JP2002350092A - Heat exchanger and gas turbine apparatus provided therewith - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide an heat exchanger having a high heat-resistance limit and heat-exchanging efficiency. SOLUTION: The heat exchanger 8 is provided with a core 36 for heat- exchange between a first fluid E and a second fluid A. The core 36 is provided with a plurality of ceramic-made heating tubes 48 for forming a first path 66 for passing the first fluid E in a first direction D1, a second path 67, an inlet 74 and an outlet 75. A space between the tubes 48 serves as the second path 67. The second fluid A is allowed to flow in the path 67. The second fluid A is let in at the inlet 74 and allowed to flow in a second direction D2 opposite to the first direction D1, then it is let out from the second path 67. The heating tubes 48 are provided with ceramic-made heat-transfer fins 68, 69 extending respectively in the radial and axial directions.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

The present invention relates to a heat exchanger having improved heat resistance and heat exchange efficiency, and a gas turbine device using the same.

[0002]

2. Description of the Related Art In a gas turbine device, it is effective to increase the temperature at the turbine inlet as a means for improving thermal efficiency. by the way,
In the regenerative gas turbine device, a heat exchanger is provided on the outlet side of the exhaust gas, and the heat exchanger exchanges heat between the compressed air from the compressor and the exhaust gas from the turbine and supplies the heat to the combustor. The temperature of the compressed air is raised. For this reason, in such a gas turbine device, even if an attempt is made to improve the thermal efficiency by increasing the turbine inlet temperature as described above, a limit is imposed on the Durbin inlet temperature due to the heat resistance limit of the heat exchanger, and the thermal efficiency is reduced. Improvement was hampered.

Further, as a conventional example of a heat exchanger used in the above-mentioned regenerative gas turbine device, a ceramic heat transfer pipe is disposed in an exhaust gas passage so as to be orthogonal to a flow direction of the exhaust gas. There is known a cross-flow type in which compressed air from the compressor flows through the heat transfer pipe to cause heat exchange between the exhaust gas and the compressed air. However, such a cross-flow heat exchanger has a lower heat exchange efficiency than a counter-flow heat exchanger in which two fluids flow in opposite directions.

[0004] The present invention has been made in view of the above circumstances, and an object of the present invention is to provide a heat exchanger having a high heat resistance limit and a high heat exchange efficiency, and a gas turbine device using the heat exchanger having a high heat efficiency.

[0005]

To achieve the above object, a heat exchanger according to a first aspect of the present invention comprises a core for heat exchange between a first fluid and a second fluid, The core includes a plurality of ceramic heat transfer pipes forming a first passage through which the first fluid flows in a first direction, and a second passage formed by a space between the second fluid and the heat transfer pipes. And an outlet and an outlet for flowing in a second direction opposite to the first direction and then flowing out of the space. The heat transfer pipe has a radial direction of the heat transfer pipe. And a ceramic heat transfer fin extending in the axial direction.
Here, the "radial direction" includes not only the radiation direction but also an oblique radiation direction slightly deviated from the radiation direction.

[0006] According to the heat exchanger, the first heat flowing through the plurality of ceramic heat transfer pipes forming the first passage is provided.
Heat is exchanged between the first fluid and the second fluid flowing in the space between the heat transfer pipes forming the second passage in a direction opposite to the first fluid, so that the ceramic itself has excellent heat resistance. The heat resistance of the heat exchanger can be increased due to the heat exchange property, and the heat exchange efficiency is also increased because of the counter flow type.

In a preferred embodiment of the present invention, the heat transfer fins are provided on at least one of the outside and the inside of the heat transfer pipe.

When the heat transfer fins are provided outside the heat transfer pipe, the contact area between the heat transfer pipe and the second fluid increases,
The heat exchange efficiency can be improved, and the second fluid can be smoothly guided. When the heat transfer fins are provided inside the heat transfer pipe, the contact area between the heat transfer pipe and the first fluid increases, and the heat exchange efficiency can be improved.

[0009] The heat exchanger according to the second configuration of the present invention comprises a first heat exchanger.
A core for heat exchange between the first fluid and the second fluid, the core having a ceramic honeycomb structure having a large number of eyes serving as passages for the first and second fluids, and traversing the core. A first row of passages for flowing the first fluid in a first direction along a first transverse direction;
And a second passage row flowing in a second direction opposite to the first direction, the first passage row and the second passage row are formed in a second transverse direction orthogonal to the first transverse direction. The upstream end of the second passage row is cut off adjacently, the cut space communicates with the inlet provided in the core, and the downstream end of the second passage row is cut off. The cutting space communicates with the outlet provided in the core.

According to the heat exchanger, the first fluid flowing through the first passage row of the honeycomb structure made of ceramic in the first direction and the second fluid row passing through the first row of the honeycomb structure correspond to the first direction. Since the heat exchange is performed between the second fluids flowing in the opposite second direction, the heat resistance of the heat exchanger can be increased by the excellent heat resistance of the ceramic itself. Efficiency also increases.

A gas turbine apparatus according to the present invention includes a heat exchanger having the first or second configuration, and a gas turbine engine for flowing exhaust gas through the first passage of the heat exchanger. An air introduction passage for introducing air that has exited the compressor of the engine into the inflow port, and an air outflow passage for guiding air from the outflow port to a combustor of the gas turbine engine are provided.

According to the gas turbine apparatus, heat is exchanged between exhaust gas from the gas turbine engine and air from the compressor by the counter-flow heat exchanger having a high heat resistance limit and high heat exchange efficiency. Therefore, the turbine inlet temperature can be increased to improve the thermal efficiency.

In a preferred embodiment of the present invention, the gas turbine engine is connected to a front surface of the heat exchanger, and a compressor of the gas turbine engine is provided between the core and a casing accommodating the core. A part of an air introduction path for introducing the discharged air to the inflow port and a part of an air outlet path for guiding the air from the outflow port to a combustor of the gas turbine engine are formed.

Since the gas turbine engine is directly connected to the front of the heat exchanger, the entire gas turbine device becomes compact.

[0015]

Preferred embodiments of the present invention will be described below in detail with reference to the drawings. FIG. 1 is a longitudinal sectional view of a gas turbine power generation apparatus using a gas turbine engine with a heat exchanger as a driving source according to an embodiment of the present invention.
The gas turbine power generator 1 includes a gas turbine engine 2 with a heat exchanger and a generator 3 driven by the gas turbine engine 2.

The gas turbine engine 2 has a centrifugal compressor 4, a turbine 5, and an annular combustor 6 located radially outward of the turbine 5. A turbine rotor 17 is joined to the back of the metal impeller 11 of the compressor 4. The compressor 4 compresses the air IA introduced from the intake passage 7 and supplies the compressed air A to the combustor 6 via the heat exchanger 8 connected to the exhaust gas outlet side at the rear of the gas turbine engine 2. And driven by the turbine 5. The compressor 4 includes a metal impeller 11.
And a shroud 12 formed at a position to cover the impeller 11 at the rear end of the intake housing 9 constituting the intake passage 7. A diffuser 13 for increasing the static pressure of the compressed air A is disposed radially outward on the outlet side of the compressor 4. The turbine 5 includes a turbine rotor 17 and a turbine nozzle 18 that is an inlet-side member of the turbine rotor 17.

The combustor 6 has a fuel nozzle 32 for injecting a gas or liquid fuel F into a combustion chamber 31 in the combustor 6, and the fuel F is sent into the combustion chamber 31 via the heat exchanger 8. It is mixed with the supplied high-temperature compressed air A1 and burns.
The high-temperature and high-pressure combustion gas G is sent from the turbine nozzle 18 to the turbine 5, and the energy of the combustion gas G drives the turbine 5. The combustor 6 is annular, and is arranged concentrically with the rotation axis C1 of the turbine 5.

The heat exchanger 8 shown in FIG. 1 includes a high-temperature exhaust gas E exiting the turbine 5 of the gas turbine engine 2 and a low-temperature compressed air A exiting the compressor 4 of the gas turbine engine 2.
The heat exchange is performed between the main housing 35 and the rear end of the main housing 35 having a circular cross section and housing the compressor 4, the combustor 6, and the turbine 5. The heat exchanger 8 is connected to the front flange 3 of the cylindrical casing 37.
8 is a state in which a front flange 49 of a tubular member 45 described below is sandwiched between a flange 39 at a rear end of the main housing 35 and a flange 39 of the main housing 35.
Are connected to the main housing 35 by being fastened with bolts 40 and nuts 41. A heat exchange core 36 having a circular cross section as shown in FIG. 3 is housed inside the heat exchanger casing 37. The heat exchange core 36 may have a rectangular cross section or another polygon. Further, the casing 37 may be in the shape of a rectangular tube.

The core 36 includes a metal tubular member 45,
A ceramic disc-shaped front and rear headers 46 and 47 for closing the front and rear portions of the cylindrical member 45, and a ceramic heat transfer pipe 48 supported by the front and rear headers 46 and 47, as shown in FIG. Have. A front flange 49 formed on the outer periphery of the front part of the cylindrical member 45 is formed by a front flange 38 of the heat exchanger casing 37 and the main housing 3.
5 is supported by the heat exchanger casing 37 by being sandwiched between the flanges 39 at the rear end and fastened together with the flanges 38 and 39 with bolts 40 and nuts 41. The rear end of the cylindrical member 45 has a rear flange 50 formed on the outer periphery thereof, which is fastened to an inward flange 51 at the rear end of the heat exchanger casing 37 with a bolt 52 and a nut 53. Heat exchanger casing 37
It is supported by.

The front and rear headers 46 and 47 are members for supporting the heat transfer pipes 48, and have a plurality of through holes 54 and 55 into which the ends of the heat transfer pipes 48 are fitted. These through holes 54, 55 are provided with flares so that the passages smoothly expand toward the inlet side (outer surface side) of the front header 46 and the outlet side (outer surface side) of the rear header 47. As shown in FIG. 2, one end of the heat transfer pipe 48 is connected to the through hole 54 of the front header 46 and the other end is connected to the through hole 5 of the rear header 47.
5 and fitted by baking etc.
Each heat transfer pipe 48 is joined to the front and rear headers 46 and 47 and supported in a direction along the axis of the heat exchanger casing 37. Pipe insertion part 5 of each through hole 54, 55
4a and 55a are large-diameter portions. By inserting the heat transfer pipe 48 therein, the inner surface of the heat transfer pipe 48 is flush with the inner surfaces of the through holes 54 and 55 connected thereto. The fluid resistance is suppressed.

In mounting the heat transfer pipes 48, first, one end of each heat transfer pipe 48 is connected to the through hole 5 of the front header 46.
4 and then the other end of each heat transfer pipe 48 is joined to the through hole 55 of the rear header 47 to form core bodies 46 to 48. Thereafter, the front header 46 of the core bodies 46 to 48 is fitted to the front inner surface of the tubular member 45. The rear end of the cylindrical member 45 of the core 36 has a larger diameter portion 56 than the other portion.
The rear header 47 is fitted to the inner surface of the large diameter portion 56.

A wave ring 61 made of a corrugated sheet and a gasket 62 are interposed between a shoulder 56a extending to the outer diameter side of the cylindrical member large diameter portion 56 and the front surface of the rear header 47. The wave ring 61 absorbs thermal expansion of the ceramic heat transfer pipe 48 and the front and rear headers 46 and 47 in the heat transfer pipe longitudinal direction. Also,
The back (outer surface) of the rear header 47 and the heat exchanger casing 37
Between the inward flange 51 at the rear end and the gasket 6
3 are interposed. Further, ceramic seal rings 64 and 65 are fitted on the outer peripheral surfaces of the front and rear headers 46 and 47. By these seal rings 64 and 65 and the gaskets 62 and 63, the fitting of the front and rear headers 46 and 47 to the tubular member 45 is sealed.

The heat transfer pipe 48 forms a first passage 66 for flowing exhaust gas E as a first fluid in a first direction D1 along the axis of the heat exchanger casing 37. A plurality of heat transfer fins 68, 69 extending in the axial direction
Having. FIG. 4 shows a front view in which a part of the heat transfer pipe 48 is cut away, and FIG. 5 shows a partial perspective view thereof. One heat transfer fin 68 extends radially outside the heat transfer pipe 48, and the other heat transfer fin 69 extends radially inside the heat transfer pipe 48. is there. The heat transfer fins 68 and 69 may be only the outer heat transfer fins 68 or only the inner heat transfer fins 69. Furthermore, these heat transfer fins 68,
In addition to the heat transfer fins 69, auxiliary heat transfer fins 71 and 72 having a shorter length in the radial direction than the heat transfer fins 68 and 69 may be added as shown by a chain line in FIG. The radial length of the outer heat transfer fins 68 is preferably set so as to slightly overlap between adjacent heat transfer pipes 48 supported by the front and rear headers 46 and 47.

The space between the heat transfer pipes 48 shown in FIG. 1 is provided in the second passage 67 through which the compressed air A as the second fluid flows.
It is said.

A plurality of inflow ports 74 are formed in the rear portion near the rear header 47 of the cylindrical member 45 constituting the core 36 in the circumferential direction, and a plurality of outflow ports 75 are formed in the front portion near the front header 46. They are formed side by side in the circumferential direction. Compressed air A from the compressor flows from the inlet 74 to the second passage 67.
And flows in a second direction D2 opposite to the first direction D1 in which the exhaust gas E flows, and then flows out of an outlet 75 to a later-described outlet path 84.

Between the core 36 and the heat exchanger casing 37, compressed air A is introduced into the inlet 74 from the front of the core 36 through the side of the core 36, that is, through the outside of the side surface. A passage 81 is formed. A compressed air passage 82 is formed between the main housing 35 in front of the heat exchanger 8 and the annular combustor 6 to guide the compressed air A exiting the compressor 4 to the introduction passage 81. The compressed air passage 82 is formed by a space formed between the main housing 35 and a cylindrical member 83 integrally formed concentrically with the main housing 35 inside the main housing 35. The front flange 4 of the core tubular member 45 is provided between the compressed air passage 82 and the introduction passage 81 on the side of the core 36.
9 communicates via a plurality of compressed air inlets 87 formed side by side in the circumferential direction.

Further, on the front side of the heat exchanger 8, the high-temperature compressed air A 1 from the outlet 75 of the heat exchanger 8 is sent to the combustor 6 of the gas turbine engine 2 on the inner peripheral side of the compressed air passage 82. An outlet path 84 for the combustor to be supplied is formed.
The lead-out path 84 is formed in a space between the cylindrical member 83 and the conical portion 45a in front of the core cylindrical member 45 which is arranged concentrically with the cylindrical member 83. 83 and a space between the substantially cylindrical exhaust diffuser 85 and the combustor 6 extending from the front end of the conical portion 45a to the rear end of the turbine shroud 18a in the turbine nozzle 18. .
Due to the inner space surrounded by the conical portion 45a and the exhaust diffuser 85, an exhaust gas inflow passage 8 for allowing the exhaust gas E exiting the turbine 5 to flow into the first passage 66 of the core 36.
6 are formed.

The generator 3 has a generator rotor 91 connected to the rotating part of the gas turbine engine 2 and a generator stator 92 arranged around the generator rotor 91, and is arranged concentrically with the intake housing 9. Generator case 94 having a circular cross section supported by intake housing 9 via struts 93
Housed within. The space formed between the intake housing 9 and the generator case 94 allows the intake passage 7
Is configured. An intake duct 95 for introducing air IA from outside into the intake passage 7 is connected to a front end of the intake housing 9. The generator stator 92 is wound around a ring-shaped core 97 fixed and disposed concentrically with the case 94 on the inner peripheral side of a generator case 94, and each local portion projecting from the core 97 to the inner diameter side. And a coil 98.

In the above configuration, heat exchange is performed between the compressed air A exiting the compressor 4 of the gas turbine engine 2 and the exhaust gas E exiting the turbine 5 by the heat exchanger 8 of FIG. Since the high-temperature compressed air A1 is guided to the combustor 6 of the gas turbine engine 2, the thermal efficiency of the gas turbine engine 2 is improved. The generator 3 is driven by the turbine 5 of the gas turbine engine 2.

In particular, in the heat exchanger 8, the exhaust gas E (first fluid) flowing through the plurality of ceramic heat transfer pipes 48 forming the first passage 66, and the second passage 6
7, heat exchange is performed between the first fluid and the compressed air A (second fluid) flowing in the opposite direction D2 in the space between the heat transfer pipes 48, and therefore, the excellent heat resistance of ceramics Thereby, the heat resistance limit of the heat exchanger 8 can be increased,
The heat exchange efficiency can be increased by using the counter flow type. The cylindrical member 45 that constitutes the outer peripheral portion of the core 36 is made of metal.
Since the passage 81 of the compressed air A (the second fluid), which is at a lower temperature than the (first fluid), is used, the temperature of the cylindrical member 45 is suppressed from being increased. Does not cause a restriction.

As shown in FIG. 5, ceramic heat transfer fins 68 and 69 extending radially and axially are provided on the heat transfer pipe 48 on the outside and inside of the heat transfer pipe 48, respectively. Since it is provided, the heat exchange efficiency can be improved. That is, the heat transfer fins 68 provided outside the heat transfer pipe 48 are separated from the heat transfer pipe 48 by the compressed air A.
The contact area of the (second fluid) is increased, and at the same time, it acts as a guide for flowing the compressed air A smoothly in the second direction D2, so that the heat exchange efficiency can be improved. Moreover, the heat transfer fins 69 provided inside the heat transfer pipe 48 increase the contact area between the heat transfer pipe 48 and the exhaust gas E (first fluid), thereby improving the heat exchange efficiency. .

Further, in the gas turbine power generator 1, the exhaust gas E from the gas turbine engine 2 and the compressed air from the compressor 4 are formed by the counter-flow heat exchanger 8 having a high heat resistance limit and high heat exchange efficiency. Since heat exchange is performed between A, the turbine inlet temperature can be increased to improve thermal efficiency.

FIG. 6 is a longitudinal sectional view showing another embodiment of the heat exchanger 8 in the gas turbine power generator 1.
In the heat exchanger 8, the inside of the core 36 has a honeycomb structure made of ceramic. That is, the first passage through which the exhaust gas E as the first fluid flows in the first direction D1 by housing the ceramic honeycomb structure inside the metal tubular member 45 constituting the core 36. Row 10
6 and a second passage row 10 for flowing the compressed air A as a second fluid in a second direction D2 opposite to the first direction D1.
7 are formed. The cylindrical member 45 of the core 36 is preferably cylindrical, but may be rectangular or polygonal.

The first and second passage arrays 106 and 10
7 is a first transverse direction P crossing the core 36 (a horizontal transverse direction orthogonal to the axial direction of the heat exchanger casing 37:
Each row consists of a group of honeycomb eyes EY arranged in FIG.
Each of the passage rows 106 and 107 is selected such that the first passage row 106 and the second passage row 107 alternately overlap in the vertical direction. The two passage arrays 106 and 107 are arranged adjacent to each other in a second transverse direction Q (a vertical direction of the heat exchanger casing 37: FIG. 10) orthogonal to the first transverse direction P.

The second row of passages 107 is shown in FIG.
The upstream end (rear end in FIG. 6) indicated by hatching is shown in FIG.
0 (B), and the cut space 108 is formed in the inflow port 7 provided in the cylindrical member 45 of the core 36 as shown in FIG.
It communicates with 4. The circulation port 74 is provided in the second passage row 107
Are provided in a row in the circumferential direction of the tubular member 45 so as to correspond to each of the steps. The downstream end of the second passage row 107 is also cut in the same manner as the upstream end, and the cut space 109 is
As shown in FIG. 9, it communicates with an outlet 75 provided in the tubular member 45.

The upstream end of the first row of passages 106 shown in FIG. Thereby, it is joined to the front header 46. Also,
The downstream end of the first passage row 106 is also joined to the rear header 47 by being fitted into a through hole 115 formed in the ceramic rear header 47 and fired. Mated. Other configurations are almost the same as those of the previous embodiment, and the description is omitted here.

In the heat exchanger 8, the turbine 5 (FIG. 1)
Exhaust gas E flows from the first passage row 106 of FIG. 6 in the first direction D 1, and compressed air A from the compressor 4 (FIG. 1) flows from the inlet 74 of the core 36 to the second passage row. After flowing through the flow path 107 in the second direction D2, the air flows out of the outlet 75 of the core 36, so that efficient counterflow-type heat exchange is performed between the exhaust gas E and the compressed air A. In particular, since the core 36 is made of ceramic, the heat resistance limit can be increased. Therefore, also in the case of the gas turbine power generator 1 using this heat exchanger 8, it is possible to increase the turbine inlet temperature and improve the thermal efficiency.

In each of the above embodiments, the gas turbine engine 2 is directly connected to the front surface of the heat exchanger 8 to reduce the size of the entire apparatus. In contrast to this, the gas turbine engine 2 and the heat exchanger 8 are connected by piping. May be connected.

[0039]

As described above, according to the heat exchanger of the first configuration of the present invention, the heat exchanger includes the core for exchanging heat between the first fluid and the second fluid, and the core includes the first fluid. A plurality of ceramic heat transfer pipes forming a first passage through which the fluid flows in a first direction; and allowing the second fluid to flow into a second passage formed in a space between the heat transfer pipes. Having an inflow port and an outflow port that flow in a second direction opposite to the first direction and then flow out of the space, and extend in the heat transfer pipe in the radial direction and the axial direction of the heat transfer pipe. Since the heat transfer fins made of ceramic are provided, the heat resistance of the heat exchanger can be increased due to the excellent heat resistance of the ceramic itself, and the heat exchange efficiency can be increased due to the counter flow type. .

Further, according to the heat exchanger of the second configuration of the present invention, the heat exchanger includes a core for heat exchange between the first fluid and the second fluid, and the core includes the first and second fluids. Has a ceramic honeycomb structure with a large number of eyes that will be the passage of
A first row of passages for flowing the first fluid in a first direction along a first transverse direction across the core; and a second passageway for flowing the second fluid in a second direction opposite to the first direction. A second passage row flowing in the direction of the first passage row is formed, and the first passage row and the second passage row are arranged adjacent to each other in a second transverse direction orthogonal to the first transverse direction, The upstream end of the second passage row is cut away, the cut space communicates with the inlet provided in the core, the downstream end of the second passage row is cut, and the cut space is cut into the core. Since it communicates with the provided outlet, the heat resistance limit can be increased, and the heat exchange efficiency can be increased due to the counterflow type.

Further, the gas turbine apparatus of the present invention has the heat exchanger of the first or second configuration, and a gas turbine engine for flowing exhaust gas through the first passage of the heat exchanger. An air introduction path that introduces air that has exited the compressor of the gas turbine engine into the inflow port, and an air outflow path that guides air from the outflow port to a combustor of the gas turbine engine, between the casing and the core. Therefore, heat is exchanged between the exhaust gas from the gas turbine engine and the air from the compressor. At this time, the counter-flow heat exchanger, which has a high heat resistance limit and high heat exchange efficiency, The heat efficiency can be improved by increasing the temperature.

[Brief description of the drawings]

FIG. 1 is a longitudinal sectional view of a gas turbine power generator according to an embodiment of the present invention.

FIG. 2 is an enlarged sectional view of a main part of a heat exchanger in the gas turbine power generator.

FIG. 3 is a perspective view showing a core in the heat exchanger.

FIG. 4 is a partially cutaway front view of a heat transfer pipe in the heat exchanger.

FIG. 5 is a partial perspective view of the heat transfer pipe.

FIG. 6 is a longitudinal sectional view of a heat exchanger according to another embodiment of the present invention.

FIG. 7 is a partial sectional view of an intermediate portion of a core in the heat exchanger.

FIG. 8 is a partial sectional view taken along line VIII-VIII in FIG.

FIG. 9 is a partial sectional view taken along line IX-IX in FIG. 6;

FIG. 10 is a perspective view showing a cutting space of a second passage row in the heat exchanger.

[Explanation of symbols]

2 gas turbine engine, 4 compressor, 8 heat exchanger, 36 core, 37 casing, 48 heat transfer pipe, 66 first passage, 67 second passage, 68, 69
... heat transfer fins, 74 ... inlet, 75 ... outlet, 81 ... introduction path, 82 ... compressed air passage, 84 ... outlet path for combustor,
106: first passage row, 107: second passage row, 10
8,109: ablation space, E: exhaust gas (first fluid),
A: compressed air (second fluid), EY: eyes of honeycomb

Claims (5)

[Claims] 1. A core for heat exchange between a first fluid and a second fluid, wherein the core is made of ceramic forming a first passage for flowing the first fluid in a first direction. A plurality of heat transfer pipes, and the second fluid flows into a second passage formed in a space between the heat transfer pipes, and flows in a second direction opposite to the first direction. A heat exchanger having an inflow port and an outflow port for flowing out of the heat transfer pipe, wherein the heat transfer pipe is provided with ceramic heat transfer fins extending in a radial direction and an axial direction of the heat transfer pipe. 2. The heat exchanger according to claim 1, wherein the heat transfer fin is provided on at least one of an outer side and an inner side of the heat transfer pipe. 3. A ceramic honeycomb structure having a plurality of eyes serving as a passage for the first and second fluids, the core having a core for heat exchange between a first fluid and a second fluid. And a first row of passages for flowing the first fluid in a first direction along a first transverse direction across the core; and opposing the second fluid to the first direction. A second passage row flowing in a second direction is formed, and the first passage row and the second passage row are arranged adjacent to each other in a second transverse direction orthogonal to the first transverse direction. The upstream end of the second passage row is cut off, the cut-out space communicates with an inlet provided in the core, and the downstream end of the second passage row is cut off, so that the cut-off space is formed. Is a heat exchanger communicating with the outlet provided in the core. 4. The heat exchanger according to claim 1, a gas turbine engine for flowing exhaust gas through the first passage of the heat exchanger, and a compressor of the gas turbine engine. A gas turbine device comprising: an air introduction passage that introduces air into the inflow port; and an air outflow passage that guides air from the outflow outlet to a combustor of a gas turbine engine. 5. The gas turbine engine according to claim 4, wherein the gas turbine engine is connected to a front surface of the heat exchanger, and a compressor of the gas turbine engine is provided between the core and a casing accommodating the core. A gas turbine device, comprising: a part of an air introduction path for introducing air into the inflow port; and a part of an air outlet path for guiding air from the outflow port to a combustor of a gas turbine engine.