Compressor, turbine engine, and application thereof

Abstract

Provided are a compressor, a turbine engine, and an application thereof, relating to the technical field of aircraft manufacturing. The compressor comprises: a low-pressure compressor (2), a high-pressure compressor (3), and a cooling mechanism (1). The cooling mechanism (1) is arranged between the low-pressure compressor (2) and the high-pressure compressor (3); the cooling mechanism (1) comprises a connection ring (12), a plurality of heat transfer pieces (11), and a power portion; and the power portion is connected to the heat transfer pieces (11) to drive the heat transfer pieces (11) to open and / or close. The cooling mechanism (1) is arranged between the low-pressure compressor (2) and the high-pressure compressor (3), thereby effectively reducing the gas output temperature of the compressor; and the present invention overcomes the technical defects in the prior art of a complex structure and high manufacturing costs of a cooling device of a turbine engine.

Description

Compressor, turbine engine and applications thereof

[0001] This disclosure claims priority from the Chinese patent application filed with the State Intellectual Property Office of China on August 15, 2023, with application number 202311027266.0 and application name “A compressor, a turbine engine and its application”, all contents of which are disclosed in this text by reference. Technical Field

[0002] The present invention belongs to the technical field of aircraft manufacturing, and in particular relates to a compressor, a turbine engine and applications thereof. Background Art

[0003] High-speed aircraft have extremely important military and civilian applications. Aviation turbine engines, with their horizontal takeoff and landing capabilities, reusability, and high specific impulse, are 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.

[0004] In the existing technology, there are two main methods for cooling the airflow of turbine engines: inlet pre-cooling or compressor inter-cooling. For example, the turbine inlet temperature is reduced through a pre-cooling heat exchanger or water spray device to offset the increase in inlet temperature caused by the aerodynamic heating effect during high-speed flight, allowing the turbine to fly at higher speeds. Whether using water spray or a heat exchanger system, it greatly increases the system complexity of the turbine engine and increases the cost of use. Alternatively, by setting a single-stage centrifugal intermediate pressure compressor between the core engine and the axial flow fan, a higher total pressure ratio can be obtained to reduce the temperature. Both of the above methods have the problems of complex structure and high preparation cost.

[0005] Therefore, a compressor, a turbine engine and their applications have been developed to solve the technical defects of the existing technology, such as the complex structure and high preparation cost of the cooling equipment of the turbine engine, which has become an urgent problem to be solved by technical personnel in this field.

[0006] Summary of the Invention

[0007] Based on this, it is necessary to provide a compressor, a turbine engine and their applications in view of the technical defects of the existing technology, such as the complex structure and high preparation cost of the cooling equipment of the turbine engine.

[0008] The present invention provides a compressor, comprising: a low-pressure compressor, a high-pressure compressor, and a cooling mechanism, wherein the cooling mechanism is arranged between the low-pressure compressor and the high-pressure compressor;

[0009] 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 to drive the heat transfer plates to open and / or close.

[0010] When the heat transfer plate is opened, the gas passing through the low-pressure compressor passes through the heat transfer plate and then enters the high-pressure compressor.

[0011] In one embodiment, the heat transfer plate is provided with a through hole, and the through hole passes through the connecting ring.

[0012] In one embodiment, meshing teeth are provided on the outer edges of the through holes, and the meshing teeth of adjacent heat transfer plates overlap.

[0013] In one embodiment, the power unit is connected to any one of the heat transfer sheets.

[0014] In one embodiment, the number of the heat transfer sheets is 50 to 100 sheets.

[0015] In one embodiment, the surface of the heat transfer sheet is covered with a thermal conductive coating.

[0016] In one embodiment, the thermally conductive coating is a graphene coating.

[0017] In one embodiment, the heat transfer plate is an aluminum alloy heat transfer plate.

[0018] The present invention also provides a turbine engine, comprising the compressor described in any one of the above.

[0019] The present invention also provides an application of any one of the above compressors and / or turbine engines in the field of aircraft.

[0020] In summary, the present invention provides a compressor comprising: a low-pressure compressor, a high-pressure compressor, and a cooling mechanism, the cooling mechanism being disposed between the low-pressure and high-pressure compressors. The cooling mechanism comprises: a connecting ring, a plurality of heat transfer fins, and a power unit. The heat transfer fins 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 fins to drive the opening and / or closing of the heat transfer fins. When the heat transfer fins are open, gas passing through the low-pressure compressor passes through the heat transfer fins before entering the high-pressure compressor. The present invention also provides a turbine engine comprising the above-described compressor, and further provides an application of the above-described compressor and / or turbine engine in the field of aircraft. In the technical solution provided by the present invention, by disposing the cooling mechanism between the low-pressure and high-pressure compressors, the outlet temperature of the compressor is effectively reduced. Furthermore, the added cooling mechanism has a simple structure and does not increase the cost of compressor production. The present invention provides a compressor, a turbine engine and applications thereof, which solve the technical defects of the prior art in that the cooling equipment of the turbine engine has a complex structure and high preparation cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are merely embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying any creative work.

[0022] FIG1 is a schematic structural diagram of a compressor provided by an embodiment of the present invention, in which a heat transfer plate is installed on a connecting ring;

[0023] FIG2 is a schematic structural diagram of a heat transfer plate in a compressor provided by an embodiment of the present invention;

[0024] FIG3 is a schematic diagram of the installation structure of the compressor in the technical solution provided by an embodiment of the present invention;

[0025] FIG4 is a schematic structural diagram of a cooling mechanism in a compressor provided by an embodiment of the present invention;

[0026] FIG5 is a schematic structural diagram of a cooling mechanism in a compressor under high-speed and high-temperature conditions provided by an embodiment of the present invention;

[0027] FIG6 is a schematic structural diagram of a cooling mechanism in a compressor provided by an embodiment of the present invention at a low speed and low temperature state;

[0028] Among them, the cooling mechanism 1, the heat transfer plate 11, the through hole 111, the connecting ring 12, the low-pressure compressor 2, the high-pressure compressor 3, the inner channel 4 and the outer channel 5;

[0029] Among them, Figure 1 is designated as the abstract figure. DETAILED DESCRIPTION

[0030] The embodiments of the present invention provide a compressor, a turbine engine and applications thereof, which are used to solve the technical defects of the prior art in that the cooling equipment of the turbine engine has a complex structure and high preparation cost.

[0031] To make the above-mentioned objects, features, and advantages of the present invention more readily apparent, specific embodiments of the present invention are described in detail below with reference to the accompanying drawings. The following description sets forth numerous specific details to facilitate a full understanding of the present invention. However, the present invention can be implemented in many other ways than those described herein, and those skilled in the art may make similar modifications without departing from the scope of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0032] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0033] 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 the technical features being referred to. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "plurality" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0034] In the present invention, unless otherwise specified or limited, the terms "installed," "connected," "connect," "fixed," etc. should be understood in a broad sense. For example, they can refer to fixed connection, detachable connection, or integration; mechanical connection, electrical connection; direct connection, or indirect connection through an intermediate medium; internal communication between two components, or interaction between two components, unless otherwise specified. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0035] In the present invention, unless otherwise expressly specified or limited, when a first feature is "above" or "below" a second feature, it may mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediary. Furthermore, when a first feature is "above," "above," or "above" a second feature, it may mean that the first feature is directly above or diagonally above the second feature, or simply means that the first feature is at a higher level than the second feature. When a first feature is "below," "below," or "below" a second feature, it may mean that the first feature is directly below or diagonally below the second feature, or simply means that the first feature is at a lower level than the second feature.

[0036] It should be noted that when an element is referred to as being "fixed to" or "disposed on" another element, it may be directly on the other element or there may be an intermediate element. When an element is considered to be "connected to" another element, it may be directly connected to the other element or there may be an intermediate 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 implementation methods.

[0037] Referring to Figures 1, 3, and 4, an embodiment of the present invention provides a compressor comprising: 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 comprises: a connecting ring 12, a plurality of heat transfer fins 11, and a power unit. The heat transfer fins 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 fins 11 to drive the opening and / or closing of the heat transfer fins 11. When the heat transfer fins 11 are opened, gas passing through the low-pressure compressor 2 passes through the heat transfer fins 11 before entering the high-pressure compressor 3. The compressor, turbine engine, and applications thereof provided by the embodiments of the present invention address the technical deficiencies in prior art turbine engine cooling equipment, which suffer from complex structures and high manufacturing costs.

[0038] Please refer to Figures 5 and 6 for further information. In the technical solution provided by the embodiment of the present invention, a plurality of heat transfer fins 11 are installed on the connecting ring 12 of the cooling mechanism 1. When the heat transfer fins 11 are open, i.e., when the corresponding speed is high, the heat transfer fins 11 are in an axially "erect" state. At this time, the gas flowing out of the low-pressure compressor 2 will pass through the heat transfer fins 11 for heat exchange. After heat exchange with the heat transfer fins 11, the cooled gas enters the high-pressure compressor 3, effectively reducing the temperature of the airflow passing through the compressor.

[0039] When there is no need to cool the gas, that is, when the corresponding speed is low, the heat transfer plate 11 is in a closed state. At this time, the heat transfer plate 11 is in a "lying flat" state in the axial direction. The "lying flat" heat transfer plate 11 forms a corresponding cavity in the air flow channel. At this time, the air flow passes directly through the cavity without exchanging heat with the heat transfer plate 11.

[0040] In the technical solution provided by the embodiments of the present invention, heat transfer plate 11 is connected to a power unit, which, under system control, provides power for opening and / or closing heat transfer plate 11. In actual use, the power unit can be instructed to open and / or close heat transfer plate 11 based on monitored airflow temperature and / or airflow velocity. The power source and control of the power unit are well known to those skilled in the art and will not be further described here.

[0041] By adding a cooling mechanism 1 between the low-pressure compressor 2 and the high-pressure compressor 3, the temperature of the air flow can be reduced after passing through the compressor. The added cooling mechanism 1 has the advantages of simple structure, easy preparation and availability, and can be widely used.

[0042] Referring to Figure 2 , a further optimized technical solution is presented. To further simplify the installation mechanism of cooling mechanism 1, while ensuring effective cooling and heat transfer, and reducing the assembly difficulty and manufacturing cost of cooling mechanism 1, an embodiment of the present invention provides a compressor in which heat transfer plate 11 is provided with a through hole 111, which passes through connecting ring 12. Once through hole 111 passes through connecting ring 12, assembly of heat transfer plate 11 and connecting ring 12 is complete, resulting in a simple and stable transfer structure that is less susceptible to separation or disengagement.

[0043] In actual use, the connecting ring 12 can be mounted on the wall of the compressor. In this case, part of the heat transfer plate 11 is located in the airflow channel inside the compressor (also known as the "inner channel 4"), while the other part of the heat transfer plate 11 is located in the airflow channel outside the compressor (also known as the "outer channel 5"). After compression, the gas in the inner channel 4 has a high temperature. After exchanging heat with the heat transfer plate 11, the heat transfer plate 11 can promptly transfer the heat to the outer channel 5, further improving the heat exchange efficiency and achieving a better cooling effect on the airflow.

[0044] To further optimize the technical solution, in the technical solution provided by 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 (i.e., from open to closed, or from closed to open) under the drive of the power unit, the rotation of the meshing teeth can drive the adjacent heat transfer plates 11 to move and change their position. This achieves rapid changes in the position and shape of the heat transfer plates 11, effectively improving the cooling efficiency and optimizing the cooling effect.

[0045] In the technical solution provided by the embodiment of the present invention, the power unit is connected to any one of the heat transfer plates 11. By providing the meshing teeth, it is only necessary to connect the power unit to any one of the heat transfer plates 11, further effectively reducing the assembly complexity of the cooling mechanism 1 and simplifying the installation structure of the cooling mechanism 1.

[0046] According to actual cooling requirements and taking into account the design concept of simplifying the installation space and the installation structure, in a compressor provided by an embodiment of the present invention, the number of heat transfer fins 11 is 50 to 100.

[0047] In actual product development, to effectively expand the heat exchange area while taking into account the actual installation space, the heat transfer fin 11 is generally shaped like a long rectangular structure. Furthermore, to facilitate the installation and fixation of the connecting ring 12 and to better fit the installation surface, the heat transfer fin 11 is bent in an S-shape at a certain angle at the through hole 111. For details, please refer to FIG. 2 .

[0048] 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 ability on the surface of the heat transfer plate 11, in the technical solution provided by the embodiment of the present invention, the surface of the heat transfer plate 11 is covered with a thermal conductive coating.

[0049] To further optimize the technical solution, in order to better laminate the thermal conductive coating with the surface of the heat transfer plate 11, the thermal conductive coating is a graphene coating. The graphene coating also has the advantages of good heat transfer effect, low cost and high stability.

[0050] 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 light weight and high thermal conductivity. At the same time, it is low in cost and suitable for large-scale promotion and application.

[0051] The present invention also provides a turbine engine comprising any one of the above compressors. Actual calculations show that the maximum flight speed of a turbine engine equipped with the above compressor can be increased by 30% to 50%.

[0052] The compressor and / or turbine engine provided by the present invention can be widely used in the field of aircraft; the turbine engine equipped with the compressor is installed on the aircraft body, which has the advantages of simple structure and easy modification, does not significantly increase the complexity of the installation structure, has low cost, and can be widely used.

[0053] In summary, the present invention provides a compressor comprising: a low-pressure compressor, a high-pressure compressor, and a cooling mechanism, the cooling mechanism being disposed between the low-pressure and high-pressure compressors. The cooling mechanism comprises: a connecting ring, a plurality of heat transfer fins, and a power unit. The heat transfer fins 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 fins to drive the opening and / or closing of the heat transfer fins. When the heat transfer fins are open, gas passing through the low-pressure compressor passes through the heat transfer fins before entering the high-pressure compressor. The present invention also provides a turbine engine comprising the above-described compressor, and further provides an application of the above-described compressor and / or turbine engine in the field of aircraft. In the technical solution provided by the present invention, by disposing the cooling mechanism between the low-pressure and high-pressure compressors, the outlet temperature of the compressor is effectively reduced. Furthermore, the added cooling mechanism has a simple structure and does not increase the cost of compressor production. The present invention provides a compressor, a turbine engine and applications thereof, which solve the technical defects of the prior art in that the cooling equipment of the turbine engine has a complex structure and high preparation cost.

[0054] The technical features of the above-described embodiments may be combined in any manner. To simplify the description, not all possible combinations of the technical features in the above-described embodiments are described. However, as long as there are no conflicts in the combination of these technical features, they should be considered to be within the scope of this specification. Furthermore, other implementations can be derived from the above-described embodiments, allowing for structural and logical substitutions and changes without departing from the scope of this disclosure.

[0055] The above-described embodiments merely illustrate several implementations of the present invention, and while their descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the patent. It should be noted that a person skilled in the art would be able to make numerous variations and improvements without departing from the spirit of the present invention, all of which fall within the scope of protection of the present invention. Therefore, the scope of protection of the patent for this invention shall be determined by the appended claims.

Claims

1. A compressor, characterized in that: The compressor comprises: a low-pressure compressor, a high-pressure compressor and a cooling mechanism, wherein 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 sheets and a power unit, wherein the heat transfer sheets are mounted on the connecting ring, the heat transfer sheets can be opened and / or closed on the connecting ring, and the power unit is connected to the heat transfer sheets to drive the heat transfer sheets to be opened and / or closed; When the heat transfer plate is opened, 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 is provided with a through hole, and the through hole 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 sheets.

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

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

7. The compressor according to claim 6, characterized in that: The thermal 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 comprises the compressor according to any one of claims 1 to 8.

10. Use of the compressor according to any one of claims 1 to 8 and / or the turbine engine according to claim 9 in the field of aircraft.

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