator 320 of the second heat pipe 32, thereby cooling the fluid to be cooled. Alternatively, depending on the circumferential orientation of the engine 100, even if the liquid-phase working fluid L in the second heat pipe 32 is not located in the evaporator 320 of the second heat pipe 32 due to the influence of gravity, the liquid-phase working fluid L in the first heat pipe 31 may be located in the evaporator 310 of the first heat pipe 31 due to the influence of gravity. At this time, even if the cooled fluid cannot exchange heat with the working fluid in the evaporation section 320 of the second heat pipe 32, it can exchange heat with the working fluid in the evaporation section 310 of the first heat pipe 31, thereby cooling the cooled fluid.

[0085] Furthermore, when the engine 100 is placed so that the first heat pipe 31 is located higher in the direction of gravity than the second heat pipe 32, the first heat exchanger 41 and the second heat exchanger 42 are located lower than the first heat pipe 31 and higher than the second heat pipe 32, so even if the attitude of the engine 100 changes in the circumferential direction, the fluid to be cooled can be cooled by both or either the first heat exchanger 41 or the second heat exchanger 42, depending on the circumferential attitude of the engine 100. This makes it possible to reduce a decrease in the cooling performance for the fluid to be cooled in response to changes in the circumferential attitude of the engine 100.

[0086] Specifically, depending on the circumferential orientation of the engine 100, even if the liquid-phase working fluid L in the first heat pipe 31 is not positioned toward the first heat exchanger 41 due to the influence of gravity, the liquid-phase working fluid L in the second heat pipe 32 may be positioned toward the second heat exchanger 42 due to the influence of gravity. In this case, even if the cooled fluid cannot exchange heat with the working fluid in the first heat exchanger 41, it can exchange heat with the working fluid in the second heat exchanger 42, thereby cooling the cooled fluid. Alternatively, depending on the circumferential orientation of the engine 100, even if the liquid-phase working fluid L in the second heat pipe 32 is not positioned toward the second heat exchanger 42 due to the influence of gravity, the liquid-phase working fluid L in the first heat pipe 31 may be positioned toward the first heat exchanger 41 due to the influence of gravity. In this case, even if the cooled fluid cannot exchange heat with the working fluid in the second heat exchanger 42, it can exchange heat with the working fluid in the first heat exchanger 41, thereby cooling the cooled fluid.

[0087] Furthermore, when the engine 100 is placed so that the first heat pipe 31 is located higher in the direction of gravity than the second heat pipe 32, the evaporator section 310 of the first heat pipe 31 and the evaporator section 320 of the second heat pipe 32 are located lower than the condenser section 313 of the first heat pipe 31 and higher than the condenser section 323 of the second heat pipe 32, respectively. Therefore, even if the attitude of the engine 100 changes in the circumferential direction, the cooled fluid can be cooled by both or either the evaporator section 310 of the first heat pipe 31 and the evaporator section 320 of the second heat pipe 32, depending on the circumferential attitude of the engine 100. This makes it possible to reduce a decrease in the cooling performance for the cooled fluid in response to changes in the circumferential attitude of the engine 100.

[0088] Specifically, depending on the circumferential orientation of the engine 100, even if the liquid-phase working fluid L in the first heat pipe 31 is not located in the evaporator 310 of the first heat pipe 31 due to the influence of gravity, the liquid-phase working fluid L in the second heat pipe 32 may be located in the evaporator 320 of the second heat pipe 32 due to the influence of gravity. In this case, even if the fluid to be cooled cannot exchange heat with the working fluid in the evaporator 310 of the first heat pipe 31, the fluid to be cooled can exchange heat with the working fluid in the evaporator 320 of the second heat pipe 32, thereby cooling the fluid to be cooled. Alternatively, depending on the circumferential orientation of the engine 100, even if the liquid-phase working fluid L in the second heat pipe 32 is not located in the evaporator 320 of the second heat pipe 32 due to the influence of gravity, the liquid-phase working fluid L in the first heat pipe 31 may be located in the evaporator 310 of the first heat pipe 31 due to the influence of gravity. At this time, even if the cooled fluid cannot exchange heat with the working fluid in the evaporation section 320 of the second heat pipe 32, it can exchange heat with the working fluid in the evaporation section 310 of the first heat pipe 31, thereby cooling the cooled fluid.

[0089] Furthermore, the evaporation section 310 of the first heat pipe 31 and the evaporation section 320 of the second heat pipe 32 each include the first evaporation sections 311, 321 and the second evaporation sections 312, 322 arranged side by side along the rotation axis X. Therefore, even if the tilt angle of the rotation axis X of the engine 100 with respect to the horizontal plane changes in accordance with a change in the attitude of the aircraft, the cooled fluid can be cooled by either or both of the first evaporation section 311 and the second evaporation section 31, or either or both of the first evaporation section 321 and the second evaporation section 322, depending on the tilt angle of the rotation axis X (the tilt attitude of the engine 100). This makes it possible to reduce a decrease in the cooling performance for the cooled fluid in response to a change in the tilt attitude of the engine 100.

[0090] More specifically, when engine 100 is in a normal position, depending on the tilted position of engine 100, even if liquid-phase working fluid L is not located in one of first evaporator 311 and second evaporator 312, liquid-phase working fluid L may be located in the other of first evaporator 311 and second evaporator 312. In this case, even if the cooled fluid cannot exchange heat with the working fluid in one of first evaporator 311 and second evaporator 312, it can exchange heat with the working fluid in the other of first evaporator 311 and second evaporator 312, and the cooled fluid can be cooled.

[0091] Furthermore, when engine 100 is in an upside-down position, depending on the tilted position of engine 100, even if liquid-phase working fluid L is not located in one of first evaporator 321 and second evaporator 322, liquid-phase working fluid L may be located in the other of first evaporator 321 and second evaporator 322. In this case, even if the cooled fluid cannot exchange heat with the working fluid in one of first evaporator 321 and second evaporator 322, it can exchange heat with the working fluid in the other of first evaporator 321 and second evaporator 322, and the cooled fluid can be cooled.

[0092] Variation 1 Fig. 9 is a side view of a gas turbine engine 100A according to Modification 1. In Fig. 9, cooled fluid flow path 50 is simply indicated by an arrow.

[0093] The gas turbine engine 100A according to the first modification differs from the gas turbine engine 100 according to the embodiment in the positions of the first heat exchanger 41 and the second heat exchanger 42. The following description will focus on the configuration of the gas turbine engine 100A according to the first modification that differs from the gas turbine engine 100 according to the embodiment. Note that in the gas turbine engine 100A according to the first modification, the same reference numerals as those in the gas turbine engine 100 according to the embodiment indicate the same configuration as in the gas turbine engine 100 according to the embodiment, and therefore description thereof will be omitted.

[0094] In the gas turbine engine 100A according to the first modification, the first heat exchanger 41 and the second heat exchanger 42 are arranged side by side in the circumferential direction. The first heat exchanger 41 is arranged closer to the first heat pipe 31 than the second heat exchanger 42, and the second heat exchanger 42 is arranged closer to the second heat pipe 32 than the first heat exchanger 41.

[0095] The first heat exchanger 41 and the second heat exchanger 42 extend in the direction of the rotation axis X. The first heat exchanger 41 has an outgoing path of the cooled fluid flow path 50, and the second heat exchanger 42 has a return path of the cooled fluid flow path 50.

[0096] The first cylindrical portion 316 and the second cylindrical portion 317 of the first heat pipe 31 are connected to the first heat exchanger 41. The first cylindrical portion 316 is connected to the front part of the first heat exchanger 41, and the second cylindrical portion 317 is connected to the rear part of the first heat exchanger 41. The first cylindrical portion 316 and the second cylindrical portion 317 are in thermal contact with the cooled fluid flowing in the outward path of the cooled fluid flow path 50.

[0097] The first cylindrical portion 326 and the second cylindrical portion 327 of the second heat pipe 32 are connected to the second heat exchanger 42. The first cylindrical portion 326 is connected to the front part of the second heat exchanger 42, and the second cylindrical portion 327 is connected to the rear part of the second heat exchanger 42. The first cylindrical portion 326 and the second cylindrical portion 327 are in thermal contact with the cooled fluid flowing in the return path of the cooled fluid flow path 50.

[0098] In the gas turbine engine 100A of the first modification, the first heat exchanger 41 extends in the direction of the rotation axis X, and therefore the first cylindrical portion 316 and the second cylindrical portion 317 can be spaced apart in the direction of the rotation axis X. As a result, when the engine 100A is in a normal up-down position, even if the inclination angle of the rotation axis X of the engine 100A with respect to the horizontal plane is large, the cooled fluid can be cooled by both or either of the first cylindrical portion 316 and the second cylindrical portion 317, i.e., both or either of the first evaporator 311 and the second evaporator 312. More specifically, when the engine 100A is tilted so that the front of the engine 100A is positioned upward in the direction of gravity, the liquid-phase working fluid L in the first heat pipe 31 is influenced by gravity and is located mainly in the second cylindrical portion 317, i.e., the second evaporator 312. As a result, the cooled fluid can exchange heat with the working fluid in the second evaporator 312 in the first heat exchanger 41, thereby cooling the cooled fluid. On the other hand, when the engine 100A is tilted so that the front of the engine 100A is positioned downward in the direction of gravity, the liquid-phase working fluid L in the first heat pipe 31 is affected by gravity and is positioned mainly in the first cylindrical portion 316, i.e., the first evaporation portion 311. This allows the cooled fluid to exchange heat with the working fluid in the first evaporation portion 311 in the first heat exchanger 41, thereby cooling the cooled fluid.

[0099] Furthermore, because the second heat exchanger 42 extends in the direction of the rotation axis X, the first cylindrical portion 326 and the second cylindrical portion 327 can be spaced apart in the direction of the rotation axis X. As a result, when the engine 100A is in an upside-down position, even if the inclination angle of the rotation axis X of the engine 100A with respect to the horizontal plane is large, the cooled fluid can be cooled by both or either of the first cylindrical portion 326 and the second cylindrical portion 327, i.e., both or either of the first evaporator 321 and the second evaporator 322. A detailed description will be omitted as this is the same as when the engine 100A is in the normal position.

[0100] Note that, although a description of other configurations, actions, and effects will be omitted, the description of the gas turbine engine 100 according to this embodiment can be used to describe the gas turbine engine 100A according to the first modification.

[0101] Variation 2 FIG. 10 is a front view of a gas turbine engine 100B according to Modification 2, as seen from the front. FIG. 11 is a cross-sectional view taken along line XI-XI in FIG. 10. FIG. 12 is a side view of a gas turbine engine 100B according to Modification 2, as seen from the side. In FIGS. 10, 11, and 12, the casing 6 is depicted as transparent to clearly show the heat pipes and heat exchanger. In FIG. 10, components inside the casing 6 are omitted. Although FIG. 11 is a cross-sectional view, hatching of the casing 6 is omitted to clearly show the heat pipes and heat exchanger. In FIGS. 11 and 12, the cooled fluid flow paths 50 are simply indicated by arrows.

[0102] The gas turbine engine 100B according to the second modification differs from the gas turbine engine 100 according to the embodiment in the number and configuration of the heat pipes and heat exchangers. The following description will focus on the configuration of the gas turbine engine 100B according to the second modification that differs from the gas turbine engine 100 according to the embodiment. Note that in the gas turbine engine 100B according to the second modification, the same reference numerals as those in the gas turbine engine 100 according to the embodiment indicate the same configuration as in the gas turbine engine 100 according to the embodiment, and therefore description thereof will be omitted.

[0103] The gas turbine engine 100B of variant 2 has a first heat pipe 31, a second heat pipe 32, a third heat pipe 33, a fourth heat pipe 34, a first heat exchanger 41, a second heat exchanger 42, a third heat exchanger 43, a fourth heat exchanger 44, a fifth heat exchanger 45, and a sixth heat exchanger 46.

[0104] The first heat pipe 31, the second heat pipe 32, the third heat pipe 33, and the fourth heat pipe 34 are arranged at different positions in the circumferential direction around the rotation axis X. Specifically, the first heat pipe 31 and the second heat pipe 32 face each other when viewed from the direction of the rotation axis X. The third heat pipe 33 and the fourth heat pipe 34 face each other when viewed from the direction of the rotation axis X. More specifically, the first heat pipe 31 is located above the rotation axis X, and the second heat pipe 32 is located below the rotation axis X. The third heat pipe 33 is located on the right side of the rotation axis X when viewed from the front, and the fourth heat pipe 34 is located on the left side of the rotation axis X when viewed from the front.

[0105] The first heat pipe 31, the second heat pipe 32, the third heat pipe 33, and the fourth heat pipe 34 are provided in the casing 6. Specifically, the first heat pipe 31, the second heat pipe 32, the third heat pipe 33, and the fourth heat pipe 34 are integrated into the casing 6. More specifically, the first heat pipe 31, the second heat pipe 32, the third heat pipe 33, and the fourth heat pipe 34 are embedded inside the wall portion 60 of the casing 6. The first heat pipe 31, the second heat pipe 32, the third heat pipe 33, and the fourth heat pipe 34 each have a flat shape that curves along the casing 6. Note that at least one of the first heat pipe 31, the second heat pipe 32, the third heat pipe 33, and the fourth heat pipe 34 may protrude from the peripheral surface of the wall portion 60.

[0106] The first heat pipe 31, the second heat pipe 32, the third heat pipe 33, and the fourth heat pipe 34 are arranged in the circumferential direction so that the central angles about the rotation axis X are equally spaced.

[0107] When a plurality of reference lines are defined that extend radially from the rotation axis X so that the central angles around the rotation axis X are equally spaced and the number of the reference lines is the same as the number of heat pipes 31, 32, 33, 34, each of the heat pipes 31, 32, 33, 34 should intersect with the reference line corresponding to each of the heat pipes 31, 32, 33, 34.

[0108] Specifically, when the first reference line K1, the second reference line K2, the third reference line K3, and the fourth reference line K4 are defined so that the central angle is 90°, the first heat pipe 31 intersects with the first reference line K1, the second heat pipe 32 intersects with the second reference line K2, the third heat pipe 33 intersects with the third reference line K3, and the fourth heat pipe 34 intersects with the fourth reference line K4. For example, the first reference line K1 passes through the circumferential center of the first heat pipe 31, the second reference line K2 passes through the circumferential center of the second heat pipe 32, the third reference line K3 passes through the circumferential center of the third heat pipe 33, and the fourth reference line K4 passes through the circumferential center of the fourth heat pipe 34.

[0109] The first heat exchanger 41 is connected to the first heat pipe 31. The second heat exchanger 42 is connected to the second heat pipe 32. The third heat exchanger 43 is connected to the third heat pipe 33. The fourth heat exchanger 44 is connected to the third heat pipe 33. The fifth heat exchanger 45 is connected to the fourth heat pipe 34. The sixth heat exchanger 46 is connected to the fourth heat pipe 34.

[0110] The first heat exchanger 41, the second heat exchanger 42, the third heat exchanger 43, the fourth heat exchanger 44, the fifth heat exchanger 45, and the sixth heat exchanger 46 are arranged at different positions in the circumferential direction around the rotation axis X. The first heat exchanger 41, the second heat exchanger 42, the third heat exchanger 43, the fourth heat exchanger 44, the fifth heat exchanger 45, and the sixth heat exchanger 46 are integrated with the casing 6. Specifically, the first heat exchanger 41, the second heat exchanger 42, the third heat exchanger 43, the fourth heat exchanger 44, the fifth heat exchanger 45, and the sixth heat exchanger 46 are embedded inside a wall portion 60 of the casing 6. The first heat exchanger 41, the second heat exchanger 42, the third heat exchanger 43, the fourth heat exchanger 44, the fifth heat exchanger 45, and the sixth heat exchanger 46 each have a flat shape curved along the casing 6. Furthermore, at least one of the first heat exchanger 41, the second heat exchanger 42, the third heat exchanger 43, the fourth heat exchanger 44, the fifth heat exchanger 45 and the sixth heat exchanger 46 may protrude from the peripheral surface of the wall portion 60.

[0111] The first heat exchanger 41 is located radially inward from the first heat pipe 31 about the rotation axis X. The second heat exchanger 42 is located radially inward from the second heat pipe 32 about the rotation axis X.

[0112] When the engine 100B is placed so that the first heat pipe 31 is positioned higher in the direction of gravity than the second heat pipe 32, the first heat exchanger 41 and the second heat exchanger 42 are each positioned lower than the first heat pipe 31 and higher than the second heat pipe 32.

[0113] The third heat exchanger 43 is located between the second heat pipe 32 and the third heat pipe 33 in the circumferential direction. The fourth heat exchanger 44 is located between the first heat pipe 31 and the third heat pipe 33 in the circumferential direction. In other words, the third heat pipe 33 is sandwiched between the third heat exchanger 43 and the fourth heat exchanger 44 in the circumferential direction. The fifth heat exchanger 45 is located between the second heat pipe 32 and the fourth heat pipe 34 in the circumferential direction. The sixth heat exchanger 46 is located between the first heat pipe 31 and the fourth heat pipe 34 in the circumferential direction. In other words, the fourth heat pipe 34 is sandwiched between the fifth heat exchanger 45 and the sixth heat exchanger 46 in the circumferential direction.

[0114] When the engine 100B is placed so that the first heat pipe 31 is located higher in the direction of gravity than the second heat pipe 32, the third heat exchanger 43 is located lower in the direction of gravity than the third heat pipe 33, and the fourth heat exchanger 44 is located higher in the direction of gravity than the third heat pipe 33. Furthermore, the fifth heat exchanger 45 is located lower in the direction of gravity than the fourth heat pipe 34, and the sixth heat exchanger 46 is located higher in the direction of gravity than the fourth heat pipe 34.

[0115] The first heat pipe 31 includes an evaporation section 310 and a condensation section 313. The evaporation section 310 includes a first evaporation section 311 and a second evaporation section 312. Specifically, the first heat pipe 31 has a main body section 315, and a first cylindrical section 316 and a second cylindrical section 317 connected to the main body section 315. The first cylindrical section 316 is located forward of the second cylindrical section 317. The main body section 315 includes the condensation section 313. The first cylindrical section 316 includes the first evaporation section 311. The second cylindrical section 317 includes the second evaporation section 312.

[0116] The first cylindrical portion 316 and the second cylindrical portion 317 each extend radially inward from the main body portion 315. Specifically, the engine 100B has two sets of the first cylindrical portion 316 and the second cylindrical portion 317. The first cylindrical portion 316 and the second cylindrical portion 317 of one of the two sets extend from the right end portion of the main body portion 315 toward the first heat exchanger 41 when viewed from the front. The first cylindrical portion 316 and the second cylindrical portion 317 of the other of the two sets extend from the left end portion of the main body portion 315 toward the first heat exchanger 41 when viewed from the front.

[0117] The second heat pipe 32 has a shape symmetrical to the first heat pipe 31 with respect to the rotation axis X. The second heat pipe 32 includes an evaporation section 320 and a condensation section 323. The evaporation section 320 includes a first evaporation section 321 and a second evaporation section. Specifically, the second heat pipe 32 has a main body section 325, and a first cylindrical section 326 and a second cylindrical section connected to the main body section 325. The first cylindrical section 326 is located forward of the second cylindrical section. The main body section 325 includes the condensation section 323. The first cylindrical section 326 includes the first evaporation section 321. The second cylindrical section includes the second evaporation section.

[0118] The first cylindrical portion 326 and the second cylindrical portion each extend radially inward from the main body portion 325. Specifically, the engine 100B has two sets of first cylindrical portions 326 and second cylindrical portions. The first cylindrical portion 326 and the second cylindrical portion of one of the two sets extend from the right end portion of the main body portion 325 toward the second heat exchanger 42 when viewed from the front. The first cylindrical portion 326 and the second cylindrical portion of the other of the two sets extend from the left end portion of the main body portion 325 toward the second heat exchanger 42 when viewed from the front.

[0119] The third heat pipe 33 includes an evaporator section 330 and a condenser section 333. The evaporator section 330 includes a first evaporator section 330a, a second evaporator section 330b, a third evaporator section 330c, and a fourth evaporator section 330d. Specifically, the third heat pipe 33 has a main body section 335 and a first cylindrical section 336, a second cylindrical section 337, a third cylindrical section 338, and a fourth cylindrical section 339 connected to the main body section 335. The first cylindrical section 336 is located forward of the second cylindrical section 337. The third cylindrical section 338 is located forward of the fourth cylindrical section 339. The first cylindrical section 336 and the second cylindrical section 337 are located lower than the third cylindrical section 338 and the fourth cylindrical section 339. The main body section 335 includes the condenser section 333. The first cylindrical section 336 includes the first evaporator section 330a. The second cylindrical portion 337 includes a second evaporation portion 330b, the third cylindrical portion 338 includes a third evaporation portion 330c, and the fourth cylindrical portion 339 includes a fourth evaporation portion 330d.

[0120] The first cylindrical portion 336, the second cylindrical portion 337, the third cylindrical portion 338, and the fourth cylindrical portion 339 each extend circumferentially from the main body portion 335. Specifically, the first cylindrical portion 336 and the second cylindrical portion 337 extend from the lower end of the main body portion 335 toward the third heat exchanger 43. The third cylindrical portion 338 and the fourth cylindrical portion 339 extend from the upper end of the main body portion 335 toward the fourth heat exchanger 44.

[0121] The fourth heat pipe 34 has a shape symmetrical to the third heat pipe 33 with respect to the rotation axis X. The fourth heat pipe 34 includes an evaporator section 340 and a condenser section 343. The evaporator section 340 includes a first evaporator section 340a, a second evaporator section, a third evaporator section 340c, and a fourth evaporator section. Specifically, the fourth heat pipe 34 has a main body section 345 and a first cylindrical section 346, a second cylindrical section, a third cylindrical section 348, and a fourth cylindrical section connected to the main body section 345. The first cylindrical section 346 is located forward of the second cylindrical section. The third cylindrical section 348 is located forward of the fourth cylindrical section. The first cylindrical section 346 and the second cylindrical section are located lower than the third cylindrical section 348 and the fourth cylindrical section. The main body section 345 includes the condenser section 343. The first cylindrical section 346 includes the first evaporator section 340a. The second cylindrical section includes the second evaporator section. The third cylindrical portion 348 includes a third evaporation portion 340c. The fourth cylindrical portion includes a fourth evaporation portion.

[0122] The first cylindrical portion 346, the second cylindrical portion, the third cylindrical portion 348, and the fourth cylindrical portion each extend circumferentially from the main body portion 345. Specifically, the first cylindrical portion 346 and the second cylindrical portion extend from the lower end of the main body portion 345 toward the fifth heat exchanger 45. The third cylindrical portion 348 and the fourth cylindrical portion extend from the upper end of the main body portion 345 toward the sixth heat exchanger 46.

[0123] In the first heat pipe 31, the evaporation section 310 is located radially inward from the condensation section 313 about the rotation axis X. In the second heat pipe 32, the evaporation section 320 is located radially inward from the condensation section 323 about the rotation axis X.

[0124] When the engine 100B is placed so that the first heat pipe 31 is positioned higher in the direction of gravity than the second heat pipe 32, the evaporation section 310 of the first heat pipe 31 and the evaporation section 320 of the second heat pipe 32 are each located lower than the condensation section 313 of the first heat pipe 31 and higher than the condensation section 323 of the second heat pipe 32.

[0125] When the engine 100B is placed so that the first heat pipe 31 is located higher in the direction of gravity than the second heat pipe 32, in the third heat pipe 33, the first evaporator 330a and the second evaporator 330b are located lower in the direction of gravity than the condenser 333, and the third evaporator 330c and the fourth evaporator 330d are located higher in the direction of gravity than the condenser 333. In addition, in the fourth heat pipe 34, the first evaporator 340a and the second evaporator are located lower in the direction of gravity than the condenser 343, and the third evaporator 340c and the fourth evaporator are located higher in the direction of gravity than the condenser 343.

[0126] The first heat exchanger 41 brings the fluid to be cooled into thermal contact with the evaporator section 310 of the first heat pipe 31. The second heat exchanger 42 brings the fluid to be cooled into thermal contact with the evaporator section 320 of the second heat pipe 32. Specifically, the first heat exchanger 41 and the second heat exchanger 42 each have a cooled fluid flow path 50. The cooled fluid flow path 50 is a flow path that is folded back in a U shape.

[0127] The first heat exchanger 41 is thermally connected to the first cylindrical portion 316 and the second cylindrical portion 317 of the first heat pipe 31. Specifically, the first cylindrical portion 316 and the second cylindrical portion 317 are inserted into the cooled fluid flow path 50, and the first cylindrical portion 316 and the second cylindrical portion 317 come into contact with the cooled fluid flowing through the cooled fluid flow path 50.

[0128] The second heat exchanger 42 is thermally connected to the first cylindrical portion 326 and the second cylindrical portion of the second heat pipe 32. Specifically, the first cylindrical portion 326 and the second cylindrical portion are inserted into the cooled fluid flow path 50, and the first cylindrical portion 326 and the second cylindrical portion come into contact with the cooled fluid flowing through the cooled fluid flow path 50.

[0129] The third heat exchanger 43 brings the cooled fluid into thermal contact with the first evaporator section 330a and the second evaporator section 330b of the third heat pipe 33. The fourth heat exchanger 44 brings the cooled fluid into thermal contact with the third evaporator section 330c and the fourth evaporator section 330d of the third heat pipe 33. Specifically, the fourth heat exchanger 44 has the outgoing path of the cooled fluid flow path 50, and the third heat exchanger 43 has the returning path of the cooled fluid flow path 50.

[0130] The third heat exchanger 43 is thermally connected to the first cylindrical portion 336 and the second cylindrical portion 337 of the third heat pipe 33. Specifically, the first cylindrical portion 336 and the second cylindrical portion 337 are inserted into the return path of the cooled fluid flow path 50, and the first cylindrical portion 336 and the second cylindrical portion 337 come into contact with the cooled fluid flowing in the return path of the cooled fluid flow path 50.

[0131] The fourth heat exchanger 44 is thermally connected to the third cylindrical portion 338 and the fourth cylindrical portion 339 of the third heat pipe 33. Specifically, the third cylindrical portion 338 and the fourth cylindrical portion 339 are inserted into the forward path of the cooled fluid flow path 50, and the third cylindrical portion 338 and the fourth cylindrical portion 339 come into contact with the cooled fluid flowing in the forward path of the cooled fluid flow path 50.

[0132] The fifth heat exchanger 45 brings the fluid to be cooled into thermal contact with the first evaporator section 340a and the second evaporator section of the fourth heat pipe 34. The sixth heat exchanger 46 brings the fluid to be cooled into thermal contact with the third evaporator section 340c and the fourth evaporator section of the fourth heat pipe 34. Specifically, the sixth heat exchanger 46 has the outgoing path of the cooled fluid flow path 50, and the fifth heat exchanger 45 has the returning path of the cooled fluid flow path 50.

[0133] The fifth heat exchanger 45 is thermally connected to the first cylindrical portion 346 and the second cylindrical portion of the fourth heat pipe 34. Specifically, the first cylindrical portion 346 and the second cylindrical portion are inserted into the return path of the cooled fluid flow path 50, and the first cylindrical portion 346 and the second cylindrical portion come into contact with the cooled fluid flowing in the return path of the cooled fluid flow path 50.

[0134] The sixth heat exchanger 46 is thermally connected to the third cylindrical portion 348 and the fourth cylindrical portion of the fourth heat pipe 34. Specifically, the third cylindrical portion 348 and the fourth cylindrical portion are inserted into the forward path of the cooled fluid flow path 50, and the third cylindrical portion 348 and the fourth cylindrical portion come into contact with the cooled fluid flowing through the forward path of the cooled fluid flow path 50.

[0135] 13 is a schematic diagram showing the flow path of the cooled fluid. The cooled fluid flows and circulates through a cooled fluid supply line 51 and a cooled fluid return line 52.

[0136] Specifically, cooled fluid supply line 51 connects cooled fluid tank 8 to components such as bearing 18 inside casing 6. A first pump 55 is connected to cooled fluid supply line 51, and first pump 55 sends the cooled fluid from cooled fluid tank 8 to the components inside casing 6. The cooled fluid is sprayed onto the components inside casing 6, for example.

[0137] Cooled fluid return line 52 connects the interior of casing 6 with cooled fluid tank 8. A second pump 56 is connected to cooled fluid return line 52, and second pump 56 sends the cooled fluid from the interior of casing 6 to cooled fluid tank 8. After being supplied to the components inside casing 6, the cooled fluid is sucked by second pump 56. After being supplied to the components inside casing 6, the cooled fluid may be stored in a reservoir provided in casing 6.

[0138] The first heat exchanger 41, the second heat exchanger 42, the third heat exchanger 43, the fourth heat exchanger 44, the fifth heat exchanger 45, and the sixth heat exchanger 46 are connected downstream of the first pump 55 in the middle of the cooled fluid supply line 51. Specifically, the cooled fluid flow path 50 of each of the heat exchangers 41 to 46 is connected in the middle of the cooled fluid supply line 51.

[0139] The first heat exchanger 41, the third heat exchanger 43, and the fifth heat exchanger 45 are connected in parallel. The first heat exchanger 41, the third heat exchanger 43, and the fifth heat exchanger 45 constitute a first heat exchanger group 21. The second heat exchanger 42, the fourth heat exchanger 44, and the sixth heat exchanger 46 are connected in parallel. The second heat exchanger 42, the fourth heat exchanger 44, and the sixth heat exchanger 46 constitute a second heat exchanger group 22. The first heat exchanger group 21 and the second heat exchanger group 22 are connected in parallel.

[0140] Next, the state of engine 100B when the attitude of an aircraft in flight changes in the circumferential direction around the direction of flight will be described.

[0141] When the aircraft has a normal vertical attitude, the engine 100B also has a normal vertical attitude. At this time, the liquid-phase working fluid in the first heat pipe 31 is located in the evaporator section 310 due to the influence of gravity. The liquid-phase working fluid in the second heat pipe 32 is located in the condenser section 323 due to the influence of gravity. The liquid-phase working fluid in the third heat pipe 33 is located in the first evaporator section 330a and the second evaporator section 330b due to the influence of gravity. The liquid-phase working fluid in the fourth heat pipe 34 is located in the first evaporator section 340a and the second evaporator section 340b due to the influence of gravity.

[0142] As a result, the fluid to be cooled can exchange heat with the working fluid in the evaporator section 310 of the first heat pipe 31 in the first heat exchanger 41, can exchange heat with the working fluid in the first evaporator section 330a and the second evaporator section 330b of the third heat pipe 33 in the third heat exchanger 43, and can exchange heat with the working fluid in the first evaporator section 340a and the second evaporator section of the fourth heat pipe 34 in the fifth heat exchanger 45. In other words, the fluid to be cooled can exchange heat with the working fluid in the first heat exchanger group 21.

[0143] When the aircraft's vertical attitude is upside down, the engine 100B also has an upside down vertical attitude. At this time, the liquid-phase working fluid in the first heat pipe 31 is located in the condenser section 313 due to the influence of gravity. The liquid-phase working fluid in the second heat pipe 32 is located in the evaporator section 320 due to the influence of gravity. The liquid-phase working fluid in the third heat pipe 33 is located in the third evaporator section 330c and the fourth evaporator section 330d due to the influence of gravity. The liquid-phase working fluid in the fourth heat pipe 34 is located in the third evaporator section 340c and the fourth evaporator section 340d due to the influence of gravity.

[0144] As a result, the fluid to be cooled can exchange heat with the working fluid in the evaporator section 320 of the second heat pipe 32 in the second heat exchanger 42, can exchange heat with the working fluid in the third evaporator section 330c and the fourth evaporator section 330d of the third heat pipe 33 in the fourth heat exchanger 44, and can exchange heat with the working fluid in the third evaporator section 340c and the fourth evaporator section of the fourth heat pipe 34 in the sixth heat exchanger 46. In other words, the fluid to be cooled can exchange heat with the working fluid in the second heat exchanger group 22.

[0145] In this way, even if the attitude of the engine 100B changes in the circumferential direction around the rotation axis X, the fluid to be cooled can be cooled.

[0146] Next, a description will be given of the state of the engine 100B when the aircraft changes its tilt attitude relative to the horizontal plane during flight. Note that a detailed description is omitted here as it is the same as that of the above embodiment.

[0147] The evaporator section 310 of the first heat pipe 31 includes a first evaporator section 311 and a second evaporator section 312 arranged side by side along the rotation axis X. The evaporator section 320 of the second heat pipe 32 includes a first evaporator section 321 and a second evaporator section arranged side by side along the rotation axis X. The evaporator section 330 of the third heat pipe 33 includes a first evaporator section 330a and a second evaporator section 330b arranged side by side along the rotation axis X, and a third evaporator section 330c and a fourth evaporator section 330d arranged side by side along the rotation axis X. The evaporator section 340 of the fourth heat pipe 34 includes a first evaporator section 340a and a second evaporator section arranged side by side along the rotation axis X, and a third evaporator section 340c and a fourth evaporator section arranged side by side along the rotation axis X.

[0148] When the aircraft is in a normal vertical position, even if the inclination angle of the rotation axis X of the engine 100B relative to the horizontal plane changes, the fluid to be cooled can be cooled by at least one of the first evaporator section 311 and the second evaporator section 312 of the first heat pipe 31, at least one of the first evaporator section 330a and the second evaporator section 330b of the third heat pipe 33, and at least one of the first evaporator section 340a and the second evaporator section of the fourth heat pipe 34, depending on the inclination angle of the rotation axis X.

[0149] Furthermore, when the aircraft is in an upside-down position, even if the inclination angle of the rotation axis X of the engine 100B relative to the horizontal plane changes, the fluid to be cooled can be cooled by at least one of the first evaporator 321 and the second evaporator of the second heat pipe 32, at least one of the third evaporator 330c and the fourth evaporator 330d of the third heat pipe 33, and at least one of the third evaporator 340c and the fourth evaporator of the fourth heat pipe 34, depending on the inclination angle of the rotation axis X.

[0150] This makes it possible to reduce the deterioration of the cooling performance for the fluid to be cooled in response to changes in the tilting posture of the engine 100B.

[0151] Next, an example of a manufacturing method for the heat pipes 31 to 34 and the heat exchangers 41 to 46 will be described. When manufacturing the casing 6, the heat pipes 31 to 34 and the heat exchangers 41 to 46 are manufactured by additive manufacturing. By manufacturing them by additive manufacturing, the heat pipes 31 to 34 and the heat exchangers 41 to 46 can be easily embedded inside the casing 6 when manufactured.

[0152] According to the gas turbine engine 100B of the second modification, the first heat pipe 31, the second heat pipe 32, the third heat pipe 33, and the fourth heat pipe 34 are arranged at different positions in the circumferential direction around the rotation axis X. Therefore, when the engine 100B is mounted on an aircraft, even if the attitude of the engine 100B changes in the circumferential direction in accordance with a change in the attitude of the aircraft, the fluid to be cooled can be cooled by at least one of the first heat pipe 31, the second heat pipe 32, the third heat pipe 33, and the fourth heat pipe 34, depending on the circumferential attitude of the engine 100B. This makes it possible to reduce a decrease in the cooling performance for the fluid to be cooled in response to a change in the circumferential attitude of the engine 100B.

[0153] Furthermore, because the first heat pipe 31, the second heat pipe 32, the third heat pipe 33, and the fourth heat pipe 34 are integrated into the casing 6, it is possible to reduce the gaps between the first heat pipe 31, the second heat pipe 32, the third heat pipe 33, and the fourth heat pipe 34 and the casing 6, thereby reducing the protrusion of the first heat pipe 31, the second heat pipe 32, the third heat pipe 33, and the fourth heat pipe 34 radially outward from the casing 6. This allows the engine 100B to be made smaller.

[0154] Furthermore, since the first heat pipe 31, the second heat pipe 32, the third heat pipe 33 and the fourth heat pipe 34 have a flattened shape curved along the casing 6, the protrusion of the first heat pipe 31, the second heat pipe 32, the third heat pipe 33 and the fourth heat pipe 34 radially outward from the casing 6 is reduced, and the engine 100B can be made smaller.

[0155] Furthermore, since the first heat pipe 31, the second heat pipe 32, the third heat pipe 33 and the fourth heat pipe 34 are embedded inside the wall portion 60 of the casing 6, the protrusion of the first heat pipe 31, the second heat pipe 32, the third heat pipe 33 and the fourth heat pipe 34 radially outward from the casing 6 is suppressed, and the engine 100B can be made smaller.

[0156] Furthermore, since the first heat pipe 31, the second heat pipe 32, the third heat pipe 33 and the fourth heat pipe 34 are embedded inside the wall portion 60 of the casing 6, the outer periphery of the engine 100B can be made smooth, thereby reducing the air resistance of the engine 100B.

[0157] Furthermore, the first heat pipe 31, the second heat pipe 32, the third heat pipe 33, and the fourth heat pipe 34 are arranged in the circumferential direction so that the central angles around the rotation axis X are equally spaced, so that even if the attitude of the engine 100B changes in the circumferential direction, the fluid to be cooled can be cooled by at least one of the first heat pipe 31, the second heat pipe 32, the third heat pipe 33, and the fourth heat pipe 34. This makes it possible to reduce a decrease in the cooling performance for the fluid to be cooled in response to changes in the attitude of the engine 100B in the circumferential direction.

[0158] Furthermore, since the first heat exchanger 41 is located radially inward from the first heat pipe 31 about the rotation axis X, when the engine 100B is placed so that the first heat pipe 31 is located above in the direction of gravity, the first heat exchanger 41 is located lower than the first heat pipe 31. As a result, when the engine 100B is positioned so that the first heat pipe 31 is located above in the direction of gravity, the liquid-phase working fluid moves by gravity toward the first heat exchanger 41, and the first heat exchanger 41 can cool the fluid to be cooled.

[0159] Furthermore, in the first heat pipe 31, the evaporator section 310 is located radially inward about the rotation axis X relative to the condenser section 313, and therefore when the engine 100B is placed so that the first heat pipe 31 is located above in the direction of gravity, the evaporator section 310 is located lower than the condenser section 313. As a result, when the engine 100B is positioned so that the first heat pipe 31 is located above in the direction of gravity, the liquid-phase working fluid moves by gravity to the evaporator section 310, and the evaporator section 310 can cool the fluid to be cooled.

[0160] Furthermore, since the second heat exchanger 42 is located radially inward from the second heat pipe 32 about the rotation axis X, when the engine 100B is placed so that the second heat pipe 32 is located above in the direction of gravity, the second heat exchanger 42 is located lower than the second heat pipe 32. As a result, when the engine 100B is positioned so that the second heat pipe 32 is located above in the direction of gravity, the liquid-phase working fluid moves by gravity toward the second heat exchanger 42, and the cooled fluid can be cooled by the second heat exchanger 42.

[0161] Furthermore, in the second heat pipe 32, the evaporator section 320 is located radially inward about the rotation axis X relative to the condenser section 323. Therefore, when the engine 100B is placed so that the second heat pipe 32 is located above in the direction of gravity, the evaporator section 320 is located lower than the condenser section 323. As a result, when the engine 100B is positioned so that the second heat pipe 32 is located above in the direction of gravity, the liquid-phase working fluid moves by gravity to the evaporator section 320, and the evaporator section 320 can cool the fluid to be cooled.

[0162] Note that, although a description of other configurations, actions, and effects will be omitted, the description of the gas turbine engine 100 according to this embodiment can be used to describe the gas turbine engine 100B according to the second modification.

[0163] Other Embodiments As described above, the above embodiment has been described as an example of the technology disclosed in this application. However, the technology of the present disclosure is not limited to this and can be applied to embodiments in which modifications, substitutions, additions, omissions, etc. are made as appropriate. Furthermore, the components described in the above embodiment can be combined to create new embodiments. Furthermore, the components described in the accompanying drawings and detailed description may include not only components essential for solving the problem, but also components that are not essential for solving the problem in order to exemplify the technology. Therefore, the fact that these non-essential components are described in the accompanying drawings or detailed description should not be interpreted as immediately determining that these non-essential components are essential.

[0164] For example, although engine 100 is used in an aircraft, it may also be used in transportation equipment other than an aircraft.

[0165] The casing 6 may be composed of a plurality of divided sections. In this case, the heat pipe needs to be provided in at least one of the sections. For example, if the casing 6 is composed of a first section that houses the fan 2 and a second section that houses the compressor 3, the combustor 4, and the turbine 5, the heat pipe is preferably provided in the first section. This makes the heat pipe less susceptible to the heat of the combustor 4, and reduces the reduction in the cooling effect of the heat pipe.

[0166] The first heat exchanger 41 and the second heat exchanger 42 are separate, but may be integrated.

[0167] The first heat pipe 31 and the second heat pipe 32 are opposed to each other when viewed from the direction of the rotation axis X, but they do not have to be opposed to each other when viewed from the direction of the rotation axis X, and may be arranged at different positions in the circumferential direction around the rotation axis X.

[0168] The first heat pipe 31 and the second heat pipe 32 are arranged on the outer peripheral surface of the casing 6 or embedded inside the wall portion 60 of the casing 6, but may also be arranged on the inner peripheral surface of the casing 6.

[0169] One of the first heat pipe 31 or the second heat pipe 32 may be arranged on the outer peripheral surface of the casing 6, and the other of the first heat pipe 31 or the second heat pipe 32 may be embedded inside the wall portion 60 of the casing 6.

[0170] The first heat pipe 31 and the second heat pipe 32 each have a flat shape that is curved along the outer peripheral surface of the casing 6, but the shapes of the first heat pipe 31 and the second heat pipe 32 are not limited to a flat shape.

[0171] The evaporation section 310 of the first heat pipe 31 includes the first evaporation section 311 and the second evaporation section 312, but may include only either the first evaporation section 311 or the second evaporation section 312, or may include another evaporation section in addition to the first evaporation section 311 and the second evaporation section 312. The same applies to the evaporation section 320 of the second heat pipe 32.

[0172] The connection structure between the first heat pipe 31 and the first heat exchanger 41 is a shell-and-tube structure in which the first cylindrical portion 316 and the second cylindrical portion 317 of the first heat pipe 31 are inserted into the cooled fluid flow path 50 of the first heat exchanger 41, but is not limited to the shell-and-tube structure and may be other structures. For example, the first cylindrical portion 316 and the second cylindrical portion 317 of the first heat pipe 31 may be configured to be wrapped around the cooled fluid flow path 50 of the first heat exchanger 41. The same applies to the connection structure between the second heat pipe 32 and the second heat exchanger 42.

[0173] In the vertical position of the engine 100, the normal position is one in which the first heat pipe 31 is positioned above the direction of gravity and the second heat pipe 32 is positioned below the direction of gravity, but the normal position may also be one in which the first heat pipe 31 is positioned below the direction of gravity and the second heat pipe 32 is positioned above the direction of gravity.

[0174] The engine 100 may include three or five or more heat pipes including the first heat pipe 31 and the second heat pipe 32. In this case, the heat pipes may be arranged circumferentially at equal central angular intervals about the rotation axis X.

[0175] The multiple heat pipes, including the first heat pipe 31 and the second heat pipe 32, are arranged in the circumferential direction so that the central angles around the rotation axis X are equally spaced, but they may also be arranged so that the central angles are different.

[0176] [Aspect] The above-described embodiment is a specific example of the following aspects.

[0177] (Aspect 1) Each of the gas turbine engines 100, 100A, and 100B includes a casing 6 surrounding a rotation axis X, a first heat pipe 31 and a second heat pipe 32 each including an evaporator 310, 320 that encloses a working fluid and converts at least a portion of the liquid-phase working fluid L into gas, and a condenser 313, 323 that converts the gas-phase working fluid into a liquid, a first heat exchanger 41 into which a fluid to be cooled flows and brings the cooled fluid into thermal contact with the evaporator 310 of the first heat pipe 31, and a second heat exchanger 42 into which a fluid to be cooled flows and brings the cooled fluid into thermal contact with the evaporator 320 of the second heat pipe 32, and the first heat pipe 31 and the second heat pipe 32 are provided in the casing 6 and are arranged at different positions in the circumferential direction around the rotation axis X.

[0178] According to this configuration, the first heat pipe 31 and the second heat pipe 32 are disposed at different positions in the circumferential direction around the rotation axis X. Therefore, when the gas turbine engines 100, 100A, 100B are mounted on an aircraft, even if the attitude of the gas turbine engines 100, 100A, 100B changes in the circumferential direction in accordance with a change in the attitude of the aircraft, the fluid to be cooled can be cooled by both or either one of the first heat pipe 31 and the second heat pipe 32, depending on the circumferential attitude of the gas turbine engines 100, 100A, 100B. This makes it possible to reduce a decrease in the cooling performance for the cooled fluid in response to a change in the circumferential attitude of the gas turbine engines 100, 100A, 100B.

[0179] (Aspect 2) In the gas turbine engine 100, 100A according to the first aspect, the first heat pipe 31 and the second heat pipe 32 are disposed on the outer circumferential surface of the casing 6.

[0180] According to this configuration, the first heat pipe 31 and the second heat pipe 32 do not interfere with the intake of the gas turbine engines 100, 100A, thereby ensuring the amount of intake air for the gas turbine engines 100, 100A.

[0181] (Aspect 3) In the gas turbine engine 100B according to the first or second aspect, the first heat pipe 31 and the second heat pipe 32 are integrated with the casing 6.

[0182] This configuration reduces the gap between the first heat pipe 31 and the second heat pipe 32 and the casing 6, thereby reducing the protrusion of the first heat pipe 31 and the second heat pipe 32 radially outward from the casing 6. This allows the gas turbine engine 100B to be made smaller.

[0183] (Aspect 4) In the gas turbine engine 100 , 100 A, 100 B according to any one of the first to third aspects, the first heat pipe 31 and the second heat pipe 32 have a flat shape curved along the casing 6 .

[0184] According to this configuration, the protrusion of the first heat pipe 31 and the second heat pipe 32 radially outward from the casing 6 can be reduced, and the gas turbine engines 100, 100A, 100B can be made smaller.

[0185] (Aspect 5) In the gas turbine engine 100B according to any one of aspects 1 to 4, the casing 6 includes a cylindrical wall portion 60, and the first heat pipe 31 and the second heat pipe 32 are embedded inside the wall portion 60.

[0186] According to this configuration, it is possible to prevent the first heat pipe 31 and the second heat pipe 32 from protruding radially outward from the casing 6, thereby making it possible to reduce the size of the gas turbine engine 100B.

[0187] (Aspect 6) In the gas turbine engine 100, 100A according to any one of aspects 1 to 5, the first heat exchanger 41 and the second heat exchanger 42 are located between the first heat pipe 31 and the second heat pipe 32 in the circumferential direction.

[0188] With this configuration, even if the attitude of the gas turbine engine 100, 100A changes in the circumferential direction, the cooled fluid can be cooled by both or either one of the first heat exchanger 41 and the second heat exchanger 42, depending on the circumferential attitude of the gas turbine engine 100, 100A. This makes it possible to reduce degradation in cooling performance for the cooled fluid in response to changes in the circumferential attitude of the gas turbine engine 100, 100A.

[0189] (Aspect 7) In the gas turbine engine 100B according to any one of the first to sixth aspects, the first heat exchanger 41 is positioned radially inward of the first heat pipe 31 about the rotation axis X.

[0190] According to this configuration, when the gas turbine engine 100B is placed so that the first heat pipe 31 is positioned upward in the direction of gravity, the first heat exchanger 41 is positioned lower than the first heat pipe 31. As a result, when the gas turbine engine 100B is positioned so that the first heat pipe 31 is positioned upward in the direction of gravity, the fluid to be cooled can be cooled by the first heat exchanger 41.

[0191] (Aspect 8) In the gas turbine engine 100, 100A, 100B according to any one of aspects 1 to 7, when the gas turbine engine 100, 100A, 100B is placed so that the first heat pipe 31 is positioned higher in the direction of gravity than the second heat pipe 32, the first heat exchanger 41 and the second heat exchanger 42 are positioned lower than the first heat pipe 31 and higher than the second heat pipe 32.

[0192] With this configuration, even if the attitude of the gas turbine engines 100, 100A, 100B changes in the circumferential direction, the cooled fluid can be cooled by both or either one of the first heat exchanger 41 and the second heat exchanger 42, depending on the circumferential attitude of the gas turbine engines 100, 100A, 100B. This makes it possible to reduce a decrease in the cooling performance for the cooled fluid in response to changes in the circumferential attitude of the gas turbine engines 100, 100A, 100B.

[0193] (Aspect 9) The gas turbine engine 100, 100A, 100B according to any one of aspects 1 to 8 includes a plurality of heat pipes including the first heat pipe 31 and the second heat pipe 32, and the plurality of heat pipes are arranged in the circumferential direction so that the central angles around the rotation axis X are equally spaced.

[0194] Here, the term "arranged such that the central angles of the plurality of heat pipes around the rotation axis X are equally spaced" means that when a plurality of reference lines, the number of which is equal to the number of heat pipes, are defined and the heat pipes extend radially from the rotation axis X so that the central angles are equally spaced around the rotation axis X, each heat pipe intersects with a reference line corresponding to the heat pipe.

[0195] With this configuration, even if the attitude of the gas turbine engine 100, 100A, 100B changes in the circumferential direction, the fluid to be cooled can be cooled by at least one of the heat pipes, thereby reducing the deterioration of the cooling performance for the fluid to be cooled in response to the change in the attitude of the gas turbine engine 100, 100A, 100B in the circumferential direction.

[0196] (Aspect 10) In the gas turbine engine 100, 100A, 100B according to any one of aspects 1 to 9, the evaporator section 310 of the first heat pipe 31 and the evaporator section 320 of the second heat pipe 32 include a first evaporator section 311, 321 and a second evaporator section 312, 322, respectively, arranged side by side along the rotation axis X.

[0197] According to this configuration, even if the tilt angle of the rotation axis X of the gas turbine engine 100, 100A, 100B relative to the horizontal plane changes in accordance with a change in the attitude of the aircraft, the cooled fluid can be cooled by both or either one of the first evaporators 311, 321 and the second evaporators 312, 322, depending on the tilt angle of the rotation axis X. This makes it possible to reduce a decrease in the cooling performance for the cooled fluid in response to a change in the tilt attitude of the gas turbine engine 100, 100A, 100B. [Explanation of symbols]

[0198] 100, 100A, 100B Gas Turbine Engine 6 Casing 60 Wall 31 First heat pipe 310 Evaporation section 311 First evaporation section 312 Second evaporation section 313 Condenser 32 Second heat pipe 320 Evaporation section 321 First evaporation section 322 Second evaporation section 323 Condenser 41 1st heat exchanger 42 Second heat exchanger X rotation axis

Claims

1. a casing surrounding the rotating shaft; a first heat pipe and a second heat pipe, each including an evaporator that encloses a working fluid and changes at least a part of the working fluid from a liquid phase into a gas, and a condenser that changes the working fluid from a gas phase into a liquid; a first heat exchanger into which a fluid to be cooled flows and which brings the fluid to thermal contact with the evaporator of the first heat pipe; a second heat exchanger into which a fluid to be cooled flows and which brings the fluid to thermal contact with the evaporator of the second heat pipe; The gas turbine engine, wherein the first heat pipe and the second heat pipe are provided in the casing and arranged at different positions in a circumferential direction around the rotation axis.

2. 2. The gas turbine engine of claim 1, The first heat pipe and the second heat pipe are disposed on an outer peripheral surface of the casing.

3. 2. The gas turbine engine of claim 1, The first heat pipe and the second heat pipe are integrated into the casing of the gas turbine engine.

4. 4. The gas turbine engine according to claim 2 or 3, The gas turbine engine, wherein the first heat pipe and the second heat pipe have a flat shape curved along the casing.

5. 4. The gas turbine engine of claim 3, the casing includes a cylindrical wall; The first heat pipe and the second heat pipe are embedded inside the wall portion of the gas turbine engine.

6. 2. The gas turbine engine of claim 1, The gas turbine engine, wherein the first heat exchanger and the second heat exchanger are located between the first heat pipe and the second heat pipe in the circumferential direction.

7. 2. The gas turbine engine of claim 1, The gas turbine engine, wherein the first heat exchanger is located radially inward of the first heat pipe in a direction centered on the rotational axis.

8. 2. The gas turbine engine of claim 1, When the gas turbine engine is placed so that the first heat pipe is positioned higher in the direction of gravity than the second heat pipe, the first heat exchanger and the second heat exchanger are positioned lower than the first heat pipe and higher than the second heat pipe.

9. 2. The gas turbine engine of claim 1, a plurality of heat pipes including the first heat pipe and the second heat pipe; The gas turbine engine, wherein the plurality of heat pipes are arranged in the circumferential direction so that the central angles about the rotation axis are equally spaced.

10. 2. The gas turbine engine of claim 1, the evaporator portion of the first heat pipe and the evaporator portion of the second heat pipe each include a first evaporator portion and a second evaporator portion arranged side by side along the rotation axis.

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