Rotor impeller connecting structure capable of preventing relative rotation

Abstract

The rotor and impeller connecting structure capable of preventing relative rotation comprises a rotor, the air inlet end of the rotor is connected with an air compressor impeller, and the air outlet end of the rotor is connected with a turbine impeller; the outer contour surface of the air inlet end of the rotor is arranged to be of a polygon prism structure, the polygon prism is sleeved with a profiled polygon sleeve, and the inner wall of the end of a shaft hole of the compressor impeller is arranged to be of an inner polygon structure profiled with the outer side wall of the polygon sleeve and used for being connected with the polygon sleeve in an embedded and sleeved mode. According to the rotor and impeller connecting structure capable of preventing relative rotation, by arranging the polygon prism structure and the polygon sleeve, stable assembly between the rotor and the compressor impeller is achieved, and therefore relative rotation of the rotor and the compressor impeller in the high-temperature environment is effectively prevented; meanwhile, by arranging the structures such as the rotor shaft sleeve, the bearing, the thrust stop shoulder, the axial spring and the stop ring, the stability and the reliability of the connecting structure are further enhanced; in addition, the arrangement of the flow guide sleeve is favorable for improving the air inlet efficiency of the engine and optimizing the performance of the engine.

Description

Technical Field

[0001] The present application belongs to the technical field of turbojet engines, and in particular relates to a rotor impeller connection structure capable of preventing relative rotation. 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. However, existing micro turbojet engines usually use the interference fit between the shaft and the shaft hole to achieve a fixed connection between the rotor and the compressor impeller. This assembly method easily causes the rotor and the compressor impeller to rotate relative to each other in a high temperature environment, resulting in an unstable connection, which affects the normal operation of the turbojet engine. 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 rotor impeller connection structure that can prevent relative rotation, which can effectively prevent the relative rotation of the rotor and the compressor impeller in a high temperature environment, thereby ensuring the stable operation of the turbojet engine.

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

[0005] The rotor impeller connection structure capable of preventing relative rotation comprises:

[0006] A rotor, wherein the air inlet end of the rotor is connected to a compressor impeller, and the air outlet end of the rotor is connected to a turbine impeller;

[0007] The outer contour surface of the rotor inlet end is set as a polygonal column structure, and a contoured polygonal sleeve is sleeved on the polygonal column. The inner wall of the axial hole end of the compressor impeller is set as an inner polygonal structure that is contoured with the outer wall of the polygonal sleeve, which is used for embedded sleeve connection of the polygonal sleeve.

[0008] Preferably, in the rotor-impeller connection structure capable of preventing relative rotation of the utility model, a rotor sleeve is rotatably sleeved on the rotor, and the rotor sleeve is located between the compressor impeller and the turbine impeller.

[0009] Preferably, in the rotor-impeller connection structure of the utility model capable of preventing relative rotation, a first bearing and a second bearing are arranged between the rotor sleeve and the rotor, and a thrust shoulder structure is respectively arranged at both ends of the rotor for positioning the first bearing and the second bearing respectively.

[0010] Preferably, in the rotor-impeller connection structure capable of preventing relative rotation of the utility model, an axial spring is provided between the second bearing and the rotor sleeve.

[0011] Preferably, in the rotor impeller connection structure capable of preventing relative rotation of the utility model, a first stop ring is provided between the first bearing and the compressor impeller.

[0012] Preferably, in the rotor impeller connection structure capable of preventing relative rotation of the utility model, a second stop ring is provided between the second bearing and the turbine impeller.

[0013] Preferably, in the rotor-impeller connection structure capable of preventing relative rotation of the utility model, a guide sleeve is provided at the end of the rotor close to the compressor impeller.

[0014] The beneficial effects of the utility model are:

[0015] The rotor impeller connection structure capable of preventing relative rotation of the utility model realizes stable assembly between the rotor and the compressor impeller by arranging a multi-prism structure and a multi-prism sleeve, thereby effectively preventing the relative rotation of the rotor and the compressor impeller in a high temperature environment;

[0016] At the same time, by setting up the rotor sleeve, bearing, thrust shoulder, axial spring and stop ring and other structures, the stability and reliability of the connection structure are further enhanced;

[0017] In addition, the setting of the guide sleeve helps to improve the engine's intake efficiency and optimize engine performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The technical solution of the present application is further described below in conjunction with the accompanying drawings and embodiments.

[0019] Figure 1 is a schematic diagram of the external structure of an embodiment of the present application;

[0020] Figure 2 is a schematic diagram of the axial cross-sectional structure of an embodiment of the present application;

[0021] Figure 3 This is a schematic diagram of the cross-sectional structure of a hexagonal sleeve according to an embodiment of the present application;

[0022] The reference numerals in the figure are:

[0023] Rotor 10 , compressor impeller 11 , turbine impeller 12 , hexagonal sleeve 13 , rotor shaft sleeve 14 , first bearing 15 , second bearing 16 , axial spring 17 , first stop ring 18 , second stop ring 19 , guide sleeve 20 . DETAILED DESCRIPTION

[0024] 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.

[0025] 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.

[0026] 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.

[0027] The technical solution of the present application will be described in detail below with reference to the accompanying drawings and in combination with embodiments.

[0028] Example

[0029] This embodiment provides a rotor impeller connection structure that can prevent relative rotation. Figure 1-3 As shown, its structure includes a rotor 10, a compressor impeller 11 and a turbine impeller 12.

[0030] Preferably, in the rotor impeller connection structure of this embodiment that can prevent relative rotation, the outer wall surface near the end of the inlet end of the rotor 10 is set as a hexagonal column structure, a hexagonal sleeve 13 that is shaped like the hexagonal column is sleeved on the hexagonal column, and the inner wall of the shaft hole end of the compressor impeller 11 is set as an inner hexagonal structure that is shaped like the outer wall of the hexagonal sleeve 13, which is used for the embedded sleeve of the multi-sided sleeve 13. This circumferential positioning assembly method can effectively prevent the relative rotation of the rotor 10 and the compressor impeller 11 in a high temperature environment.

[0031] Preferably, in the rotor impeller connection structure capable of preventing relative rotation of the present embodiment, a rotor sleeve 14 is rotatably sleeved on the rotor 10, and the rotor sleeve 14 is located between the compressor impeller 11 and the turbine impeller 12. A first bearing 15 and a second bearing 16 are arranged between the rotor sleeve 14 and the rotor 10, and a thrust shoulder structure is respectively arranged at both ends of the rotor 10, which is used to position the first bearing 15 and the second bearing 16, respectively, to ensure the stable operation of the bearings.

[0032] Preferably, in the rotor impeller connection structure of this embodiment that can prevent relative rotation, an axial spring 17 is provided between the second bearing 16 and the rotor sleeve 14 to compensate for dimensional changes caused by thermal expansion, while absorbing and dispersing vibrations and impacts to improve the reliability of the engine.

[0033] Preferably, the rotor impeller connection structure of this embodiment can prevent relative rotation, and a first stop ring 18 is provided between the first bearing 15 and the compressor impeller 11, and a second stop ring 19 is provided between the second bearing 16 and the turbine impeller 12. The provision of the stop ring helps to prevent the bearings from falling off and shifting, and realizes the axial positioning and locking of the first bearing 15 and the second bearing 16.

[0034] Preferably, in the rotor-impeller connection structure of this embodiment that can prevent relative rotation, a guide sleeve 20 is provided at the end of the rotor 10 close to the compressor impeller 11 to optimize the intake air flow field of the engine and improve the intake efficiency.

[0035] The rotor impeller connection structure capable of preventing relative rotation of the utility model realizes effective prevention of relative rotation between the rotor and the compressor impeller by adopting a circumferential positioning assembly method and adding a variety of auxiliary structures, thereby improving the rotation stability and reliability of the rotor of the micro turbojet engine.

[0036] 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 rotor impeller connection structure capable of preventing relative rotation, characterized in that: include: A rotor (10), wherein an air inlet end of the rotor (10) is connected to a compressor impeller (11), and an air outlet end of the rotor (10) is connected to a turbine impeller (12); The outer contour surface of the air inlet end of the rotor (10) is arranged as a polygonal column structure, a contoured polygonal sleeve (13) is sleeved on the polygonal column, and the inner wall of the shaft hole end of the compressor impeller (11) is arranged as an inner polygonal structure contoured to the outer wall of the polygonal sleeve (13), for embedded sleeve connection of the polygonal sleeve (13).

2. The rotor impeller connection structure capable of preventing relative rotation according to claim 1, characterized in that: A rotor sleeve (14) is rotatably sleeved on the rotor (10), and the rotor sleeve (14) is located between the compressor impeller (11) and the turbine impeller (12).

3. The rotor impeller connection structure capable of preventing relative rotation according to claim 2, characterized in that: A first bearing (15) and a second bearing (16) are arranged between the rotor sleeve (14) and the rotor (10), and a thrust shoulder structure is respectively arranged at both ends of the rotor (10) for positioning the first bearing (15) and the second bearing (16).

4. The rotor impeller connection structure capable of preventing relative rotation according to claim 3, characterized in that: An axial spring (17) is arranged between the second bearing (16) and the rotor sleeve (14).

5. The rotor impeller connection structure capable of preventing relative rotation according to claim 4, characterized in that: A first stop ring (18) is arranged between the first bearing (15) and the compressor impeller (11).

6. The rotor impeller connection structure capable of preventing relative rotation according to claim 5, characterized in that: A second stop ring (19) is provided between the second bearing (16) and the turbine impeller (12).

7. The rotor impeller connection structure capable of preventing relative rotation according to any one of claims 1 to 6, characterized in that: A guide sleeve (20) is provided at the end of the rotor (10) close to the compressor impeller (11).

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