Air bearing aeroengine

Abstract

The application relates to the technical field of aero-engines, in particular to an air-floating aero-engine. The air-floating aero-engine comprises a rotating shaft, a blade wheel and a diffuser are sleeved on one end of the rotating shaft, a turbine and a guide are sleeved on the other end of the rotating shaft, a groove is formed on one side of the diffuser close to the blade wheel, so that a first gas film layer is formed; the first gas film layer transmits an axial load towards the diffuser; a groove is formed on one side of the guide close to the turbine, so that a second gas film layer is formed; the second gas film layer transmits an axial load towards the guide; a shaft sleeve; an air-floating bearing forms a third gas film layer; the air-floating bearing and the third gas film layer transmit a radial load. The air-floating aero-engine provided by the application generates a dynamic pressure lubrication effect between a rotor and a stator, forms the first gas film layer, the second gas film layer and the third gas film layer with bearing capacity, realizes air-floating support of the rotor system, replaces a structural support scheme, and guarantees that the rotor in the engine always works efficiently and normally.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and specifically to an air-float aero-engine. Background Technology

[0002] Aero engines are highly complex and precise thermodynamic machines. Micro aero engines are mainly used in aircraft such as subsonic cruise missiles, target drones, and unmanned aerial vehicles. Due to their high consumption during use, they generally adopt a low-cost and short-life design concept, which requires the engine structure to be simplified and the number of parts to be small.

[0003] When an aero-engine is working, the rotor experiences various loads, including mechanical, aerodynamic, thermal, and inertial loads. These loads are transmitted to the engine mounting section through the support structure and load-bearing system. The support structure uses rolling bearings, which are mainly used to support the smooth rotation of the engine rotor. The bearings are mainly divided into ball bearings and roller bearings, which bear the radial force and axial force of the rotor, respectively.

[0004] In existing technologies, the rotor's support structure is a bearing. Due to the high-speed rotation of the rotor, the support bearing is in a high-temperature working environment for a long time, which reduces its service life. In addition, the support bearing must always maintain good centering accuracy, resulting in extremely high installation precision and complicated installation procedures. Furthermore, the support bearing has high requirements for the working environment. If foreign objects enter the bearing, it will generate significant vibration and noise, and may even cause damage. Secondly, the bearing needs to be lubricated simultaneously during operation, which requires the addition of a lubrication system inside the engine, making the engine structure complex and contrary to the original design intention. Summary of the Invention

[0005] Therefore, the technical problem to be solved by the present invention is to overcome the defects of the existing technology, such as high temperature operation of the support bearing, complicated installation, susceptibility to damage by foreign objects, and the need to add a lubrication system, so as to provide an air-floating aero engine with airflow heat dissipation, simple installation, no fear of foreign objects, and no need for lubrication.

[0006] To solve the above-mentioned technical problems, the present invention provides an air-floating aero-engine, comprising:

[0007] Shaft;

[0008] Along the direction from the shaft end toward the center of the shaft, one end of the rotating shaft is sequentially fitted with an impeller and a diffuser, and the other end of the rotating shaft is sequentially fitted with a turbine and a guide.

[0009] A first gap is left between the impeller and the diffuser. The impeller rotates relative to the diffuser, and a groove is provided on the end face of the diffuser near the impeller, so that the gas in the first gap forms a first gas film layer.

[0010] The first air film layer transmits the axial load toward the diffuser;

[0011] A second gap is left between the turbine and the guide. The turbine rotates relative to the guide, and a groove is provided on the end face of the guide near the turbine, so that the gas in the second gap forms a second gas film layer.

[0012] The second air film layer transmits the axial load toward the guide;

[0013] A bushing is fitted onto the rotating shaft and is spaced apart from the rotating shaft.

[0014] An air bearing is sleeved on the rotating shaft and located inside the bushing, adapted to form a third air film layer between the rotating shaft and the bushing, and the air bearing and the third air film layer are adapted to transmit radial loads.

[0015] Optionally, the plurality of grooves are circumferentially distributed on the diffuser and the guide, which is suitable for the axial force to be uniformly applied to the wall surface of the diffuser and the guide.

[0016] Optionally, the groove extends radially and is curved along the airflow rotation direction to conform to the airflow trajectory.

[0017] Optionally, the air bearing includes a corrugated foil and a top foil radially fitted inside the corrugated foil;

[0018] The corrugated foil is wrapped around the bushing and radially fitted inside the bushing. The corrugated foil is wave-shaped and suitable for providing support stiffness to the air bearing.

[0019] The top foil is fitted onto the rotating shaft and is adapted to provide a smooth surface for the third air film layer.

[0020] Optionally, under the action of axial load, the airflow in the first air film layer adheres to the wall surfaces of the impeller and the diffuser respectively, which is suitable for carrying away high-temperature heat and cooling down;

[0021] Under the action of axial load, the airflow in the second air film layer adheres to the walls of the turbine and the guide, respectively, which is suitable for carrying away high-temperature heat and cooling down.

[0022] Optionally, the airflow within the third air film layer, under the action of radial load, adheres to the rotating shaft and the air bearing, which is suitable for carrying away high-temperature heat and cooling down.

[0023] Optionally, it also includes: a casing that houses the impeller, the shaft, and the turbine;

[0024] The diffuser and the guide transfer axial and radial loads to the casing.

[0025] Optionally, it also includes an exhaust device located on the casing near the turbine and open to the outside.

[0026] Optionally, it also includes a flame tube disposed inside the casing and with its outlet facing the turbine blades.

[0027] The technical solution of this invention has the following advantages:

[0028] 1. The air-floating aero-engine provided by this invention, through grooves on the diffuser and guide facing the rotor side, and air-floating bearings sleeved on the shaft, generates a dynamic pressure lubrication effect in the airflow between the rotor and stator, forming a first air film layer, a second air film layer, and a third air film layer with load-bearing capacity. This achieves air-floating support for the rotor system, replacing the structural support scheme and ensuring that the rotor inside the engine always operates efficiently and normally. The air-floating support scheme can remove heat from inside the engine through airflow, achieving the purpose of heat dissipation. Moreover, the air-floating support system is easy to install, has a simple structure, is easy to disassemble and assemble, and is easy to maintain. The air-floating support system transmits load through the gas film layer, so it is not affected by foreign objects in the environment, and uses air as the lubrication medium, so there is no need to add a separate lubrication system. The air-floating support scheme has the characteristics of no contact and no friction, so the working accuracy will not decrease with the use time, and it has the advantages of long service life and low operating noise.

[0029] 2. The air-floating aero-engine provided by the present invention has grooves extending radially from the center to the edge, increasing the airflow through the grooves in the radial direction; the grooves are also curved along the direction of airflow rotation, increasing the airflow through the grooves in the circumferential direction; the dual-angle synergistic effect maximizes the airflow through the grooves per unit area within the air film layer, improves the load-bearing capacity of the air film layer, meets the rotor support requirements, and improves the engine's working performance. Attached Figure Description

[0030] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0031] Figure 1 This is a schematic diagram of the structure of the air-floating aero-engine of the present invention;

[0032] Figure 2 This is a schematic diagram of the axial load transmission path of the air-float aero-engine of the present invention.

[0033] Figure 3 This is a schematic diagram of the radial load transfer path of the air-float aero-engine of the present invention.

[0034] Figure 4 This is a schematic diagram of the diffuser structure of the present invention;

[0035] Figure 5 This is a schematic diagram of the operation of the impeller and diffuser of the present invention;

[0036] Figure 6 This is a cross-sectional view of the impeller and diffuser of the present invention;

[0037] Figure 7 This is an enlarged schematic diagram of point A in the present invention;

[0038] Figure 8 This is a schematic diagram of the structure of the guide of the present invention;

[0039] Figure 9 This is a schematic diagram of the operation of the guide and turbine of the present invention;

[0040] Figure 10 This is a cross-sectional view of the guide and turbine of the present invention;

[0041] Figure 11 This is an enlarged schematic diagram of section B of the present invention;

[0042] Figure 12 This is a schematic diagram showing the fit between the rotating shaft and the air bearing of the present invention;

[0043] Figure 13 This is a schematic diagram of the forces acting on the rotating shaft of the present invention.

[0044] Explanation of reference numerals in the attached figures:

[0045] 1. Motor; 2. Impeller; 3. Casing; 4. Diffuser; 5. Flame tube; 6. Air bearing; 61. Corrugated foil; 62. Top foil; 7. Bushing; 8. Shaft; 9. Guide; 10. Turbine; 11. Exhaust device; 12. Groove; 13. First air film layer; 14. Third air film layer; 15. Second air film layer. Detailed Implementation

[0046] The technical solution of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. 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.

[0047] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0048] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0049] Furthermore, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0050] Example 1

[0051] Combination Figures 1-13 As shown, the air-floating aero-engine provided in this embodiment includes:

[0052] 8-axis pivot;

[0053] Along the direction from the shaft end toward the center of the shaft, one end of the rotating shaft 8 is sequentially fitted with an impeller 2 and a diffuser 4, and the other end of the rotating shaft 8 is sequentially fitted with a turbine 10 and a guide 9;

[0054] A first gap is left between the impeller 2 and the diffuser 4. The impeller 2 rotates relative to the diffuser 4, and a groove 12 is provided on the end face of the diffuser 4 near the impeller 2, so that the gas in the first gap forms a first gas film layer 13.

[0055] The first air film layer 13 transmits the axial load toward the diffuser 4;

[0056] A second gap is left between the turbine 10 and the guide 9. The turbine 10 rotates relative to the guide 9, and a groove 12 is provided on the end face of the guide 9 near the turbine 10, so that the gas in the second gap forms a second gas film layer 15.

[0057] The second air film layer 15 transmits axial loads toward the guide 9;

[0058] A bushing 7 is fitted onto the rotating shaft 8 and is spaced apart from the rotating shaft 8;

[0059] An air bearing 6 is sleeved on the rotating shaft 8 and located inside the bushing 7, which is suitable for forming a third air film layer 14 between the rotating shaft 8 and the bushing 7. The air bearing 6 and the third air film layer 14 are suitable for transmitting radial loads.

[0060] Combination Figures 1-3 As shown, when the engine is in operation, the rotor generates axial and radial forces. The forward force generated by the rotor during operation is defined as the positive axial force, and the backward force is defined as the negative axial force. In this embodiment, the negative axial force is transmitted from the impeller 2 to the diffuser 4 via the first film layer 13, and then from the diffuser 4 to the casing 3. The positive axial force is transmitted from the turbine 10 to the guide 9 via the first film layer 13, and then from the guide 9 to the casing 3. The radial force is transmitted from the shaft 8 to the bushing 7 via the third film layer 14 and the air bearing 6, and then from the bushing 7 to the diffuser 4 or the guide 9, and finally to the casing 3. In this embodiment, the stable bearing of axial and radial forces is achieved by relying on the fluid film with dynamic pressure effect formed between the two relatively moving gap surfaces, replacing bearings and other support schemes, and providing an air-floating aero-engine that supports the rotor and transmits loads by means of a gas film layer.

[0061] Combination Figures 4-7 As shown, impeller 2 is the rotor and diffuser 4 is the stator; a certain gap is left between impeller 2 and diffuser 4; the gas between impeller 2 and diffuser 4 flows at high speed with impeller 2, and the airflow flows synchronously on the end faces of impeller 2 and diffuser 4 respectively. Since there is a groove 12 recessed on the end face of diffuser 4, the airflow needs to flow along the inner surface of the groove 12, so that the flow path of the airflow on the end face of diffuser 4 is greater than the flow path on the end face of impeller 2. As a result, the flow velocity of the airflow on the end face of diffuser 4 is greater than the flow velocity on the end face of impeller 2, which satisfies the condition for forming dynamic pressure lubrication. The airflow forms a first gas film layer 13 with dynamic pressure effect between impeller 2 and diffuser 4. The axial load is transmitted unidirectionally from impeller 2 to diffuser 4 through the first gas film layer 13, realizing the stable bearing of the reverse axial force.

[0062] Furthermore, the airflow continuously flows between the impeller 2, diffuser 4 and the first gap, which can effectively remove heat from the high-temperature area and achieve a good heat dissipation effect.

[0063] Combination Figures 8-11As shown, turbine 10 is the rotor and guide vane 9 is the stator; a certain gap is left between turbine 10 and guide vane 9; the gas between turbine 10 and guide vane 9 flows at high speed with impeller 2, and the airflow flows synchronously on the end faces of turbine 10 and guide vane 9 respectively. Since there is a groove 12 recessed on the end face of guide vane 9, the airflow needs to flow along the inner surface of groove 12, so that the flow path of the airflow on the end face of guide vane 9 is greater than the flow path on the end face of turbine 10, and thus the flow velocity of the airflow on the end face of guide vane 9 is greater than the flow velocity on the end face of turbine 10, which satisfies the conditions for forming dynamic pressure lubrication. The airflow forms a second air film layer 15 with dynamic pressure effect between turbine 10 and guide vane 9. The axial load is transmitted unidirectionally from turbine 10 to guide vane 9 through the second air film layer 15, realizing the stable bearing of positive axial force.

[0064] Furthermore, the airflow continuously flows between the turbine 10, the guide vane 9, and the second gap, which can effectively remove heat from the high-temperature area and achieve a good heat dissipation effect.

[0065] Combination Figures 12-13 As shown, the rotating shaft 8 is the rotor, the bushing 7 is the stator, and the air bearing 6 is sleeved at both ends of the rotating shaft 8 and located inside the bushing 7. When the rotating shaft 8 is stationary, the rotating shaft 8 is in direct contact with the air bearing 6, and a wedge-shaped gap is left between the rotating shaft 8 and the bushing 7. When the rotating shaft 8 rotates, the air bearing 6 provides support for the rotating shaft 8, and the gas between the rotating shaft 8 and the bushing 7 moves at high speed with the rotating shaft 8. The airflow continuously passes through the wedge-shaped gap, which satisfies the conditions for forming dynamic pressure lubrication. The airflow forms a third air film layer 14 with dynamic pressure effect between the rotating shaft 8 and the bushing 7. At the same time, the thrust generated pushes the rotating shaft 8 away from the wedge-shaped gap, and the rotating shaft 8 is suspended in the bushing 7. The third air film layer 14 supports the frictionless movement of the rotating shaft 8. The radial load is transmitted from the rotating shaft 8 through the third air film layer 14 and the air bearing 6 to the diffuser 4 or the guide 9, realizing the stable bearing of the radial force.

[0066] Furthermore, the airflow continuously flows between the rotating shaft 8, the bushing 7, and the air bearing 6, which can effectively remove heat from the high-temperature area and achieve a good heat dissipation effect. The air bearing 6 uses air as a lubricating medium, so there is no need to add a lubrication system. Moreover, there is no mechanical contact or mechanical friction between the rotor and the stator, resulting in a long service life. The air bearing 6 has high positioning accuracy, and the accuracy will not decrease with the use time. The air bearing 6 has low requirements for the operating environment, is not affected by foreign objects in the environment, and has strong practicality.

[0067] In this embodiment, by using the grooves 12 on the diffuser 4 and guide 9 facing the rotor side, and the air bearing 6 sleeved on the rotating shaft 8, the airflow between the rotor and stator generates a dynamic pressure lubrication effect, forming a first air film layer 13, a second air film layer 15, and a third air film layer 14 with load-bearing capacity. This achieves air-floating support for the rotor system, replacing the structural support scheme and ensuring that the rotor inside the engine always operates efficiently. The air-floating support scheme can remove heat from inside the engine through airflow, achieving the purpose of heat dissipation. Moreover, the air-floating support system is easy to install, has a simple structure, is easy to disassemble and assemble, and is easy to maintain. The air-floating support system transmits load through the gas film layer, so it is not affected by foreign objects in the environment, and uses air as the lubricating medium, so there is no need to add a separate lubrication system. The air-floating support scheme has the characteristics of no contact and no friction, so the working accuracy will not decrease with the use time, and it has the advantages of long service life and low working noise.

[0068] Specifically, multiple grooves 12 are circumferentially distributed on the diffuser 4 and the guide 9, which is suitable for making the axial force act uniformly on the wall surface of the diffuser 4 and the guide 9.

[0069] Combination Figure 4 and Figure 8 As shown, multiple grooves 12 are evenly spaced and arranged around the end faces of the diffuser 4 and the guide 9, so that the airflow velocity on the diffuser 4 and the guide 9 is relatively evenly distributed, thereby making the axial force acting on the diffuser 4 and the guide 9 relatively evenly distributed on the end faces, preventing the diffuser 4 and the guide 9 from being affected by uneven force, thus improving the service life of the engine and reducing operating noise.

[0070] Specifically, the groove 12 extends radially and is curved along the airflow rotation direction to conform to the airflow trajectory.

[0071] Combination Figure 4 and Figure 8 As shown, the groove 12 extends radially from the center to the edge, increasing the airflow through the groove 12 in the radial direction; the groove 12 is bent along the direction of airflow rotation, increasing the airflow through the groove 12 in the circumferential direction; the dual angles work together to maximize the airflow through the groove 12 per unit area within the air film layer, improve the load-bearing capacity of the air film layer, meet the rotor's support requirements, and improve the engine's working performance.

[0072] Specifically, the air bearing 6 includes a corrugated foil 61 and a top foil 62 that is radially fitted inside the corrugated foil 61;

[0073] The corrugated foil 61 is wrapped around the bushing 7 radially and is shaped like a wave to provide support stiffness for the air bearing 6.

[0074] The top foil 62 is fitted onto the rotating shaft 8 and is adapted to provide a smooth surface for the third air film layer 14.

[0075] Combination Figure 12 As shown, the air bearing 6 has a foil structure. The corrugated foil 61 and the top foil 62 work together to support the rotating shaft 8. The corrugated foil 61 is an elastic structure, which keeps the rotating shaft 8 in a balanced state during rotation, effectively resists the vibration caused by external impact, and has a certain strength and load-bearing capacity. It is not easily deformed when subjected to air film pressure and always maintains good working performance. The inner surface of the top foil 62 is smooth, providing a smooth surface for the air film layer, increasing the air film pressure, which is conducive to the buoyancy of the rotating shaft 8 and improves the operating performance of the support structure.

[0076] Specifically, under the action of axial load, the airflow in the first air film layer 13 adheres to the wall surfaces of the impeller 2 and the diffuser 4 respectively, which is suitable for carrying away high-temperature heat and cooling down;

[0077] Under the action of axial load, the airflow in the second air film layer 15 adheres to the walls of the turbine 10 and the guide 9 respectively, which is suitable for carrying away high-temperature heat and cooling down.

[0078] Specifically, the airflow within the third air film layer 14, under the action of radial load, adheres to the rotating shaft 8 and the air bearing 6, which is suitable for carrying away high-temperature heat and cooling down.

[0079] Combination Figures 5-12 As shown, by utilizing the viscosity of air, the gas in the air film layer adheres to the rotor and stator respectively, and carries away the high-temperature heat on them through flow, achieving a good cooling effect; the airflow continuously passes through the rotor and stator, continuously carrying away the heat generated therefrom, ensuring that the working temperature of the stator and rotor always meets the requirements, improving the practical performance of the engine and extending its service life.

[0080] Specifically, it also includes: a casing 3, which encloses the impeller 2, the shaft 8 and the turbine 10;

[0081] The diffuser 4 and the guide 9 transfer axial and radial loads to the casing 3.

[0082] Combination Figures 1-3 As shown, the diffuser 4 and guide 9 are connected to the casing 3. The casing 3 is the load-bearing structure of the engine. The diffuser 4 and guide 9 transfer the load to the casing 3, and then the casing 3 transfers the load to the mounting section, and then to the aircraft fuselage through the mounting section, thus completing the load transfer.

[0083] Specifically, it also includes: an exhaust device 11, which is located on the casing 3 near the turbine 10 and is open to the outside.

[0084] Specifically, it also includes: a flame tube 5, which is located inside the casing 3 and has its outlet facing the blades of the turbine 10.

[0085] Combination Figure 1 As shown, the exhaust device 11 is located on the side of the casing 3 near the turbine 10 and is open to the outside. It is used to discharge the gas discharged from the turbine 10 and the flame tube 5 to the outside and generate positive thrust. The rotating shaft 8 extends through the casing 3 to the outside. The motor 1 is fixed on the rotating shaft 8 located on the outside of the casing 3 to provide starting power.

[0086] Obviously, the above embodiments are merely illustrative examples for clear explanation and are not intended to limit the implementation. Those skilled in the art will recognize that other variations or modifications can be made based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. However, obvious variations or modifications derived therefrom are still within the scope of protection of this invention.

Claims

1. An air-floating aero-engine, characterized in that, include: Rotating shaft (8); Along the direction from the shaft end toward the center of the shaft, one end of the rotating shaft (8) is fitted with an impeller (2) and a diffuser (4) in sequence, and the other end of the rotating shaft (8) is fitted with a turbine (10) and a guide (9) in sequence. A first gap is left between the impeller (2) and the diffuser (4). The impeller (2) rotates relative to the diffuser (4), and a groove (12) is provided on the side end face of the diffuser (4) near the impeller (2), so that the gas in the first gap forms a first gas film layer (13). The first air film layer (13) transmits the axial load toward the diffuser (4); A second gap is left between the turbine (10) and the guide (9). The turbine (10) rotates relative to the guide (9), and a groove (12) is provided on the end face of the guide (9) near the turbine (10), so that the gas in the second gap forms a second gas film layer (15). The second air film layer (15) transmits axial loads toward the guide (9); A bushing (7) is fitted onto the rotating shaft (8) and is spaced apart from the rotating shaft (8); An air bearing (6) is sleeved on the rotating shaft (8) and located inside the bushing (7) cylinder, which is suitable for forming a third air film layer (14) between the rotating shaft (8) and the bushing (7). The air bearing (6) and the third air film layer (14) are suitable for transmitting radial loads. Multiple grooves (12) are circumferentially distributed on the diffuser (4) and the guide (9), which is suitable for making the axial force act uniformly on the diffuser (4) and the guide (9); The groove (12) extends radially and is bent along the direction of airflow rotation, which is suitable for matching the airflow trajectory.

2. The air-floating aero-engine according to claim 1, characterized in that, The air bearing (6) includes a corrugated foil (61) and a top foil (62) that is radially fitted inside the corrugated foil (61). The corrugated foil (61) is wrapped around the bushing (7) and is radially fitted inside the bushing (7). The corrugated foil (61) is wave-shaped and is suitable for providing support stiffness to the air bearing (6). The top foil (62) is fitted onto the rotating shaft (8).

3. The air-floating aero-engine according to claim 1, characterized in that, Under the action of axial load, the airflow in the first air film layer (13) adheres to the wall surfaces of the impeller (2) and the diffuser (4) respectively, which is suitable for carrying away heat and cooling down; Under the action of axial load, the airflow in the second air film layer (15) adheres to the wall surface of the turbine (10) and the guide (9) respectively, which is suitable for carrying away heat and cooling.

4. The air-floating aero-engine according to claim 1, characterized in that, Under the action of radial load, the airflow in the third air film layer (14) adheres to the rotating shaft (8) and the air bearing (6), which is suitable for carrying away heat and cooling down.

5. The air-floating aero-engine according to claim 1, characterized in that, Also includes: A casing (3) is provided that encloses the impeller (2), the shaft (8) and the turbine (10); The diffuser (4) and the guide (9) transfer axial and radial loads to the casing (3).

6. The air-floating aero-engine according to claim 5, characterized in that, Also includes: An exhaust device (11) is located on the casing (3) near the turbine (10) and is open to the outside.

7. The air-floating aero-engine according to claim 5, characterized in that, Also includes: The flame tube (5) is located inside the casing (3) and its outlet is directed toward the blades of the turbine (10).

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