Core engine of an aero-engine and aero-engine

Abstract

The application discloses an aero-engine core and an aero-engine. The aero-engine core comprises a compressor, an air guide pipe and an exhaust device. The compressor comprises a gas collection cavity. The air guide pipe has an air inlet end and an air outlet end, and the air inlet end is arranged in the gas collection cavity to guide the gas in the gas collection cavity out. The exhaust device is arranged at the air outlet end of the air guide pipe. The exhaust device comprises an exhaust plate. The exhaust plate has a plurality of exhaust holes. The aero-engine core of the application leads out the air guide pipe at the gas collection cavity of the compressor to discharge the gas during starting, thereby improving the surge problem of the engine during starting. Moreover, the exhaust device is arranged at the air outlet end of the air guide pipe, and the exhaust device is provided with the exhaust plate having a plurality of exhaust holes, so that the gas needs to flow out through the plurality of exhaust holes, thereby avoiding the adverse effect caused by the direct impact of high-temperature and high-speed gas on electronic components.

Description

Technical Field

[0001] This invention relates to the field of aviation technology, and in particular to a core engine of an aircraft engine and an aircraft engine. Background Technology

[0002] The core components of an aero engine include a fan, compressor, combustion chamber, and turbine. During startup, the electric motor drives the fan to rotate. At this time, the work done by the fan blades causes the air pressure in the internal combustion chamber to become very high, which can lead to engine surge during startup.

[0003] It should be noted that the statements in this background section only provide background information related to the present invention and do not necessarily constitute prior art. Summary of the Invention

[0004] This invention provides a core engine and an aero-engine to improve the surge problem of the engine during startup.

[0005] The first aspect of this invention provides a core mechanism for an aero-engine, comprising:

[0006] Air compressor, including the air collection chamber;

[0007] The air intake pipe has an inlet end and an outlet end, with the inlet end located inside the air collecting chamber to draw out the gas from the chamber; and

[0008] An exhaust device is provided at the exhaust end of the air intake pipe, and the exhaust device includes an exhaust plate having multiple exhaust holes.

[0009] In some embodiments, the exhaust device includes at least two exhaust plates arranged sequentially in the direction of gas flow.

[0010] In some embodiments, at least two exhaust plates include a first exhaust plate and a second exhaust plate, the first exhaust plate including a columnar panel, the second exhaust plate including a hemispherical panel, and the second exhaust plate covering the outside of the first exhaust plate.

[0011] In some embodiments, the column panel includes an open end communicating with an air intake pipe, a bottom wall and a side wall disposed opposite to the open end, the side wall and the bottom wall being smoothly connected, the bottom wall being provided with a plurality of exhaust holes, and the side wall being provided with a plurality of exhaust holes.

[0012] In some embodiments, the exhaust device further includes a connecting pipe, a first end of which is connected to an air intake pipe, and a second end of which is connected to a column panel. The connecting pipe is a columnar pipe, and the radius of the column panel is smaller than the radius of the connecting pipe.

[0013] In some embodiments, the radius of the hemispherical panel is equal to the radius of the connecting tube.

[0014] In some embodiments, the exhaust plate includes a curved panel.

[0015] In some embodiments, the curved panel is a spherical panel.

[0016] In some embodiments, the curved panel includes a column panel.

[0017] In some embodiments, the core unit further includes a casing and an outer casing disposed outside the casing, a compressor disposed inside the casing, and an exhaust end of an air intake pipe extending into a cavity between the casing and the outer casing.

[0018] A second aspect of the present invention provides an aircraft engine, including the aforementioned core engine.

[0019] Based on the aspects provided by this invention, the core of the aero-engine of this invention includes a compressor, a bleed air pipe, and an exhaust device. The compressor includes a gas collection chamber. The bleed air pipe has an inlet end and an outlet end, with the inlet end disposed within the gas collection chamber to draw gas out of the chamber. The exhaust device is disposed at the outlet end of the bleed air pipe. The exhaust device includes an exhaust plate. The exhaust plate has multiple exhaust holes. The core of this invention improves the engine surge problem during startup by extending a bleed air pipe from the gas collection chamber of the compressor for venting during startup. Furthermore, the exhaust device, which has an exhaust plate with multiple exhaust holes at the outlet end of the bleed air pipe, ensures that the gas flows out dispersedly through multiple exhaust holes, preventing high-temperature, high-speed gas from directly impacting electronic components and causing adverse effects.

[0020] Other features and advantages of the invention will become clear from the following detailed description of exemplary embodiments of the invention with reference to the accompanying drawings. Attached Figure Description

[0021] The accompanying drawings, which are included to provide a further understanding of the invention and form part of this application, illustrate exemplary embodiments of the invention and, together with their description, serve to explain the invention and do not constitute an undue limitation thereof. In the drawings:

[0022] Figure 1 This is a partial structural diagram of an aero-engine according to an embodiment of the present invention.

[0023] Figure 2 This is a three-dimensional structural diagram of the exhaust device according to an embodiment of the present invention.

[0024] Figure 3 for Figure 2 The diagram shows a top view of the exhaust system.

[0025] Figure 4 for Figure 2 The diagram shows a rear view of the exhaust system.

[0026] Figure 5 for Figure 2 The diagram shows a partial exploded view of the exhaust device.

[0027] Figure 6 for Figure 5 A schematic diagram of the structure of the first and second exhaust plates. Detailed Implementation

[0028] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the present invention or its application or use. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0029] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the invention. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following drawings denote similar items; therefore, once an item is defined in one drawing, it need not be further discussed in subsequent drawings.

[0030] For ease of description, spatial relative terms such as "above," "over," "on the upper surface of," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation beyond the orientation of the device as described in the figures. For example, if the device in the figures were inverted, a device described as "above" or "above" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways, and the spatial relative descriptions used herein will be interpreted accordingly.

[0031] like Figure 1 As shown, the aero-engine includes an outer bypass duct A and an inner bypass duct B, with a compressor 20 and a turbine 40 arranged inside the inner bypass duct B.

[0032] In some embodiments, the core unit further includes a casing and a housing disposed outside the casing. The compressor 20 is disposed within the casing.

[0033] To improve engine surge during startup, it is necessary to bleed gas from the engine's internal combustion chamber B. One method is to extend a bleed pipe 30 from the compressor 20's intake chamber for bleed gas release during startup. Specifically, the exhaust end of the bleed pipe extends into the cavity between the casing and the outer shell. The gas discharged from this bleed pipe 30 enters the cavity between the core engine's casing and the outer shell. Since various sensors, control devices, and other electronic components are typically housed in this cavity, the high-temperature, high-speed gas discharged from the bleed pipe 30 can adversely affect these electronic components.

[0034] To address this issue, in some embodiments, reference is made to... Figure 1 The core of the aero-engine provided in this embodiment of the invention includes a compressor 20, a bleed pipe 30, and an exhaust device 10. The compressor 20 includes a gas collecting chamber. The bleed pipe 30 has an inlet end and an exhaust end, with the inlet end disposed within the gas collecting chamber to draw gas out of the chamber. The exhaust device 10 is disposed at the exhaust end of the bleed pipe 30. (Reference) Figures 2 to 6 The exhaust device 10 includes an exhaust plate. The exhaust plate has multiple exhaust holes.

[0035] The core unit of this invention is equipped with an exhaust device 10 at the exhaust end of the exhaust pipe 30. The exhaust device 10 is equipped with an exhaust plate with multiple exhaust holes, so that the gas needs to be dispersed out through multiple exhaust holes, avoiding the adverse effects caused by high temperature and high speed gas directly impacting electronic components.

[0036] In some embodiments, reference Figure 5 The exhaust device 10 includes at least two exhaust plates arranged sequentially in the direction of gas flow. Thus, when the high-temperature, high-speed gas is discharged from the exhaust end of the exhaust pipe 30, it needs to pass through at least two exhaust plates sequentially to reduce the airflow speed. Figure 5 An exemplary exhaust device 10 includes two exhaust plates arranged sequentially in the gas flow direction.

[0037] refer to Figure 5In some embodiments, at least two exhaust plates include a first exhaust plate 13 and a second exhaust plate 14. The first exhaust plate 13 includes a cylindrical panel. The second exhaust plate 14 includes a hemispherical panel, which covers the outside of the cylindrical panel. This arrangement allows high-temperature, high-speed gas to first enter the cavity of the hemispherical panel through exhaust holes on the cylindrical panel, and then exit into the cavity between the core machine's casing and the outer shell through exhaust holes on the hemispherical panel. The two-layer exhaust plate arrangement reduces the gas velocity. Moreover, as... Figure 6 As shown, the spherical panel allows gas to flow out in multiple directions, thus preventing high-speed, high-temperature airflow from directly impacting sensitive areas within the cavity between the core unit's casing and the outer shell. Furthermore, because the gas passes through two exhaust plates within the exhaust device 10, the gas mixes more thoroughly during flow, resulting in a more uniform gas temperature.

[0038] In some embodiments, reference Figure 5 and Figure 6 The column panel includes an open end communicating with the air intake pipe 30, a bottom wall 132 opposite to the open end, and a side wall 131. The side wall 131 and the bottom wall 132 are smoothly connected. Multiple exhaust holes are provided on the bottom wall 132, and multiple exhaust holes are provided on the side wall 131. That is, in some embodiments, the column panel encloses a cylindrical cavity, allowing the gas to be fully mixed after entering the cavity before being discharged from the exhaust holes of the bottom wall 132 and the side wall 131. Furthermore, the flow directions of the gas flowing from the bottom wall 132 and the gas flowing from the side wall 131 are different.

[0039] In some embodiments, no vent is provided at the connection between the side wall 131 and the bottom wall 132. Specifically, as shown in the figure... Figure 5 As shown, no exhaust vents are provided at the edge of the side wall 131 or at the edge of the bottom wall 132 near the side wall 131. This further makes the flow direction of the gas flowing out from the bottom wall 132 different from that of the gas flowing out from the side wall 131, making the flow direction of the gas flowing into the cavity between the casing and the outer shell more dispersed.

[0040] In some other embodiments not shown in the accompanying drawings, the exhaust device may have only one exhaust plate. This exhaust plate includes a curved panel. The curved panel increases the total gas flow area and allows the gas to flow in different directions. The curved panel can be a spherical panel. It can also be a cylindrical panel. In other embodiments, the exhaust device includes two exhaust plates, both of which can be cylindrical panels, or both can be spherical panels, or other curved shapes.

[0041] This invention also provides an aero engine, including the aforementioned core engine.

[0042] The following is based on Figures 1 to 6The structure of the core machine in a specific embodiment of the present invention will be described in detail.

[0043] like Figure 1 As shown, the core unit includes a compressor 20, an air intake pipe 30, and an exhaust device 10.

[0044] like Figures 2 to 6 As shown, the exhaust device 10 includes a fixing clamp 11, a connecting pipe 12, a first exhaust plate 13, and a second exhaust plate 14. The fixing clamp 11 is fixedly disposed on the outside of the connecting pipe 12 for connection with external components to fix the exhaust device 10. The first end of the connecting pipe 12 is connected to the air intake pipe 30, and the second end of the connecting pipe 12 is connected to the first exhaust plate 13. The second exhaust plate 14 covers the outside of the first exhaust plate 13.

[0045] Specifically, the connecting pipe 12 is a cylindrical pipe. The first exhaust plate 13 is a cylindrical plate. The radius of the connecting pipe 12 is larger than the radius of the cylindrical plate. For example... Figure 5 As shown, a through hole is provided in the middle of the second end face of the connecting pipe 12, and the open end of the first exhaust plate 13 is connected to the connecting pipe 12 through the through hole.

[0046] The second exhaust plate 14 is a hemispherical panel. The radius of the hemispherical panel is larger than the radius of the cylindrical plate and equal to the radius of the connecting pipe 12. The circumferential edge of the second exhaust plate 14 is installed on the edge of the second end face of the connecting pipe 12. This creates a cavity between the second exhaust plate 14 and the first exhaust plate 13, so that the gas flowing out of the first exhaust plate 13 will first pass through this cavity before flowing out of the exhaust hole of the second exhaust plate 14, thus further improving the gas mixing.

[0047] like Figure 5 As shown, the exhaust holes on both the first exhaust plate 13 and the second exhaust plate 14 are circular. Furthermore, the exhaust holes on the second exhaust plate 14 are evenly distributed across its entire surface, while the exhaust holes on the first exhaust plate 13 are not evenly distributed across its entire surface. Specifically, as shown... Figure 5 As shown, the part of the side wall 131 of the first exhaust plate 13 near the bottom wall 132 is not provided with exhaust holes. Similarly, the edge of the bottom wall 132 is not provided with exhaust holes. That is to say, there are basically no exhaust holes at the connection between the bottom wall 132 and the side wall 131. This makes the flow direction of the gas flowing out from the bottom wall 132 and the gas flowing out from the side wall 131 different.

[0048] In summary, this embodiment of the invention, by setting an exhaust device at the exhaust end of the air intake pipe, allows high-temperature, high-speed gas to pass through two layers of porous exhaust plates, ensuring thorough mixing of the hot gas and resulting in uniform temperature of the discharged hot gas. Simultaneously, the outermost semi-circular perforated plate increases the total outlet flow area, reduces the airflow velocity, and alters the airflow direction, allowing it to diffuse outwards and preventing the airflow from directly impacting one location and causing excessively high temperatures at that point.

[0049] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit them; although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications can still be made to the specific implementation of the present invention or equivalent substitutions can be made to some technical features without departing from the spirit of the technical solutions of the present invention, and all such modifications and substitutions should be covered within the scope of the technical solutions claimed in the present invention.

Claims

1. A core engine for an aero-engine, characterized in that, include: The casing and the outer casing disposed on the outside of the casing; A compressor (20) is disposed within the casing and includes an air collection chamber; The air intake pipe (30) has an air inlet end and an air outlet end. The air inlet end is disposed in the air collection chamber to draw out the gas in the air collection chamber. The air outlet end of the air intake pipe (30) extends into the cavity between the casing and the outer shell. and An exhaust device (10) is provided at the exhaust end of the air intake pipe (30), and the exhaust device (10) includes an exhaust plate having a plurality of exhaust holes; The exhaust device (10) includes at least two exhaust plates arranged sequentially in the direction of gas flow. The at least two exhaust plates include a first exhaust plate (13) and a second exhaust plate (14). The first exhaust plate (13) includes a columnar panel, and the second exhaust plate (14) includes a hemispherical panel. The second exhaust plate (14) covers the outside of the first exhaust plate (13), and the exhaust holes on the second exhaust plate (14) are evenly arranged on the entire wall surface of the second exhaust plate (14).

2. The core engine of the aero-engine according to claim 1, characterized in that, The column panel includes an open end connected to the air intake pipe (30), a bottom wall and a side wall opposite to the open end, the side wall and the bottom wall are smoothly connected, the bottom wall is provided with a plurality of exhaust holes, and the side wall is provided with a plurality of exhaust holes.

3. The core engine of the aero-engine according to claim 2, characterized in that, The exhaust device (10) further includes a connecting pipe (12), the first end of which is connected to the air intake pipe (30), and the second end of which is connected to the column panel. The connecting pipe (12) is a columnar pipe, and the radius of the column panel is smaller than the radius of the connecting pipe (12).

4. The core engine of the aero-engine according to claim 3, characterized in that, The radius of the hemispherical panel is larger than the radius of the cylindrical panel.

5. An aircraft engine, characterized in that, Includes the core machine as described in any one of claims 1 to 4.

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