Lubricating structure of turbojet engine rotor bearing

Abstract

The utility model relates to a lubricating structure of a turbojet engine rotor bearing, a first sealing cover and a second sealing cover are respectively arranged at two ends of a cavity, a rotor shaft sleeve is fixedly connected between the first sealing cover and the second sealing cover, and a rotor is rotatably arranged in the rotor shaft sleeve; a first bearing and a second bearing are arranged between the rotor and the rotor shaft sleeve; the outer side wall of the first sealing cover is fixedly connected with a flow guide cover, the flow guide cover comprises an outer ring plate and an inner ring plate protruding out of the outer ring plate, and the rotor penetrates through a shaft hole of the inner ring plate. The flow guide cover is arranged, so that the flowing state of airflow at the rotor bearing is optimized, the distribution uniformity of lubricating oil is improved, and the bearing abrasion risk caused by non-uniform distribution of the lubricating oil is reduced; distribution of lubricating oil during working of the rotor bearing is improved, and working performance and service life of the rotor bearing are improved.

Description

Technical Field

[0001] The present application belongs to the technical field of turbojet engines, and in particular to a lubrication structure of a turbojet engine rotor bearing. Background Art

[0002] Micro turbojet engines have been widely used in the fields of drones, model airplanes, etc. due to their small size, light weight, and high power density. Turbojet engines work by adsorbing airflow through the compressor impeller. In the existing turbojet engine structure, when the airflow passes through the rotor bearing, the instability of the airflow often causes uneven force on the lubricating oil on the rotor bearing, resulting in uneven distribution of the lubricating oil, which in turn affects the normal operation of the rotor bearing and reduces its service life. Utility Model Content

[0003] The technical problem to be solved by the utility model is: to solve the deficiencies in the prior art, thereby providing a lubrication structure for a turbojet engine rotor bearing, aiming to improve the distribution of lubricating oil when the rotor bearing is working, and to increase the working performance and life of the rotor bearing.

[0004] The technical solution adopted by the utility model to solve its technical problems is:

[0005] The lubrication structure of the turbojet engine rotor bearing includes:

[0006] A cavity, wherein a first cover and a second cover are respectively disposed at two ends of the cavity, a rotor sleeve is fixedly connected between the first cover and the second cover, and a rotor is rotatably disposed in the rotor sleeve;

[0007] A first bearing and a second bearing are arranged between the rotor and the rotor sleeve;

[0008] The outer side wall of the first cover is fixedly connected with a guide cover, the guide cover comprises an outer ring plate and an inner ring plate protruding from the outer ring plate, and the rotor passes through the axial hole of the inner ring plate.

[0009] Preferably, in the lubrication structure of the turbojet engine rotor bearing of the utility model, lubricating oil spray nozzles are further provided on the outer sides of the balls of the first bearing and the second bearing.

[0010] Preferably, in the lubrication structure of the turbojet engine rotor bearing of the utility model, the two ends of the rotor are respectively connected to a compressor impeller and a turbine impeller, a first stop ring is further arranged between the compressor impeller and the first bearing, and the outer wall of the first stop ring is arranged as a conical arc surface.

[0011] Preferably, in the lubrication structure of the turbojet engine rotor bearing of the utility model, a thrust shoulder structure is respectively provided at both ends of the rotor, which is used to position the first bearing and the second bearing respectively.

[0012] Preferably, in the lubrication structure of the turbojet engine rotor bearing of the utility model, an axial spring is provided between the second bearing and the rotor sleeve.

[0013] Preferably, in the lubrication structure of the turbojet engine rotor bearing of the utility model, a guide sleeve is provided at the end of the rotor close to the compressor impeller.

[0014] Preferably, in the lubrication structure of the turbojet engine rotor bearing of the utility model, a combustion chamber is further provided inside the cavity, and a guide air duct structure is provided between the first cover and the inner wall of the cavity for guiding air flow into the combustion chamber.

[0015] The beneficial effects of the utility model are:

[0016] (1) The setting of the guide cover optimizes the flow state of the airflow at the rotor bearing, improves the uniformity of lubricating oil distribution, and reduces the risk of bearing wear caused by uneven distribution of lubricating oil;

[0017] (2) The provision of the first stop ring effectively prevents lubricating oil from entering the compressor impeller, thereby ensuring the normal operation of the compressor impeller and improving the overall performance of the turbojet engine;

[0018] (3) The setting of the thrust shoulder structure ensures the accurate positioning of the bearing in the rotor sleeve and improves the working stability of the bearing;

[0019] (4) The setting of the axial spring effectively buffers the vibration of the rotor during operation and further improves the working stability of the rotor. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The technical solution of the present application is further described below in conjunction with the accompanying drawings and embodiments.

[0021] Figure 1 is a schematic diagram of the external structure of an embodiment of the present application;

[0022] Figure 2 is a schematic diagram of the structure of the guide cover of an embodiment of the present application;

[0023] Figure 3 is a schematic diagram of the internal structure of the cavity of an embodiment of the present application;

[0024] Figure 4 This is a schematic diagram of the installation structure of the lubricating oil spray nozzle of the embodiment of the present application;

[0025] The reference numerals in the figure are:

[0026] Cavity 10, first cover 11, second cover 12, rotor sleeve 13, rotor 14, compressor impeller 15, turbine impeller 16, first bearing 17, second bearing 18, guide cover 19, outer ring plate 191, inner ring plate 192, first stop ring 20, axial spring 21, guide sleeve 22, lubricating oil spray nozzle 23. DETAILED DESCRIPTION

[0027] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application may be combined with each other.

[0028] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application 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 cannot be understood as limiting the scope of protection of the present application. In addition, the terms "first", "second", etc. are used only for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", etc. may explicitly or implicitly include one or more of the features. In the description of the invention, unless otherwise specified, "multiple" means two or more.

[0029] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood by specific circumstances.

[0030] The technical solution of the present application will be described in detail below with reference to the accompanying drawings and in combination with embodiments.

[0031] Example

[0032] This embodiment provides a lubrication structure for a turbojet engine rotor bearing, referring to Figure 1 and Figure 3The structure includes a cavity 10, with a first cover 11 and a second cover 12 respectively provided at both ends of the cavity 10, a rotor sleeve 13 fixedly connected between the first cover 11 and the second cover 12, a rotor 14 rotatably provided in the rotor sleeve 13, and a first bearing 17 and a second bearing 18 provided between the rotor 14 and the rotor sleeve 13.

[0033] Reference Figure 2 The outer wall of the first cover 11 is fixedly connected with a guide cover 19, which includes an outer ring plate 191 and an inner ring plate 192 protruding from the outer ring plate, and the rotor 14 passes through the shaft hole of the inner ring plate 192. This design allows the airflow to be guided by the guide cover when passing through the rotor bearing, making the airflow more stable, thereby improving the distribution of the lubricating oil.

[0034] Preferably, the lubrication structure of the turbojet engine rotor bearing of this embodiment is as follows: Figure 4 Lubricating oil spray nozzles 23 are installed on the outer sides of the balls of the first bearing 17 and the second bearing 18 to ensure that the lubricating oil can be accurately and evenly sprayed onto the bearings.

[0035] Preferably, in the lubrication structure of the turbojet engine rotor bearing of the present embodiment, the compressor impeller 15 and the turbine impeller 16 are respectively connected to the two ends of the rotor 14, and a first stop ring 20 is also arranged between the compressor impeller 15 and the first bearing 17. The outer wall of the first stop ring 20 is arranged as a conical arc surface. This design not only enhances the stability of the structure, but also helps to guide the flow of airflow and lubricating oil.

[0036] Preferably, the lubrication structure of the turbojet engine rotor bearing of this embodiment is also provided with a thrust shoulder structure at both ends of the rotor in order to more accurately position the bearings. These structures are used to position the first bearing 17 and the second bearing 18 respectively to ensure the stability of the bearings during operation.

[0037] Preferably, in the lubrication structure of the turbojet engine rotor bearing of this embodiment, an axial spring 21 is provided between the second bearing 18 and the rotor sleeve 13. Through the elastic action of the spring, the vibration and impact generated by the bearing during operation can be further absorbed and dispersed, thereby increasing the service life of the bearing.

[0038] Preferably, in the lubrication structure of the turbojet engine rotor bearing of this embodiment, a guide sleeve 22 is provided at the end of the rotor 14 close to the compressor impeller 15, and the guide sleeve can further guide the airflow so that the airflow enters the compressor impeller 15 more stably, thereby reducing the wind resistance of the turbojet engine.

[0039] Preferably, in the lubrication structure of the turbojet engine rotor bearing of this embodiment, a combustion chamber is also provided inside the cavity 10, and a guide air duct structure is provided between the first cover 11 and the inner wall of the cavity for guiding air flow into the combustion chamber to ensure the normal operation of the combustion chamber.

[0040] In summary, the lubrication structure of the turbojet engine rotor bearing provided by the present invention improves the distribution uniformity of the lubricating oil and the working stability of the bearing by optimizing the airflow guidance and the bearing positioning structure, thereby improving the overall performance and life of the turbojet engine.

[0041] Based on the above ideal embodiments of this application, the relevant staff can make various changes and modifications without departing from the technical concept of this application through the above description. The technical scope of this application is not limited to the content in the specification, and its technical scope must be determined according to the scope of the claims.

Claims

1. A lubrication structure for a turbojet engine rotor bearing, characterized in that: include: A cavity (10), wherein a first cover (11) and a second cover (12) are respectively disposed at two ends of the cavity (10), a rotor sleeve (13) is fixedly connected between the first cover (11) and the second cover (12), and a rotor (14) is rotatably disposed in the rotor sleeve (13); A first bearing (17) and a second bearing (18) are arranged between the rotor (14) and the rotor sleeve (13); The outer wall of the first cover (11) is fixedly connected with a guide cover (19), the guide cover (19) comprising an outer ring plate (191) and an inner ring plate (192) protruding from the outer ring plate, and the rotor (14) passes through the axial hole of the inner ring plate (192).

2. The lubrication structure of the turbojet engine rotor bearing according to claim 1, characterized in that: Lubricating oil spray nozzles are also provided on the outer sides of the balls of the first bearing (17) and the second bearing (18).

3. The lubrication structure of the turbojet engine rotor bearing according to claim 2, characterized in that: The two ends of the rotor (14) are respectively connected to a compressor impeller (15) and a turbine impeller (16); a first stop ring (20) is also arranged between the compressor impeller (15) and the first bearing (17); and the outer wall of the first stop ring (20) is arranged to be a conical arc surface.

4. The lubrication structure of the turbojet engine rotor bearing according to claim 3, characterized in that: A thrust shoulder structure is provided at both ends of the rotor (14), respectively, for positioning the first bearing (17) and the second bearing (18).

5. The lubrication structure of a turbojet engine rotor bearing according to any one of claims 1 to 4, characterized in that: An axial spring (21) is arranged between the second bearing (18) and the rotor sleeve (13).

6. The lubrication structure of the turbojet engine rotor bearing according to claim 1, characterized in that: A guide sleeve (22) is provided at the end of the rotor (14) close to the compressor impeller (15).

7. The lubrication structure of the turbojet engine rotor bearing according to claim 1, characterized in that: A combustion chamber is also provided inside the cavity (10), and a flow guide airway structure is provided between the first cover (11) and the inner wall of the cavity for guiding air flow into the combustion chamber.

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