CN115949530B - Stealthy device of dysmorphism spray tube - Google Patents
Stealthy device of dysmorphism spray tube Download PDFInfo
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- CN115949530B CN115949530B CN202310218508.8A CN202310218508A CN115949530B CN 115949530 B CN115949530 B CN 115949530B CN 202310218508 A CN202310218508 A CN 202310218508A CN 115949530 B CN115949530 B CN 115949530B
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Abstract
The invention provides a stealth device of a special-shaped spray pipe, which comprises: the spray tube body comprises a hollow and mutually communicated stealth device accommodating cavity and a spray tube cavity; the mixer and the center cone are both arranged in the stealth device accommodating cavity, and the center cone is coaxially sleeved at the axis position of the mixer; a first annular space is formed between the inner wall of the mixer and the outer wall of the central cone, a second annular space is formed between the outer wall of the mixer and the inner wall of the spray tube body, the air inlet end of the mixer is connected with the section of the engine content outlet, and the air outlet end of the mixer is connected with the inner wall of the spray tube body; each group of the suction waveguide flow support plates comprises two parallel suction waveguide flow support plates which are arranged at intervals, one end of each suction waveguide flow support plate is fixedly connected with the inner wall of the mixer, and the other end of each suction waveguide flow support plate is fixedly connected with the outer wall of the center cone. Through the cooperation of the mixer, the suction waveguide flows the extension board, the external culvert shields the extension board and the internal culvert shields the extension board, the purpose of improving the infrared and radar stealth effect of the aircraft is achieved.
Description
Technical Field
The specification relates to the technical field of engine stealth devices, in particular to a stealth device of a special-shaped spray pipe.
Background
Aircraft engines are the main sources of infrared radiation and radar scatter for aircraft rearward. The backward infrared radiation signal of the aeroengine is mainly contributed by high-temperature components such as low-pressure turbine blades, turbine rectifying support plates, center cones and the like; radar scatter signals are mainly generated by resonance effects between low pressure turbine blades, outer ducted fan blades and smaller internal size components. Compared with the turbofan engine, the large duct has larger outer duct size than other engines, and radar scattering signals generated by the outer duct fan blades are stronger, so that the large duct belongs to a double-cavity strong scattering structure; and it is similar to other engines, possessing high temperature strong radiation characteristics inside the cavity. Therefore, the design idea of the backward stealth of the large-bypass-ratio turbofan engine is greatly different from that of other engines, and the design of the outward culvert stealth and the structural fusion design of the large-bypass-ratio turbofan engine are developed on the basis that the conventional engine takes the connotation as the stealth design key point.
For the design of the backward infrared and radar stealth of the turbofan engine, stealth materials, stealth structures and other measures are generally adopted.
The stealth material can effectively inhibit the characteristic signals of a main radar scattering source and an infrared radiation source in the engine cavity. The stealth structure is mainly divided into a flow passage restraining structure and an engine internal stealth structure. The flow passage restraining structure mainly comprises an S-bend spray pipe, a two-dimensional spray pipe and the like. The S-shaped spray pipe has remarkable inhibition effect on radar scattering and infrared radiation in the engine cavity, but the S-shaped spray pipe can realize effective shielding only by larger eccentricity, so that the flow passage is long and the weight is increased; the two-dimensional spray pipe runner is simple in design, small in length and weight gain, and limited in radar and infrared stealth benefits. The internal stealth device of the engine comprises structures such as a suction waveguide fluid and a shielding type integrated afterburner, and the application cases comprise that the suction waveguide fluid is applied to a forward air inlet channel of an American F/A-18E/F and X-32 aircraft, and the F-119 engine adopts an integrated afterburner, so that the stealth benefit is remarkable, but the technical difficulty is high and the development period is long aiming at the small duct compared with the rear internal culvert stealth of a turbofan engine or the forward stealth of the engine.
Large bypass ratio turbofan engines are generally limited by installation space and other conditions, and high stealth performance must be achieved in a limited space size. Because the S-bend spray pipe can realize effective shielding only by larger eccentricity, the use requirement of the turbofan engine with large bypass ratio cannot be met; the flat outlet of the two-dimensional spray pipe is beneficial to infrared stealth of the engine, but also leads to exposure of fan blades outside the turbofan engine with a large bypass ratio, which is not beneficial to efficient inhibition of radar characteristic signals. The internal stealth device of the engine mainly focuses on improving the internal stealth performance of the engine with the middle and small duct ratio, and is not suitable for improving the radar and infrared stealth capacity of the turbofan engine with the large duct ratio and the double-cavity strong scattering structure and the internal high-temperature strong radiation characteristic.
Disclosure of Invention
In view of this, the embodiments of the present disclosure provide a stealth device for a special-shaped nozzle to achieve the purpose of improving the infrared and radar stealth effects of an aircraft.
The embodiment of the specification provides the following technical scheme:
a cloaking device for a contoured nozzle, comprising:
the spray tube body comprises a hollow and mutually communicated stealth device accommodating cavity and a spray tube cavity;
the mixer and the center cone are arranged in the stealth device accommodating cavity, and the mixer is coaxially sleeved on the periphery of the center cone;
a first annular space is formed between the inner wall of the mixer and the outer wall of the central cone, a second annular space is formed between the outer wall of the mixer and the inner wall of the spray tube body, the air inlet end of the mixer is connected with the section of the engine content outlet, and the air outlet end of the mixer is connected with the inner wall of the spray tube body;
the wave-absorbing and flow-guiding support plates of the multiple groups are arranged in the first annular space at intervals, the first annular space is radially divided into a first subspace and a second subspace which are distributed at intervals, one end of each wave-absorbing and flow-guiding support plate is fixedly connected with the inner wall of the mixer, and the other end of each wave-absorbing and flow-guiding support plate is fixedly connected with the outer wall of the central cone.
Further, the stealth device of the special-shaped spray pipe further comprises an inner inclusion shielding support plate and an outer inclusion shielding support plate, wherein the inner inclusion shielding support plate is arranged in the first subspace, two ends of the inner inclusion shielding support plate are fixedly connected between a group of suction waveguide flow support plates, the outer inclusion shielding support plate is arranged in the second subspace, and two ends of the outer inclusion shielding support plate are fixedly connected between two adjacent groups of suction waveguide flow support plates.
Further, the inclusion shielding support plates are multiple, the number of the inclusion shielding support plates is the same as that of the suction waveguide flow support plate groups, each inclusion shielding support plate is parallel to the wall surface of the mixer, the first annular space is communicated with an engine inclusion outlet to form an air inlet end of high-temperature fuel gas, and the inclusion shielding support plates and the suction waveguide flow support plates form an air outlet end of the high-temperature fuel gas and are communicated to the spray pipe cavity.
Further, the number of the wave-absorbing and flow-guiding support plates is 12 to 24, and the number of the inclusion shielding support plates is the same as the number of the wave-absorbing and flow-guiding support plate groups.
Further, the outer culvert shielding support plates between two adjacent suction waveguide flow support plates are arranged in parallel and at intervals, a group of outer culvert shielding support plates are formed by a plurality of outer culvert shielding support plates, and the outer culvert shielding support plates of the same group are coaxially arranged along the axis of the mixer.
Further, the length of the suction waveguide flow support plate positioned in the horizontal direction of the nozzle barrel is larger than that of the suction waveguide flow support plate positioned in the vertical direction of the nozzle barrel, and the number of the outer culvert shielding support plates arranged in the horizontal direction of the nozzle barrel is larger than that of the outer culvert shielding support plates arranged in the vertical direction of the nozzle barrel.
Further, the outer culvert shielding support plates are arranged at the air outlet end of the second subspace, and the number of the outer culvert shielding support plates of one outer culvert shielding support plate group is 6 to 10.
Further, the second annular space is communicated with an engine outer culvert outlet to form an air inlet end of outer culvert cold air, and the outer culvert shielding support plate and the suction waveguide flow support plate form an air outlet end of the outer culvert cold air and are communicated to the spray pipe cavity.
Further, the upper edge of the nozzle cavity outlet of the nozzle barrel is flush with the central axis of the central cone.
Further, the stealth device of the special-shaped spray pipe further comprises an exhaust casing, and the mixer is connected with the engine through the exhaust casing.
Compared with the prior art, the beneficial effects that above-mentioned at least one technical scheme that this description embodiment adopted can reach include at least:
the outer culvert cold air flowing through the outer wall of the mixer and the high-temperature fuel gas flowing through the inner wall of the mixer are mixed and fused through the mixer, so that the micro-jet fuel gas is cooled down efficiently, the radar strong scattering sources in the inner culvert and the outer culvert of the engine are restrained through the set multi-group wave-absorbing and flow-guiding support plates, and the effect of improving the radar and infrared stealth capacity is achieved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of the overall structure of a cloaking device of a special-shaped spray pipe according to an embodiment of the invention;
FIG. 2 is a schematic view of a stealth apparatus of a profiled nozzle according to an embodiment of the present invention in semi-section;
FIG. 3 is a schematic front view of a stealth apparatus for a profiled nozzle according to an embodiment of the present invention;
FIG. 4 is a schematic illustration of the internal and external bypass gas flow paths of the cloaking device of the profiled nozzle in an embodiment of the invention.
Reference numerals illustrate: 1. a mixer; 2. a center cone; 3. an connotation shielding support plate; 4. a nozzle barrel; 5. the outer culvert shields the support plate; 6. a suction waveguide flow support plate; 7. an exhaust casing; 8. a first subspace; 9. and a second subspace.
Detailed Description
Embodiments of the present application are described in detail below with reference to the accompanying drawings.
Other advantages and effects of the present application will become apparent to those skilled in the art from the present disclosure, when the following description of the embodiments is taken in conjunction with the accompanying drawings. It will be apparent that the described embodiments are only some, but not all, of the embodiments of the present application. The present application may be embodied or carried out in other specific embodiments, and the details of the present application may be modified or changed from various points of view and applications without departing from the spirit of the present application. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application.
It is noted that various aspects of the embodiments are described below within the scope of the following claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present application, one skilled in the art will appreciate that one aspect described herein may be implemented independently of any other aspect, and that two or more of these aspects may be combined in various ways. For example, apparatus may be implemented and/or methods practiced using any number and aspects set forth herein. In addition, such apparatus may be implemented and/or such methods practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should also be noted that the illustrations provided in the following embodiments merely illustrate the basic concepts of the application by way of illustration, and only the components related to the application are shown in the drawings and are not drawn according to the number, shape and size of the components in actual implementation, and the form, number and proportion of the components in actual implementation may be arbitrarily changed, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided in order to provide a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.
The following describes the technical solutions provided by the embodiments of the present application with reference to the accompanying drawings.
As shown in fig. 1, 2 and 3, a stealth device for a profiled nozzle according to an embodiment of the present invention includes: the device comprises a mixer 1, a central cone 2, an inner culvert shielding support plate 3, a spray tube body 4, an outer culvert shielding support plate 5, a suction waveguide flow support plate 6 and an exhaust casing 7.
The spray tube body 4 is provided with an inner cavity which comprises a hollow and mutually communicated stealth device accommodating cavity and a spray tube cavity. The mixer 1 is fixedly arranged in the cloaking device accommodating cavity, and the mixer 1 is coaxially sleeved on the periphery of the center cone 2. The mixer 1 is in a horn-shaped structure, and the caliber of the air outlet end of the mixer 1 is larger than that of the air inlet end of the mixer 1. The inlet end of the mixer 1 is connected with the section of the engine inner culvert outlet, the outlet end of the mixer 1 is connected with the inner wall of the spray tube body 4, a first annular space is formed between the outer wall of the mixer and the inner wall of the spray tube body, and a second annular space is formed between the inner wall of the mixer 1 and the outer wall of the center cone 2. The main function of the mixer 1 is to blend and fuse the external cold air flowing through the outer wall of the mixer 1 with the high-temperature fuel gas flowing through the inner wall of the mixer 1, so as to realize the efficient cooling of the micro-jet fuel gas.
Each group of wave-absorbing guide support plates 6 comprises two parallel wave-absorbing guide support plates 6 which are arranged at intervals, and the plurality of groups of wave-absorbing guide support plates 6 are arranged in the first annular space at intervals and divide the first annular space into a first subspace 8 and a second subspace 9 which are distributed at intervals along the radial direction. The two ends of each group of the suction waveguide flow support plates 6 are fixedly connected with the inner wall of the mixer 1 and the outer wall of the center cone 2 respectively, namely one end of each suction waveguide flow support plate 6 is fixedly connected with the inner wall of the mixer 1, and the other end of each suction waveguide flow support plate 6 is fixedly connected with the outer wall of the center cone 2. The main function of the suction waveguide flow support plate 6 is to restrain radar strong scattering sources inside and outside the engine.
The connotation shielding support plate 3 is arranged in the first subspace 8, and two ends of the connotation shielding support plate 3 are respectively and fixedly connected between a group of suction waveguide flow support plates 6. The inclusion shielding support plates 3 between the group of suction guide flow support plates 6 can be multiple, and each inclusion shielding support plate 3 is parallel to the wall surface of the mixer. The inner culvert shielding support plate 3 is communicated to the high-temperature gas inlet end of the inner culvert outlet end forming an inner culvert of the engine, and the inner culvert shielding support plate 3 and the inner wall surface of the mixer 1 form the high-temperature gas outlet end of the inner culvert. The inner culvert shielding support plate 3 has the main functions of shielding and guiding, and reducing infrared radiation and radar scattering of the inner culvert of the engine.
The outer culvert shielding support plates 5 are arranged in the second subspace 9, each outer culvert shielding support plate 5 is fixedly connected between two adjacent groups of suction waveguide flow support plates, the air inlet ends of the second subspace 9 are sealed through the corresponding suction waveguide flow support plates 6 groups, and the outer culvert shielding support plates 5 are arranged at the air outlet ends of the second subspace 9. The outer culvert shielding support plates 5 between two adjacent groups of suction waveguide flow support plates 6 are a group consisting of a plurality of pieces, the same group of outer culvert shielding support plates 5 are arranged at parallel intervals, the outer culvert shielding support plates 5 of one group are coaxially arranged along the axis of the mixer 1, and the main functions of the outer culvert shielding support plates 5 are shielding and guiding, so that radar scattering of the outer culvert of the engine is reduced.
The mixer 1 is connected to an engine through an exhaust casing 7.
As shown in fig. 2, the lengths of the suction waveguide flow support plates 6 positioned at both sides of the nozzle body 4 in the horizontal direction are longer than those of the suction waveguide flow support plates 6 positioned at both ends in the vertical direction, so that the number of the outer culvert shielding support plates 5 positioned at both sides in the horizontal direction is greater than that of the outer culvert shielding support plates 5 positioned at both ends in the vertical direction.
As shown in fig. 3, the edge of the tail nozzle (outlet of the nozzle cavity) of the nozzle barrel 4 is flush with the central axis of the central cone 2, and the wall surface of the nozzle barrel 4 is used for partially shielding the inner culvert from the outer culvert, so that the airflow at the outlet of the nozzle flows along the axial direction, and the aerodynamic loss is reduced.
As shown in fig. 4, the second annular space is communicated with the end face of the outlet of the engine outer culvert to form an outer culvert cold air inlet end, and the outer culvert shielding support plate 5 and the suction waveguide flow support plate form an outer culvert cold air outlet end and are communicated to the spray pipe cavity; the inner inclusion shielding support plate 3 and the outer wall surface of the central cone 2 form an air inlet end of high-temperature fuel gas and are communicated with an inner inclusion outlet end surface of the engine, and the inner inclusion shielding support plate 3 and the suction waveguide flow support plate 6 form an air outlet end of the high-temperature fuel gas and are communicated to the spray pipe cavity. The outer culvert cold air of the outer culvert of the engine enters the first subspace 8 through the second annular space and the mixer 1 respectively, and the outer cold air is guided through a plurality of passages formed by the outer culvert shielding support plate 5 arranged in the first subspace 8. The high-temperature fuel gas of the internal duct of the engine enters the second subspace 9 through the mixer 1, and the high-temperature fuel gas is guided through a passage formed by the inner duct shielding support plate 3 arranged in the second subspace 9.
The surfaces of the wave-absorbing and wave-guiding flow supporting plate 6, the outer culvert shielding supporting plate 5 and the inner culvert shielding supporting plate 3 are all provided with certain bending, and the bending structure has the functions of wave-absorbing, flow guiding, multiple reflection, supporting and the like. The outer culvert shielding support plate 5 further has the functions of shielding, cooling, strong mixing and the like, and can realize strong inhibition in a large detection angle range for a strong scattering source and a strong radiation source of the inner culvert and the outer culvert of the large-bypass-ratio turbofan engine. Meanwhile, the suction waveguide flow support plate 6, the outer culvert shielding support plate 5 and the inner culvert shielding support plate 3 can be structurally integrated, and cold air of the outer culvert can be introduced between two adjacent groups of suction waveguide flow support plates 6 to realize cooling on the visible hot wall surface of the suction waveguide flow support plates 6. Meanwhile, the inner culvert shielding support plate 3 can shield the inner culvert hot wall surface.
The inner surfaces of the absorbing waveguide flow support plate 6, the outer culvert shielding support plate 5, the inner culvert shielding support plate 3, the spray pipe barrel 4, the center cone 2 and the inner surface of the mixer 1 are made of radar and infrared compatible materials or radar absorbing materials.
In order to realize full shielding of the internal culvert and the external culvert, the number of the suction waveguide flow support plates 6 is usually between twelve groups and twenty-four groups, and when the number is smaller than twelve groups, the torsion angle between the suction waveguide flow support plates 6 and the axis of the engine is larger, and at the moment, the aerodynamic loss is larger; when the number is more than twenty-four groups, the number of the suction guide flow support plates 6 is excessive, so that the flow passage is seriously blocked, and the pneumatic loss is also larger. The number of the outer culvert shielding support plates 5 in a group is usually six to ten.
In some embodiments, the number of the suction waveguide flow support plates 6 is twelve, the number of the corresponding external culvert shielding support plates 5 is also twelve, and the number of the corresponding internal culvert shielding support plates 3 is twelve.
In some embodiments, the number of the suction waveguide flow support plates 6 is eighteen, the number of the corresponding external culvert shielding support plates 5 is eighteen, the number of the external culvert shielding support plates 5 in one group is typically six to ten, and the number of the corresponding internal culvert shielding support plates 3 is eighteen. The test by adopting the structure can be as follows: under the typical working condition of the engine, the infrared radiation intensity of the engine is reduced by about 70% compared with the standard in the wave band range of 3-5 microns; in the X-band (8 GHz-12 GHz) of the typical frequency band of the engine, the radar scattering cross section of the engine is reduced by about 80% compared with the standard.
In some embodiments, the number of the suction waveguide flow support plates 6 is twenty-four groups, the number of the corresponding external culvert shielding support plates 5 is also twenty-four groups, and the number of the corresponding internal culvert shielding support plates 3 is twenty-four.
In some embodiments, the outer culvert shielding support plates 5 on two sides in the horizontal direction are in one group of ten pieces, the outer culvert shielding support plates 5 on two ends in the vertical direction are in one group of six pieces, and the number of the outer culvert shielding support plates 5 in the 45-degree angle is in one group of eight pieces.
The mixer 1, the suction waveguide flow support plate 6, the connotation shielding support plate 3 and the external connotation shielding support plate 5 have radar and infrared stealth capability on the basis of considering the basic aerodynamic performance and the function of the engine; the non-uniform stealth structure (the length of the suction waveguide flow support plate 6 in the horizontal direction of the nozzle barrel 4 is longer than that of the suction waveguide flow support plate 6 in the vertical direction of the nozzle barrel 4, and the number of the external culvert shielding support plates 5 in the horizontal direction of the nozzle barrel 4 is greater than that of the external culvert shielding support plates 5 in the vertical direction of the nozzle barrel 4) can be flexibly designed according to the characteristics of the engine nozzle, is suitable for various engine nozzle structural forms, such as axisymmetric nozzles, binary vector nozzles, straight special-shaped nozzles, single-deviation special-shaped nozzles and the like, and reduces the coupling design difficulty of the engine and the rear engine body structure of an aircraft; the high-integration structural layout consisting of the suction waveguide flow support plate 6, the outer culvert shielding support plate 5 and the inner culvert shielding support plate 3 is beneficial to inhibiting secondary scattering signals such as engine radar diffraction and the like and is beneficial to the high stealth design of the engine.
In this specification, each embodiment is described in a progressive manner, and identical and similar parts of each embodiment are all referred to each other, and each embodiment focuses on differences from other embodiments. In particular, for the method embodiments described later, since they correspond to the system, the description is relatively simple, and reference should be made to the description of some of the system embodiments.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (9)
1. A cloaking device for a contoured nozzle, comprising:
the spray tube body (4), the spray tube body (4) includes hollow and mutually communicated stealth device accommodating cavity and spray tube cavity;
the device comprises a mixer (1) and a central cone (2), wherein the mixer (1) and the central cone (2) are arranged in a housing cavity of the stealth device, and the mixer (1) is coaxially sleeved on the periphery of the central cone (2);
a first annular space is formed between the inner wall of the mixer (1) and the outer wall of the central cone (2), a second annular space is formed between the outer wall of the mixer (1) and the inner wall of the spray tube body (4), the air inlet end of the mixer (1) is connected with the section of the engine inner inclusion outlet, and the air outlet end of the mixer (1) is connected with the inner wall of the spray tube body (4);
the wave-absorbing and guiding support plates (6) are arranged in the first annular space at intervals, the first annular space is divided into a first subspace (8) and a second subspace (9) which are distributed at intervals along the radial direction, one end of each wave-absorbing and guiding support plate (6) is fixedly connected with the inner wall of the mixer (1), and the other end of each wave-absorbing and guiding support plate (6) is fixedly connected with the outer wall of the central cone (2);
the inner culvert shielding support plate (3) and the outer culvert shielding support plate (5) are arranged in the first subspace (8) and two ends of the inner culvert shielding support plate (3) are fixedly connected between a group of wave-absorbing and wave-guiding support plates (6), and the outer culvert shielding support plate (5) is arranged in the second subspace (9) and two ends of the outer culvert shielding support plate are fixedly connected between two adjacent groups of wave-absorbing and wave-guiding support plates (6).
2. The stealth device of a special-shaped spray pipe according to claim 1, wherein the inclusion shielding support plates (3) are multiple, the number of the inclusion shielding support plates (3) is the same as the number of the suction waveguide flow support plate (6) groups, each inclusion shielding support plate (3) is parallel to the wall surface of the mixer (1), the first annular space is communicated with an engine inclusion outlet to form an air inlet end of high-temperature fuel gas, and the inclusion shielding support plates (3) and the suction waveguide flow support plates (6) form an air outlet end of the high-temperature fuel gas and are communicated to the spray pipe cavity.
3. The stealth device of a special-shaped spray pipe according to claim 2, wherein the number of the wave-absorbing and flow-guiding support plates (6) is 12-24, and the number of the inner culvert shielding support plates (3) is the same as the number of the wave-absorbing and flow-guiding support plates (6).
4. The stealth device of a special-shaped spray pipe according to claim 1, wherein the outer culvert shielding support plates (5) between two adjacent wave-absorbing and guiding support plates (6) are arranged in parallel and at intervals, a group of outer culvert shielding support plates (5) is formed by a plurality of outer culvert shielding support plates, and the outer culvert shielding support plates (5) in the same group are coaxially arranged along the axis of the mixer (1).
5. The stealth device for a special-shaped spray pipe according to claim 4, wherein the length of the wave-absorbing and flow-guiding support plate (6) positioned in the horizontal direction of the spray pipe barrel (4) is larger than the length of the wave-absorbing and flow-guiding support plate (6) positioned in the vertical direction of the spray pipe barrel (4), and the number of the outer culvert shielding support plates (5) arranged in the horizontal direction of the spray pipe barrel (4) is larger than the number of the outer culvert shielding support plates (5) arranged in the vertical direction of the spray pipe barrel (4).
6. The stealth device of a special-shaped spray pipe according to claim 4, wherein the outer culvert shielding support plates (5) are arranged at the air outlet end of the second subspace (9), and the number of the outer culvert shielding support plates of one outer culvert shielding support plate (5) group is 6 to 10.
7. The stealth device of a profiled nozzle as claimed in claim 4, wherein the second annular space is communicated with an engine culvert outlet to form an air inlet end of the culvert cold air, and the culvert shielding support plate (5) and the suction waveguide flow support plate (6) form an air outlet end of the culvert cold air and are communicated to the nozzle cavity.
8. Cloaking device for a profiled nozzle as claimed in claim 1, characterized in that the upper edge of the nozzle chamber outlet of the nozzle body (4) is flush with the central axis of the central cone (2).
9. The cloaking device for a shaped nozzle according to claim 1, characterized in that the cloaking device for a shaped nozzle further comprises an exhaust casing (7), through which exhaust casing (7) the mixer (1) is connected to the engine.
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| CN202310218508.8A CN115949530B (en) | 2023-03-09 | 2023-03-09 | Stealthy device of dysmorphism spray tube |
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| CN202310218508.8A CN115949530B (en) | 2023-03-09 | 2023-03-09 | Stealthy device of dysmorphism spray tube |
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| CN115949530B true CN115949530B (en) | 2023-06-30 |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4117671A (en) * | 1976-12-30 | 1978-10-03 | The Boeing Company | Noise suppressing exhaust mixer assembly for ducted-fan, turbojet engine |
| CN113339156A (en) * | 2021-06-28 | 2021-09-03 | 西北工业大学 | Dual-bearing binary plug type thrust vectoring nozzle |
| CN113775436A (en) * | 2021-08-16 | 2021-12-10 | 中国航发贵阳发动机设计研究所 | Stealthy whirl mixing arrangement |
| CN114151226A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Multi-partition-plate comprehensive stealth structure arranged in straight binary convergent nozzle flow channel |
Family Cites Families (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4018046A (en) * | 1975-07-17 | 1977-04-19 | Avco Corporation | Infrared radiation suppressor for gas turbine engine |
| US4077206A (en) * | 1976-04-16 | 1978-03-07 | The Boeing Company | Gas turbine mixer apparatus for suppressing engine core noise and engine fan noise |
| US4135363A (en) * | 1976-05-13 | 1979-01-23 | United Technologies Corporation | Device to provide flow inversion in a turbofan exhaust tailpipe to achieve low jet noise |
| FR2409387A1 (en) * | 1977-11-17 | 1979-06-15 | Gen Electric | Jet engine with reduced exhaust gas noise - has coplanar discharge nozzle to mix high and low speed gas flows |
| US4226297A (en) * | 1979-01-12 | 1980-10-07 | United Technologies Corporation | Acoustic treated exhaust plug for turbine engine |
| GB2119859A (en) * | 1982-05-06 | 1983-11-23 | Rolls Royce | Exhaust mixer for bypass gas turbine aeroengine |
| US8341935B2 (en) * | 2007-06-05 | 2013-01-01 | The Boeing Company | Internal mixing of a portion of fan exhaust flow and full core exhaust flow in aircraft turbofan engines |
| RU2490496C2 (en) * | 2011-11-10 | 2013-08-20 | Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") | Outlet device of double-flow gas-turbine engine |
| FR3010454B1 (en) * | 2013-09-10 | 2024-02-16 | Snecma | REAR BODY OF A MIXED FLOW TURBOREACTOR COMPRISING A LOBED MIXER AND RAFFLES WITH NON-AXISYMMETRICAL INTERNAL SURFACE |
| US10100705B2 (en) * | 2014-08-27 | 2018-10-16 | Sikorsky Aircraft Corporation | Exhaust mixer and method of making same |
| CN113586281B (en) * | 2021-07-15 | 2022-08-02 | 哈尔滨工程大学 | Ship gas turbine with non-uniform lobe injection mixer |
| CN115614176B (en) * | 2022-08-29 | 2024-04-19 | 中国航发四川燃气涡轮研究院 | Infrared and radar comprehensive stealth device based on internal and external culvert structure integration |
| CN115614177B (en) * | 2022-08-29 | 2024-04-16 | 中国航发四川燃气涡轮研究院 | Full shielding blending integrated casing |
| CN115653782B (en) * | 2022-10-13 | 2024-05-03 | 中国航发四川燃气涡轮研究院 | Stealthy spray tube structure based on two cavity structures of turbofan engine |
-
2023
- 2023-03-09 CN CN202310218508.8A patent/CN115949530B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4117671A (en) * | 1976-12-30 | 1978-10-03 | The Boeing Company | Noise suppressing exhaust mixer assembly for ducted-fan, turbojet engine |
| CN113339156A (en) * | 2021-06-28 | 2021-09-03 | 西北工业大学 | Dual-bearing binary plug type thrust vectoring nozzle |
| CN113775436A (en) * | 2021-08-16 | 2021-12-10 | 中国航发贵阳发动机设计研究所 | Stealthy whirl mixing arrangement |
| CN114151226A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Multi-partition-plate comprehensive stealth structure arranged in straight binary convergent nozzle flow channel |
Non-Patent Citations (2)
| Title |
|---|
| 波瓣喷管引射-混合器的数值研究与验证;单勇,张靖周;燃气涡轮试验与研究(第03期);全文 * |
| 混合排气二元收敛喷管气动与红外隐身综合设计方法;李娜;吉洪湖;黄伟;陈俊;斯仁;刘常春;;航空动力学报(第11期);全文 * |
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