A turbine engine and its application in aero engines
By employing a dual-mode heat exchanger and clutch structure in the turbine engine, directional airflow is achieved, solving the problems of complex components and turbine idling in reverse cycle engines, and realizing lightweight and efficient wide-speed range flight performance.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- AERO ENGINE ACAD OF CHINA
- Filing Date
- 2023-09-21
- Publication Date
- 2026-07-17
Smart Images
Figure CN117090686B_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of aircraft manufacturing technology, and in particular, it designs a turbine engine and its application in aero engines. Background Technology
[0002] With the technological advancements in traditional aero-engines, the concept of variable cycle engines has emerged and become the mainstream approach. Variable cycle engines alter engine cycle parameters by adjusting the geometry, size, or position of certain components, achieving thermodynamic cycles with different characteristics. This enhances the engine's adaptability, enabling it to change its operating state over a wider speed range, significantly improving its adaptability to complex and variable missions. Currently, aero-engines typically operate within the Mach 0–2 range, but extending this range to Mach 3–4 would be impossible with conventional variable cycle technology.
[0003] In existing technologies, such as the reverse cycle engine patent US3204403, relatively high flight speeds (e.g., Ma>3) can be achieved. However, this reverse cycle engine has the problem of not being able to start at low speeds. The solution of this patent is to add a combustion chamber and a turbine after the compressor, but there are two problems: First, there are too many additional components, adding two main components; second, several components interfere with each other. At low speeds, the front turbine idles, and at high speeds, the airflow after passing through the compressor has to expand and depressurize in the rear turbine, both of which affect the thrust performance of the engine.
[0004] Therefore, developing a turbine engine and its application in aero engines to address the technical shortcomings of existing reverse cycle engines, such as complex component construction and the impact of partial turbine idling on thrust, has become an urgent problem for those skilled in the art. Summary of the Invention
[0005] Therefore, it is necessary to address the technical shortcomings of existing technologies, such as the complex structure of components in rotary cycle engines and the impact of partial turbine idling on thrust, and to provide a turbine engine and its application in aero engines.
[0006] The present invention provides a turbine engine, the turbine engine comprising: a housing, a compressor section, a turbine, a clutch section, and a heat exchange section;
[0007] The housing includes a first housing and a second housing, the first housing is disposed inside the second housing, the cavity inside the first housing is a first channel, and the cavity between the first housing and the second housing is a second channel;
[0008] The compressed air section includes a first compressed air section and a second compressed air section, and the clutch section includes a first clutch section and a second clutch section. The first compressed air section is connected to the heat exchange section through the first clutch section, and the second compressed air section and the second clutch section are disposed at the rear end of the first compressed air section in the first channel.
[0009] The first air compressor and the first clutch are disposed in the first channel, and the second air compressor and the second clutch are disposed in the second channel;
[0010] The heat exchange section is connected to the turbine, and the airflow enters the turbine after passing through the heat exchange section.
[0011] In one embodiment, the heat exchange section is a dual-mode heat exchange section.
[0012] In one embodiment, the heat exchange section includes: a heat exchange body, a circulation pipeline, a switching valve, and a radiator;
[0013] The heat exchange body is disposed in the second channel, the heat exchange body can move in the second channel, and the heat exchange body can be connected to the airflow outlet of the first clutch and the airflow outlet of the second clutch respectively;
[0014] The circulation pipeline is connected to the heat exchange body. The circulation pipeline includes a first pipeline and a second pipeline. The first pipeline is a heating pipeline, and the second pipeline is a cooling pipeline. A circulation medium is provided in the circulation pipeline for heat exchange.
[0015] The switching valve is used to switch the connection between the heat exchanger body and the first pipeline / second pipeline.
[0016] In one embodiment, the heat exchange section further includes a blocking block connected to the heat exchange body for preventing airflow from passing through the heat exchange body in the second channel.
[0017] In one embodiment, the turbine engine further includes: a guide ring, the guide ring comprising: a first guide ring and a second guide ring;
[0018] The first guide ring is disposed in the first channel, between the airflow outlet of the heat exchange body and the turbine, and the second guide ring is disposed between the heat exchange body and the turbine.
[0019] In one embodiment, the heat exchange body is provided with a sealing ring to prevent gas from the first channel from entering the heat exchange body.
[0020] In one embodiment, the sealing ring includes a first sealing ring, a second sealing ring, and a third sealing ring. The first and second sealing rings are disposed at the communication points between the heat exchange body and the first housing at both ends, and the third sealing ring is disposed at the communication point between the heat exchange body and the first guide ring / second guide ring.
[0021] In one embodiment, the circulating medium is a supercritical fluid and / or liquid metal.
[0022] In one embodiment, the first pipeline is provided with a heat absorption pipe, which is located at the airflow outlet at the tail end of the turbine engine;
[0023] And / or,
[0024] A radiator is installed in the second pipeline.
[0025] The present invention also provides an application of a turbine engine, including any one of the above-described features, in an aero engine.
[0026] In summary, this invention provides a turbine engine comprising: a casing, a compressor section, a turbine, a clutch section, and a heat exchange section. The casing includes a first casing and a second casing, with the first casing disposed inside the second casing. A cavity inside the first casing forms a first channel, and a cavity between the first and second casings forms a second channel. The compressor section includes a first compressor section and a second compressor section. The clutch section includes a first clutch section and a second clutch section. The first compressor section communicates with the heat exchange section via the first clutch section, and the second compressor section communicates with the heat exchange section via the second clutch section. The first compressor section and the first clutch section are disposed in the first channel, and the second compressor section and the second clutch section are disposed at the rear end of the first compressor section in the first channel. The heat exchange section communicates with the turbine, and airflow enters the turbine after passing through the heat exchange section. This invention also provides an application of the above-described turbine engine in an aero-engine. In the technical solution provided by this invention, the compressed air from the first or second compressor section can be directed to the turbine through the action of the first and second clutch sections, respectively. The entire device only requires one turbine, resulting in a lighter weight. Simultaneously, it enables directional airflow, eliminating the problem of idling. This invention provides a turbine engine and its application in aero engines, addressing the technical shortcomings of existing reverse cycle engines, such as complex component structures and the impact of partial turbine idling on thrust. Attached Figure Description
[0027] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.
[0028] Figure 1 A schematic diagram of the structure of a turbine engine is provided in the technical solution of the embodiments of the present invention;
[0029] Figure 2 This is a structural schematic diagram of a low-speed flight mode in a turbine engine, provided by an embodiment of the present invention.
[0030] Figure 3 This is a structural schematic diagram of a high-speed flight mode in a turbine engine, provided by an embodiment of the present invention.
[0031] Figure 4 A schematic diagram of airflow circulation in a low-speed flight mode of a turbine engine, provided as an embodiment of the present invention;
[0032] Figure 5 A schematic diagram of airflow circulation in a high-speed flight mode of a turbine engine provided in an embodiment of the present invention;
[0033] The components include a first housing 1, a second housing 2, a first channel 3, a second channel 4, a first air compressor 5, a second air compressor 6, a first clutch 7, a second clutch 8, a turbine 9, a heat exchanger body 10, a first pipeline 11, a second pipeline 12, a switching valve 13, a radiator 14, a first guide ring 15, a second guide ring 16, a first sealing ring 17, a second sealing ring 18, a third sealing ring 19, a heat absorption pipe 20, a radiator 21, and a plug 22. Detailed Implementation
[0034] This invention provides a turbine engine and its application in aero engines, which addresses the technical shortcomings of existing reverse cycle engines, such as complex component structures and the impact of partial turbine idling on thrust.
[0035] To make the above-mentioned objects, features, and advantages of the present invention more apparent and understandable, specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a thorough understanding of the present invention. However, the present invention can be practiced in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.
[0036] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.
[0037] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.
[0038] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "communication," and "fixation," etc., should be interpreted broadly. For example, they can refer to fixed communication, detachable communication, or integral connection; they can refer to mechanical communication or electrical communication; they can refer to direct connection or indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.
[0039] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "over," and "on top" of the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.
[0040] It should be noted that when an element is referred to as being "fixed to" or "set on" another element, it can be directly on the other element or there may be an intervening element. When an element is considered to be "connected to" another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "upper," "lower," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only possible implementation.
[0041] Please see Figures 1 to 3 This invention provides a turbine-9 engine, comprising: a casing, a compressor section, a turbine-9, a clutch section, and a heat exchange section. The casing includes a first casing 1 and a second casing 2, with the first casing 1 disposed inside the second casing 2. The cavity inside the first casing 1 is a first channel 3, and the cavity between the first casing 1 and the second casing 2 is a second channel 4. The compressor section includes a first compressor section 5 and a second compressor section 6. The clutch section includes a first clutch section 7 and a second clutch section 8. The first compressor section 5 communicates with the heat exchange section through the first clutch section 7, and the second compressor section 6 communicates with the heat exchange section through the second clutch section 8. The first compressor section 5 and the first clutch section 7 are disposed in the first channel 3, and the second compressor section 6 and the second clutch section 8 are disposed at the rear end of the first compressor section 5 in the first channel 3. The heat exchange section communicates with the turbine-9, and the airflow enters the turbine-9 after passing through the heat exchange section. This invention provides a turbine-9 engine and its application in aero engines, solving the technical defects of existing reverse cycle engines, such as complex component structures and the impact of partial turbine-9 idling on thrust.
[0042] The technical solution provided in this embodiment of the invention, in conjunction with the structural components of the Turbo 9 engine, explains its working process and principle:
[0043] The first housing 1 is nested inside the cavity of the second housing 2, and the cavity between the two forms the second channel 4. The cavity of the first housing 1 forms the first channel 3. The gas outside the turbine 9 engine can enter the first channel 3 or the second channel 4 respectively.
[0044] Further reading is available here. Figure 2 When in a low-speed flight state (such as Ma≤2.5), the airflow outside the turbine 9 engine enters the first channel 3 and then enters the first compressor section 5. At this time, the first clutch section 7 connects the first compressor section 5 with the heat exchange section. The air compressed by the first compressor section 5 enters the heat exchange section for heating, and the heated compressed gas enters the turbine 9 for driving.
[0045] Please see here. Figure 4 , Figure 4 The arrows in the diagram represent the direction of airflow. Blue, yellow, and red indicate a gradual increase in air temperature, from... Figure 4 It can be seen that the low-temperature gas after passing through the first air compression part 5 is heated by the heat exchange part and its temperature rises.
[0046] For further reference here Figure 3 , when in a high-speed flight state (such as 2.5 < Ma < 5), the airflow outside the turbine 9 engine enters the second channel 4, bypasses the first air compression part 5 and then enters the first channel 3, and then enters the second air compression part 6. At this time, the second clutch part 8 connects the second air compression part 6 and the heat exchange part. The air compressed by the second air compression part 6 enters the heat exchange part for cooling, and the cooled compressed gas enters the turbine 9 for driving.
[0047] Please refer to here Figure 5 , Figure 5 The arrows in Figure 5 represent the flow direction of the airflow. Among them, red, yellow, and blue represent the gradual decrease of the airflow temperature. It can be seen that the high-temperature gas after passing through the second air compression part 6 is cooled by the heat exchange part and its temperature decreases.
[0048] When in a low-speed flight state, since the second clutch part 8 does not connect the second air compression part 6 and the heat exchange part at this time, only the gas compressed by the first air compression part 5 and heated and raised in temperature can enter the turbine 9 at this time; similarly, when in a high-speed flight state, since the first clutch part 7 does not connect the first air compression part 5 and the heat exchange part at this time, only the gas compressed by the second air compression part 6 and cooled and lowered in temperature can enter the turbine 9 at this time.
[0049] In the actual application process, the real-time speed detected by the speed detection module can be used to specifically determine whether it is the first clutch part 7 or the second clutch part 8 that is connected. There can be various specific implementation methods. Here, an example of one implementation method is given, which does not constitute a limitation on the protection scope of the technical solution provided by the embodiments of the present invention.
[0050] For example, when the speed is lower than a certain preset value, the speed detection module sends a signal to the first clutch part 7. At this time, the first clutch part 7 can move and connect the first air compression part 5 and the heat exchange part; when the speed is greater than the aforementioned preset value, the speed detection module sends a signal to the second clutch part 8. After the second clutch part 8 moves, it connects the second air compression part 6 and the heat exchange part. At this time, when the first clutch part 7 receives the second signal from the speed detection module synchronously, the first clutch part 7 moves and disconnects the connection between the first air compression part 5 and the heat exchange part.
[0051] With this structural design, the entire Turbine-9 engine only needs one Turbine-9 to meet the propulsion requirements for both low-speed and high-speed flight. The weight of the Turbine-9 engine will be significantly reduced, and the complexity of the structure will also be reduced. At the same time, it can also avoid the problem of idle Turbine-9 spinning when there are two Turbine-9 engines, thus avoiding the defect of affecting engine thrust caused by idle Turbine-9 spinning. Thirdly, the airflow can only pass through a certain channel, which can effectively ensure the maximum intake volume and make full use of the airflow in the environment.
[0052] Further optimizing the technical solution effectively reduces the overall structural complexity and weight of the Turbo 9 engine. In this embodiment of the invention, the heat exchange section of the Turbo 9 engine is a dual-mode heat exchange section. A single dual-mode heat exchange section can complete the heating / cooling function of the compressed gas, making the entire Turbo 9 engine simpler in structure and lighter in weight.
[0053] Further explanation of the structure of the dual-mode heat exchanger: In a turbine 9 engine provided by an embodiment of the present invention, the heat exchanger includes: a heat exchange body, a circulation pipeline, a switching valve 13, and a radiator 2114; the heat exchange body is disposed in the second channel 4 and can move within the second channel 4; the heat exchange body can be connected to the airflow outlet of the first clutch 7 and the airflow outlet of the second clutch 8 respectively; the circulation pipeline is connected to the heat exchange body and includes: a first pipeline 11 and a second pipeline 12, the first pipeline 11 being a heating pipeline and the second pipeline 12 being a cooling pipeline; a circulating medium is provided in the circulation pipeline for heat exchange; the switching valve 13 is used to switch the connection between the heat exchange body and the first pipeline 11 / second pipeline 12.
[0054] In the heat exchange section, the heat exchanger body heats / cools the air compressed by the first or second compressor. To ensure the heat exchange effect, the heat exchanger body can move within the second channel 4. Further details can be found here. Figure 2 and Figure 3 To more clearly indicate the current position and status of the heat exchanger, Figure 2 and Figure 3 Only the heat exchanger body was highlighted; the markings on the other components were similar to those on the heat exchanger body. Figure 1 The same applies. When in low-speed flight, the heat exchanger body is located at the airflow outlet of the first clutch 7; when in high-speed flight, the heat exchanger body is located at the airflow outlet of the second clutch 8. In this way, the heat exchanger body can only exchange heat with the air compressed by a certain compressor, which further improves the heat exchange efficiency.
[0055] At this time, the switching valve is responsible for switching whether the heat exchanger is connected to the first pipeline 11 or the second pipeline 12. The first pipeline 11 and the second pipeline 12 together form a circulation pipeline. The circulation pipeline contains a circulating medium that exchanges heat with compressed air. The circulating medium in the first pipeline 11 and the second pipeline 12 can be the same or different, and no specific restrictions are imposed here. The switching of the switching valve 13 can also be achieved by detecting the speed signal sent by the speed monitoring module, which is similar to the working principle of the first clutch 7 and the second clutch 8 mentioned above, and will not be described in detail here.
[0056] Further optimization of the technical solution can be found here. Figure 5 , Figure 5 To ensure airflow follows a preset path, during high-speed flight, air passes through the second channel 4, bypasses the first compressor section 5, and enters the second compressor in the first channel 3. In the technical solution provided by this embodiment, the heat exchange section further includes a blocking block 22 connected to the heat exchange body to prevent airflow from passing through the heat exchange body in the second channel 4. In this case, the blocking block 22 acts as a barrier, preventing uncompressed air from entering the heat exchange body. Instead, it allows the high-temperature gas to bypass the first compressor and enter the first channel 3, where it is compressed by the second compressor before entering the heat exchange body.
[0057] To further optimize the technical solution, the turbine 9 engine provided in this embodiment of the invention also includes: a guide ring, which includes: a first guide ring 15 and a second guide ring 16; the first guide ring 15 is disposed in the first channel 3, between the airflow outlet of the heat exchange body and the turbine 9, and the second guide ring 16 is disposed between the heat exchange body and the turbine 9.
[0058] At this time, the guide ring can play a good role in guiding the airflow, so that the airflow moves forward along the preset path. In practical applications, the guide ring can be designed as an irregularly shaped guide ring that matches the actual size and shape of the guide space, according to the actual situation of the assembly space.
[0059] To further improve the guiding effect of the flow guide ring, so that only compressed gas guided by the flow guide ring can enter the heat exchange body, thereby achieving orderly and quantitative heat exchange of compressed air and further effectively optimizing the heat exchange effect, the heat exchange body is provided with a sealing ring in the technical solution provided in this embodiment of the invention. The sealing ring is used to prevent gas from the first channel 3 from entering the heat exchange body.
[0060] To further optimize the technical solution, in a turbine 9 engine provided by an embodiment of the present invention, the sealing ring includes: a first sealing ring 17, a second sealing ring 18 and a third sealing ring 19. The first sealing ring 17 and the second sealing ring 18 are disposed at the communication points between the two ends of the heat exchange body and the first housing 1, and the third sealing ring 19 is disposed at the communication point between the heat exchange body and the first guide ring 15 / the second guide ring 16.
[0061] To effectively ensure the stability of the heat exchange unit's operation, and to prevent heat exchange instability caused by phase change of the circulating medium in the circulating pipeline during practical applications while maintaining good heat exchange performance, the circulating medium in the circulating pipeline provided in this embodiment of the invention is: supercritical fluid and / or liquid metal.
[0062] To ensure stable heat exchange performance, the structural complexity of the heat exchange section is further simplified. The first pipe 11 is equipped with a heat-absorbing pipe 20, which is located at the airflow outlet at the tail end of the turbine 9 engine. The heat-absorbing pipe 20 can absorb the high-temperature gas ejected from the tail end of the turbine 9 engine, heat it, and then transfer the heat to the circulating medium in the first pipe 11, achieving a heating effect.
[0063] And / or, a radiator 2114 is provided in the second pipe 12, and the radiator 2114 of the second pipe 12 is directly exposed to the outside of the shell for heat dissipation. Heat dissipation can be completed without designing an additional cooling compressor. The structure is simple and the heat dissipation effect is good.
[0064] Therefore, the present invention also provides an application of the above-mentioned turbine engine in aero engines. The turbine engine is adaptable to wide-speed cruise, has good performance in a wide speed range, and has a simple structure, making it suitable for widespread promotion in the field of aero engines.
[0065] In summary, this invention provides a turbine engine comprising: a casing, a compressor section, a turbine, a clutch section, and a heat exchange section; the casing includes a first casing and a second casing, the first casing being disposed inside the second casing, the cavity inside the second casing being a first channel, and the cavity between the first casing and the second casing being a second channel; the compressor section includes a first compressor section and a second compressor section, the clutch section includes a first clutch section and a second clutch section, the first compressor section communicating with the heat exchange section through the first clutch section, and the second compressor section communicating with the heat exchange section through the second clutch section; the first compressor section and the first clutch section are disposed in the first channel, and the second compressor section and the second clutch section are disposed at the rear end of the first compressor section in the first channel; the heat exchange section is connected to the turbine, and airflow enters the turbine after passing through the heat exchange section. This invention also provides an application of the above-mentioned turbine engine in an aero-engine. In the technical solution provided by this invention, the compressed air from the first or second compressor section can be directed to the turbine through the action of the first and second clutch sections, respectively. The entire device only requires one turbine, resulting in a lighter weight. Simultaneously, it enables directional airflow, eliminating the problem of idling. This invention provides a turbine engine and its application in aero engines, addressing the technical shortcomings of existing reverse cycle engines, such as complex component structures and the impact of partial turbine idling on thrust.
[0066] The technical features of the embodiments described above can be combined arbitrarily. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as the combination of these technical features does not contradict each other, it should be considered within the scope of this specification. Furthermore, other implementation methods can be derived from the above embodiments, allowing for structural and logical substitutions and changes without departing from the scope of this disclosure.
[0067] The embodiments described above are merely illustrative of several implementations of the present invention, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the invention patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these all fall within the protection scope of the present invention. Therefore, the protection scope of this invention patent should be determined by the appended claims.
Claims
1. A turbine engine, characterized in that, The turbine engine includes: a casing, a compressor section, a turbine, a clutch section, and a heat exchange section; The housing includes a first housing and a second housing, the first housing is disposed inside the second housing, the cavity inside the first housing is a first channel, and the cavity between the first housing and the second housing is a second channel; The air compressor section includes a first air compressor section and a second air compressor section, and the clutch section includes a first clutch section and a second clutch section. The first air compressor section is connected to the heat exchange section through the first clutch section, and the second air compressor section is connected to the heat exchange section through the second clutch section. The first air compressor and the first clutch are disposed in the first channel, and the second air compressor and the second clutch are disposed at the rear end of the first air compressor in the first channel; The heat exchange section is connected to the turbine, and the airflow enters the turbine after passing through the heat exchange section; When in low-speed flight, the airflow outside the turbine engine enters the first channel and the first compressor in sequence. The first clutch connects the first compressor to the heat exchange section. The air compressed by the first compressor enters the heat exchange section for heating, and the heated compressed gas enters the turbine for driving. When in high-speed flight, the airflow outside the turbine engine enters the second channel, bypasses the first compressor section, enters the first channel, and then enters the second compressor section. The second clutch section connects the second compressor section with the heat exchange section. The air compressed by the second compressor section enters the heat exchange section for cooling, and the cooled compressed gas enters the turbine for driving.
2. The turbine engine according to claim 1, characterized in that, The heat exchange section is a dual-mode heat exchange section.
3. The turbine engine according to claim 2, characterized in that, The heat exchange section includes: a heat exchange body, a circulation pipeline, a switching valve, and a radiator; The heat exchange body is disposed in the second channel, the heat exchange body can move in the second channel, and the heat exchange body can be connected to the airflow outlet of the first clutch and the airflow outlet of the second clutch respectively; The circulation pipeline is connected to the heat exchange body. The circulation pipeline includes a first pipeline and a second pipeline. The first pipeline is a heating pipeline, and the second pipeline is a cooling pipeline. A circulation medium is provided in the circulation pipeline for heat exchange. The switching valve is used to switch the connection between the heat exchanger body and the first pipeline / second pipeline.
4. The turbine engine according to claim 3, characterized in that, The heat exchange section further includes a blocking block, which is connected to the heat exchange body and is used to prevent airflow from passing through the heat exchange body in the second channel.
5. The turbine engine according to claim 3 or 4, characterized in that, The turbine engine further includes: a flow guide ring, the flow guide ring comprising: a first flow guide ring and a second flow guide ring; The first guide ring is disposed in the first channel, between the airflow outlet of the heat exchange body and the turbine, and the second guide ring is disposed between the heat exchange body and the turbine.
6. The turbine engine according to claim 5, characterized in that, The heat exchanger body is provided with a sealing ring, which is used to prevent gas from the first channel from entering the heat exchanger body.
7. The turbine engine according to claim 6, characterized in that, The sealing ring includes a first sealing ring, a second sealing ring, and a third sealing ring. The first and second sealing rings are disposed at the communication points between the heat exchange body and the first housing at both ends, and the third sealing ring is disposed at the communication point between the heat exchange body and the first guide ring / second guide ring.
8. The turbine engine according to claim 3, characterized in that, The circulating medium is: supercritical fluid and / or liquid metal.
9. The turbine engine according to claim 3 or 8, characterized in that, The first pipeline is equipped with a heat absorption pipe, which is located at the airflow outlet at the tail end of the turbine engine; And / or, A radiator is installed in the second pipeline.
10. An application of a turbine engine as described in any one of claims 1 to 9 in an aircraft engine.