CN114671034B - A dual-nozzle flying engine overlapping cover structure - Google Patents
A dual-nozzle flying engine overlapping cover structure Download PDFInfo
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- CN114671034B CN114671034B CN202210471123.8A CN202210471123A CN114671034B CN 114671034 B CN114671034 B CN 114671034B CN 202210471123 A CN202210471123 A CN 202210471123A CN 114671034 B CN114671034 B CN 114671034B
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- cover
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- 230000002787 reinforcement Effects 0.000 claims description 16
- 238000009434 installation Methods 0.000 claims description 13
- 239000011347 resin Substances 0.000 claims description 7
- 229920005989 resin Polymers 0.000 claims description 7
- 239000000463 material Substances 0.000 claims description 4
- 238000003466 welding Methods 0.000 claims description 4
- 238000005452 bending Methods 0.000 claims description 3
- 230000001681 protective effect Effects 0.000 claims description 3
- 230000009977 dual effect Effects 0.000 claims 6
- 239000000805 composite resin Substances 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 9
- 239000007921 spray Substances 0.000 description 24
- 230000003014 reinforcing effect Effects 0.000 description 10
- 239000003351 stiffener Substances 0.000 description 9
- 239000011248 coating agent Substances 0.000 description 8
- 238000000576 coating method Methods 0.000 description 8
- 230000004048 modification Effects 0.000 description 6
- 238000012986 modification Methods 0.000 description 6
- 239000010410 layer Substances 0.000 description 5
- 230000001105 regulatory effect Effects 0.000 description 5
- 235000017166 Bambusa arundinacea Nutrition 0.000 description 4
- 235000017491 Bambusa tulda Nutrition 0.000 description 4
- 241001330002 Bambuseae Species 0.000 description 4
- 235000015334 Phyllostachys viridis Nutrition 0.000 description 4
- 239000011425 bamboo Substances 0.000 description 4
- 239000002131 composite material Substances 0.000 description 4
- 210000001503 joint Anatomy 0.000 description 4
- 239000011159 matrix material Substances 0.000 description 4
- 230000006835 compression Effects 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- 230000007704 transition Effects 0.000 description 3
- 230000004584 weight gain Effects 0.000 description 3
- 235000019786 weight gain Nutrition 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 238000007493 shaping process Methods 0.000 description 2
- 239000002356 single layer Substances 0.000 description 2
- 238000009966 trimming Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000005489 elastic deformation Effects 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings or cowlings
- B64D29/06—Attaching of nacelles, fairings or cowlings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings or cowlings
- B64D29/04—Power-plant nacelles, fairings or cowlings associated with fuselages
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/10—Constructional aspects of UAVs for stealth, e.g. reduction of cross-section detectable by radars
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Radar, Positioning & Navigation (AREA)
- Mechanical Engineering (AREA)
- Details Or Accessories Of Spraying Plant Or Apparatus (AREA)
Abstract
本申请属于航空发动机领域，特别涉及一种二元喷管飞发搭接外罩结构，所述二元喷管飞发搭接外罩结构主要包括呈圆弧片状的外壳体、内壳体，外壳体的前、后端为锯齿修型，内壳体位于外壳体的内侧，与外壳体有部分重叠搭接区域，外壳体的后端与外调节片前端搭接且具有间隙，避免运动干涉，同时形成发动机舱和外流交换的气流通道。喷管状态调整变化时，飞发搭接外罩始终与机尾罩、外调节片保持良好搭接关系，保证飞发搭接外罩良好的整流作用和达到飞机前向和发动机后向隐身的要求。
The present application belongs to the field of aviation engines, and particularly relates to a dual-nozzle flying engine overlapping outer cover structure, wherein the dual-nozzle flying engine overlapping outer cover structure mainly includes an outer shell and an inner shell in the shape of an arc sheet, the front and rear ends of the outer shell are serrated, the inner shell is located on the inner side of the outer shell, and has a partially overlapping overlapping area with the outer shell, the rear end of the outer shell overlaps the front end of the outer adjustment sheet and has a gap to avoid motion interference, and at the same time forms an airflow channel for the exchange between the engine compartment and the external flow. When the nozzle state is adjusted and changed, the flying engine overlapping outer cover always maintains a good overlapping relationship with the tail cover and the outer adjustment sheet, ensuring a good rectifying effect of the flying engine overlapping outer cover and meeting the requirements of the aircraft forward and engine rearward stealth.
Description
Technical Field
The application belongs to the field of aeroengines, and particularly relates to a two-dimensional spray pipe fly lap joint outer cover structure.
Background
The flying lap joint outer cover structure of the military aircraft engine is used as a component for lap joint of the engine and the rear fuselage of the aircraft, is a rectifying structure for switching the outer regulating piece of the engine spray pipe and the tail cover of the aircraft, is an important component system for realizing integration of the engine and the rear fuselage of the aircraft, is exposed outside the aircraft and the engine body, and has a stealth function.
The prior structure scheme of the fly-hair lap joint outer cover mainly adopts a compression contact type elastic sheet scheme. Taking a conventional axisymmetric spray pipe scheme as an example, the structure scheme of the flying hair lap joint outer cover mainly comprises a supporting ring structure and an elastic sheet, wherein the supporting ring is fixed on a barrel casing mounting seat through a supporting rod, and the elastic sheet is fixedly arranged on the supporting ring. When the aircraft and the engine are assembled, the elastic sheet is in pressing contact with the aircraft tail cover through elastic deformation. The stealth measure of the elastic sheet is mainly to adopt a stealth coating.
The existing domestic axisymmetric spray pipe compacting contact type elastic sheet structure scheme has the following defects:
(1) The problem of reliability is that in order to meet the air quantity required by engine starting, the elastic sheet in compression contact type is subjected to slotting treatment, and the elastic sheet is subjected to the action of an external flow field and elastic compression pretightening force, so that larger deformation and stress concentration are easy to occur in a slotting area, and cracks are caused;
(2) The stealth coating has the advantages that the reliability and the weight gain of the stealth coating are high, the elastic sheet is easy to deform greatly and collide with adjacent components, the adhesion of the stealth coating is greatly affected due to the influence of vibration and thermal stress, the circumferential area of the elastic sheet is large, and the weight of the stealth coating is increased.
At present, no two-dimensional spray pipe flying lap joint outer cover exists in China, if an elastic ring and a tail cover are adopted for lap joint, lap joint steps appear, the flying lap joint outer cover does not meet the design of flying lap joint integration, the aircraft rear body stealth is not facilitated, the elastic ring is large in area, and if a stealth coating is adopted, the weight is further increased.
Disclosure of Invention
In order to solve the problems, the application provides a two-dimensional spray pipe flyer lap joint outer cover structure, which is overlapped between an outer adjusting sheet and a tail cover, and mainly comprises an outer shell and an inner shell which are in circular arc sheet shapes, wherein the front end and the rear end of the outer shell are saw-tooth trimming parts, the inner shell is positioned at the inner side of the outer shell and has a part of overlapped area with the outer shell, steps exist between the two parts due to thickness, the two side ends of the outer shell and the inner shell are straight fixed mounting edges formed by bending, the outer shell is fixedly connected with two side walls of a spray pipe through the fixed mounting edges, the tail cover is a part of an aircraft rear body, the tail end saw-tooth trimming part of the tail cover is consistent with the saw teeth at the front end of the outer shell, the tail cover is clung to the outer wall surface of the front end of the inner shell and is overlapped with the saw teeth at the front end of the outer shell, the tail cover and is in smooth transition with the outer surface of the outer shell, the tail end of the outer shell is overlapped with the front end of the outer adjusting sheet and has a gap, and the movement is avoided, and an airflow channel for exchanging engine cabin and engine cabin is formed. When the state of the spray pipe is adjusted and changed, the flying hair overlap cover always keeps good overlap relation with the tail cover and the outer adjusting piece, so that good rectifying effect of the flying hair overlap cover is ensured, and the requirements of forward direction of an airplane and backward direction stealth of an engine are met.
The special scheme of the application is that the two-dimensional spray pipe flying lap joint outer cover structure is lapped between the outer adjusting piece and the tail cover;
The two-dimensional spray pipe flying lap joint outer cover structure comprises an outer shell body and an inner shell body of an outer layer, wherein the front end and the rear end of the outer shell body are subjected to sawtooth modification, and the sawtooth modification at the front end of the outer shell body is in butt joint with the sawtooth modification at the rear end of the tail cover;
The tail cover is a part of the rear body of the airplane, the tail end saw teeth of the tail cover are shaped, the shaping angles and the number are consistent with those of the saw teeth at the front end of the outer shell, the tail part of the tail cover is lapped on the outer wall surface of the front end of the inner shell, the saw teeth at the front end of the outer shell are meshed with each other, no gaps exist, the tail cover and the outer surface of the outer shell are in smooth transition, the resistance of the tail cover of the airplane can be effectively reduced, the step surface between the tail cover and the outer adjusting piece is reduced, in addition, the two axial ends of the outer shell are shaped by saw teeth, the front end and the tail cover are shaped by corresponding saw teeth, the stealth problem caused by the straight surface connection can be reduced, and the stealth effect is improved.
The front end of inner casing extends forward and overlap joint with the medial surface of tail cover, and the both sides end of outer casing along circumference has the fixed mounting limit of buckling formation, and the outer casing passes through two lateral wall fixed mounting that fixed mounting limit and spray tube have, the front end of inner casing overlap joint with the medial surface of tail cover, outer casing front end and the mutual meshing of tail cover sawtooth and outer casing pass through the cooperation of these three angles of two lateral wall fixed mounting that fixed mounting limit and spray tube have can with the constraint of a plurality of angles is carried out to two-dimensional spray tube flying overlap joint dustcoat structure, realizes firm and the stability of assembly to do not need to install with the help of traditional elastic sheet, the life-span is durable and firm.
Preferably, the inner side of the inner shell is provided with an arc-shaped supporting reinforcing ring, the supporting reinforcing ring is arranged along the circumferential direction of the inner shell, and the supporting reinforcing ring can provide the strength of the inner shell.
Preferably, the cross section of supporting the stiffener ring is "several" style of calligraphy, including the flat section in the middle and the foot limit of both sides, the foot limit of both sides and the surface contact of interior casing, through welding or rivet and shell body, interior casing fixed connection, the surface formation ring chamber of supporting stiffener ring and interior casing is equipped with a plurality of circumference distribution's a pad section of thick bamboo in the ring chamber, pad section of thick bamboo one end welding Yu Pingduan, the other end is installed in shell body and interior casing corresponding mounting hole through the spacing boss that has, screw or bolt will support stiffener ring and spray tube fixed connection through pad section of thick bamboo, the structural weight of supporting stiffener ring self can be alleviateed to the structure of supporting stiffener ring "several" style of calligraphy structure, the installation intensity of supporting stiffener ring can be realized to the pad section of thick bamboo simultaneously, when avoiding supporting stiffener ring through the screw installation, because the pretightning force of screw makes the supporting stiffener ring produce the destruction.
Preferably, the material of the outer shell comprises a wave-absorbing function resin matrix composite material, and the outer surface is coated with a protective resin for changing the appearance color, so that the stealth function of the outer shell is improved.
Preferably, the front end of the inner shell is an inward arc surface for guiding the assembly during the installation of the tail cover.
Preferably, the fixed mounting edge is provided with a shell hole with a large aperture, and the center of the shell hole is provided with a shell threaded hole with a small aperture;
The junction between fixed mounting limit and the lateral wall of shell body has the mount pad, and the mount pad has the mount pad hole that corresponds with the casing hole position, the outer lane of mount pad hole has annular spacing round platform, spacing round platform is arranged in the casing hole, the screw passes the casing screw hole with the mount pad hole is connected with the lateral wall.
Preferably, in the axial direction, the inner shell is integrally located at the front end of the outer adjusting piece, the inner shell, the supporting reinforcing ring and the outer shell form a step surface due to different axial positions and heights, and an s-shaped gas channel can be formed by adding a gap formed by the outer shell and the outer adjusting piece, so that the stealth effect can be realized while the outflow of gas is realized.
Preferably, the rear end of the outer case has a curved surface of the same curvature as the outer regulating piece at the same axial position, and the outer case and the outer regulating piece have a gap formed by a difference in radius.
Preferably, the inner diameter of the supporting reinforcing ring is smaller than the outer diameter of the outer adjusting piece, so that the clearance formed by the radius difference between the outer shell and the outer adjusting piece can be effectively shielded, and the stealth effect is improved.
The advantages of the application include:
(1) The flyer lap joint outer cover implements the flyer integrated design idea and adopts a double-layer design, single-layer lap joint and zigzag butt joint mode;
(2) The gap is reserved between the flyer lap joint outer cover and the outer adjusting piece, so that movement interference is avoided, an engine cabin and an outflow exchange airflow channel are formed at the same time, and pressure load born by the flyer lap joint outer cover and the outer adjusting piece is reduced;
(3) The fly-by lap joint outer cover structurally adopts a support reinforcing ring in a shape like a Chinese character 'ji', so that support and installation are ensured, and radar waves entering through a gap between the fly-by lap joint outer cover and the outer adjusting piece are shielded;
(4) The outer layer structure of the fly-hair lap joint outer cover adopts a wave-absorbing function resin matrix composite material, so that the problem of weight gain of the coating is solved, and the stealth performance is improved.
Drawings
FIG. 1 is a schematic illustration of the installation of a two-dimensional nozzle fly lap housing structure;
FIG. 2 is a schematic view of the outside of the housing;
FIG. 3 is a schematic view of the inside of the housing;
FIG. 4 is a cross-sectional view of a structure of a fly-hair overlap housing
FIG. 5 is a schematic view of a support stiffener ring;
FIG. 6 is an inboard schematic view of the fly-by cover structure in mounted relation to the outer conditioner sheet;
the device comprises a 1-outer shell, a 2-supporting reinforcing ring, a 3-pad cylinder, a 4-mounting seat, a 5-inner shell, an 8-tail cover, a 9-outer adjusting piece and a 10-side wall.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the drawings are exemplary and intended to illustrate the present application and should not be construed as limiting the application. All other embodiments, based on the embodiments of the application, which are apparent to those of ordinary skill in the art without inventive faculty, are intended to be within the scope of the application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
The application provides a two-dimensional spray pipe flying lap joint outer cover structure, which is lapped between an outer adjusting piece 9 and a tail cover 8, wherein the outer adjusting piece 9 is positioned at the inner side of the rear end of the tail cover 8, and the outer adjusting piece 9 and the tail cover 8 are arranged in a clearance way;
The two-dimensional spray pipe flying lap joint outer cover structure comprises an outer shell 1 and an inner shell 5, wherein the outer shell 1 and the inner shell are arranged on the inner shell, as shown in fig. 1, the front end and the rear end of the outer shell 1 are subjected to sawtooth modification, and the sawtooth modification at the front end of the outer shell 1 is in butt joint with the sawtooth modification at the rear end of a tail cover 8;
The tail cover 8 is a part of the rear fuselage of the airplane, the tail end saw teeth of the tail cover 8 are shaped, the shaping angles and the number are consistent with those of the saw teeth at the front end of the outer shell 1, the tail part of the tail cover 8 is lapped on the outer wall surface at the front end of the inner shell 5, the tail cover 8 is meshed with the saw teeth at the front end of the outer shell 1 without gaps, the tail cover 8 and the outer surface of the outer shell 1 are in smooth transition, the resistance of the tail cover 8 of the airplane can be effectively reduced, the step surface between the tail cover 8 and the outer adjusting piece 9 is reduced, in addition, the two axial ends of the outer shell 1 are shaped by the saw teeth, and the front end and the tail cover 8 are shaped by the saw teeth correspondingly, so that the stealth problem caused by the straight surface connection can be reduced, and the stealth effect is improved.
The front end of the inner shell 5 extends forwards and is lapped with the inner side surface of the tail cover 8, the two side ends of the outer shell 1 along the circumferential direction are provided with fixed installation edges formed by bending, the outer shell 1 is fixedly installed through the two side walls 10 which are arranged on the fixed installation edges and the spray pipe, the front end of the inner shell 5 is lapped with the inner side surface of the tail cover 8, the front end of the outer shell 1 is meshed with the sawteeth of the tail cover 8, and the outer shell 1 can restrict the two-dimensional spray pipe fly lap joint outer cover structure in multiple angles through the cooperation of the fixed installation edges and the two side walls 10 which are arranged on the spray pipe, so that the firm and stable assembly is realized, the installation by means of a traditional elastic sheet is not needed, and the service life is durable and stable.
Preferably, the inner side of the inner housing 5 is provided with a circular arc-shaped supporting reinforcement ring 2, the supporting reinforcement ring 2 is arranged along the circumferential direction of the inner housing 5, and the supporting reinforcement ring 2 can provide the strength of the inner housing 5.
Preferably, as shown in fig. 3-5, the cross section of the supporting reinforcement ring 2 is in a shape of a Chinese character 'ji', which comprises a middle flat section and two sides of the flat section, the two sides of the flat section are in contact with the surface of the inner shell 5, the flat section is in fixed connection with the outer shell 1 and the inner shell 5 through welding or rivets, a ring cavity is formed between the supporting reinforcement ring 2 and the surface of the inner shell 5, a plurality of circumferentially distributed cushion cylinders 3 are arranged in the ring cavity, one end of each cushion cylinder 3 is welded Yu Pingduan, the other end of each cushion cylinder is arranged in a corresponding mounting hole of the outer shell 1 and the inner shell 5 through a limiting boss, the supporting reinforcement ring 2 is fixedly connected with a spray pipe through the cushion cylinder 3 by a screw or a bolt, the structure of the Chinese character 'ji' of the supporting reinforcement ring 2 can lighten the structural weight of the supporting reinforcement ring 2, and meanwhile, the cushion cylinders 3 can realize the mounting strength of the supporting reinforcement ring 2, and avoid the supporting reinforcement ring 2 from being damaged due to the pretightening force of the screw.
Preferably, the material of the outer shell 1 comprises a wave-absorbing function resin matrix composite material, and the outer surface is coated with a protective resin for changing the appearance color, so that the stealth function of the outer shell 1 is improved.
Preferably, the front end of the inner housing 5 is an inward arc surface for guiding the assembly of the tail cover 8.
Preferably, the fixed mounting edge is provided with a shell hole with a large aperture, and the center of the shell hole is provided with a shell threaded hole with a small aperture;
the junction between the fixed mounting limit of shell 1 and lateral wall 10 has mount pad 4, and mount pad 4 has the mount pad hole that corresponds with the casing hole position, the outer lane of mount pad hole has annular spacing round platform, spacing round platform is arranged in the casing hole, the screw passes the casing screw hole with the mount pad hole is connected with lateral wall 10.
Preferably, in the axial direction, the inner casing 5 is integrally located at the front end of the outer adjusting piece 9, the inner casing 5, the supporting reinforcing ring 2 and the outer casing form a step surface due to different axial positions and heights, and an s-shaped gas channel can be formed by adding a gap formed by the outer casing and the outer adjusting piece 9, so that the stealth effect can be realized while the outflow of gas is realized.
Preferably, the rear end of the outer housing 1 has a curved surface of the same curvature as the outer regulating piece 9 at the same axial position, and the outer housing 1 and the outer regulating piece 9 have a gap formed by a difference in radius.
Preferably, the inner diameter of the supporting reinforcing ring 2 is smaller than the outer diameter of the outer adjusting piece 9, so that the gap formed by the radius difference between the outer shell 1 and the outer adjusting piece 9 can be effectively shielded, and the stealth effect is improved, as shown in fig. 6.
The flyer lap joint outer cover is sleeved on the periphery of the two-dimensional spray pipe and is arranged on the upper side and the lower side of the two-dimensional spray pipe, the flyer lap joint outer cover is a non-moving component, and when the state of the spray pipe is adjusted and changed, the flyer lap joint outer cover always keeps good lap joint relation with the tail cover 8 and the outer adjusting piece 9, so that good rectifying effect of the flyer lap joint outer cover is ensured, and the requirements of forward direction of an airplane and backward direction stealth of an engine are met, as shown in figure 6.
1, Implementing the design idea of integrating the flyer and the overlap cover of the flyer, and adopting a double-layer design, single-layer overlap and zigzag butt joint mode;
2, a gap is reserved between the flyer lap joint outer cover and the outer adjusting piece, so that movement interference is avoided, an engine cabin and an outflow exchange air flow channel are formed at the same time, and pressure load born by the flyer lap joint outer cover and the outer adjusting piece is reduced;
3, the fly-by lap joint outer cover structurally adopts a support reinforcing ring in a shape like a Chinese character 'ji', so that the support and the installation are ensured, and radar waves entering through a gap between the fly-by lap joint outer cover and the outer adjusting piece are shielded;
4, the outer layer structure of the fly-hair lap joint outer cover adopts a wave-absorbing function resin matrix composite material, so that the problem of weight gain of the coating is solved, and the stealth performance is improved.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210471123.8A CN114671034B (en) | 2022-04-28 | 2022-04-28 | A dual-nozzle flying engine overlapping cover structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210471123.8A CN114671034B (en) | 2022-04-28 | 2022-04-28 | A dual-nozzle flying engine overlapping cover structure |
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| Publication Number | Publication Date |
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| CN114671034A CN114671034A (en) | 2022-06-28 |
| CN114671034B true CN114671034B (en) | 2025-04-04 |
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| CN202210471123.8A Active CN114671034B (en) | 2022-04-28 | 2022-04-28 | A dual-nozzle flying engine overlapping cover structure |
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| CN119772527A (en) * | 2025-03-11 | 2025-04-08 | 蓝箭航天空间科技股份有限公司 | A method for manufacturing a rocket engine nozzle reinforcement structure and a nozzle structure |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110439707A (en) * | 2019-07-26 | 2019-11-12 | 中国航发沈阳发动机研究所 | A kind of airplane tail group elastic piece component |
| CN110466783A (en) * | 2019-07-26 | 2019-11-19 | 中国航发沈阳发动机研究所 | A kind of airplane tail group commutator segment component |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7578132B2 (en) * | 2001-03-03 | 2009-08-25 | Rolls-Royce Plc | Gas turbine engine exhaust nozzle |
| DE102006019299B3 (en) * | 2006-04-26 | 2007-11-08 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Aircraft turbofan jet engine, with a primary and a ring-shaped side jet, has an adjustment mechanism of rings to reduce noise emissions on take-off |
| US8181905B2 (en) * | 2008-12-17 | 2012-05-22 | Rohr, Inc. | Aircraft engine nacelle with translating inlet cowl |
| US9915225B2 (en) * | 2015-02-06 | 2018-03-13 | United Technologies Corporation | Propulsion system arrangement for turbofan gas turbine engine |
| DE102017106954A1 (en) * | 2017-03-31 | 2018-10-04 | Rolls-Royce Deutschland Ltd & Co Kg | Engine nacelle for a turbofan engine |
| RU2729591C1 (en) * | 2019-08-01 | 2020-08-11 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Rotary axisymmetric turbine jet nozzle |
| CN113107706B (en) * | 2021-04-25 | 2022-03-22 | 中国航发沈阳发动机研究所 | Binary vector spray pipe outer cover structure and design method thereof |
| CN113250854A (en) * | 2021-04-28 | 2021-08-13 | 中国航发沈阳发动机研究所 | Spray pipe structure |
| CN114109648B (en) * | 2021-11-12 | 2023-02-28 | 中国航发沈阳发动机研究所 | Adjustable spray pipe outer cover mechanism |
| CN114017203B (en) * | 2021-11-19 | 2023-12-19 | 中国航发沈阳发动机研究所 | Jet pipe and airplane rear body slit exhaust cooling device |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110439707A (en) * | 2019-07-26 | 2019-11-12 | 中国航发沈阳发动机研究所 | A kind of airplane tail group elastic piece component |
| CN110466783A (en) * | 2019-07-26 | 2019-11-19 | 中国航发沈阳发动机研究所 | A kind of airplane tail group commutator segment component |
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