Heat exchange system for recovering exhaust waste heat of an aero-engine and aero-engine thereof

Abstract

The application provides a heat exchange system for recycling aviation engine tail gas waste heat and an aviation engine thereof, and the heat exchange system comprises a hot end heat exchanger, a plurality of special-shaped heat pipe pipelines and a graphite heat exchange unit; the condensing end of the hot end heat exchanger is connected with the graphite heat exchange unit through the special-shaped heat pipe pipelines; the graphite heat exchange unit comprises a heat exchange main body, a plurality of gas inlets are arranged on the first wall surface of the heat exchange main body, and a plurality of gas outlets are arranged on the second wall surface of the heat exchange main body; a plurality of gas passages are arranged in the heat exchange main body, the gas inlets and the entrances of the gas passages are in one-to-one correspondence and are communicated, and the gas outlets and the side walls of the gas passages are communicated; and the evaporation end of the special-shaped heat pipe pipeline is arranged between two adjacent gas passages. The heat exchange unit body for extracting the heat of the engine tail gas is used to realize the recycling of the tail gas heat. The evaporation end of the heat pipe and the graphite heat exchanger core body are coupled and integrated to realize the rapid transmission and further recycling of the tail gas heat.

Description

Technical Field

[0001] This invention relates to the field of thermal management of aircraft engines, and in particular to a heat exchange system for recovering waste heat from aircraft engine exhaust and an aircraft engine thereof. Background Technology

[0002] In the field of aero-engine thermal management, waste heat recovery from aero-engines is one of the important ways to improve engine energy utilization and reduce carbon emissions. Compared with traditional energy industries, aero-engine waste heat recovery technology faces challenges such as stringent space constraints, high power density, and high reliability requirements.

[0003] Waste heat recovery technology based on thermoacoustic energy conversion offers advantages such as low vibration, high reliability, long lifespan, and high potential efficiency due to its simple structure and lack of moving mechanical parts. Furthermore, the use of an inert gas working fluid aligns with environmentally friendly and "dual-carbon" development goals. Thermoacoustic technology provides a highly promising development path for waste heat recovery from aero-engines. This technology recovers waste heat from exhaust gases to drive a thermoacoustic engine, generating acoustic power. This acoustic power then drives a thermoacoustic heat pump to transfer low-grade waste heat to a higher grade for utilization.

[0004] The first step in waste heat recovery is the recovery of aircraft engine exhaust. The heat exchanger units in the recovery device need to withstand temperatures as high as 500–650°C, and their coefficient of thermal expansion needs to be compatible with the heat pipe material to avoid localized stress caused by thermal expansion. At the same time, they need to have good manufacturability and be lightweight.

[0005] As mentioned above, the recovery of waste heat from aero-engine exhaust gas has placed higher demands on the following technical issues:

[0006] 1. Design a heat exchanger for extracting heat from aero-engine exhaust gas to achieve heat recovery from exhaust gas under high temperature (650℃) conditions.

[0007] Second, the heat recovery heat exchanger for exhaust gas meets the system's requirements for good thermal conductivity and lightweight materials.

[0008] Third, the exhaust gas heat needs to be coupled with the evaporation end of the irregularly shaped heat pipe to ensure the required heat exchange area.

[0009] In view of this, the inventors of this application have designed a heat exchange system for recovering waste heat from the exhaust gas of an aircraft engine and an aircraft engine thereof, in order to overcome the above-mentioned technical problems. Summary of the Invention

[0010] The technical problem to be solved by the present invention is to overcome the shortcomings of the prior art in heat exchange of waste heat from aero-engine exhaust gas, such as higher requirements for heat exchange, improved thermal conductivity, and guaranteed heat exchange area, and to provide a heat exchange system for recovering waste heat from aero-engine exhaust gas and the aero-engine thereof.

[0011] The present invention solves the above-mentioned technical problems through the following technical solution:

[0012] A heat exchange system for recovering waste heat from aircraft engine exhaust is characterized in that the heat exchange system includes a hot-end heat exchanger, multiple rows of irregularly shaped heat pipes, and a graphite heat exchange unit, wherein the condensation end of the hot-end heat exchanger is connected to the graphite heat exchange unit through the irregularly shaped heat pipes.

[0013] The graphite heat exchange unit includes a heat exchange body, with multiple air inlets on the first wall of the heat exchange body and multiple air outlets on the second wall of the heat exchange body, the first wall and the second wall being adjacent to each other.

[0014] The heat exchanger body is provided with multiple gas passages, the gas inlet is connected to the inlet of the gas passage in a one-to-one correspondence, and the gas outlet is connected to the side wall of the gas passage; the evaporation end of the irregular heat pipe is arranged between two adjacent gas passages.

[0015] When the gas enters the gas passage from the inlet, it makes indirect thermal contact with the evaporation end of the irregularly shaped heat pipe in the heat exchange body, and the internal working fluid undergoes evaporation phase change to absorb the heat from the gas.

[0016] According to one embodiment of the present invention, a steam collection chamber is further provided inside the heat exchange body, and the steam collection chamber surrounds the gas passage.

[0017] According to one embodiment of the present invention, the evaporation end of the irregularly shaped heat pipe is connected to the vapor collection chamber through a guide groove.

[0018] According to one embodiment of the present invention, the heat exchange system further includes a load unit and a acoustic tube unit connected in sequence, wherein the acoustic tube unit is connected to one side of the hot end heat exchanger;

[0019] The heat exchange system also includes a control unit, a cold-end heat exchanger, and a regeneration unit connected in sequence, with the regeneration unit connected to the other side of the hot-end heat exchanger.

[0020] According to one embodiment of the present invention, the acoustic tube unit is coupled to the condenser end of the irregularly shaped heat pipe.

[0021] According to one embodiment of the present invention, the air outlet is arranged in a honeycomb pattern.

[0022] According to one embodiment of the present invention, the evaporation end of the irregularly shaped heat pipe is coupled to the middle portion of two adjacent gas passages.

[0023] According to one embodiment of the present invention, the wall of the irregular heat pipe is provided with a wire mesh wick for storing and absorbing condensate.

[0024] According to one embodiment of the present invention, a flange structure is provided at the end of the heat exchange body, and the heat exchange body is fixed to the heat extraction design location through the flange structure.

[0025] The present invention also provides an aircraft engine, characterized in that the aircraft engine includes a heat exchange system for recovering waste heat from the aircraft engine exhaust gas as described above.

[0026] The positive and progressive effects of this invention are as follows:

[0027] The heat exchange system for recovering waste heat from aircraft engine exhaust gas and the aircraft engine thereof, as described in this invention, have the following advantages:

[0028] I. By using a heat exchange unit to extract heat from engine exhaust gas, the heat from exhaust gas is recovered and utilized.

[0029] Second, by coupling and integrating the heat pipe evaporator end with the graphite heat exchanger core, rapid heat transfer and further recovery of exhaust gas are achieved.

[0030] Third, the design of the heat exchanger core surface was incorporated to reduce flow resistance, the heat exchange was enhanced through the microchannel design, and the heat exchange area at the heat pipe evaporation end was further expanded by combining the layered design. Attached Figure Description

[0031] The above and other features, properties and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and embodiments, in which the same reference numerals always denote the same features, wherein:

[0032] Figure 1 This is a schematic diagram of the structure of the aero-engine of the present invention.

[0033] Figure 2 This is a schematic diagram of the heat exchange system for recovering waste heat from aircraft engine exhaust according to the present invention.

[0034] Figure 3 This is a schematic diagram of the graphite heat exchange unit in the heat exchange system for recovering waste heat from aircraft engine exhaust gas according to the present invention.

[0035] Figure 4 for Figure 3 The main view.

[0036] Figure 5 for Figure 4 A sectional view taken along the CC line.

[0037] Figure 6 for Figure 4 A sectional view taken along line DD.

[0038] Figure 7 for Figure 4 A sectional view taken along line EE.

[0039] Figure 8 This is a schematic diagram of the arrangement of graphite heat exchange units in the heat exchange system for recovering waste heat from aircraft engine exhaust gas according to the present invention. Detailed Implementation

[0040] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0041] Embodiments of the invention will now be described in detail with reference to the accompanying drawings. Preferred embodiments of the invention will now be described in detail, examples of which are shown in the drawings. Wherever possible, the same reference numerals will be used in all the drawings to denote the same or similar parts.

[0042] Furthermore, although the terminology used in this invention is selected from commonly known and used terms, some terms mentioned in this specification may have been selected by the applicant in his or her judgment, and their detailed meanings are explained in the relevant sections of the description herein.

[0043] Furthermore, the invention should be understood not only through the actual terminology used, but also through the meaning implied by each term.

[0044] like Figure 1 As shown, this invention discloses an aero-engine with a heat exchange system for recovering waste heat from the engine exhaust. The aero-engine, following the airflow direction, comprises: incoming gas 10, open fan 20, booster stage 30, high-pressure compressor 40, combustion chamber 50, high-pressure turbine 60, low-pressure turbine 70, turbine rear casing inclined support plate 80, exhaust nozzle 90, open bypass duct 11, core compartment outer side 12, and heat exchange system 100 (for waste heat recovery). The heat exchange system 100 is located at the engine exhaust and utilizes a temperature gradient to generate acoustic mechanical energy. The system includes a hot-end heat exchanger 110 and a cold-end heat exchanger 150 to form a temperature potential, and under the action of a regenerator 160, a thermoacoustic conversion effect is generated. The cold-end heat exchanger 150 can use bypass air as a cold source, while the hot-end heat exchanger extracts heat from the engine exhaust for secondary utilization. The main purpose of this heat exchange system for recovering waste heat from the exhaust is to recover the heat from the exhaust to the hot-end heat exchanger 110 for utilization.

[0045] like Figures 2 to 8As shown, the heat exchange system 100 in this application includes a hot-end heat exchanger 110, multiple rows of irregularly shaped heat pipes 200, and a graphite heat exchange unit 300. Here, the irregularly shaped heat pipes 200 refer to a heat-conducting component based on the phase change principle, generally consisting of an evaporation end, a condensation end, and an adiabatic section, used for long-distance heat transfer. The graphite heat exchange unit 300 refers to the inner core of a heat exchange device for recovering exhaust gas from an aircraft engine; it is made of graphite and has tiny gas channels.

[0046] In this embodiment, the condensing end of the hot-end heat exchanger 110 is connected to the graphite heat exchange unit 300 via a shaped heat pipe 200. The graphite heat exchange unit 300 includes a heat exchange body 310. Multiple air inlets 312 are provided on the first wall surface 311 of the heat exchange body 310, and multiple air outlets 314 are provided on the second wall surface 313 of the heat exchange body 310. The first wall surface 311 and the second wall surface 313 are adjacent to each other. Multiple gas passages 315 are also provided within the heat exchange body 310, such that the air inlets 312 are connected to the inlets of the gas passages 315 in a one-to-one correspondence, and the air outlets 314 are connected to the sidewalls of the gas passages 315. The evaporating end of the shaped heat pipe 200 is arranged between two adjacent gas passages 315. When the gas enters the gas passage 315 from the inlet 312, it makes indirect thermal contact with the evaporation end of the irregular heat pipe 200 in the heat exchange body 310, and the internal working fluid undergoes evaporation phase change to absorb the heat of the gas.

[0047] Preferably, a steam collecting chamber 316 is also provided inside the heat exchange body 310, so that the steam collecting chamber 316 surrounds the gas passage 315. The evaporation end of the irregular heat pipe 200 is connected to the steam collecting chamber 316 through a guide groove 317.

[0048] The heat exchange system 100 also includes a load unit 120 and a sound tube unit 130 connected in sequence, with the sound tube unit 130 connected to one side of the hot-end heat exchanger 110 (e.g., Figure 2 (The left side of the hot-end heat exchanger 110). The heat exchange system 100 also includes a control unit 140, a cold-end heat exchanger 150, and a regeneration unit 160 connected in sequence. The regeneration unit 160 is connected to the other side of the hot-end heat exchanger 110 (e.g., the left side of the hot-end heat exchanger 110). Figure 2 (Right side of the hot-end heat exchanger 110). Here, the acoustic tube unit 130 is coupled to the condenser end of the irregular heat pipe line 200.

[0049] The heat exchange system 100 (i.e., the waste heat recovery system) operates on the principle of thermoacoustic conversion, using the exhaust gas of the aircraft engine as a usable heat source to drive the waste heat recovery system. The key lies in the implementation of the heat exchange system 100. Its working principle is as follows: when the gas enters the gas passage 315 of the graphite heat exchange unit 300 from the inlet 312, it makes indirect thermal contact with the evaporation end 210 of the internal irregular heat pipe 200. The internal working fluid undergoes evaporation and phase change, absorbing the heat of the gas, and enters the steam collection chamber 316 through the guide groove 317, and then flows to the condensation end 220 of the irregular heat pipe 200.

[0050] Here, the evaporation end 210 of the irregular heat pipe 200 can also be designed as a plate structure, with the working fluid vapor near the outer side directly entering the vapor collection chamber 316, and the working fluid vapor in the middle entering the vapor collection chamber 316 through the guide groove 317.

[0051] like Figure 3 As shown, the gas enters through the air inlet 312, and the number of air inlets 312 is not limited to a certain number. Figure 3 The four shown can also be arranged in multiple rows. Then, the gas is discharged from the honeycomb-shaped outlets 314 on both sides, the purpose of which is to increase the heat exchange area. The outlets 314 are located in the lower pressure areas of the streamlined geometry, and their number and arrangement are not limited. Figure 3 As shown, multiple rows can also be arranged. The evaporation end 210 of the irregular heat pipe 200 coupled in the middle part of the double-layer gas passage 315 can adopt a pipe type or plate type structure.

[0052] In addition, the wall of the irregularly shaped heat pipe 200 can preferably be designed with a wire mesh wick for storing and absorbing condensate. The upper end of the heat exchange body 310 is provided with a connecting flange structure 318, and the heat exchange unit is designed to be fixed to the heat extraction location through the flange structure 318. This location is not limited to the turbine rear casing, nozzle wall, etc.

[0053] Figure 3 The diagram shows a single-unit layout structure. In practical applications, the number of units can be calculated and adjusted according to the specific heat exchange capacity and location layout, using a staggered layout, such as... Figure 8 As shown.

[0054] As described above, the heat exchange system for recovering waste heat from aircraft engine exhaust gas and the aircraft engine of the present invention realize the recovery and utilization of waste heat from engine exhaust gas, and have the following characteristics:

[0055] I. A graphite heat exchange unit with a streamlined structure was designed. Some of the exhaust gas can flow directly into the heat exchanger through the front inlet and flow through the internal pores through the pressure difference drive function, and then flow out from both sides. At the same time, its structural design has low resistance and has little impact on the mainstream.

[0056] Second, an internal heat exchange core was designed, using a graphite structure and a thermally conductive and high-temperature resistant coating to withstand the temperature impact of the engine exhaust and prevent cracks from forming.

[0057] Third, a honeycomb-shaped heat exchange microchannel was designed and manufactured using additive manufacturing technology to further expand the area of ​​the exhaust gas heat exchange channel and enhance heat exchange.

[0058] Fourth, a layered heat pipe layout was designed, which couples the evaporation end of the heat pipe with the graphite core, and the recovered heat is directly transferred to the condensation end of the irregularly shaped heat pipe.

[0059] In summary, the heat exchange system for recovering waste heat from aircraft engine exhaust gas and the aircraft engine thereof, as described in this invention, have the following advantages:

[0060] I. By using a heat exchange unit to extract heat from engine exhaust gas, the heat from exhaust gas is recovered and utilized.

[0061] Second, by coupling and integrating the heat pipe evaporator end with the graphite heat exchanger core, rapid heat transfer and further recovery of exhaust gas are achieved.

[0062] Third, the design of the heat exchanger core surface was incorporated to reduce flow resistance, the heat exchange was enhanced through the microchannel design, and the heat exchange area at the heat pipe evaporation end was further expanded by combining the layered design.

[0063] For those skilled in the art, the above disclosure is merely illustrative and does not constitute a limitation of this application. Although not explicitly stated herein, those skilled in the art may make various modifications, improvements, and corrections to this application. Such modifications, improvements, and corrections are suggested in this application and therefore remain within the spirit and scope of the exemplary embodiments of this application.

[0064] Furthermore, this application uses specific terms to describe embodiments of the application. For example, "an embodiment," "one embodiment," and / or "some embodiments" refer to a particular feature, structure, or characteristic related to at least one embodiment of the application. Therefore, it should be emphasized and noted that "an embodiment," "one embodiment," or "an alternative embodiment" mentioned twice or more in different locations in this specification do not necessarily refer to the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of the application can be appropriately combined.

[0065] Similarly, it should be noted that, in order to simplify the description of the embodiments disclosed in this application and thus aid in the understanding of one or more embodiments of the invention, the foregoing description of the embodiments of this application sometimes combines multiple features into a single embodiment, drawing, or description thereof. However, this disclosure method does not imply that the subject matter of this application requires more features than those mentioned in the claims. In fact, the embodiments have fewer features than all the features of a single embodiment disclosed above. Some embodiments use numbers describing the number of components or attributes; it should be understood that such numbers used in the description of embodiments are modified in some examples by the terms "approximately," "about," or "generally."

[0066] While specific embodiments of the present invention have been described above, those skilled in the art should understand that these are merely illustrative examples, and the scope of protection of the present invention is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of the present invention, but all such changes and modifications fall within the scope of protection of the present invention.

Claims

1. A heat exchange system for recovering waste heat from aircraft engine exhaust, characterized in that, The heat exchange system includes a hot-end heat exchanger, multiple rows of irregularly shaped heat pipes, and a graphite heat exchange unit. The condensing end of the hot-end heat exchanger is connected to the graphite heat exchange unit through the irregularly shaped heat pipes. The graphite heat exchange unit includes a heat exchange body, with multiple air inlets on the first wall of the heat exchange body and multiple air outlets on the second wall of the heat exchange body, the first wall and the second wall being adjacent to each other. The heat exchanger body is provided with multiple gas passages, the gas inlet is connected to the inlet of the gas passage in a one-to-one correspondence, and the gas outlet is connected to the side wall of the gas passage; the evaporation end of the irregular heat pipe is arranged between two adjacent gas passages. When the gas enters the gas passage from the inlet, it makes indirect thermal contact with the evaporation end of the irregularly shaped heat pipe in the heat exchange body, and the internal working fluid undergoes evaporation phase change to absorb the heat from the gas.

2. The heat exchange system for recovering waste heat from aircraft engine exhaust as described in claim 1, characterized in that, The heat exchanger body is also provided with a steam collection chamber, which surrounds the gas passage.

3. The heat exchange system for recovering waste heat from aircraft engine exhaust as described in claim 2, characterized in that, The evaporation end of the irregularly shaped heat pipe is connected to the vapor collection chamber via a guide groove.

4. The heat exchange system for recovering waste heat from aircraft engine exhaust as described in claim 1, characterized in that, The heat exchange system also includes a load unit and a sound tube unit connected in sequence, and the sound tube unit is connected to one side of the hot end heat exchanger. The heat exchange system also includes a control unit, a cold-end heat exchanger, and a regeneration unit connected in sequence, with the regeneration unit connected to the other side of the hot-end heat exchanger.

5. The heat exchange system for recovering waste heat from aircraft engine exhaust as described in claim 4, characterized in that, The acoustic tube unit is coupled to the condenser end of the irregularly shaped heat pipe.

6. The heat exchange system for recovering waste heat from aircraft engine exhaust as described in claim 1, characterized in that, The air outlets are arranged in a honeycomb pattern.

7. The heat exchange system for recovering waste heat from aircraft engine exhaust as described in claim 1, characterized in that, The evaporation end of the irregularly shaped heat pipe is coupled to the middle part of the two adjacent gas passages.

8. The heat exchange system for recovering waste heat from aircraft engine exhaust as described in claim 7, characterized in that, The irregularly shaped heat pipe is equipped with a wire mesh wick on its wall for storing and absorbing condensate.

9. The heat exchange system for recovering waste heat from aircraft engine exhaust as described in claim 1, characterized in that, The heat exchanger body is provided with a flange structure at its end, and the heat exchanger body is fixed to the heat extraction design location through the flange structure.

10. An aircraft engine, characterized in that, The aircraft engine includes a heat exchange system for recovering waste heat from aircraft engine exhaust as described in any one of claims 1-9.

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