Turbine guider and turbojet engine

Abstract

The utility model belongs to the technical field of engines and parts of the engines, and discloses a turbine guider and a turbojet engine adopting the turbine guider, the turbine guider comprises a guider cover and a high-temperature alloy guide impeller located in the guider cover, and the guider cover and the guide impeller are fixedly connected through a fastener and then welded; or the guide impeller and the cylinder part of the guider cover are integrally cast and molded by adopting high-temperature alloy, and the flange part of the guider cover is made of heat-resistant steel; the turbine guider not only can ensure that the guide impeller meets the requirements of severe working conditions, but also is convenient to process and manufacture; according to the turbojet engine adopting the turbine guider, the turbine guider plays an axial thrust role while playing roles of guiding airflow, reducing airflow loss, balancing gas flow and the like, so that the damage to the engine caused by axial movement of a rotor assembly is prevented, and the service life of the turbojet engine is ensured.

Description

Technical Field

[0001] The utility model belongs to the technical field of engines and parts thereof, and particularly relates to a turbine guide vane and a turbojet engine using the turbine guide vane. Background Art

[0002] As an emerging small thermal engine, micro-turbojet engines are widely used in military and civilian fields due to their advantages such as light weight, high power, long life, low fuel consumption, compact structure and high energy density. Among them, the turbine guide vane plays a vital role in the turbojet engine. Its main functions are as follows:

[0003] Guiding airflow: The turbine guide vane shape and arrangement effectively guide high-temperature, high-pressure gas from the combustion chamber into the turbine. This process achieves efficient energy conversion, converting thermal energy into mechanical energy.

[0004] Reduce airflow loss: Through the carefully designed turbine guide vane, the vortex and loss generated by the airflow during the flow process can be reduced, thereby improving the efficiency of the entire engine.

[0005] Balanced gas flow: The arrangement of the turbine guide vane helps to evenly distribute the airflow among the blades, avoid flow deviation and ensure stable operation of the turbine.

[0006] Due to these multiple functions, the turbine guide vane is an indispensable and critical component in gas turbine engines. The turbine guide vane consists of a guide vane cover and a guide vane located within the guide vane cover. The guide vane is fixedly connected to the engine's outer casing, and the guide vane is mounted on the outer periphery of the bearing housing end of the engine's main shaft. Due to the harsh operating conditions of the turbine guide vane, the guide vanes are surrounded by the gas flow and directly contact the high-temperature gas, resulting in high and unevenly distributed temperatures. Therefore, the guide vanes are preferably made of high-temperature alloys. However, due to the high hardness and difficulty in machining, the guide vane cover is preferably made of heat-resistant steel, which is easy to machine. This facilitates threaded holes in the guide vane cover and bolts to securely connect the guide vane to the engine's outer casing. The guide vane and guide vane are designed as separate components, with a radial gap between them for easy installation. However, in actual use, it has been found that during engine operation, the turbine is affected by axial reverse thrust, causing the turbine, guide vane, main shaft, and its components to move toward the engine's compressor, resulting in axial movement, which can affect engine operation and, in severe cases, even damage the engine.

[0007] This application is proposed in view of the above-mentioned technical defects.

[0008] It should be noted that the disclosure of the above background technology content is only used to assist in understanding the inventive concept and technical solution of this application, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above content has been disclosed on the filing date of this application, the above background technology should not be used to evaluate the novelty and creativity of this application. Summary of the Invention

[0009] In view of this, the technical problem to be solved by the present invention is: to provide a turbine guide and a turbojet engine using the turbine guide, which can prevent axial movement during operation, ensure the normal operation of the engine, and ensure the service life.

[0010] In order to solve the above-mentioned technical problems regarding the turbine guide, the technical solution of the present invention is: a turbine guide, the turbine guide includes a guide cover made of heat-resistant steel and a guide impeller made of high-temperature alloy located inside the guide cover; the guide cover includes a cylindrical portion and a flange portion arranged on the outer periphery of the cylindrical portion, the flange portion is provided with a flange through-hole, the inner cavity of the cylindrical portion is divided into an impeller cavity and a turbine cavity along its axial direction, and the cylindrical portion corresponding to the impeller cavity is provided with a cylindrical through-hole; the guide impeller includes a hub portion and a plurality of guide blades arranged on the outer periphery of the hub portion, and the end of the guide blade is provided with a blade hole extending along its longitudinal direction; it also includes a fastener, the fastener penetrates the cylindrical through-hole and the blade hole to fix the guide cover and the guide impeller together.

[0011] Preferably, the outer end of the fastener is welded to the guide cover.

[0012] Preferably, the radial size of the turbine chamber is larger than the radial size of the impeller chamber, and a step is formed between the turbine chamber and the impeller chamber.

[0013] Preferably, a positioning stop is provided on the outer periphery of the front end of the guide cover, and a concave arc surface is provided on the outer periphery of the rear end of the guide cover.

[0014] In order to solve the above-mentioned technical problems regarding the turbine guide, the technical solution of the present invention can also be: a turbine guide, the turbine guide includes a guide cover and a guide impeller located inside the guide cover; the guide cover includes a cylindrical body and a flange portion arranged on the outer periphery of the cylindrical body, the flange portion is provided with a flange through hole, the inner cavity of the cylindrical body is divided into an impeller cavity and a turbine cavity along its axial direction, the guide impeller includes a hub portion and a plurality of guide blades arranged on the outer periphery of the hub portion, the guide impeller and the cylindrical body are integrally cast using a high-temperature alloy, the flange portion is a flange portion made of heat-resistant steel, and the flange portion is welded to the cylindrical body.

[0015] Preferably, the radial size of the turbine chamber is larger than the radial size of the impeller chamber, and a step is formed between the turbine chamber and the impeller chamber.

[0016] Preferably, a positioning stop is provided on the outer periphery of the front end of the guide cover, and a concave arc surface is provided on the outer periphery of the rear end of the guide cover.

[0017] In order to solve the above-mentioned technical problems regarding turbojet engines, the technical solution of the present invention is: a turbojet engine, the turbojet engine includes an outer shell, a rotor assembly driven by a starter motor is arranged in the outer shell, the rotor assembly includes a main shaft, the main shaft is rotatably arranged in a bearing chamber, a combustion chamber is arranged on the periphery of the bearing chamber, a compressor impeller is arranged at the front end of the main shaft, a turbine is arranged at the rear end of the main shaft, a tail nozzle is arranged at the rear end of the turbine, and the turbine is located in a turbine guide, wherein the turbine guide is the turbine guide of the present invention described above, the flange through hole of the guide cover is fixedly connected to the outer shell by threaded fasteners, the hub portion of the guide impeller is installed on the outer periphery of the bearing chamber end, and the rear end of the combustion chamber is supported on the front end of the guide cover.

[0018] After adopting the above technical solution, the utility model has achieved at least the following beneficial effects:

[0019] Since the turbine guide of the present invention includes a guide cover made of heat-resistant steel and a guide impeller made of a high-temperature alloy located inside the guide cover, the guide cover and the guide impeller are fixed together by fasteners and then further welded; or, the guide impeller and the cylindrical portion of the guide cover are integrally cast using a high-temperature alloy, and the flange portion of the guide cover is made of heat-resistant steel; the turbine guide of the present invention can ensure that the guide impeller meets the requirements of harsh working conditions and is easy to process and manufacture.

[0020] In a turbojet engine adopting the turbine guide of the utility model, the guide cover flange portion is fixedly connected to the engine outer shell by threaded fasteners, the guide impeller hub portion is installed on the outer periphery of the bearing chamber end portion, and the rear end of the combustion chamber is supported on the front end of the guide cover; during the operation of the engine, even if the turbine is affected by the axial reverse thrust and has a tendency to drive the rotor assembly to move axially toward the compressor direction, since the guide cover of the turbine guide and the guide impeller are fixedly arranged as a whole, and the guide cover is fixedly connected to the engine outer shell, they are axially blocked by the turbine guide, and the turbine and the rotor assembly cannot move axially toward the compressor direction. Therefore, the turbine guide plays the role of guiding airflow, reducing airflow loss, balancing gas flow, etc., and also plays the role of axial thrust, thereby preventing the rotor assembly from axially moving and causing damage to the engine, thereby ensuring its service life. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1This is a schematic structural diagram of a turbojet engine according to an embodiment of the present invention;

[0022] Figure 2 yes Figure 1 A schematic diagram of the structure of a turbine guide vane;

[0023] Figure 3 yes Figure 2 Schematic diagram of turbine guide vane from top view;

[0024] Figure 4 yes Figure 3 Schematic diagram of CC cross section;

[0025] Figure 5 yes Figure 2 Schematic diagram of the guide impeller structure of the middle turbine guide device;

[0026] Figure 6 yes Figure 2 Schematic diagram of the guide cover structure of the turbine guide;

[0027] Figure 7 yes Figure 6 Schematic diagram of axial section;

[0028] Figure 8 It is another structural diagram of the turbine guide;

[0029] In the figure: 1. guide impeller; 101. hub; 102. guide blade; 1021. blade hole; 2. guide cover; 201. cylinder; 2011. impeller cavity; 20111. cylinder through hole; 2012. turbine cavity; 2013. positioning stop; 2014. concave arc surface; 202. flange; 2021. flange through hole; 3. fastener; 4. combustion chamber; 5. turbine; 6. bearing chamber; 7. main shaft; 8. locking nut; 9. bearing; 10. outer shell; 11. diffuser; 12. mounting plate; 13. compressor impeller; 14. air inlet; 15. starting motor; 16. tail nozzle. DETAILED DESCRIPTION

[0030] The following is a non-limiting description of the embodiments of the present invention in further detail with reference to the accompanying drawings.

[0031] It should be noted that, in the description herein, unless otherwise specified or limited, the terms "connected," "connected," and "connected" should be understood in a broad sense, and may refer to a direct connection between two elements or an indirect connection through an intermediate medium. Those skilled in the art will understand the specific meanings of the above terms based on the specific circumstances. The orientations or positional relationships described by "front" and "rear" are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate the description of the present invention and simplify the description. They do not indicate or imply that the device or element referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limitations on the present invention.

[0032] refer to Figures 1 to 8 As shown, the turbojet engine of the embodiment of the present invention includes: an outer shell 10, a rotor assembly driven by a starter motor 15 is arranged in the outer shell 10, the rotor assembly includes a main shaft 7, the main shaft 7 is rotatably arranged in a bearing chamber 6 through a bearing 9, a combustion chamber 4 is arranged on the outer periphery of the bearing chamber 6, a compressor impeller 13 is arranged at the front end of the main shaft, the inlet end of the compressor impeller 13 is connected to the inlet duct 14, and the outlet end of the compressor impeller 13 is provided with a diffuser 11 located in a mounting plate 12, a turbine 5 is arranged at the rear end of the main shaft, the turbine 5 is locked by a locking nut 8, a tail nozzle 16 is provided at the rear of the turbine, and the turbine 5 is located in the turbine guide.

[0033] like Figures 2 to 7 As shown, one structure of the turbine guide is that it includes a guide cover 2 made of heat-resistant steel and a guide impeller 1 made of a high-temperature alloy located inside the guide cover 2. The guide cover 2 and the guide impeller 1 are fixed together by a fastener 3 (preferably a cylindrical pin). To ensure a firm and reliable connection between the two, the outer end of the fastener 3 is further welded to the guide cover 2, preferably by laser welding. Figure 6 and Figure 7 As shown, the guide cover 2 includes a cylindrical portion 201 and a flange portion 202 provided on the outer periphery of the cylindrical portion. The flange portion is provided with a flange through hole 2021. The inner cavity of the cylindrical portion is divided into an impeller cavity 2011 and a turbine cavity 2012 along its axial direction. The cylindrical portion corresponding to the impeller cavity is provided with a cylindrical through hole 20111. Figure 5 As shown, the guide impeller 1 includes a hub portion 101 and a plurality of guide blades 102 disposed on its periphery. The ends of the guide blades are provided with blade holes 1021 extending longitudinally thereof. Fasteners 3 penetrate through the barrel through-holes 20111 and the blade holes 1021, securely connecting the guide vane cover 2 to the guide impeller 1. Furthermore, the outer ends of the fasteners 3 are welded to the guide vane cover 2, preferably by laser welding, to ensure a secure and reliable connection between the guide impeller 1 and the guide vane cover 2.

[0034] The optimized design is that the radial dimension of the turbine chamber 2012 is larger than the radial dimension of the impeller chamber 2011 , and a step is formed between the turbine chamber 2012 and the impeller chamber 2011 to prevent the turbine 5 from pressing against the guide impeller 1 .

[0035] The optimized design is that a positioning stop 2013 is provided on the outer periphery of the front end of the guide cover 2, and a concave arc surface 2014 is provided on the outer periphery of the rear end of the guide cover 2.

[0036] refer to Figure 1 、 Figure 5 and Figure 7 The turbine guide vane is in a turbojet engine, wherein the flange through hole 2021 of the guide vane cover 2 is fixedly connected to the engine outer shell 10 by threaded fasteners (bolts, etc., not specifically shown), the hub portion 101 of the guide impeller 1 is mounted on the outer periphery of the end of the bearing chamber 6, the rear end of the combustion chamber 4 is supported on the front end of the guide vane cover 2, and is adapted to the positioning stop 2013, and the concave arc surface 2014 at the rear end of the guide vane cover 2 is adapted to the diameter-changing corner at the front end of the tail nozzle 16, which is conducive to the positioning between the components.

[0037] like Figure 8 The figure shows another structure of the turbine guide of the present invention. The turbine guide of this structure includes a guide cover 2 and a guide impeller 1 located inside the guide cover 2. The guide cover 2 includes a cylindrical portion 201 and a flange portion 202 arranged on the outer periphery of the cylindrical portion. The flange portion is provided with a flange through-hole 2021. The inner cavity of the cylindrical portion is divided into an impeller cavity 2011 and a turbine cavity 2012 along its axial direction. The guide impeller 1 includes a hub portion and a plurality of guide blades arranged on the outer periphery of the hub portion. In addition, the guide impeller 1 and the cylindrical portion 201 are integrally cast using a high-temperature alloy. The flange portion 202 is a flange portion made of heat-resistant steel. The flange portion 202 is welded to the cylindrical portion 201.

[0038] The optimized design is that the radial dimension of the turbine chamber 2012 is larger than the radial dimension of the impeller chamber 2011, and a step is formed between the turbine chamber and the impeller chamber.

[0039] The optimized design is that a positioning stop 2013 is provided on the outer periphery of the front end of the guide cover, and a concave arc surface 2014 is provided on the outer periphery of the rear end of the guide cover.

[0040] Figure 8 The turbine guide shown is Figure 2 Compared with the turbine guide vanes shown in the figure, the design concept is basically the same, that is, the guide vane cover is fixedly set as an integral whole, which can prevent the turbine and rotor assembly from moving axially toward the compressor, prevent engine damage caused by axial movement, and ensure its service life.

[0041] The above description is an example of a preferred embodiment of the present invention. The parts not described in detail are all known technologies in the field. The scope of protection of the present invention is based on the content of the claims. Any equivalent transformation based on the technical inspiration of the present invention is within the scope of protection of the present invention.

Claims

1. A turbine guide vane, comprising: The guide cover is made of heat-resistant steel and the guide impeller is made of high-temperature alloy located inside the guide cover, characterized in that: The guide cover includes a cylindrical portion and a flange portion provided on the outer periphery of the cylindrical portion, the flange portion is provided with a flange through-hole, the inner cavity of the cylindrical portion is divided into an impeller cavity and a turbine cavity along its axial direction, and the cylindrical portion corresponding to the impeller cavity is provided with a cylindrical through-hole; The guide impeller includes a hub portion and a plurality of guide blades arranged on the periphery of the hub portion, wherein the ends of the guide blades are provided with blade holes extending in the longitudinal direction thereof; A fastener is inserted into the barrel through hole and the blade hole to fixedly connect the guide cover and the guide impeller.

2. The turbine guide vane according to claim 1, wherein: The outer end of the fastener is welded to the guide cover.

3. The turbine guide vane according to claim 1, wherein: The radial size of the turbine chamber is larger than the radial size of the impeller chamber, and a step is formed between the turbine chamber and the impeller chamber.

4. The turbine guide vane according to claim 1, wherein: The outer periphery of the front end of the guide cover is provided with a positioning stop, and the outer periphery of the rear end of the guide cover is provided with a concave arc surface.

5. A turbine guide vane, comprising: a guide vane and a guide cover located inside the guide vane, The guide cover includes a cylindrical portion and a flange portion provided on the outer periphery of the cylindrical portion, wherein the flange portion is provided with a flange through hole, and the inner cavity of the cylindrical portion is divided into an impeller cavity and a turbine cavity along its axial direction. The guide impeller includes a hub portion and a plurality of guide blades arranged on the outer periphery of the hub portion, and is characterized in that the guide impeller and the barrel portion are integrally cast using a high-temperature alloy, the flange portion is a flange portion made of heat-resistant steel, and the flange portion is welded to the barrel portion.

6. The turbine guide vane according to claim 5, wherein: The radial size of the turbine chamber is larger than the radial size of the impeller chamber, and a step is formed between the turbine chamber and the impeller chamber.

7. The turbine guide vane according to claim 5, wherein: The outer periphery of the front end of the guide cover is provided with a positioning stop, and the outer periphery of the rear end of the guide cover is provided with a concave arc surface.

8. A turbojet engine, comprising: An outer shell is provided with a rotor assembly driven by a starting motor, the rotor assembly includes a main shaft, the main shaft is rotatably arranged in a bearing chamber, a combustion chamber is provided on the periphery of the bearing chamber, a compressor impeller is provided at the front end of the main shaft, a turbine is provided at the rear end of the main shaft, a tail nozzle is provided at the rear end of the turbine, and the turbine is located in a turbine guide, and is characterized in that the turbine guide is the turbine guide according to any one of claims 1 to 7, the flange through hole of the guide cover is fixedly connected to the outer shell by threaded fasteners, the hub portion of the guide impeller is mounted on the outer periphery of the end portion of the bearing chamber, and the rear end of the combustion chamber is supported at the front end of the guide cover.

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