CN111237083A - Combined spray pipe structure and airplane with same - Google Patents
Combined spray pipe structure and airplane with same Download PDFInfo
- Publication number
- CN111237083A CN111237083A CN201811429745.4A CN201811429745A CN111237083A CN 111237083 A CN111237083 A CN 111237083A CN 201811429745 A CN201811429745 A CN 201811429745A CN 111237083 A CN111237083 A CN 111237083A
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- nozzle
- sealing
- engine
- flange
- groove
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/80—Couplings or connections
- F02K1/805—Sealing devices therefor, e.g. for movable parts of jet pipes or nozzle flaps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Jet Pumps And Other Pumps (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
Abstract
The invention provides a combined spray pipe structure and an airplane with the same. The combined spray pipe structure provided by the invention can solve the technical problem that the requirements of axial thermal elongation compensation and engine disassembly and assembly maintenance on the structure of the traditional engine spray pipe are contradictory to the requirements of airplane rear stealth on the structure.
Description
Technical Field
The invention relates to the technical field of design of jet pipes of aero-engines, in particular to a combined jet pipe structure and an airplane with the same.
Background
Stealth airplanes and unconventional layout airplanes are developed rapidly in China. Particularly, stealth aircraft has a difficult point for designing the stealth aircraft in a backward stealth requirement. In order to reduce the radar reflection cross section, it is necessary to require no gap between the engine nozzle and the skin, which is difficult to do with conventional engine nozzles because: on one hand, the engine can be heated and elongated along the axial direction when in work, so that a gap is required to be reserved between the traditional engine nozzle and the aircraft skin; on the other hand, due to the requirements of engine disassembly and assembly and maintainability, the connection points of the engine and the engine body need to be as few as possible, so that the requirement of no gap between the engine spray pipe and the engine body skin is difficult to guarantee.
Disclosure of Invention
The following presents a simplified summary of the invention in order to provide a basic understanding of some aspects of the invention. It should be understood that this summary is not an exhaustive overview of the invention. It is not intended to determine the key or critical elements of the present invention, nor is it intended to limit the scope of the present invention. Its sole purpose is to present some concepts in a simplified form as a prelude to the more detailed description that is discussed later.
The invention aims to overcome the defects in the prior art and provides a combined spray pipe structure and an airplane with the same.
The technical solution of the invention is as follows:
according to an aspect, a combination nozzle pipe structure is provided, and combination nozzle pipe structure includes engine nozzle, compensating nozzle and seal assembly, and the gas outlet end of engine nozzle sets up and the air inlet end interval of compensating nozzle is connected for dismantling between the two, and seal assembly is used for sealing the junction of gas outlet end and air inlet end to and compensating nozzle still circumference laminating is fixed on aircraft skin inner wall.
Further, the air outlet end of the compensating nozzle is circumferentially attached and fixed to the inner wall of the aircraft skin.
Furthermore, a first butt flange is arranged at the air outlet end of the engine spray pipe, a second butt flange is arranged at the air inlet end of the compensation spray pipe, and the first butt flange and the second butt flange are arranged at intervals and detachably connected.
Further, the first butt flange and the second butt flange are connected by a clamping hoop.
Furthermore, the first butt flange is connected with the air outlet end of the engine spray pipe in a welding, gluing or screwing mode; the second butt-joint flange is connected with the air inlet end of the compensating nozzle in a welding, gluing or screwing mode.
Further, the sealing assembly comprises a plurality of first sealing elements and a plurality of second sealing elements, and the first sealing elements are arranged between the first butting flange and the clamping hoop; a second seal is disposed between the second mating flange and the clamp.
Further, first sealing member includes first recess and the first sealing washer of one-to-one setting, and first recess circumference sets up in the outside of first flange, and first sealing washer sets up in first recess.
Further, the second sealing element comprises a second groove and a second sealing ring which are arranged in a one-to-one correspondence mode, the second groove is circumferentially arranged on the outer side of the second butt flange, and the second sealing ring is arranged in the second groove.
Further, the number of the first sealing parts is at least two, and the at least two first sealing parts are arranged at intervals; the number of the second sealing parts is at least two, and the at least two second sealing parts are arranged at intervals.
According to another aspect, an aircraft is provided that includes the above-described composite nozzle structure.
By applying the technical scheme, the air outlet end of the traditional engine spray pipe is connected with the compensating spray pipe which is arranged on the inner wall of the aircraft skin in a circumferential fit manner, so that the requirement of backward stealth of the aircraft is met; and, on the basis of guaranteeing to stealthy after, set up and can dismantle through design engine spray tube and compensating nozzle interval and be connected, satisfied two spray tube axial extension and heated the demand of compensation and the engine dismouting maintainability demand. The combined spray pipe structure provided by the embodiment of the invention can meet the requirement of airplane rear stealth under the condition that the engine spray pipe is not directly connected with the skin (a gap is formed between the engine spray pipe and the skin), is convenient for assembling, disassembling and maintaining the engine, greatly reduces the maintenance cost, and can meet the requirement of heating compensation of axial extension of the two spray pipes on the basis of ensuring the rear stealth.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
FIG. 1 is a schematic view of a partial connection of a composite nozzle structure provided in accordance with an embodiment of the present invention;
FIG. 2 is an assembly schematic of a composite nozzle structure provided in accordance with an embodiment of the present invention;
FIG. 3 is an assembled cross-sectional view of a composite nozzle structure provided in accordance with an embodiment of the present invention;
the above figures contain the following reference numerals:
10. a first mating flange; 20. a second mating flange; 30. a first seal member; 31. a first groove; 32. a first seal ring; 40. a second seal member; 41. a second groove; 42. a second seal ring; 50. and (5) clamping a hoop.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail, but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
As mentioned in the background art, the requirement of backward stealth always provides a difficult point for stealth aircraft, and in order to reduce the radar reflection cross section, it is necessary to require no gap between the engine nozzle and the skin, which is difficult to achieve by the conventional engine nozzle, because: if no clearance is provided between the engine nozzle and the aircraft skin, the following problems may result: 1) in the flying process of the airplane, the engine nozzle is influenced by high temperature, axial thermal extension cannot be avoided, and if the engine nozzle is attached to the skin at the moment, the skin is ejected out and bulges, so that the airplane is damaged; 2) because the engine nozzle and the engine are designed into a whole usually, when the engine is maintained, the engine needs to be disassembled, if the engine nozzle is attached to the skin, the engine is difficult to disassemble, and the maintenance cost is greatly increased.
Based on the above background, an embodiment of the present invention provides a combined nozzle structure, including an engine nozzle, a compensation nozzle, and a sealing assembly, where an air outlet end of the engine nozzle and an air inlet end of the compensation nozzle are disposed at an interval and detachably connected, the sealing assembly is configured to seal a joint between the air outlet end and the air inlet end, and the compensation nozzle is further circumferentially attached and fixedly disposed on an inner wall of an aircraft skin.
By applying the combined spray pipe structure provided by the embodiment of the invention, the problem of designing the hidden airplane backwards hidden is solved. According to the embodiment of the invention, the air outlet end of the traditional engine nozzle is connected with the compensating nozzle, on one hand, at least part of the compensating nozzle is circumferentially attached and fixedly arranged on the inner wall of the aircraft skin, namely, no gap is ensured between the following compensating nozzle and the aircraft skin, and the requirement of backward stealth of the aircraft is met; on the other hand, on the basis of ensuring the backward stealth of the aircraft, in order to solve the problems of disassembly of the engine and thermal expansion of the nozzle (as mentioned above, if the nozzle is connected with the skin, the skin can be ejected out), the embodiment of the invention designs that the engine nozzle and the compensating nozzle are arranged at intervals and are detachably connected, and the two nozzles are arranged at intervals, namely under the condition that the two nozzles are axially expanded when heated, the expansion deformation can be compensated because of the gap between the two nozzles; the aircraft jet pipe assembly and the compensation jet pipe assembly can be detachably connected, the compensation jet pipe is fixedly arranged on an aircraft skin, the engine jet pipe at the moment can not be connected with the aircraft skin, and only the engine jet pipe and the compensation jet pipe are required to be detached when the aircraft jet pipe assembly and the compensation jet pipe assembly are detached, so that the aircraft parts are not damaged, the detachment convenience is greatly realized, and the assembly and disassembly cost is reduced.
In the embodiment of the invention, the engine nozzle is the engine nozzle of the traditional airplane, the position relation between the engine nozzle and other parts of the airplane is not described in detail, and for the scheme of the embodiment of the invention, the engine nozzle can meet the compensation amount of expansion caused by heat and contraction caused by cold of the engine and the installation requirement of the engine under the condition that the rear compensation nozzle and the skin have no clearance (namely, the stealth requirement is met).
In an embodiment of the present invention, the compensation nozzle is disposed in the aircraft skin in a direction consistent with a direction of disposition of the engine nozzle in the skin.
In the embodiment of the invention, the shape of the compensating nozzle is not specifically limited, the compensating nozzle can be consistent with the shape of an engine, the compensating nozzle can also be designed according to the space of the skin of an airplane, and in addition, in order to better realize the sealing connection between the engine nozzle and the compensating nozzle, the air outlet end of the engine nozzle and the air inlet end of the compensating nozzle are set to be consistent.
In the embodiment of the invention, the air outlet end of the engine spray pipe and the air inlet end of the compensating spray pipe are arranged at intervals, namely a gap is reserved between the air outlet end of the engine spray pipe and the air inlet end of the compensating spray pipe, so that the axial displacement of the engine spray pipe is not restrained, and the heated axial elongation of an engine is ensured; in addition, the size of the gap can be designed according to the installation requirements of the engine.
In the embodiment of the invention, the compensating nozzle can be circumferentially attached and fixed on the inner wall of the aircraft skin in a riveting or welding mode.
As an embodiment of the invention, in order to ensure a better backward stealth effect of an airplane, the air outlet end of the compensating nozzle is designed to be circumferentially attached and fixed on the inner wall of the airplane skin. The air outlet end of the compensating nozzle is circumferentially attached and fixed to the inner wall of the aircraft skin, so that the radar reflection cross section can be greatly reduced, and the backward stealth effect is guaranteed.
As an embodiment of the present invention, as shown in fig. 1 to 3, in order to connect the engine nozzle and the compensating nozzle, the outlet end of the engine nozzle is provided with a first docking flange 10, the inlet end of the compensating nozzle is provided with a second docking flange 20, and the first docking flange 10 and the second docking flange 20 are spaced apart and detachably connected.
In the embodiment of the invention, the first butt flange 10 can be sleeved on the air outlet section of the engine spray pipe, and the first butt flange 10 can be connected with the air outlet end of the engine spray pipe in a welding, gluing or screwing mode; the second butt-joint flange 20 can be sleeved at the air inlet end of the compensating nozzle, and the second butt-joint flange 20 is connected with the air inlet end of the compensating nozzle in a welding, gluing or screwing mode.
In one embodiment of the present invention, as shown in FIGS. 1-3, to removably attach the engine nozzle to the compensator nozzle, the first docking flange 10 and the second docking flange 20 are connected by a clamp 50.
In the embodiment of the present invention, as shown in fig. 1 to 3, two semicircular clips 50 are used to fix the first butt flange 10 and the second butt flange 20, and 4M 8 bolts are used to fix the two clips 50. When the engine nozzle and the compensating nozzle need to be disassembled, only the clamp 50 needs to be disassembled, and therefore the detachable connection between the engine nozzle and the compensating nozzle is achieved.
As an embodiment of the present invention, as shown in fig. 1 to 3, in order to achieve the sealing function of the sealing assembly, the sealing assembly may include a plurality of first sealing members 30 and a plurality of second sealing members 40, the first sealing members 30 being disposed between the first counterflange 10 and the clip 50; the second seal 40 is disposed between the second docking flange 20 and the clip 50. With this arrangement, the first sealing member 30 is disposed between the first docking flange 10 and the clip 50 to achieve a seal between the first docking flange 10 and the clip 50; the second sealing member 40 is disposed between the second docking flange 20 and the clamp 50 to seal the second docking flange 20 and the clamp 50, and the above-described design is designed to seal the engine nozzle and the compensating nozzle to ensure the normal flight of the aircraft.
As an embodiment of the present invention, as shown in fig. 1 to 3, in order to facilitate the sealing and the connection between the band 50 and the flange; the first sealing element 30 comprises a first groove 31 and a first sealing ring 32 which are arranged in a one-to-one correspondence, the first groove 31 is circumferentially arranged on the outer side of the first butt flange 10, and the first sealing ring 32 is arranged in the first groove 31. Similarly, the second sealing member 40 includes a second groove 41 and a second sealing ring 42, which are disposed in a one-to-one correspondence, the second groove 41 is circumferentially disposed outside the second docking flange 20, and the second sealing ring 42 is disposed in the second groove 41. In the embodiment of the present invention, the first groove 31 and the second groove 41 may be formed on the first docking flange 10 and the second docking flange 20.
In an embodiment of the present invention, the first seal ring 32 and the second seal ring 42 may be rubber seal rings.
As an embodiment of the present invention, in order to ensure better sealing effect, the number of the first sealing members 30 is at least two, and the at least two first sealing members 30 are arranged at intervals; similarly, at least two second sealing members 40 may be provided, and at least two second sealing members 40 may be provided at intervals.
There is also provided in accordance with another embodiment an aircraft including the composite nozzle structure described above. The connection of the composite nozzle structure to other aircraft components may be as described above.
According to the embodiment of the invention, the air outlet end of the traditional engine spray pipe is connected with the compensating spray pipe, and at least part of the compensating spray pipe is circumferentially attached to the inner wall of the aircraft skin, so that the requirement of backward stealth of the aircraft is met; and, on the basis of guaranteeing to stealthy after, set up and can dismantle through design engine spray tube and compensating nozzle interval and be connected, satisfied two spray tube axial extension and heated the demand of compensation and the engine dismouting maintainability demand. The combined spray pipe structure provided by the embodiment of the invention can meet the requirement of airplane rear stealth under the condition that the engine spray pipe is not directly connected with the skin (a gap is formed between the engine spray pipe and the skin), is convenient for assembling, disassembling and maintaining the engine, greatly reduces the maintenance cost, and can meet the requirement of heating compensation of axial extension of the two spray pipes on the basis of ensuring the rear stealth.
Spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, the scope of the present invention should not be construed as being limited.
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
The invention has not been described in detail and is in part known to those of skill in the art.
Claims (10)
1. The utility model provides a combination spray pipe structure, its characterized in that, combination spray pipe structure includes engine spray pipe, compensating nozzle and seal assembly, the air outlet end of engine spray pipe with the air inlet end interval of compensating nozzle sets up and be connected for dismantling between the two, seal assembly is used for sealing the junction of air outlet end and air inlet end, and compensating nozzle still circumference laminating is fixed on aircraft skin inner wall.
2. The composite nozzle tube structure as claimed in claim 1, wherein the outlet end of the compensation nozzle tube is circumferentially and snugly fixed to the inner wall of the aircraft skin.
3. The composite nozzle pipe structure as claimed in claim 1 or 2, wherein the outlet end of the engine nozzle is provided with a first docking flange, the inlet end of the compensation nozzle is provided with a second docking flange, and the first docking flange and the second docking flange are spaced apart and detachably connected.
4. The composite nozzle structure as claimed in claim 3, wherein the first and second docking flanges are connected by a clip.
5. The composite nozzle tube structure of claim 3, wherein the first docking flange is connected to the outlet end of the engine nozzle by welding, gluing or screwing; the second butt joint flange is connected with the air inlet end of the compensating nozzle in a welding, gluing or screwing mode.
6. The composite nozzle structure as claimed in claim 4, wherein the sealing assembly comprises a plurality of first sealing members and a plurality of second sealing members, the first sealing members being disposed between the first docking flange and the collar; the second seal is disposed between the second docking flange and the collar.
7. The combined nozzle structure as claimed in claim 6, wherein the first sealing element comprises a first groove and a first sealing ring, the first groove and the first sealing ring are arranged in a one-to-one correspondence, the first groove is circumferentially arranged outside the first butting flange, and the first sealing ring is arranged in the first groove.
8. The combined nozzle structure as claimed in claim 6 or 7, wherein the second sealing element comprises a second groove and a second sealing ring, the second groove and the second sealing ring are arranged in a one-to-one correspondence, the second groove is circumferentially arranged at the outer side of the second butting flange, and the second sealing ring is arranged in the second groove.
9. The combined nozzle structure as claimed in claim 6, wherein the number of the first sealing members is at least two, and the at least two first sealing members are spaced apart from each other; the number of the second sealing parts is at least two, and the at least two second sealing parts are arranged at intervals.
10. An aircraft, characterized in that the aircraft comprises a composite nozzle structure according to claims 1-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811429745.4A CN111237083B (en) | 2018-11-28 | 2018-11-28 | Combined spray pipe structure and airplane with same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811429745.4A CN111237083B (en) | 2018-11-28 | 2018-11-28 | Combined spray pipe structure and airplane with same |
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| Publication Number | Publication Date |
|---|---|
| CN111237083A true CN111237083A (en) | 2020-06-05 |
| CN111237083B CN111237083B (en) | 2022-01-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201811429745.4A Active CN111237083B (en) | 2018-11-28 | 2018-11-28 | Combined spray pipe structure and airplane with same |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115899399A (en) * | 2022-11-18 | 2023-04-04 | 大连长之琳科技发展有限公司 | On-site quick assembly pipeline connecting joint with axial compensation |
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| CN111237083B (en) | 2022-01-11 |
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