A turbojet engine

Abstract

A turbojet engine includes: a main body with a first combustion chamber and a second combustion chamber inside, the second combustion chamber having a functional structure; a compressor impeller disposed within the main body and forming an intake path with the main body; a turbine disposed within the main body and forming an exhaust path with the main body, the second combustion chamber surrounding the turbine; a shaft rotatably disposed within the main body, the compressor impeller and the turbine mounted on the shaft, the first combustion chamber located between the compressor impeller and the turbine and surrounding the shaft; and a fuel supply device disposed on the main body for supplying fuel to the first and second combustion chambers. In operation, the turbojet engine, with the rotation of the compressor impeller, compresses outside air through the intake path to the first and second combustion chambers. Fuel in the first combustion chamber burns and is then ejected to the outside through the exhaust path, while fuel in the second combustion chamber, after combustion in a detonation mode, is ejected to the outside as high-temperature, high-pressure exhaust gas. This turbojet engine provides greater thrust per unit of frontal thrust.

Description

Technical Field

[0001] This article relates to engine equipment technology, particularly a turbojet engine. Background Technology

[0002] Specific frontal thrust is an important indicator for turbojet engines. For micro-turbojet engines, due to cost and structural size limitations, high cycle parameters cannot be used in the design. The design pressure ratio and turbine inlet temperature are relatively low, and the compressor impeller adopts a centrifugal structure, all of which result in low specific frontal thrust of turbojet engines.

[0003] Improving the unit frontal thrust of turbojet engines has always been a technical challenge that those skilled in the art have been working to solve. Summary of the Invention

[0004] To solve at least one of the above-mentioned technical problems, this application provides a turbojet engine with greater thrust per unit frontal thrust during operation.

[0005] The turbojet engine provided in this embodiment of the invention includes: a main body, which has a first combustion chamber and a second combustion chamber inside, the second combustion chamber having a functional structure configured to cause the combustion mode of the fuel inside the second combustion chamber to be a knock mode; a compressor impeller disposed within the main body and forming an intake path with the main body; a turbine disposed within the main body and forming an injection path with the main body, the second combustion chamber surrounding the turbine; and a rotating shaft rotatably disposed within the main body, the compressor impeller and the turbine being mounted on... Mounted on the rotating shaft, the first combustion chamber is located between the compressor impeller and the turbine, and surrounds the rotating shaft; a fuel supply device is provided on the main body for supplying fuel to the first combustion chamber and the second combustion chamber; wherein, the air inlet of the first combustion chamber and the air inlet of the second combustion chamber are both connected to the air outlet of the air intake path, the air outlet of the first combustion chamber is connected to the air inlet of the jet path, and the air outlet of the second combustion chamber, the air outlet of the jet path, and the air inlet of the air intake path are all connected to the outside.

[0006] The subject includes:

[0007] An annular casing, in which the compressor impeller and the turbine are disposed;

[0008] A bushing, diffuser, guide, and inner nozzle are disposed within the casing. The diffuser and the guide are both fixed to the bushing, and the inner nozzle is fixed to the guide. The rotating shaft is rotatably disposed within the bushing.

[0009] An injection ring is disposed between the inner nozzle and the casing and fixed to the guide. The injection ring and the casing form the second combustion chamber.

[0010] A first combustion chamber component is provided with a first combustion chamber. The bushing, the casing, the diffuser, the guide, and the injection ring form a receiving cavity. The first combustion chamber component is disposed in the receiving cavity. The air outlet of the air intake path, the air inlet of the first combustion chamber, and the air inlet of the second combustion chamber are all connected to the receiving cavity.

[0011] The guide is fixed to the injection ring by a flange structure. The functional structure includes a plurality of injection holes arranged sequentially along the circumference of the second combustion chamber. The fuel supply device includes a fuel supply pipe that communicates with the injection holes and is used to supply fuel from the injection holes into the second combustion chamber. The other end of the fuel supply pipe passes sequentially through the receiving cavity, the diffuser, and the casing, and then communicates with the fuel tank outside the casing.

[0012] In some exemplary embodiments, the second combustion chamber is an annular structure, and the functional structure is configured such that the combustion mode of the fuel inside the second combustion chamber is a rotating detonation mode.

[0013] In some exemplary embodiments, the plurality of fuel injection holes are all oriented toward the exhaust port side of the second combustion chamber, and the injection direction of the plurality of fuel injection holes is deflected toward the same side of the circumference of the rotating shaft relative to the axis of the rotating shaft.

[0014] In some exemplary embodiments, the inner side of the second combustion chamber is provided with a protruding structure, the protruding structure having a first inclined surface and a second inclined surface, the first inclined surface facing the air inlet side of the second combustion chamber, the second inclined surface facing the air outlet side of the second combustion chamber, and the plurality of fuel injection holes are all located on the second inclined surface.

[0015] In some exemplary embodiments, the number of the plurality of oil injection holes is not less than 72.

[0016] In some exemplary embodiments, the nozzle diameter of each of the fuel injection holes is 0.2 mm to 0.5 mm.

[0017] In some exemplary embodiments, the exhaust ports of the second combustion chamber and the exhaust ports of the jet passage have the same injection direction.

[0018] In some exemplary embodiments, the turbine is located between the guide vane and the inner nozzle, the compressor impeller, the diffuser and the casing form the intake path, the guide vane, the turbine and the inner nozzle form the jet path, the inlet of the jet path is located on the guide vane, and the outlet of the jet path is located on the inner nozzle.

[0019] In some exemplary embodiments, the compressor impeller is a centrifugal impeller, and the gap between the centrifugal impeller and the casing is 0.2 mm to 0.5 mm.

[0020] The turbojet engine provided in this embodiment of the invention, in operation, causes the compressor impeller to rotate, causing outside air to be compressed through the intake path to the first combustion chamber and the second combustion chamber. After the fuel in the first combustion chamber is burned, it is injected to the outside through the jet path. The fuel in the second combustion chamber is injected to the outside as high-temperature and high-pressure exhaust gas after combustion in the detonation mode. Compared with the technical solution that only uses the first combustion chamber for propulsion, the technical solution of this application that uses the first combustion chamber and the second combustion chamber for propulsion together forms a larger unit frontal thrust.

[0021] Other features and advantages of this application will be set forth in the following description, and will be apparent in part from the description, or may be learned by practicing the application. Other advantages of this application can be realized and obtained by means of the solutions described in the description and the accompanying drawings. Attached Figure Description

[0022] The accompanying drawings are used to provide an understanding of the technical solutions of this application and constitute a part of the specification. They are used together with the embodiments of this application to explain the technical solutions of this application and do not constitute a limitation on the technical solutions of this application.

[0023] Figure 1 This is a cross-sectional structural schematic diagram of a turbojet engine according to some embodiments of the present invention;

[0024] Figure 2 for Figure 1 The diagram shows a right-side view of the turbojet engine.

[0025] in, Figure 1 and Figure 2 The correspondence between the reference numerals and component names in the attached drawings is as follows:

[0026] 110 First combustion chamber component, 111 First combustion chamber, 112 Connecting hole, 120 Second combustion chamber, 130 Protruding structure, 131 Injection hole, 132 Oil passage, 141 Casing, 142 Bushing, 143 Diffuser, 144 Guide, 145 Inner nozzle, 146 Injection ring, 150 Receiving cavity, 160 Nut, 170 Bearing, 200 Compressor impeller, 300 Turbine, 400 Shaft, 510 Oil supply pipe, 520 Evaporator pipe. Detailed Implementation

[0027] This application describes several embodiments, but these descriptions are exemplary and not restrictive. To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that, unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

[0028] The turbojet engine provided in the embodiments of the present invention, such as Figure 1 As shown, it includes: a main body, which has a first combustion chamber 111 and a second combustion chamber 120 inside. The second combustion chamber 120 has a functional structure configured to make the combustion mode of the fuel inside the second combustion chamber 120 a knock mode; a compressor impeller 200, which is located inside the main body and forms an intake path with the main body; a turbine 300, which is located inside the main body and forms an injection path with the main body, and the second combustion chamber 120 is spaced around the turbine 300; and a rotating shaft 400, which is rotatably located inside the main body. The compressor impeller 200 and the turbine 300 are mounted on... On the rotating shaft 400, the first combustion chamber 111 is located between the compressor impeller 200 and the turbine 300 and is spaced around the outside of the rotating shaft 400; the fuel supply device is located on the main body and is used to supply fuel to the first combustion chamber 111 and the second combustion chamber 120; wherein, the air inlet of the first combustion chamber 111 and the air inlet of the second combustion chamber 120 are both connected to the air outlet of the air intake path, the air outlet of the first combustion chamber 111 is connected to the air inlet of the jet path, and the air outlet of the second combustion chamber 120, the air outlet of the jet path and the air inlet of the air intake path are all connected to the outside.

[0029] When the turbojet engine is running, the compressor impeller 200 rotates, causing outside air to be compressed through the intake path to the first combustion chamber 111 and the second combustion chamber 120. After the fuel in the first combustion chamber 111 is burned, it is injected to the outside through the jet path. The fuel in the second combustion chamber 120 is injected to the outside as high-temperature and high-pressure exhaust gas after combustion in the detonation mode. Compared with the technical solution that only uses the first combustion chamber 111 for propulsion, the technical solution of this application that uses the first combustion chamber 111 and the second combustion chamber 120 for joint propulsion results in a greater unit frontal thrust, thus the turbojet engine has a greater thrust.

[0030] High temperature range: 800K~2400K; High pressure range: 0.5~2MPa.

[0031] In some exemplary embodiments, such as Figure 1 and Figure 2 As shown, the second combustion chamber 120 has an annular structure and extends along the axial direction of the main body. The air outlet of the second combustion chamber 120 and the air outlet of the jet passage are located at one end of the main body and have the same injection direction. The air inlet of the air intake path is located at the other end of the main body. The functional structure is configured to make the combustion mode of the fuel inside the second combustion chamber 120 a rotating detonation mode.

[0032] Fuel and air can achieve efficient combustion in a rotating detonation mode within a confined space and short distance. Therefore, the size of the second combustion chamber 120 can be designed to be relatively small. The first combustion chamber 111 and the second combustion chamber 120 are spaced apart in the axial direction of the main body, and the second combustion chamber 120 is surrounded by the turbine 300. This scheme does not increase the maximum radial dimension of the turbojet engine. Therefore, the turbojet engine has a larger unit frontal thrust and can be applied to micro-sized turbojet engines.

[0033] In some examples, such as Figure 1 and Figure 2 As shown, the functional structure includes a plurality of fuel injection holes 131 arranged sequentially along the circumference of the second combustion chamber 120. The plurality of fuel injection holes 131 are all facing the exhaust port side of the second combustion chamber 120, and the injection direction of the plurality of fuel injection holes 131 is deflected relative to the axis of the rotating shaft 400 toward the same side of the circumference of the rotating shaft 400, so that the fuel inside the second combustion chamber 120 forms a high temperature and high pressure rotational knock mode during combustion.

[0034] In one embodiment, such as Figure 1 and Figure 2 As shown, multiple injection holes 131 are evenly distributed around the second combustion chamber 120, and the number of multiple injection holes 131 is set to be no less than 72, and the nozzle diameter of each injection hole 131 is set to 0.2 mm to 0.5 mm.

[0035] In some examples, such as Figure 1As shown, a protruding structure 130 is provided on the inner side of the second combustion chamber 120. A throat is formed at the protruding structure 130 inside the second combustion chamber 120. The protruding structure 130 has a first inclined surface and a second inclined surface. The first inclined surface faces the air inlet side of the second combustion chamber 120, and the second inclined surface faces the air outlet side of the second combustion chamber 120. Multiple fuel injection holes 131 are located on the second inclined surface, and fuel is injected in a rotating manner towards the air outlet side of the second combustion chamber 120. When the fuel and air are mixed and burned in a rotating detonation mode, the high-temperature and high-pressure exhaust gas after combustion in the rotating detonation mode is injected into the air outlet side of the second combustion chamber 120, and finally sprayed out to the outside from the air outlet of the second combustion chamber 120.

[0036] In some examples, such as Figure 1 As shown, the fuel supply device includes: a fuel supply pipe 510, one end of which communicates with the injection port 131, and the other end extends out of the main body and communicates with the fuel tank outside the main body. The fuel tank supplies fuel to the second combustion chamber 120 through the fuel supply pipe 510 from the injection port 131. The fuel supply device also includes: an evaporator pipe 520, located in the first combustion chamber 111, for supplying fuel to the first combustion chamber 111. Alternatively, the protruding structure may have an internal fuel passage 132, which connects the fuel supply pipe 510 and the injection port 131.

[0037] In some exemplary embodiments, such as Figure 1 As shown, the main body includes: an annular casing 141, with a compressor impeller 200 and a turbine 300 disposed within the casing 141; a bushing 142, a diffuser 143, a guide vane 144, and an inner nozzle 145, all disposed within the casing 141. The diffuser 143 and the guide vane 144 are both fixed to the bushing 142, and the inner nozzle 145 is fixed to the guide vane 144. A rotating shaft 400 is rotatably disposed within the bushing 142. The turbine 300 is located between the guide vane 144 and the inner nozzle 145. The compressor impeller 200, diffuser 143, and casing 141 form an intake path, while the guide vane 144, turbine 300, and inner nozzle 145 form an exhaust path. An air inlet is located on the guide 144, and an air outlet of the jet path is located on the inner nozzle 145. An injection ring 146 is positioned between the inner nozzle 145 and the casing 141 and fixed to the guide 144. The injection ring 146 and the casing 141 form a second combustion chamber 120. A first combustion chamber component 110, equipped with a first combustion chamber 111, is formed by a bushing 142, casing 141, diffuser 143, guide 144, and injection ring 146, creating a receiving cavity 150. The first combustion chamber component 110 is located within the receiving cavity 150. The air outlet of the air inlet path, the air inlet of the first combustion chamber 111, and the air inlet of the second combustion chamber 120 are all connected to the receiving cavity 150. The first combustion chamber 111 has an annular structure, and the first combustion chamber component 110 has multiple connecting holes 112 of varying sizes, which connect the first combustion chamber 111 to the receiving cavity 150.

[0038] In some embodiments, the compressor impeller 200 is a centrifugal impeller, and the clearance between the centrifugal impeller and the casing 141 is set to be 0.2 mm to 0.5 mm; a bearing 170 is provided between the rotating shaft 400 and the bushing 142; reverse threads are provided at both ends of the rotating shaft 400, and two reverse threads are respectively screwed with nuts 160 to fix the centrifugal impeller and the turbine 300; both ends of the bushing 142 are fixed to the diffuser 143 and the guide vane 144 through flange structures. The guide vane 144 is fixed to the injection ring 146 through a flange structure. The other end of the fuel supply pipe 510 passes through the accommodation chamber 150, the diffuser 143 and the casing 141 in sequence and then communicates with the fuel tank outside the casing 141.

[0039] The centrifugal impeller sucks in outside air through high-speed rotation and adds work and boosts pressure in the intake path. The outside air then passes through the diffuser 143 for deceleration and pressure expansion and then enters the accommodation chamber 150; a part of the air in the accommodation chamber enters the first combustion chamber 111. The fuel in the first combustion chamber 111 burns, and then the combustion exhaust gas first passes through the guide vane 144 for expansion and acceleration, then passes through the turbine 300 for expansion, and then is ejected to the outside from the air outlet of the inner nozzle 145. During this process, the turbine 300 continuously generates rotational torque to drive the centrifugal impeller to rotate continuously; another part of the air in the accommodation chamber 150 enters the second combustion chamber 120. The fuel is mixed and burned with the air in the second combustion chamber 120, and the combustion mode is a high-temperature and high-pressure rotating detonation mode. The combustion exhaust gas is ejected to the outside from the air outlet of the second combustion chamber 120.

[0040] In summary, for the turbojet engine provided by the embodiment of the present invention, in the operating state, the rotation of the compressor impeller causes outside air to be pressurized and sent to the first combustion chamber and the second combustion chamber through the intake path. The fuel in the first combustion chamber burns and then is ejected to the outside through the jet path. The high-temperature and high-pressure exhaust gas after the fuel in the second combustion chamber burns in a detonation mode is ejected to the outside. Compared with the technical solution that only uses the first combustion chamber for propulsion, the technical solution that the present application uses the first combustion chamber and the second combustion chamber for joint propulsion forms a greater unit frontal thrust.

[0041] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by terms such as "upper", "lower", "one side", "the other side", "one end", "the other end", "side", "opposite", "four corners", "perimeter", "the structure of the character 'kou'" is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the structure referred to has a specific orientation, is constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention.

[0042] In the description of the embodiments of the present invention, unless otherwise expressly specified and limited, the terms "connection," "direct connection," "indirect connection," "fixed connection," "installation," and "assembly" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection. The terms "installation," "connection," and "fixed connection" can refer to a direct connection or an indirect connection through an intermediate medium, or they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in the present invention based on the specific circumstances.

[0043] While the embodiments disclosed in this invention are as described above, the content is merely for the purpose of facilitating understanding of the invention and is not intended to limit the invention. Any person skilled in the art to which this invention pertains may make any modifications and changes to the form and details of the implementation without departing from the spirit and scope disclosed herein; however, the scope of patent protection of this invention shall still be defined by the appended claims.

Claims

1. A turbojet engine, characterized in that, include: The main body has a first combustion chamber and a second combustion chamber inside. The second combustion chamber has a functional structure, which is configured to make the combustion mode of the fuel inside the second combustion chamber the knock mode. The compressor impeller is located inside the main body and forms an air intake path with the main body; A turbine is disposed within the main body and forms an air jet path with the main body, and a second combustion chamber is disposed outside the turbine; A rotating shaft is rotatably disposed within the main body, the compressor impeller and the turbine are mounted on the rotating shaft, and the first combustion chamber is located between the compressor impeller and the turbine and surrounds the rotating shaft; A fuel supply device, disposed on the main body, is used to supply fuel to the first combustion chamber and the second combustion chamber; The air inlet of the first combustion chamber and the air inlet of the second combustion chamber are both connected to the air outlet of the air intake path, the air outlet of the first combustion chamber is connected to the air inlet of the jet path, and the air outlet of the second combustion chamber, the air outlet of the jet path, and the air inlet of the air intake path are all connected to the outside. The subject includes: An annular casing, in which the compressor impeller and the turbine are disposed; A bushing, diffuser, guide, and inner nozzle are disposed within the casing. The diffuser and the guide are both fixed to the bushing, and the inner nozzle is fixed to the guide. The rotating shaft is rotatably disposed within the bushing. An injection ring is disposed between the inner nozzle and the casing and fixed to the guide. The injection ring and the casing form the second combustion chamber. A first combustion chamber component is provided with a first combustion chamber. The bushing, the casing, the diffuser, the guide, and the injection ring form a receiving cavity. The first combustion chamber component is disposed in the receiving cavity. The air outlet of the air intake path, the air inlet of the first combustion chamber, and the air inlet of the second combustion chamber are all connected to the receiving cavity. The guide is fixed to the injection ring by a flange structure. The functional structure includes a plurality of injection holes arranged sequentially along the circumference of the second combustion chamber. The fuel supply device includes a fuel supply pipe that communicates with the injection holes and is used to supply fuel from the injection holes into the second combustion chamber. The other end of the fuel supply pipe passes sequentially through the receiving cavity, the diffuser, and the casing, and then communicates with the fuel tank outside the casing.

2. The turbojet engine according to claim 1, characterized in that, The second combustion chamber has an annular structure, and the functional structure is configured such that the combustion mode of the fuel inside the second combustion chamber is the rotating detonation mode.

3. The turbojet engine according to claim 2, characterized in that, The plurality of fuel injection holes are all oriented toward the exhaust port side of the second combustion chamber, and the injection direction of the plurality of fuel injection holes is deflected toward the same side of the circumference of the rotating shaft relative to the axis of the rotating shaft.

4. The turbojet engine according to claim 3, characterized in that, The inner side of the second combustion chamber is provided with a protruding structure, the protruding structure having a first inclined surface and a second inclined surface, the first inclined surface facing the air inlet side of the second combustion chamber, the second inclined surface facing the air outlet side of the second combustion chamber, and the plurality of fuel injection holes are located on the second inclined surface.

5. The turbojet engine according to claim 3, characterized in that, The number of the plurality of oil injection holes is not less than 72.

6. The turbojet engine according to claim 3, characterized in that, The nozzle diameter of each of the aforementioned injection holes is 0.2mm to 0.5mm.

7. The turbojet engine according to claim 1, characterized in that, The exhaust ports of the second combustion chamber and the exhaust ports of the jet passage have the same injection direction.

8. The turbojet engine according to any one of claims 1 to 7, characterized in that, The turbine is located between the guide vane and the inner nozzle. The compressor impeller, the diffuser, and the casing form the intake path. The guide vane, the turbine, and the inner nozzle form the jet path. The intake port of the jet path is located on the guide vane, and the outlet port of the jet path is located on the inner nozzle.

9. The turbojet engine according to claim 1, characterized in that, The compressor impeller is a centrifugal impeller, and the gap between the centrifugal impeller and the casing is 0.2 mm to 0.5 mm.

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