A compressor, a turbine engine and applications thereof

Abstract

The application belongs to the technical field of aircraft manufacturing, and particularly relates to a compressor, a turbine engine and application thereof. The application provides a compressor, which comprises a low-pressure compressor, a high-pressure compressor and a cooling mechanism, the cooling mechanism is arranged between the low-pressure compressor and the high-pressure compressor; the cooling mechanism comprises a connecting ring, a plurality of heat transfer fins and a power part, the power part is connected with the heat transfer fins and drives the opening and / or closing of the heat transfer fins. The application further provides a turbine engine comprising the compressor, and further provides application of the compressor and / or the turbine engine in the field of aircraft. In the application, the cooling mechanism is arranged between the low-pressure compressor and the high-pressure compressor, so that the outlet gas temperature of the compressor is effectively reduced; and the technical defects of the cooling equipment of the turbine engine in the prior art, such as complex structure and high preparation cost, are solved.

Description

Technical Field

[0001] This invention belongs to the field of aircraft manufacturing technology, and in particular relates to a compressor, a turbine engine and their applications. Background Technology

[0002] The pursuit of high-speed aircraft has extremely important military and civilian value. The horizontal takeoff and landing, reusability, and high specific impulse of aero-turbine engines make them a preferred option for aircraft. The upper speed limit of a turbine engine is typically determined by the temperature of the airflow after the compressor.

[0003] In existing technologies, the main methods for cooling the airflow in turbine engines are inlet pre-cooling and compressor intercooling. For example, pre-cooling heat exchangers or water spray devices can lower the turbine inlet temperature to offset the increase in inlet temperature caused by aerodynamic heating during high-speed flight, allowing the turbine to fly at higher speeds. However, both water spraying and heat exchanger systems significantly increase the system complexity and operating costs of the turbine engine. Alternatively, a single-stage centrifugal intermediate-pressure compressor can be installed between the core engine and the axial fan to achieve a higher overall pressure ratio and reduce temperature. Both of these methods suffer from structural complexity and high manufacturing costs.

[0004] Therefore, developing a compressor, a turbine engine, and their applications to address the technical shortcomings of existing turbine engine cooling devices, such as complex structures and high manufacturing costs, 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 turbine engine cooling devices, such as complex structure and high manufacturing cost, and to provide a compressor, turbine engine, and its application.

[0006] This invention provides an air compressor, which includes: a low-pressure air compressor, a high-pressure air compressor, and a cooling mechanism, wherein the cooling mechanism is disposed between the low-pressure air compressor and the high-pressure air compressor;

[0007] The cooling mechanism includes: a connecting ring, a plurality of heat transfer plates and a power unit. The heat transfer plates are mounted on the connecting ring and can be opened and / or closed on the connecting ring. The power unit is connected to the heat transfer plates and drives the heat transfer plates to open and / or close.

[0008] When the heat transfer plate is turned on, the gas passing through the low-pressure compressor passes through the heat transfer plate and then enters the high-pressure compressor.

[0009] In one embodiment, the heat transfer plate is provided with a through hole that passes through the connecting ring.

[0010] In one embodiment, the outer edge of the through hole is provided with meshing teeth, and the meshing teeth of adjacent heat transfer plates overlap.

[0011] In one embodiment, the power unit is connected to any one of the heat transfer plates.

[0012] In one embodiment, the number of heat transfer plates is 50 to 100.

[0013] In one embodiment, the surface of the heat transfer sheet is covered with a thermally conductive coating.

[0014] In one embodiment, the thermally conductive coating is a graphene coating.

[0015] In one embodiment, the heat transfer plate is an aluminum alloy heat transfer plate.

[0016] The present invention also provides a turbine engine, the turbine engine comprising the compressor described in any of the above claims.

[0017] The present invention also provides an application of the compressor and / or the turbine engine described above in the field of aircraft.

[0018] In summary, this invention provides a compressor comprising: a low-pressure compressor, a high-pressure compressor, and a cooling mechanism, wherein the cooling mechanism is disposed between the low-pressure compressor and the high-pressure compressor. The cooling mechanism includes: a connecting ring, a plurality of heat transfer plates, and a power unit. The heat transfer plates are mounted on the connecting ring and are openable and / or closeable on the connecting ring. The power unit is connected to the heat transfer plates, driving the opening and / or closing of the heat transfer plates. When the heat transfer plates are open, the gas passing through the low-pressure compressor passes through the heat transfer plates before entering the high-pressure compressor. This invention also provides a turbine engine including the above-described compressor, and further provides an application of the above-described compressor and / or the above-described turbine engine in the field of aircraft. In the technical solution provided by this invention, by providing a cooling mechanism between the low-pressure compressor and the high-pressure compressor, the outlet temperature of the compressor is effectively reduced; simultaneously, the added cooling mechanism has a simple structure and does not increase the manufacturing cost of the compressor. The present invention provides a compressor, a turbine engine and its application, which solves the technical defects of existing turbine engine cooling devices, which have complex structures and high manufacturing costs. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of a compressor provided by an embodiment of the present invention, in which a heat transfer plate is installed on a connecting ring;

[0020] Figure 2This is a schematic diagram of the structure of a heat transfer plate in a compressor provided by an embodiment of the present invention;

[0021] Figure 3 A schematic diagram of the compressor installation structure in the technical solution provided by the embodiments of the present invention;

[0022] Figure 4 This is a schematic diagram of the cooling mechanism in a compressor provided by an embodiment of the present invention;

[0023] Figure 5 This invention provides a schematic diagram of the cooling mechanism in a compressor under high-speed and high-temperature conditions, as provided in an embodiment of the invention.

[0024] Figure 6 This invention provides a schematic diagram of the cooling mechanism in a compressor under low-speed and low-temperature conditions, as provided in an embodiment of the invention.

[0025] The components include a cooling mechanism 1, a heat transfer plate 11, a through hole 111, a connecting ring 12, a low-pressure compressor 2, a high-pressure compressor 3, an inner channel 4, and an outer channel 5. Detailed Implementation

[0026] This invention provides a compressor, a turbine engine, and their applications to address the technical shortcomings of existing turbine engine cooling devices, which suffer from complex structures and high manufacturing costs.

[0027] 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.

[0028] 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.

[0029] 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.

[0030] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an 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.

[0031] 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.

[0032] 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.

[0033] Please see Figure 1 , Figure 3 and Figure 4This invention provides a compressor, including a low-pressure compressor 2, a high-pressure compressor 3, and a cooling mechanism 1. The cooling mechanism 1 is disposed between the low-pressure compressor 2 and the high-pressure compressor 3. The cooling mechanism 1 includes a connecting ring 12, a plurality of heat transfer plates 11, and a power unit. The heat transfer plates 11 are mounted on the connecting ring 12 and can be opened and / or closed on the connecting ring 12. The power unit is connected to the heat transfer plates 11 and drives the heat transfer plates 11 to open and / or close. When the heat transfer plates 11 are open, the gas passing through the low-pressure compressor 2 passes through the heat transfer plates 11 and then enters the high-pressure compressor 3. This invention provides a compressor, a turbine engine, and their application, which solves the technical defects of existing turbine engine cooling devices, such as complex structure and high manufacturing cost.

[0034] Please refer to this section for further information. Figure 5 and Figure 6 In the technical solution provided by the embodiment of the present invention, the connecting ring 12 of the cooling mechanism 1 is equipped with a plurality of heat transfer plates 11. When the heat transfer plates 11 are turned on, that is, when the corresponding speed is high, the heat transfer plates 11 are in a "vertical" state in the axial direction. At this time, the gas flowing out from the low-pressure compressor 2 will exchange heat through the heat transfer plates 11. After heat exchange with the heat transfer plates 11, the cooled gas enters the high-pressure compressor 3, so that the temperature of the airflow passing through the compressor is effectively reduced.

[0035] When there is no need to cool the gas, i.e. when the corresponding velocity is low, the heat transfer plate 11 is in a closed state. At this time, the heat transfer plate 11 is in a "flat" state in the axial direction. The "flat" heat transfer plate 11 forms a corresponding cavity in the airflow channel. At this time, the airflow passes directly through the cavity without exchanging heat with the heat transfer plate 11.

[0036] In the technical solution provided by this embodiment of the invention, the heat transfer plate 11 is connected to the power unit. The power unit provides power for the opening and / or closing of the heat transfer plate 11 through system control. In practical applications, the power unit can be controlled to open and / or close based on the monitoring of airflow temperature and / or speed. The power source and control of the power unit are both prior art well known to those skilled in the art, and will not be described in detail here.

[0037] By adding a cooling mechanism 1 between the low-pressure compressor 2 and the high-pressure compressor 3, the temperature of the airflow can be reduced after passing through the compressor. The added cooling mechanism 1 has the advantages of simple structure and easy and readily available preparation, and can be widely used.

[0038] Please see here. Figure 2To further optimize the technical solution and simplify the installation mechanism of the cooling mechanism 1, while ensuring effective cooling and heat transfer, the assembly difficulty and manufacturing cost of the cooling mechanism 1 are reduced. In a compressor provided by this embodiment of the invention, the heat transfer plate 11 is provided with a through hole 111, through which the connecting ring 12 passes. After the through hole 111 passes through the connecting ring 12, the assembly of the heat transfer plate 11 and the connecting ring 12 can be completed. The assembly structure is simple, highly stable, and not prone to separation or detachment.

[0039] In practical applications, the connecting ring 12 can be installed on the compressor wall. At this time, part of the heat transfer plate 11 is located inside the compressor's airflow channel (also known as the "inner channel 4"), while the other part is located outside the compressor's airflow channel (also known as the "outer bypass channel 5"). The gas in the inner channel 4, after compression, has a higher temperature. When it exchanges heat with the heat transfer plate 11, the heat transfer plate 11 can promptly transfer the heat to the outer bypass channel 5, further improving heat exchange efficiency and achieving a better cooling effect on the airflow.

[0040] To further optimize the technical solution, in the embodiment of the present invention, the outer edge of the through hole 111 is provided with meshing teeth, and the meshing teeth of adjacent heat transfer plates 11 overlap. After the meshing teeth of adjacent heat transfer plates 11 overlap, as long as any one of the heat transfer plates 11 changes its position state under the drive of the power unit (i.e., from open to closed, or from closed to open), the rotation of the meshing teeth can drive the adjacent heat transfer plates 11 to move and change their position state. This realizes rapid change of the position and shape of the heat transfer plates 11, effectively improving the cooling efficiency and optimizing the cooling effect.

[0041] In the technical solution provided by this embodiment of the invention, the power unit is connected to any one of the heat transfer plates 11. By setting the meshing teeth, it is only necessary to connect the power unit to any one of the heat transfer plates 11, which further effectively reduces the assembly complexity of the cooling mechanism 1 and simplifies the installation structure of the cooling mechanism 1.

[0042] Based on actual cooling requirements and taking into account the design concept of simplifying installation space and installation structure, the number of heat transfer plates 11 in the compressor provided in this embodiment of the invention is 50 to 100.

[0043] In actual product applications, to effectively expand the heat exchange area while considering the actual installation space, the heat transfer fin 11 is generally a long rectangular structure. Furthermore, to ensure proper installation and fixation of the connecting ring 12 and better fit to the mounting surface, the heat transfer fin 11 is bent at a certain angle in an S-shape at the through hole 111. Further details can be found in [reference needed]. Figure 2 The display in the middle.

[0044] In order to effectively optimize the cooling effect of the heat transfer plate 11, improve the cooling efficiency, accelerate the heat transfer speed on the surface of the heat transfer plate 11, and enhance the heat transfer capability on the surface of the heat transfer plate 11, the surface of the heat transfer plate 11 is covered with a thermally conductive coating in the technical solution provided in this embodiment of the invention.

[0045] To further optimize the technical solution, and to better bond the thermally conductive coating to the surface of the heat transfer plate 11, the thermally conductive coating is a graphene coating. The graphene coating also has the advantages of good heat transfer performance, low cost, and high stability.

[0046] In a compressor provided by an embodiment of the present invention, the heat transfer plate 11 is an aluminum alloy heat transfer plate. The aluminum alloy heat transfer plate has the advantages of being lightweight and having high thermal conductivity. At the same time, it is inexpensive and suitable for large-scale application.

[0047] The present invention also provides a turbine engine including any of the above compressors. Actual calculations show that the turbine engine equipped with the above compressors can increase its maximum flight speed by 30% to 50%.

[0048] The compressor and / or turbine engine provided by this invention can be widely applied in the field of aircraft. Installing a turbine engine with the aforementioned compressor on an aircraft fuselage has the advantages of simple structure and easy modification, without significantly increasing the complexity of the installation structure, and is inexpensive, thus enabling its widespread application.

[0049] In summary, this invention provides a compressor comprising: a low-pressure compressor, a high-pressure compressor, and a cooling mechanism, wherein the cooling mechanism is disposed between the low-pressure compressor and the high-pressure compressor. The cooling mechanism includes: a connecting ring, a plurality of heat transfer plates, and a power unit. The heat transfer plates are mounted on the connecting ring and are openable and / or closeable on the connecting ring. The power unit is connected to the heat transfer plates, driving the opening and / or closing of the heat transfer plates. When the heat transfer plates are open, the gas passing through the low-pressure compressor passes through the heat transfer plates before entering the high-pressure compressor. This invention also provides a turbine engine including the above-described compressor, and further provides an application of the above-described compressor and / or the above-described turbine engine in the field of aircraft. In the technical solution provided by this invention, by providing a cooling mechanism between the low-pressure compressor and the high-pressure compressor, the outlet temperature of the compressor is effectively reduced; simultaneously, the added cooling mechanism has a simple structure and does not increase the manufacturing cost of the compressor. The present invention provides a compressor, a turbine engine and its application, which solves the technical defects of existing turbine engine cooling devices, which have complex structures and high manufacturing costs.

[0050] 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.

[0051] 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 compressor, characterized in that, The compressor includes: a low-pressure compressor, a high-pressure compressor, and a cooling mechanism, wherein the cooling mechanism is disposed between the low-pressure compressor and the high-pressure compressor; The cooling mechanism includes: a connecting ring, a plurality of heat transfer plates and a power unit. The heat transfer plates are mounted on the connecting ring and can be opened and / or closed on the connecting ring. The power unit is connected to the heat transfer plates and drives the heat transfer plates to open and / or close. When the heat transfer plate is turned on, the gas passing through the low-pressure compressor passes through the heat transfer plate and then enters the high-pressure compressor.

2. The compressor according to claim 1, characterized in that, The heat transfer plate has a through hole that passes through the connecting ring.

3. The compressor according to claim 2, characterized in that, The outer edge of the through hole is provided with meshing teeth, and the meshing teeth of adjacent heat transfer plates overlap.

4. The compressor according to claim 3, characterized in that, The power unit is connected to any one of the heat transfer plates.

5. The compressor according to claim 4, characterized in that, The number of heat transfer plates is 50 to 100.

6. The compressor according to claim 4, characterized in that, The surface of the heat transfer plate is covered with a thermally conductive coating.

7. The compressor according to claim 6, characterized in that, The thermally conductive coating is a graphene coating.

8. The compressor according to claim 6 or 7, characterized in that, The heat transfer plate is an aluminum alloy heat transfer plate.

9. A turbine engine, characterized in that, The turbine engine includes the compressor as described in any one of claims 1 to 8.

10. An application of a compressor comprising any one of claims 1 to 8 and / or a turbine engine comprising claim 9 in the field of aircraft.

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