Turbojet engine and flight equipment

Abstract

The present invention discloses a turbojet engine and flight equipment. The turbojet engine includes a compressor; a combustion chamber connected to the compressor; a guide, the guide including a guide body and a guide housing, the guide housing being sleeved on the outside of the guide body, and the end face of the guide body being provided with a circumferential positioning groove, the guide body being coaxially sleeved with the main shaft sleeve of the turbojet engine, and the main shaft sleeve being provided with a matching positioning groove capable of matching with the circumferential positioning groove; a circumferential positioning member, the two ends of the circumferential positioning member being respectively inserted and matched with the circumferential positioning groove and the matching positioning groove; an axial positioning member for axially positioning the guide; and a tail nozzle assembly for ejecting reverse thrust airflow. The present invention fixes the guide by means of circumferential positioning members and axial positioning members, thereby reducing the contact area between the guide and the main shaft sleeve, reducing the heat transferred to the main shaft, thereby reducing the operating temperature of the bearings on the main shaft and extending the service life of the bearings.

Description

Technical Field

[0001] The present invention relates to the technical field of turbojet engines, and in particular to a turbojet engine and flight equipment. Background Art

[0002] A turbojet is a type of turbine engine that relies entirely on gas flow to generate thrust and is commonly used as a power source for high-speed aircraft.

[0003] The guide is an important component of a turbojet engine. Existing guides are usually of an integral structure. A connecting flange is provided on the guide, and another connecting flange is provided on the main shaft sleeve of the turbojet engine, and the guide is installed through the two connecting flanges. During the operation of the turbojet engine, since the fuel combustion position is close to the guide, the heat generated by the combustion will be transferred to the guide and transferred to the main shaft sleeve through the above-mentioned two connecting flanges, causing the bearings on the main shaft to operate under high-temperature conditions, reducing the service life of the bearings and increasing the subsequent maintenance costs of the turbojet engine.

[0004] Therefore, how to extend the service life of the bearings of the turbojet engine so as to reduce the subsequent maintenance costs of the turbojet engine is a technical problem that those skilled in the art currently need to solve. Summary of the Invention

[0005] In view of this, an object of the present invention is to provide a turbojet engine to extend the service life of the turbojet engine's bearings and reduce the subsequent maintenance costs of the turbojet engine.

[0006] In order to achieve the above object, the present invention provides the following technical solutions:

[0007] A turbojet engine comprising:

[0008] compressor, used to compress air;

[0009] a combustion chamber, in communication with the compressor;

[0010] a guide, disposed on a side of the combustion chamber away from the compressor, the guide comprising a guide body and a guide housing, the guide housing being sleeved on the outer side of the guide body, and an end surface of the guide body being provided with a circumferential positioning groove, the guide body being coaxially sleeved with a main shaft sleeve of the turbojet engine, the main shaft sleeve being provided with a mating positioning groove capable of mating with the circumferential positioning groove;

[0011] a circumferential positioning member, one end of which is inserted and matched with the circumferential positioning groove, and the other end of which is inserted and matched with the matching positioning groove, so as to circumferentially position the guide;

[0012] an axial positioning member, provided on a main shaft sleeve of the turbojet engine, for axially positioning the guide; and

[0013] Tail nozzle assembly, used to inject reverse thrust airflow.

[0014] Optionally, in the above-mentioned turbojet engine, the circumferential positioning member is a positioning pin; the axial positioning member is a retaining ring, and the main shaft sleeve is provided with a mounting groove for mounting the retaining ring.

[0015] Optionally, in the above-mentioned turbojet engine, the outer wall of the guide body has a first conical surface structure, the inner wall of the guide housing has a second conical surface structure, and the first conical surface structure and the second conical surface structure cooperate with each other.

[0016] Optionally, in the above-mentioned turbojet engine, the guide body is made of high-temperature alloy, and the guide shell is made of stainless steel.

[0017] Optionally, in the above-mentioned turbojet engine, the compressor and the combustion chamber are connected together by a stud and a fastening nut, and an elastic buffer is provided on the stud;

[0018] One end of the elastic buffer is in contact with the fastening nut, the other end of the elastic buffer is in contact with the combustion chamber, and one end of the combustion chamber away from the elastic buffer is in clearance fit with the guide housing.

[0019] Optionally, in the above-mentioned turbojet engine, a turbine is provided between the combustion chamber and the tail nozzle assembly, and the turbine is coaxially connected to the main shaft sleeve of the turbojet engine.

[0020] Optionally, in the above-mentioned turbojet engine, the compressor includes an air inlet that can communicate with the outside air, a centrifugal impeller arranged on the main shaft and a diffuser for pressurizing the air, the diffuser is coaxially connected to the main shaft sleeve, the main shaft sleeve is installed on the main shaft of the turbojet engine, and the turbojet engine also includes a drive motor for driving the main shaft to rotate.

[0021] Optionally, in the above-mentioned turbojet engine, the combustion chamber includes an inner ring of the combustion chamber and an outer ring of the combustion chamber, a combustion space for burning fuel is formed between the inner ring of the combustion chamber and the outer ring of the combustion chamber, and the combustion chamber is provided with a fuel injection nozzle for injecting atomized fuel into the combustion space.

[0022] Optionally, in the above-mentioned turbojet engine, the combustion chamber inner ring is coaxially mounted with the guide body, and the combustion chamber inner ring is provided with an interference adjustment structure, and the guide body is provided with a mounting hole for cooperating with the interference adjustment structure;

[0023] The interference adjustment structure includes a plurality of plates extending in parallel along the axial direction of the guide body, and deformation grooves are formed between adjacent plates to achieve elastic interference installation between the interference adjustment structure and the mounting hole.

[0024] A flying device comprises the turbojet engine as described above.

[0025] When the turbojet engine provided by the present invention is used, the compressor compresses the air and passes it into the combustion chamber to introduce air into the combustion chamber to assist combustion, so that the fuel in the combustion chamber burns. After the combustion products flow through the guide, they are discharged into the atmosphere in the direction opposite to the forward direction through the tail nozzle assembly, thereby accelerating the gas flow to generate reaction thrust and providing forward power for the flight equipment. Since the guide provided by the present invention includes a guide body and a guide shell, the guide shell is sleeved on the outer side of the guide body, that is, the guide adopts a split structure, which reduces the manufacturing difficulty compared with the existing integral structure guide. In addition, the above-mentioned guide body is coaxially sleeved with the main shaft sleeve of the turbojet engine, and one end of the circumferential positioning member is inserted into the circumferential positioning groove provided on the end face of the guide body. After the other end of the positioning piece is inserted into the matching positioning groove on the main shaft sleeve, the circumferential positioning between the guide and the main shaft sleeve is achieved, and the axial positioning piece is set on the main shaft sleeve of the turbojet engine to achieve axial positioning between the guide and the main shaft sleeve, thereby achieving the installation of the guide on the main shaft sleeve; it can be seen that the present invention fixes the guide by means of circumferential positioning pieces and axial positioning pieces, which reduces the contact area between the guide and the main shaft sleeve compared to the existing installation method of installing the guide on the main shaft sleeve of the compressor through two connecting flanges, thereby reducing the heat transferred to the main shaft, thereby reducing the operating temperature of the bearings on the main shaft, extending the bearing service life of the turbojet engine, and reducing the later maintenance costs of the turbojet engine. It has good economic benefits and is suitable for popularization and use. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] 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 only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0027] Figure 1 A schematic diagram of a partial cross-sectional structure of a turbojet engine provided by an embodiment of the present invention;

[0028] Figure 2 The embodiment of the present invention provides Figure 1Schematic diagram of the local structure at position A;

[0029] Figure 3 A schematic cross-sectional view of a guide housing provided by an embodiment of the present invention;

[0030] Figure 4 A schematic diagram of the front structure of a guide housing provided by an embodiment of the present invention;

[0031] Figure 5 A schematic cross-sectional view of a guide body provided by an embodiment of the present invention;

[0032] Figure 6 A schematic diagram of the front structure of a guide body provided by an embodiment of the present invention;

[0033] Figure 7 A schematic cross-sectional view of a spindle sleeve installed on a spindle provided by an embodiment of the present invention;

[0034] Figure 8 A schematic side view of the structure of a spindle sleeve installed on a spindle provided by an embodiment of the present invention;

[0035] Figure 9 A schematic diagram of the structure of a retaining ring provided by an embodiment of the present invention fitted on a guide body;

[0036] Figure 10 The present invention provides a schematic structural diagram of an interference adjustment structure.

[0037] Among them, 100 is the compressor, 101 is the air inlet, 102 is the centrifugal impeller, 103 is the diffuser, 200 is the main shaft, 201 is the main shaft sleeve, 202 is the drive motor, 300 is the combustion chamber, 300-a is the inner ring of the combustion chamber, 300-b is the outer ring of the combustion chamber, 301 is the stud, 302 is the fastening nut, 303 is the elastic buffer, 400 is the guide, 401 is the guide body, 4011 is the first conical surface structure, 402 is the guide shell, 4021 is the second conical surface structure, 500 is the circumferential positioning part, 600 is the axial positioning part, 700 is the tail nozzle assembly, 800 is the turbine, 900 is the interference adjustment structure, 901 is the sheet body, and 902 is the deformation groove. DETAILED DESCRIPTION

[0038] In view of this, the core of the present invention is to provide a turbojet engine to extend the service life of the turbojet engine's bearings and reduce the subsequent maintenance costs of the turbojet engine.

[0039] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0040] like Figures 1 to 10 As shown, an embodiment of the present invention discloses a turbojet engine, including a compressor 100 , a combustion chamber 300 , a guide vane 400 , a circumferential positioning member 500 , an axial positioning member 600 and a tail nozzle assembly 700 .

[0041] Among them, the compressor 100 is used to compress air; the combustion chamber 300 is connected to the compressor 100; the guide 400 is arranged on the side of the combustion chamber 300 away from the compressor 100, and the guide 400 includes a guide body 401 and a guide shell 402, the guide shell 402 is sleeved on the outer side of the guide body 401, and the end face of the guide body 401 is provided with a circumferential positioning groove, the guide body 401 is coaxially sleeved with the main shaft sleeve 201 of the turbojet engine, and the main shaft sleeve 201 is provided with a matching positioning groove that can cooperate with the circumferential positioning groove; one end of the circumferential positioning member 500 is inserted into the circumferential positioning groove, and the other end is inserted into the matching positioning groove to circumferentially position the guide 400; the axial positioning member 600 is arranged on the main shaft sleeve 201 of the turbojet engine to axially position the guide 400; the tail nozzle assembly 700 is used to inject reverse thrust airflow.

[0042] When the turbojet engine provided by the present invention is used, the compressor 100 compresses the air and then passes it into the combustion chamber 300, so as to introduce air into the combustion chamber 300 to assist combustion, so that the fuel in the combustion chamber 300 burns. After the combustion products flow through the guide vane 400, they are discharged into the atmosphere in the direction opposite to the forward direction through the tail nozzle assembly 700, thereby accelerating the gas flow to generate reaction thrust, thereby providing forward power for the flight equipment. Since the guide vane 400 provided by the present invention includes a guide vane body 401 and a guide vane housing 402, the guide vane housing 402 is sleeved on the outer side of the guide vane body 401, that is, the guide vane 400 adopts a split structure, which reduces the manufacturing difficulty compared with the existing integral structure guide vane 400. In addition, the guide vane body 401 is coaxially sleeved with the main shaft sleeve 201 of the turbojet engine, and one end of the circumferential positioning member 500 is inserted into the circumferential positioning groove provided on the end face of the guide vane body 401. After the other end of 00 is inserted into the matching positioning groove on the main shaft sleeve 201, the circumferential positioning between the guide 400 and the main shaft sleeve 201 is realized, and the axial positioning piece 600 is set on the main shaft sleeve 201 of the turbojet engine to realize the axial positioning between the guide 400 and the main shaft sleeve 201, thereby realizing the installation of the guide 400 on the main shaft sleeve 201; it can be seen that the present invention fixes the guide 400 through the circumferential positioning piece 500 and the axial positioning piece 600. Compared with the existing installation method of installing the guide 400 on the main shaft sleeve 201 of the compressor 100 through two connecting flanges, the contact area between the guide 400 and the main shaft sleeve 201 is reduced, so that the heat transferred to the main shaft 200 is reduced, thereby reducing the operating temperature of the bearings on the main shaft 200, extending the bearing service life of the turbojet engine, and reducing the later maintenance cost of the turbojet engine. It has good economic benefits and is suitable for promotion and use.

[0043] In addition, the above-mentioned axial positioning member 600 is located on the side of the guide 400 close to the compressor 100 and the combustion chamber 300. Under the action of the airflow thrust of the compressor 100 and the expansion of the heat of fuel combustion, the axial positioning member 600 is firmly attached to the guide body 401. Under high temperature conditions, the axial positioning member 600 will not be loosened or deformed, making the fixation of the guide 400 and the main shaft sleeve 201 more reliable, and improving the convenience of disassembly compared with the existing method of connecting the guide 400 and the main shaft sleeve 201 by bolts.

[0044] It should be noted that the above-mentioned circumferential positioning member 500 can be a positioning block, a positioning column or a positioning pin and other types of parts. As long as the type of part can meet the circumferential positioning requirements, it belongs to the protection scope of the present invention; similarly, the axial positioning member 600 can be a retaining ring, a sleeve or a retaining spring and other types of parts. As long as the type of part can meet the axial positioning requirements, it belongs to the protection scope of the present invention; optionally, the circumferential positioning member 500 provided in the embodiment of the present invention is a positioning pin; the axial positioning member 600 is a retaining ring, and the spindle sleeve 201 is provided with an installation groove to embed the inner edge of the retaining ring into the installation groove, and the guide body 401 is axially positioned through the middle and outer edge of the retaining ring.

[0045] It should be understood that the present invention does not specifically limit the number and distribution of the positioning pins. In practical applications, the number and specific distribution of the positioning pins can be adaptively modified according to actual requirements. As long as the number and distribution can meet the use requirements, they are within the scope of protection of the present invention. Optionally, Figure 7 and Figure 8 As shown, the number of positioning pins provided in the embodiment of the present invention is four, and the four positioning pins are evenly distributed in the outer circumferential direction of the spindle sleeve 201, and each positioning pin is clearance-matched with its corresponding circumferential positioning groove.

[0046] In addition, the outer wall of the guide body 401 is a first conical surface structure 4011, and the inner wall of the guide shell 402 is a second conical surface structure 4021. The first conical surface structure 4011 and the second conical surface structure 4021 cooperate to achieve conical surface cooperation and fixation between the guide body 401 and the guide shell 402 through the first conical surface structure 4011 and the second conical surface structure 4021. The structure is simple and easy to assemble and disassemble.

[0047] The present invention does not specifically limit the taper of the above-mentioned first conical surface structure 4011 and the second conical surface structure 4021. As long as the taper can meet the use requirements, it falls within the protection scope of the present invention; optionally, the taper of the first conical surface structure 4011 and the second conical surface structure 4021 provided in the embodiment of the present invention is 1°~2°.

[0048] Furthermore, the guide body 401 and the guide shell 402 are made of different materials. The guide body 401 is made of high-temperature alloy to withstand the high temperature generated by fuel combustion, and the guide shell 402 is made of stainless steel to reduce the manufacturing cost and difficulty of the guide 400.

[0049] like Figure 1As shown, the diffuser 103 of the compressor 100 is connected to the combustion chamber 300 through a stud 301 and a fastening nut 302, and an elastic buffer 303 is provided on the stud 301 to achieve elastic fixation of the combustion chamber 300. Under high temperature conditions, the combustion chamber 300 is allowed to move within a preset space to release stress.

[0050] Specifically, one end of the elastic buffer 303 contacts the fastening nut 302, and the other end of the elastic buffer 303 contacts the combustion chamber 300, so that under high temperature conditions, the combustion chamber 300 can move toward the side close to the elastic buffer 303, and the elastic buffer 303 plays a buffering role; and the end of the combustion chamber 300 away from the elastic buffer 303 is loosely matched with the guide housing 402, so that under high temperature conditions, the combustion chamber 300 can move toward the side close to the guide 400.

[0051] The present invention does not limit the specific number and distribution form of the above-mentioned studs 301 and elastic buffers 303. In actual applications, they can be adaptively adjusted according to actual needs. As long as the number and distribution form can meet the use requirements, they fall within the protection scope of the present invention; optionally, the number of studs 301 provided in the embodiment of the present invention is three, and the three studs 301 are evenly distributed along the circumference of the diffuser 103. Accordingly, the number of elastic buffers 303 is also three, and the three elastic buffers 303 are respectively sleeved on the three studs 301.

[0052] It should be understood that the above-mentioned elastic buffer 303 can be a cylindrical spring, a rubber buffer block or a colloidal airbag type part. As long as the part type can meet the use requirements, it falls within the protection scope of the present invention; optionally, the elastic buffer 303 provided in the embodiment of the present invention is a cylindrical spring, which has a simple structure and is easy to install.

[0053] In addition, a turbine 800 is provided between the combustion chamber 300 and the tail nozzle assembly 700, and the turbine 800 is coaxially connected to the main shaft sleeve 201 of the compressor 100. The main shaft sleeve 201 is sleeved on the main shaft 200 of the turbojet engine, so that a part of the heat generated by the combustion of the fuel in the combustion chamber 300 is guided by the guide device 400 and flows through the turbine 800. The expansion work generated when flowing through the turbine 800 drives the turbine 800 to rotate, and the turbine 800 drives the main shaft 200 of the turbojet engine to rotate. As the main shaft 200 rotates, the centrifugal impeller 102 and the diffuser 103 provided on the main shaft 200 compress and pressurize the air respectively; another part of the heat generated by the combustion of the fuel is used to accelerate the gas flow to generate reaction thrust and provide forward power for the flight equipment.

[0054] The compressor 100 includes an air inlet 101 capable of communicating with the outside air, a centrifugal impeller 102 provided on a main shaft 200, and a diffuser 103 for supercharging the air. The diffuser 103 is coaxially connected to the main shaft sleeve 201, and the main shaft sleeve 201 is installed on the main shaft 200 of the turbojet engine. The turbojet engine also includes a drive motor 202 for driving the main shaft 200 to rotate. When the turbojet engine is started, the main shaft 200 is driven to rotate by the drive motor 202. The outside air enters the compressor 100 through the air inlet 101, is compressed and supercharged by the centrifugal impeller 102 and the diffuser 103 in the compressor 100, and then continuously flows into the combustion chamber 300 to provide combustion-supporting air for the fuel in the combustion chamber 300. When the heat generated by the combustion of fuel in the combustion chamber 300 reaches a certain threshold, a portion of the heat can drive the turbine 800 to rotate when flowing through the turbine 800. Since the turbine 800 is coaxially connected to the main shaft sleeve 201, and the main shaft sleeve 201 is installed on the main shaft 200 of the turbojet engine, when the turbine 800 rotates, it can drive the centrifugal impeller 102 arranged on the main shaft 200 and the diffuser 103 coaxially connected to the main shaft sleeve 201 to rotate. At this time, the expansion work of a portion of the combustion heat on the turbine 800 can drive the compressor 100 to operate, and the drive motor 202 is no longer needed to drive the main shaft 200 to rotate, thereby reducing the power consumption of the drive motor 202. The other portion of the combustion heat is ejected by the tail nozzle assembly 700 to generate a reaction thrust on the turbojet engine.

[0055] The combustion chamber 300 provided by the present invention includes an inner ring 300-a of the combustion chamber and an outer ring 300-b of the combustion chamber, and a combustion space for burning fuel is formed between the inner ring 300-a of the combustion chamber and the outer ring 300-b of the combustion chamber, and the combustion chamber 300 is provided with a fuel injection nozzle for injecting atomized fuel into the combustion space, so that the atomized fuel is injected into the combustion space through the fuel injection nozzle so that the atomized fuel burns in the combustion space.

[0056] Furthermore, the inner ring 300-a of the combustion chamber is coaxially installed with the guide body 401, and the inner ring 300-a of the combustion chamber is provided with an interference adjustment structure 900, and the guide body 401 is provided with a mounting hole for cooperating with the interference adjustment structure 900, so that the guide body 401 and the outer ring 300-a of the combustion chamber are connected together through the cooperation between the interference adjustment structure 900 and the mounting hole.

[0057] Specifically, the interference adjustment structure 900 includes a plurality of sheets 901 extending parallel to the axial direction of the guide body 401, and the plurality of sheets 901 form a cylindrical structure to install the interference adjustment structure 900 in the mounting hole on the guide body 401, thereby realizing the connection between the guide body 401 and the inner ring 300-a of the combustion chamber; deformation grooves 902 are formed between adjacent sheets 901 to realize the interference size adjustment between the interference adjustment structure 900 and the mounting hole, so that the interference adjustment structure 900 can undergo elastic expansion under high temperature working conditions, thereby realizing an elastic interference connection between the guide body 401 and the inner ring 300-a of the combustion chamber.

[0058] It should be understood that the present invention does not impose any specific restrictions on parameters such as the number and size of the above-mentioned sheet 901 and deformation grooves 902. As long as the parameters can meet the use requirements, they are within the protection scope of the present invention; optionally, the length of the sheet 901 provided in the embodiment of the present invention is 7 mm, the number of deformation grooves 902 is 28, and the width of each deformation groove 902 is 0.2 mm.

[0059] In addition, the above-mentioned turbojet engine also includes a casing for installing parts such as the combustion chamber 300, the guide vane 400 and the turbine 800 inside the casing. The guide vane housing 402 is provided with bolt holes for fixing the casing, so that the casing and the guide vane housing 402 are connected by bolts. During the connection, the axial deviation generated when the guide vane housing 402 and the conical surface of the guide vane body 401 are matched is adjusted by adjusting the gasket.

[0060] In addition, the present invention also discloses a flight device, including the turbojet engine as described above, and thus has all the technical effects of the above-mentioned turbojet engine, which will not be described in detail herein.

[0061] The terms "first," "second," and the like in the specification, claims, and accompanying drawings of the present invention are used to distinguish between different items, not to describe a specific order. Furthermore, the terms "including," "having," and any variations thereof are intended to cover non-exclusive inclusions. For example, a process, method, system, product, or apparatus comprising a series of steps or elements is not limited to the listed steps or elements and may include steps or elements that are not listed.

[0062] The above description of the disclosed embodiments is intended to enable one skilled in the art to implement or use the present invention. Various modifications to these embodiments will be readily apparent to one skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention is not limited to the embodiments shown herein but is intended to conform to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A turbojet engine, characterized in that: include: compressor, used to compress air; a combustion chamber, in communication with the compressor; a guide, disposed on a side of the combustion chamber away from the compressor, the guide comprising a guide body and a guide housing, the guide housing being sleeved on the outer side of the guide body, and an end surface of the guide body being provided with a circumferential positioning groove, the guide body being coaxially sleeved with a main shaft sleeve of the turbojet engine, the main shaft sleeve being provided with a mating positioning groove capable of mating with the circumferential positioning groove; a circumferential positioning member, one end of which is inserted and matched with the circumferential positioning groove, and the other end of which is inserted and matched with the matching positioning groove, so as to circumferentially position the guide; an axial positioning member, provided on a main shaft sleeve of the turbojet engine, for axially positioning the guide; and Tail nozzle assembly, used for ejecting reverse thrust airflow; The combustion chamber comprises an inner ring of the combustion chamber and an outer ring of the combustion chamber, wherein a combustion space for burning fuel is formed between the inner ring of the combustion chamber and the outer ring of the combustion chamber, and the combustion chamber is provided with a fuel injection nozzle for injecting atomized fuel into the combustion space; The inner ring of the combustion chamber is coaxially mounted with the guide body, and the inner ring of the combustion chamber is provided with an interference adjustment structure, and the guide body is provided with a mounting hole for cooperating with the interference adjustment structure; The interference adjustment structure includes a plurality of plates extending in parallel along the axial direction of the guide body, and deformation grooves are formed between adjacent plates to achieve elastic interference installation between the interference adjustment structure and the mounting hole.

2. The turbojet engine according to claim 1, characterized in that The circumferential positioning member is a positioning pin; the axial positioning member is a retaining ring, and the main shaft sleeve is provided with a mounting groove for mounting the retaining ring.

3. The turbojet engine according to claim 1, characterized in that The outer wall of the guide body is in a first conical surface structure, and the inner wall of the guide shell is in a second conical surface structure, and the first conical surface structure and the second conical surface structure cooperate with each other.

4. The turbojet engine according to claim 1, characterized in that The guide body is made of high-temperature alloy, and the guide shell is made of stainless steel.

5. The turbojet engine according to claim 1, characterized in that The compressor and the combustion chamber are connected together through studs and fastening nuts, and elastic buffers are provided on the studs; One end of the elastic buffer is in contact with the fastening nut, the other end of the elastic buffer is in contact with the combustion chamber, and one end of the combustion chamber away from the elastic buffer is in clearance fit with the guide housing.

6. The turbojet engine according to claim 1, characterized in that A turbine is provided between the combustion chamber and the tail nozzle assembly, and the turbine is coaxially connected to the main shaft sleeve of the turbojet engine.

7. The turbojet engine according to claim 1, characterized in that The compressor includes an air inlet that can communicate with the outside air, a centrifugal impeller arranged on the main shaft and a diffuser for pressurizing the air. The diffuser is coaxially connected to the main shaft sleeve, and the main shaft sleeve is installed on the main shaft of the turbojet engine. The turbojet engine also includes a drive motor for driving the main shaft to rotate.

8. A flying device, characterized in that: Comprising a turbojet engine according to any one of claims 1 to 7.

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