Turbojet engine guider

Abstract

The utility model discloses a turbojet engine guider which comprises a guider body, the outer wall of the guider body is sleeved with a shell, a first connecting plate is integrally formed on the outer wall of the guider body, and a plurality of first reinforcing plates in an annular array are integrally formed above the first connecting plate and the outer wall of the guider body. A second connecting plate is integrally formed in the shell, a plurality of second reinforcing plates in an annular array are integrally formed below the second connecting plate and the outer wall of the shell, the outer wall of the guider body is sleeved with a heat insulation ring, and the heat insulation ring is located between the first connecting plate and the second connecting plate. Corresponding inserting holes are formed among the first connecting plate, the second connecting plate and the heat insulation ring, and the first connecting plate, the second connecting plate and the heat insulation ring are fixedly connected through inserting hole bolts. The utility model relates to the technical field of turbojet engines, which is characterized in that a connecting plate I is arranged on the outer wall of a guider, a connecting plate II is arranged on the inner wall of a shell, and the guider body and the shell are respectively reinforced by a reinforcing plate I and a reinforcing plate II, so that the connection between the guider body and the shell can further bear high-speed airflow.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of turbojet engine, specifically a kind of turbojet engine guider. BACKGROUND

[0002] The turbojet engine includes an air inlet, an axial-flow compressor, a combustion chamber, a turbine, and an exhaust nozzle. The axial-flow compressor is fixed to the turbine by a concentric shaft. When the turbojet engine is in operation, air enters the air inlet of the turbojet engine from the outside and flows along the axial direction of the axial-flow compressor. The air is compressed by the axial-flow compressor and then enters the combustion chamber, where it is burned and expanded to produce high-speed and high-pressure air. The high-speed and high-pressure air drives the turbine to rotate, and finally is ejected through the exhaust nozzle to generate a thrust. The guider plays a guiding role in the turbojet engine. When the high-speed airflow is discharged at the guider, a large thrust is generated. However, the guider and the outer shell are mostly connected by straight bolts, which can easily deform under the strong thrust, affecting the overall operation. Therefore, we provide a turbojet engine guider to solve the above problems. SUMMARY

[0003] To solve the above problems, i.e. to solve the problems raised in the background art, the utility model provides a turbojet engine guider, which includes a guider body, an outer shell is sleeved on the outer wall of the guider body, a connecting plate one is integrally formed on the outer wall of the guider body, a plurality of annular arrayed reinforcing plates one are integrally formed on the upper part of the outer wall of the guider body with the connecting plate one, a connecting plate two is integrally formed inside the outer shell, a plurality of annular arrayed reinforcing plates two are integrally formed on the lower part of the outer wall of the outer shell with the connecting plate two, a heat insulation ring is sleeved on the outer wall of the guider body, the heat insulation ring is located between the connecting plate one and the connecting plate two, corresponding insertion holes are formed between the connecting plate one, the connecting plate two and the heat insulation ring, and the insertion holes are fixed and connected by bolts.

[0004] Preferably, an exhaust pipe is detachably fixed to the bottom of the outer wall of the guider body.

[0005] Preferably, the bottom end of the outer shell is designed in a converging manner.

[0006] Preferably, the cross section of the heat insulation ring is in a stepped shape, so as to completely isolate the guider body and the outer shell.

[0007] The beneficial technical effect of the utility model discloses: through setting up connecting plate no. 1 on the outer wall of the guider, setting up connecting plate no. 2 on the inner wall of the shell, and respectively reinforcing through reinforcing plate no. 1 and reinforcing plate no. 2, the connection between the guider body and the shell can further bear high-speed airflow, at the same time, the heat insulation plate can insulate the heat from the guider, avoids the overheating deformation of the shell, improves the service life of the guider and the shell. BRIEF DESCRIPTION OF DRAWINGS

[0008] Figure 1 The sectional structure schematic diagram of the utility model is shown.

[0009] Figure 2 The sectional structure schematic diagram of the utility model is shown. Figure 1 The sectional structure schematic diagram of the utility model is shown.

[0010] Reference signs 1, guider body;11, connecting plate no. 1;12, reinforcing plate no. 1;2, shell;21 connecting plate no. 2;22, reinforcing plate no. 2;3, exhaust pipe;4, heat insulation ring;5, bolt. DETAILED DESCRIPTION

[0011] The preferred embodiments of the utility model are described below with reference to the drawings. Those skilled in the art should understand that these embodiments are only used to explain the technical principles of the utility model, and are not intended to limit the protection scope of the utility model.

[0012] The utility model proposes a kind of turbojet engine guider, including guider body 1, the outer wall of guider body 1 is sleeved with shell 2, the bottom end of shell 2 is designed as inside, this design can strengthen the stability of shell 2, the outer wall bottom of guider body 1 is detachably fixed with exhaust pipe 3, for external gas, the outer wall of guider body 1 is integrally formed with connecting plate no. 1 11, connecting plate no. 1 11 and the outer wall upper side of guider body 1 are integrally formed with several annular array reinforcing plate no. 1 12, the stability between guider body 1 and connecting plate no. 1 11 is reinforced by the connection of reinforcing plate no. 1 12, the inside of shell 2 is integrally formed with connecting plate no. 2, connecting plate no. 2 and the outer wall lower side of shell 2 are integrally formed with several annular array reinforcing plate no. 2 21 connecting plate no. 2;22, the stability between shell 2 and connecting plate no. 2 is reinforced by the connection of reinforcing plate no. 2 21 connecting plate no. 2;22, the outer wall of guider body 1 is sleeved with heat insulation ring 4, the material is ceramic fiber, it has low thermal conductivity, high temperature resistance, light weight and other characteristics, so that it becomes the ideal heat insulation material of aerospace equipment, heat insulation ring 4 is located between connecting plate no. 1 11 and connecting plate no. 2, the cross section of heat insulation ring 4 is ladder-shaped, so as to completely insulate guider body 1 and shell 2, corresponding jack is opened between connecting plate no. 1 11, connecting plate no. 2 and heat insulation ring 4, and bolt 5 is fixedly connected by the jack.

[0013] Through the person skilled in the art, all electrical components and parts in the case are general standard parts or parts known to those skilled in the art, the structure and principle of which can be known by technical personnel through technical manual or through conventional experimental method, the model and the scheme are adapted to normally operate, all electrical components and the power supply matched with them are connected through wires, and according to the actual situation, a suitable controller is selected to meet the control requirement, and the specific connection and control sequence should be referred to the working principle of the following working principle, the working order of each electrical component is completed, and the detailed connection means is a public technical knowledge in the art, and the electrical control is not described.

[0014] Working principle: when installing the guide, the heat insulation ring 4 can be placed on the outer wall of the guide body 1 below the connecting plate, then the guide body 1 is inserted into the inner cavity of the shell 2, when the jack corresponds, it is fixed by the bolt 5, the connecting plate one 11 is arranged on the outer wall of the guide, the connecting plate two is arranged on the inner wall of the shell 2, and the connecting plate two is connected by the reinforcing plate one 12 and the reinforcing plate two 21 respectively; 22 is reinforced, so that the connection between the guide body 1 and the shell 2 can further withstand high-speed airflow, at the same time, the heat insulation plate can insulate the heat from the guide, avoid the shell 2 from overheating and deforming, and improve the service life of the guide and the shell 2.

[0015] Although the utility model has been described with reference to the preferred embodiments, various improvements can be made and equivalent parts can be replaced without departing from the scope of the utility model, especially, as long as there is no structural conflict, the technical features mentioned in each embodiment can be combined in any way. The utility model is not limited to the specific embodiments disclosed in the text, but includes all technical solutions falling within the scope of the claims.

[0016] In the description of the utility model, the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" and other terms indicating direction or positional relationship are based on the direction or positional relationship shown in the drawings, which is only for the convenience of description, and does not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, therefore it cannot be understood as a limitation on the utility model. In addition, the terms "first", "second", "third" are only for the purpose of description, and cannot be understood as indicating or implying relative importance.

[0017] In addition, it needs to be explained that, in the description of the utility model, unless another explicit provision and limitation, the term "mount", "link", "connect" should be broad sense understanding, for example, can be fixed connection, also can be detachable connection, or integrally connected; can be mechanical connection, also can be electrical connection; can be directly connected, also can pass through the indirect connection of intermediate medium, can be two element internal communication. For the person skilled in the art, the specific meaning of the above-mentioned terms in the utility model can be understood according to the specific circumstances.

[0018] The term "comprising" or any other similar word is intended to encompass a non-exclusive inclusion, such that a process, article, or apparatus / device that comprises a list of elements is not limited to those elements, but can include other elements not expressly listed, or also include elements inherent in the process, article, or apparatus / device.

[0019] So far, the technical scheme of the utility model has been described in combination with the preferred embodiments shown in the drawings, but the person skilled in the art can easily understand that the protection scope of the utility model is obviously not limited to these specific embodiments. Without deviating from the principles of the utility model, the person skilled in the art can make equivalent changes or replacements to the related technical features, and the technical schemes after these changes or replacements will fall within the protection scope of the utility model.

Claims

1. A turbojet engine guide, characterized in that: Including the guider body (1), the outer wall of guider body (1) is sleeved with shell (2), the outer wall of guider body (1) is integrally formed with connecting plate one (11), connecting plate one (11) and the outer wall of guider body (1) are integrally formed with a plurality of annular array of reinforcing plate one (12) top, the inside of shell (2) is integrally formed with connecting plate two, connecting plate two and the outer wall of shell (2) are integrally formed with a plurality of annular array of reinforcing plate two (22) bottom, the outer wall of guider body (1) is sleeved with heat insulation ring (4), heat insulation ring (4) is located between connecting plate one (11) and connecting plate two, the corresponding jack is opened between connecting plate one (11), connecting plate two and heat insulation ring (4), and is fixedly connected by jack bolt (5).

2. A turbojet engine guide according to claim 1, characterized in that: The outer wall bottom of guider body (1) is detachably fixedly provided with exhaust pipe (3).

3. A turbojet engine guide according to claim 1, characterized in that: The bottom end of shell (2) is designed as a converging type.

4. A turbojet engine guide according to claim 1, wherein: The cross section of heat insulation ring (4) is in a stepped shape, so as to completely isolate guider body (1) and shell (2).

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