A cooling and noise reduction turbojet engine and aircraft

Abstract

The application discloses a cooling and noise reduction turbojet engine and aircraft. The turbojet engine comprises: a casing with a combustion chamber; a tail nozzle located downstream of the casing, an air inlet of the tail nozzle being connected with an air outlet of the casing; a fairing sleeved outside an air inlet of the casing and surrounding a mouth wall of the air inlet of the casing to form an annular containing chamber, the containing chamber being provided with a noise reduction structure; and a transmission-connected compressor and turbine, the compressor being arranged at an air inlet of the casing, and the turbine being arranged at an air outlet of the casing. The turbojet engine, under the working state of the compressor, the noise reduction structure reduces the noise generated by the interaction of the stator and the stator, and thus the noise generated by the turbojet engine under the working state is smaller.

Description

Technical Field

[0001] This invention relates to engine equipment technology, and more specifically, to a coolable and noise-reducing turbojet engine and aircraft. Background Technology

[0002] A turbojet engine is a type of aircraft engine that includes a casing with a combustion chamber, a cowling, an open annular bushing, a compressor, a turbine, a tailpipe, a muffler, and other accessories. Other accessories include fuel lines, solenoid valves, fuel pumps, and control units. The tail nozzle is located downstream of the casing, and its inlet is connected to the outlet of the casing. The muffler is located downstream of the tail nozzle, and its inlet is fitted outside the outlet of the tail nozzle. The inlet walls of the muffler and the outlet of the tail nozzle together form an ejector channel. The inlet of the ejector channel is connected to the outside, and the outlet of the ejector channel is connected to the inside of the muffler. The fairing is fitted outside the inlet of the casing and together with the inlet wall of the casing's inlet, forms an annular receiving chamber. Other accessories are located within the receiving chamber. The bushing is located within the receiving chamber, and its opening is used to avoid other accessories. The compressor is located inside the inlet of the casing, and the turbine is located inside the outlet of the compressor. The compressor and the turbine are connected via a drive shaft.

[0003] The compressor, rotating at high speed, draws in air, pressurizes it to perform work, and then sends the increased air into the combustion chamber for combustion. The high-temperature, high-pressure gas from combustion in the combustion chamber expands and performs work again through the turbine, then expands and accelerates through the exhaust nozzle before being exhausted at high speed. As the exhaust gas travels from the exhaust nozzle to the muffler, the outlet of the ejector channel draws in outside air into the muffler. The outside air mixes with the high-temperature, high-pressure exhaust gas inside the muffler, reducing the temperature and velocity of the exhaust gas. The mixture is then ejected from the muffler's outlet, propelling the aircraft. The muffler is used to reduce exhaust noise.

[0004] For turbojet engines, the thrust-to-weight ratio is a crucial performance indicator. Therefore, how to reduce the noise generated by turbojet engines during operation without increasing engine weight has always been a technical challenge that those skilled in the art have been working to solve. Summary of the Invention

[0005] This invention provides a coolable and noise-reducing turbojet engine that produces less noise during operation.

[0006] This invention also provides an aircraft.

[0007] The present invention provides a coolable and noise-reducing turbojet engine, comprising: a casing with a combustion chamber; a tail nozzle located downstream of the casing, the air inlet of the tail nozzle being connected to the air outlet of the casing; a cowling fitted outside the air inlet of the casing and forming an annular receiving chamber with the inlet wall of the air inlet of the casing, the receiving chamber being provided with a sound-absorbing structure; and a compressor and a turbine connected in a transmission, the compressor being located at the air inlet of the casing and the turbine being located at the air outlet of the casing.

[0008] In some exemplary embodiments, the inlet wall of the air inlet is provided with a first silencing hole, and the silencing structure includes the first silencing hole.

[0009] In some exemplary embodiments, the cross-section of the air inlet wall of the casing and the cross-section of the fairing are both curved structures. The first silencing hole includes a plurality of holes, which are arranged sequentially in the circumference of the air inlet, and the axis of each silencing hole is arranged radially along the air inlet.

[0010] In some exemplary embodiments, the turbojet engine further includes: a bushing disposed in the receiving chamber, the bushing having a second silencing hole, and the silencing structure further including the second silencing hole.

[0011] In some exemplary embodiments, the second silencing holes include a plurality of holes, which are arranged in a matrix and cover the bushing in both the circumferential and radial directions.

[0012] In some exemplary embodiments, the bushing is in the form of an open annulus and is disposed on the fairing.

[0013] In some exemplary embodiments, the turbojet engine further includes: a muffler pipe located downstream of the tail nozzle and connected to the tail nozzle, wherein the peripheral wall of the muffler pipe is provided with a process hole and a reverse muffler scale, the downstream end of the reverse muffler scale is connected to the inlet wall of the process hole away from the tail nozzle, and the upstream end of the reverse muffler scale is located inside the muffler pipe and extends toward the tail nozzle.

[0014] In some exemplary embodiments, the process holes and the reverse silencing flakes comprise multiple sets, and the multiple process holes and the multiple reverse silencing flakes are arranged in a matrix in the circumferential and radial directions of the silencing pipe.

[0015] In some exemplary embodiments, the air inlet of the muffler is sleeved outside the air outlet of the tail nozzle, and the inlet wall of the air inlet of the muffler and the inlet wall of the tail nozzle together form an ejector channel. The air inlet of the ejector channel is connected to the outside, and the air outlet of the ejector channel is connected to the interior of the muffler. The process hole and the reverse muffler scales are both located downstream of the tail nozzle.

[0016] In some exemplary embodiments, the tail nozzle is a lobed nozzle, and the number of peaks or troughs at the outlet of the lobed nozzle is 6 to 12.

[0017] The aircraft provided in the embodiments of the present invention includes the coolable and noise-reducing turbojet engine described in any of the above embodiments.

[0018] The turbojet engine provided in this embodiment of the invention has a noise reduction structure that reduces the noise generated by the interaction between the stator and the stator during compressor operation, thus resulting in less noise generated by the turbojet engine during operation.

[0019] Other features and advantages of the invention will be set forth in the following description, and will be apparent in part from the description, or may be learned by practicing the invention. The objects and other advantages of the invention may be realized and obtained by means of the structures particularly pointed out in the description and the drawings. Attached Figure Description

[0020] The accompanying drawings are provided to further understand the technical solutions of the present invention and constitute a part of the specification. They are used together with the embodiments of this application to explain the technical solutions of the present invention and do not constitute a limitation on the technical solutions of the present invention.

[0021] Figure 1 This is a cross-sectional structural schematic diagram of a turbojet engine provided in some embodiments of the present invention, with arrows indicating the direction of gas flow;

[0022] Figure 2 for Figure 1 A three-dimensional structural diagram of the middle bushing;

[0023] Figure 3 for Figure 1 A three-dimensional structural diagram of the mid-tail nozzle;

[0024] Figure 4 for Figure 1 Schematic diagram of the main structure of the silencer pipe;

[0025] Figure 5 for Figure 4 The diagram shows a front view of the silencing pipe in cross-section.

[0026] The correspondence between the reference numerals and the component names is as follows:

[0027] 100 Casing, 110 First Silencing Hole, 120 Air Inlet, 200 Tail Nozzle, 300 Silencing Pipe, 310 Process Hole, 320 Reverse Silencing Flakes, 410 Injection Channel, 420 Receiving Chamber, 500 Fairing, 600 Bushing, 610 Second Silencing Hole. Detailed Implementation

[0028] 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.

[0029] The coolable and noise-reducing turbojet engine provided in this embodiment of the invention, such as... Figure 1 As shown, it includes: a casing 100 with a combustion chamber; a tailpipe 200, located downstream of the casing 100, with its air inlet connected to the air outlet of the casing 100; and a muffler 300, located downstream of the tailpipe 200, with its air inlet sleeved outside the air outlet of the tailpipe 200. The inlet wall of the muffler 300 and the outlet wall of the tailpipe 200 together form an ejector channel 410, the air inlet of the ejector channel 410 communicating with the outside, and the air outlet of the ejector channel 410 connected to the muffler. The internal structure of the tube 300 is connected; the shroud 500 is fitted outside the air inlet 120 of the casing 100 and forms an annular receiving chamber 420 with the inlet wall of the air inlet 120 of the casing 100. The receiving chamber 420 is equipped with a noise reduction structure, which is configured to reduce the noise generated by the compressor during operation; the compressor and turbine (not shown in the figure) are connected by a drive. The compressor is located at the air inlet of the casing 100 and the turbine is located at the air outlet of the casing 100. The noise reduction structure is configured to reduce the noise generated by the compressor during operation.

[0030] This turbojet engine, in its compressor operation, draws in air at high speed, pressurizes the air to perform work, and then sends the pressurized air into the combustion chamber for combustion. During this process, the silencing structure reduces the noise generated by the interaction between the stator and stator of the compressor, thus reducing the noise generated by the turbojet engine in its operating state. The high-temperature and high-pressure gas after combustion in the combustion chamber expands and performs work through the turbine, and then expands and accelerates through the tail nozzle 200 before being exhausted at high speed. As the exhaust gas travels from the tail nozzle 200 to the silencer 300, the outlet of the ejector channel 410, under the guidance of the airflow, draws outside air into the silencer 300 and mixes it with the high-temperature and high-pressure exhaust gas inside the silencer 300, thereby reducing the temperature and velocity of the exhaust gas. Finally, the exhaust gas mixed with air is ejected from the outlet of the silencer 300, propelling the aircraft. The silencer 300 reduces exhaust noise during the exhaust process. Therefore, the turbojet engine provided by this design generates less noise in its operating state.

[0031] The compressor and turbine are connected by a drive shaft.

[0032] In some examples, such as Figure 1 As shown, the inlet wall of the air inlet is provided with a first silencing hole 110. The silencing structure includes the first silencing hole 110, which achieves noise reduction by eliminating the vortex noise generated by the compressor. The casing 100 is an existing component of the turbojet engine. The first silencing hole 110 is located on the inlet wall of the air inlet 120 of the casing 100. This design does not increase the weight of the turbojet engine, i.e., it does not increase the thrust-to-weight ratio of the turbojet engine. Preferably, there are multiple first silencing holes 110, which are sequentially arranged circumferentially around the air inlet. This improves the noise reduction effect of the first silencing holes 110 on the compressor. Furthermore, the axis of each silencing hole is arranged radially along the air inlet, further enhancing the noise reduction effect of the first silencing hole 110.

[0033] In one embodiment, such as Figure 1 As shown, the cross-section of the inlet wall of the air inlet 120 of the casing 100 and the cross-section of the fairing 500 are both curved structures, which improves the airflow guiding effect of the fairing 500 and the inlet wall of the air inlet 120 of the casing 100.

[0034] In some examples, such as Figure 1 and Figure 2As shown, the turbojet engine also includes a bushing 600, which is disposed within the receiving chamber 420. The bushing 600 is provided with a second silencing hole 610. The silencing structure also includes the second silencing hole 610, which also achieves noise reduction by eliminating the vortex noise generated by the compressor. The bushing 600 is an existing component of the turbojet engine, and the second silencing hole 610 is formed on the bushing 600. This design does not increase the weight of the turbojet engine, i.e., it does not increase the thrust-to-weight ratio of the turbojet engine. Preferably, there are multiple second silencing holes 610, arranged in a matrix and covering the bushing 600 circumferentially and radially. This results in better noise reduction for the compressor.

[0035] In one embodiment, such as Figure 2 As shown, the bushing 600 is an open ring (which can be understood as a C shape) and is provided on the fairing 500. The shape of the bushing 600 is adapted to the shape of the inner circumferential surface of the fairing 500, so that the structure after the bushing 600 and the fairing 500 are assembled is more compact.

[0036] The accommodating chamber 420 contains other accessories, including components such as oil pipes, solenoid valves, oil pumps, and control units. The opening of the bushing 600 is used to avoid at least one of the other components.

[0037] In some examples, such as Figure 1 , Figure 4 and Figure 5 As shown, the peripheral wall of the muffler 300 is provided with a process hole 310 and a reverse muffler scale 320. Both the process hole 310 and the reverse muffler scale 320 are located downstream of the tail nozzle 200. The downstream end of the reverse muffler scale 320 is connected to the opening wall of the process hole 310 away from the tail nozzle 200, and the upstream end of the reverse muffler scale 320 is located inside the muffler 300 and extends towards the tail nozzle 200. The process hole 310 and the reverse muffler scale 320 achieve noise reduction by eliminating the vortex noise generated by the exhaust gas mixed with air inside the muffler 300. The muffler 300 is an original component of the turbojet engine. The process hole 310 and the reverse muffler scale 320 are manufactured on the muffler 300 by stamping. This design does not increase the weight of the turbojet engine, i.e., it does not increase the thrust-to-weight ratio of the turbojet engine. Preferably, the process holes 310 and the reverse noise-reducing scales 320 include multiple sets, and the multiple process holes 310 and multiple reverse noise-reducing scales 320 are arranged in a matrix in the circumferential and radial directions of the muffler pipe 300. In this way, the process holes 310 and the reverse noise-reducing scales 320 have a better noise reduction effect on the exhaust gas mixed with air in the muffler pipe 300.

[0038] In some examples, such as Figure 1 and Figure 3As shown, the tail nozzle 200 is a lobed nozzle, and the number of peaks or troughs at the outlet of the lobed nozzle is 6 to 12, and the amplitude height of the peaks and troughs can be reasonably set according to the area layout requirements.

[0039] It could be that the number of wave crests at the outlet of the lobed nozzle is 6; or it could be that the number of wave crests at the outlet of the lobed nozzle is 8; or it could be that the number of wave crests at the outlet of the lobed nozzle is 10; or it could be, as... Figure 3 As shown, the number of peaks at the outlet of the lobed nozzle is 12, etc.; it could also be that the number of troughs at the outlet of the lobed nozzle is 6; or it could be that the number of troughs at the outlet of the lobed nozzle is 8; or it could be that the number of troughs at the outlet of the lobed nozzle is 10; or it could be, as... Figure 3 As shown, the number of troughs at the outlet of the lobed nozzle is 12, etc.; it is possible that the number of peaks and troughs at the outlet of the lobed nozzle are the same; or it is possible that the number of peaks and troughs at the outlet of the lobed nozzle are different; all of the above can achieve the purpose of this application, and their purpose has not departed from the design concept of this invention, and will not be elaborated here, and should all fall within the protection scope of this application.

[0040] Compared with related technologies, the turbojet engine provided in this application generates at least 10% less noise during operation.

[0041] The aircraft provided in this embodiment of the invention (not shown in the figure) includes the coolable and noise-reducing turbojet engine described in any of the above embodiments.

[0042] This aircraft possesses all the advantages of the cooled and noise-reducing turbojet engine provided in any of the above embodiments, which will not be elaborated here.

[0043] In summary, the turbojet engine provided by the embodiments of the present invention reduces the noise generated by the interaction between the stator and the stator in the compressor operating state through the noise reduction structure, thus resulting in less noise generated by the turbojet engine in the operating state.

[0044] In the description of this invention, it should be noted that the terms "upper", "lower", "one side", "the other side", "one end", "the other end", "side", "opposite", "four corners", "periphery", "'mouth' structure", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the structure referred to has a specific orientation, or is constructed and operated in a specific orientation. Therefore, they should not be construed as limiting this invention.

[0045] 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.

[0046] 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 with cooling and noise reduction capability, characterized in that, include: A casing with a combustion chamber; The tail nozzle is located downstream of the casing, and the air inlet of the tail nozzle is connected to the air outlet of the casing. A fairing is fitted over the air inlet of the casing and forms an annular receiving chamber with the inlet wall of the air inlet of the casing. The receiving chamber is equipped with a sound-absorbing structure. A compressor and a turbine are connected by a drive mechanism, wherein the compressor is located at the air inlet of the casing and the turbine is located at the air outlet of the casing; A muffler is located downstream of the tail nozzle and connected to the tail nozzle. The peripheral wall of the muffler is provided with a process hole and a reverse muffler scale. The downstream end of the reverse muffler scale is connected to the inlet wall of the process hole away from the tail nozzle. The upstream end of the reverse muffler scale is located inside the muffler and extends toward the tail nozzle. The process holes and the reverse noise-absorbing scales comprise multiple sets and are distributed in a matrix pattern; The air inlet of the muffler is sleeved outside the air outlet of the tail nozzle. The inlet wall of the muffler and the outlet wall of the tail nozzle together form an ejector channel. The air inlet of the ejector channel is connected to the outside, and the air outlet of the ejector channel is connected to the inside of the muffler. The process hole and the reverse noise-reducing scales are both located downstream of the tail nozzle.

2. The coolable and noise-reducing turbojet engine according to claim 1, characterized in that, The air inlet wall is provided with a first silencing hole, and the silencing structure includes the first silencing hole.

3. The coolable and noise-reducing turbojet engine according to claim 2, characterized in that, The cross-section of the air inlet wall of the casing and the cross-section of the fairing are both curved structures. The first silencing hole includes multiple holes, which are arranged sequentially around the air inlet. The axis of each silencing hole is arranged radially along the air inlet.

4. The coolable and noise-reducing turbojet engine according to claim 2, characterized in that, Also includes: A bushing is disposed in the receiving cavity, and the bushing is provided with a second silencing hole. The silencing structure also includes the second silencing hole.

5. The coolable and noise-reducing turbojet engine according to claim 4, characterized in that, The second silencing hole includes multiple holes, which are arranged in a matrix and cover the bushing in both the circumferential and radial directions.

6. The coolable and noise-reducing turbojet engine according to claim 4, characterized in that, The bushing is in the shape of an open ring and is disposed on the fairing; The casing has an air inlet equipped with a compressor and an air outlet equipped with a turbine, with the compressor and turbine being connected in a drive connection.

7. The coolable and noise-reducing turbojet engine according to any one of claims 1 to 6, characterized in that, The plurality of process holes and the plurality of reverse silencing scales are arranged in a matrix in the circumferential and radial directions of the silencing pipe.

8. The coolable and noise-reducing turbojet engine according to any one of claims 1 to 6, characterized in that, The tail nozzle is a lobed nozzle, and the number of peaks or troughs at the outlet of the lobed nozzle is 6 to 12.

9. An aircraft, characterized in that, Including the coolable and noise-reducing turbojet engine as described in any one of claims 1 to 8.

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