CN108678871B - Jet pipe heat insulation structure for thrust steering jet engine - Google Patents
Jet pipe heat insulation structure for thrust steering jet engine Download PDFInfo
- Publication number
- CN108678871B CN108678871B CN201711428587.6A CN201711428587A CN108678871B CN 108678871 B CN108678871 B CN 108678871B CN 201711428587 A CN201711428587 A CN 201711428587A CN 108678871 B CN108678871 B CN 108678871B
- Authority
- CN
- China
- Prior art keywords
- heat shield
- cylinder body
- heat
- outer cylinder
- shield
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000009413 insulation Methods 0.000 title claims abstract description 19
- 239000007921 spray Substances 0.000 claims abstract description 27
- 238000001816 cooling Methods 0.000 claims abstract description 25
- 238000013461 design Methods 0.000 claims abstract description 12
- 238000000034 method Methods 0.000 claims abstract description 4
- 230000006835 compression Effects 0.000 claims description 14
- 238000007906 compression Methods 0.000 claims description 14
- 238000007789 sealing Methods 0.000 claims description 11
- 230000003014 reinforcing effect Effects 0.000 claims description 9
- 239000000956 alloy Substances 0.000 abstract description 2
- 229910045601 alloy Inorganic materials 0.000 abstract description 2
- 239000002783 friction material Substances 0.000 abstract description 2
- 230000008569 process Effects 0.000 abstract description 2
- 238000010276 construction Methods 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 239000000306 component Substances 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000036544 posture Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Images
Classifications
-
- 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
- F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Exhaust Silencers (AREA)
Abstract
The invention relates to a spray pipe heat insulation structure for a thrust steering jet engine, which is suitable for the field of medium and small thrust aero-engines with thrust steering requirements. The structure consists of a No. 1 heat shield (9), a No. 2 heat shield (8), a No. 3 heat shield (7), a No. 4 heat shield (6), an elastic connecting sleeve piece (13) and a gas-leading hole (2), wherein the heat shield is an integral structural member, a friction material is high-temperature alloy, and the structure is simple, the weight is light, the structure can be repeatedly assembled and disassembled, and the maintainability is good; gaps are designed among the heat shields, and no additional load exists in the steering process of the spray pipe; the heat bearing part and the force bearing part are separated, so that the high-temperature resistance requirement can be met, the service life is longer, and the reliability of the structure is improved; by controlling the design clearance, the cooling air-entraining amount is reduced, and the thrust loss of the engine is reduced.
Description
1. Field of the invention
The invention relates to an integral rotary spray pipe heat insulation and a connection structure thereof, which are suitable for the field of medium and small thrust aero-engines with thrust steering requirements.
2. Background of the invention
The large deflection angle vector thrust engine is one of necessary components for realizing vertical/short take-off and landing of a fighter, the three-bearing steering spray pipe is a core component of the large deflection angle vector thrust engine, in order to realize that the thrust of the engine is vertically turned from the horizontal direction, the tail spray pipe of the engine is divided into three sections, the interface end surface of each section of spray pipe forms a certain angle with the axis of the section of spray pipe and is provided with a switching bearing, and the three sections of spray pipes rotate at different speeds and directions according to a certain control rule through a driving device so as to realize the steering of the thrust. Along with the continuous change of the deflection angle, the high-temperature gas of the flow channel in the spray pipe directly impacts the wall surface of the spray pipe, so that the local temperature of the spray pipe is prevented from being unevenly distributed, the allowable temperature of materials is prevented from being exceeded, meanwhile, the temperature of the spray pipe is prevented from rising to cause that surrounding accessories exceed the normal use temperature of the surrounding accessories, a high-efficiency heat insulation cooling measure needs to be adopted in the spray pipe, the common heat insulation cooling scheme mainly adopts two modes of coating heat insulation and structural heat insulation cooling, and the heat insulation cooling is the most efficient mode from the structure under the premise of space allowance. The structure heat insulation cooling is mainly characterized in that a double-layer wall design is adopted for an outer cylinder body of a steering spray pipe to form a cooling annular cavity, low-temperature gas is led out from a low-pressure gas compressor of an aircraft engine, or bypass gas is directly adopted, the gas flow which is subjected to sufficient heat exchange with a hot (inner) wall surface is discharged into a main flow channel continuously, and a heat insulation barrier is formed between the outer wall surface and the inner flow channel.
Because the three-bearing steering spray pipe is complex in structure, the heat-insulating cooling structure is required to realize the effective cooling and heat insulation purposes under all postures, additional running resistance cannot be brought to the normal running of the mechanism, and the three-bearing steering spray pipe is limited by factors such as the size limitation of medium and small thrust engine spray pipes, so that the design difficulty and the processing difficulty of the heat-insulating structure are improved. Over the years, the structural design, especially the heat insulation protection design technology, is always mastered in foreign advanced countries, and few achievements exist for completing the design and developing related test groups in China.
3. Summary of the invention
3.1. The purpose of the invention is as follows:
in order to realize the thrust steering of the gas turbine engine, the cooling and protection of a steering bearing are realized, the temperature of the outer wall surface of the spray pipe is reduced, and accessories around the spray pipe are protected.
3.2. The technical scheme of the invention is as follows:
1. a spray pipe heat insulation structure for a thrust steering engine is composed of a 1# heat shield (9), a 2# heat shield (8), a 3# heat shield (7), a 4# heat shield (6), an elastic connecting sleeve (13) and a gas introducing hole (2), wherein the heat shields comprise the 1# heat shield (9), the 2# heat shield (8), the 3# heat shield (7) and the 4# heat shield (6); the method is characterized in that: a cooling cavity (4) is formed between the heat shield and the outer cylinder body (1), the outer wall surface of the heat shield is provided with transverse reinforcing ribs (16) and longitudinal reinforcing ribs (17) facing to the side of the cooling cavity, the heat shield and the outer cylinder body (1) are longitudinally and transversely uniformly distributed, the heat shield is connected with the outer cylinder body (1) through an elastic connection sleeve (13), the heat shield (9) and the heat shield (8) adopt a lap joint structure, the tail end of the heat shield (9) is sleeved at the front end of the heat shield (8), the heat shield (8) and the heat shield (7) are respectively designed with the heat shield (7) and the heat shield (6) in an arc lap joint structure, and the outer cylinder body (1) of the heat shield (8) and the outer cylinder body (1) of the heat shield (7) and the outer cylinder body (1) of the heat shield (6) are respectively provided with two air introducing holes (2); outer barrel (1) is connected through elastic connection external member (13) with the heat screen, along outer cylinder surface equipartition of outer barrel (1), wherein 25 departments are designed to 2# heat screen (8), 19 departments are designed to 3# heat screen (7), 18 departments are designed to 4# heat screen (6).
2. The tail end of the No. 1 heat shield (9) extends into the No. 2 heat shield (8) to ensure that a certain gap is reserved, the tail ends of the No. 2 heat shield (8) and the No. 3 heat shield (7) extend to the front ends of the No. 3 heat shield (7) and the No. 4 heat shield (6) respectively, the lapping surfaces are arc surfaces, and a certain gap is reserved between the two lapping surfaces; the heat shield is characterized in that the No. 1 heat shield (9), the No. 2 heat shield (8), the No. 3 heat shield (7) and the No. 4 heat shield (6) are all integral or split structural members, and a cooling cavity (4) is formed between the heat shields and the outer cylinder body (1).
3. The elastic connection external member (13) comprises an upper elastic member (23), a lower elastic member (25), a D-shaped connecting bolt (26), a sealing gasket (24), a distance sleeve, a compression gasket (22) and a compression nut (21), wherein the upper elastic member (23) and the lower elastic member (25) are both composed of elastic elements, the upper elastic member is arranged outside the outer cylinder body (1), the distance sleeve is used as an inner guide mandrel between the sealing gasket (24) and the compression gasket (22) and is compressed by the compression nut (21) to form a pre-pressing force, the lower elastic member (25) is arranged between the outer cylinder body and the heat shield, the distance sleeve is used as the inner guide mandrel and is used as a pre-pressing force by the assembling distance between the outer cylinder body and the heat shield, and the sealing gasket (24) is directly compressed with the outer wall surface of the outer cylinder body to seal the gas in the cooling cavity (4).
4. The air guide hole (2) is positioned at the axial middle position of the outer cylinder body (1).
3.3. The invention has the beneficial effects that:
the invention provides an integral rotary spray pipe heat insulation and connection structure thereof.A heat shield is an integral structural member, a friction material is high-temperature alloy, the structure is simple, the weight is light, the heat shield can be repeatedly assembled and disassembled, and the maintainability is good; gaps are designed among the heat shields, and no additional load exists in the steering process of the spray pipe; the heat bearing part and the force bearing part are separated, so that the high-temperature resistance requirement can be met, the service life is longer, and the reliability of the structure is improved; by controlling the design clearance, the cooling air-entraining amount is reduced, and the thrust loss of the engine is reduced; the elastic connecting sleeve is newly designed to be connected with the force bearing part, the energy absorption and vibration reduction effects of the elastic connecting sleeve are utilized, the influence of the vibration of the spray pipe on an engine is obviously reduced, and the stability of the steering spray pipe is improved.
The integral rotary spray pipe heat insulation and connection structure is developed for a thrust steering engine, makes it possible for the gas turbine engine to realize the steering of high-temperature airflow, further improves the response speed and maneuverability of a fighter plane, effectively reduces the dependence of the fighter plane on facilities such as an airport runway and the like, can be conveniently applied to equipment needing the steering of the high-temperature airflow, and has certain application prospect and better popularization value.
4. Description of the drawings
FIG. 1 is a schematic view of a three-bearing steering nozzle insulation configuration;
FIG. 2 is a schematic view of an insulated structural cooling chamber;
FIG. 3 is a view showing the construction of the 2# heat shield connection;
FIG. 4 is a view of a lap joint of a # 1 heat shield and a # 2 heat shield;
FIG. 5 is a view of a lap joint of # 2 heat shield and # 3 heat shield;
FIG. 6 is a schematic view of a # 2 heat shield configuration;
FIG. 7 is a view of the construction of the connecting elastic sleeve;
wherein:
1-an outer cylinder body, wherein,
2-an air-guide hole is arranged,
3-the lapping surface of the heat shield,
4-a cooling cavity is arranged in the shell,
5-the location of the attachment,
6-4# heat-insulating screen,
a 7-3# heat shield, wherein,
the number 8-2 heat-insulating screen,
a 9-1# heat shield, wherein the heat shield is provided with a heat-insulating layer,
the bearing is connected with the bearing at the position 10-A,
11-B is connected with a bearing,
12-C is connected with a bearing,
13-connecting the elastic sleeve member to the elastic sleeve member,
14-1#/2# heat shield vent slot,
15-2#/3# heat shield exhaust gap,
16-a transverse reinforcing rib, the transverse reinforcing rib,
17-longitudinal reinforcing ribs are arranged on the upper surface of the steel plate,
18-the connection boss is arranged on the upper surface of the shell,
19-an arc-shaped lapping surface,
the 20-D-shaped mounting hole is arranged on the bracket,
21-pressing the nut, wherein the nut is pressed,
22-pressing the gasket tightly and tightly,
23-an upper elastic element, which is,
24-a sealing gasket, wherein the sealing gasket is a hollow cylinder,
25-a lower elastic member, which is provided with a plurality of elastic pieces,
26-D bolt.
5. Detailed description of the preferred embodiments
The invention is further described below with reference to the accompanying drawings.
Referring to the attached drawings 1-3, a spray pipe heat insulation structure for a thrust steering engine comprises a 1# heat shield, a 2# heat shield, a 3# heat shield, a 4# heat shield, an elastic connection sleeve, a heat shield lap joint structure and air entraining holes, wherein the 1# to 4# heat shield is an integral structural member, a cooling cavity is formed between the heat shield and an outer cylinder body, the heat shield is connected with the outer cylinder body through the elastic connection sleeve, and the elastic element in the elastic connection sleeve is utilized to offset the thermal expansion of the outer cylinder body.
Referring to the attached drawings 4-6, the outer wall surface of the heat shield is provided with a reinforcing rib plate facing to the side of the cooling cavity, the reinforcing rib plate is uniformly distributed in the longitudinal direction and the transverse direction, the 1# heat shield and the 2# heat shield adopt a lap joint structure, the tail end of the 1# heat shield is sleeved in the front end of the 2# heat shield, the 3# heat shield and the 3# heat shield adopt arc lap joint structural design respectively, the tail end of the 2# heat shield and the 3# heat shield are sleeved in the front end of the 4# heat shield respectively, the 2# outer cylinder, the 3# outer cylinder and the 4# outer cylinder are provided with two air introducing holes respectively, and. Outer barrel passes through the elastic connection external member with the heat screen and is connected, and the outer cylinder surface equipartition of outer barrel is followed to the hookup location, and wherein 25 departments of 2# heat screen design, 19 departments of 3# heat screen design, 18 departments of 4# heat screen design.
Referring to fig. 4 and 5, the tail end of the 1# heat shield extends to the inside of the 2# heat shield to ensure that a certain gap is left, and referring to fig. 5, the tail ends of the 2# and 3# heat shields extend to the front ends of the 3# and 4# heat shields respectively, the lapping surfaces are arc surfaces, and a certain gap is ensured to be left between the two lapping surfaces.
The elastic connection kit comprises an upper elastic part, a lower elastic part, a D-shaped connecting bolt, a sealing gasket, a centering sleeve, a compression gasket and a compression nut, wherein the upper elastic part and the lower elastic part are both formed by disc springs, the upper elastic part is arranged on the outer side of the outer barrel body, the spacing sleeve is used as an inner guide mandrel between the sealing gasket and the compression gasket and is compressed by the compression nut to form a pre-compression force, the lower elastic part is arranged between the lower elastic part and the outer barrel body and the heat shield, the spacing sleeve is used as the inner guide mandrel, and a transfer spacing between the outer barrel body and the heat shield is used to form a pre-compression force, and the sealing gasket is directly compressed with the outer wall surface of the outer barrel body to tightly.
The wall surface of the outer cylinder is provided with air introducing holes, as shown in figure 1, and each section of the outer cylinder is provided with two parts for introducing cooling air into the cooling cavity.
Claims (1)
1. A spray pipe heat insulation structure for a thrust steering jet engine is characterized by comprising a 1# heat shield (9), a 2# heat shield (8), a 3# heat shield (7), a 4# heat shield (6), an elastic connecting sleeve (13) and a gas introducing hole (2), wherein the heat shield comprises the 1# heat shield (9), the 2# heat shield (8), the 3# heat shield (7) and the 4# heat shield (6); the method is characterized in that: a cooling cavity (4) is formed between the heat shield and the outer cylinder body (1), the outer wall surface of the heat shield, namely the side facing the cooling cavity, is provided with transverse reinforcing ribs (16) and longitudinal reinforcing ribs (17) which are longitudinally and transversely uniformly distributed, the heat shield is connected with the outer bearing cylinder body (1) through an elastic connecting sleeve (13), the 1# heat shield (9) and the 2# heat shield (8) adopt a lap joint structure, the tail end of the 1# heat shield (9) is sleeved into the front end of the 2# heat shield (8), the 2# heat shield (8) and the 3# heat shield (7) respectively adopt an arc lap joint structure design with the 3# heat shield (7) and the 4# heat shield (6), and the outer cylinder body (1) of the outer cylinder body (1) and the outer cylinder body (1) of the 3# heat shield (7) and the outer cylinder body (1) of the 4# heat shield (6) of the 2# heat shield; the outer cylinder body (1) is connected with the heat shields through the elastic connecting sleeve (13) and uniformly distributed along the outer cylindrical surface of the outer cylinder body (1), wherein 25 parts are designed on the No. 2 heat shield (8), 19 parts are designed on the No. 3 heat shield (7) and 18 parts are designed on the No. 4 heat shield (6);
the tail end of the No. 1 heat shield (9) extends into the No. 2 heat shield (8) to ensure that a certain gap is reserved, the tail ends of the No. 2 heat shield (8) and the No. 3 heat shield (7) extend to the front ends of the No. 3 heat shield (7) and the No. 4 heat shield (6) respectively, the lapping surfaces are arc surfaces, and a certain gap is reserved between the two lapping surfaces; the No. 1 heat shield (9), the No. 2 heat shield (8), the No. 3 heat shield (7) and the No. 4 heat shield (6) are all integral or split structural members, and a cooling cavity (4) is formed between the heat shields and the outer cylinder body (1); the elastic connection external member (13) comprises an upper elastic member (23), a lower elastic member (25), a D-shaped connecting bolt (26), a sealing gasket (24), a distance sleeve, a compression gasket (22) and a compression nut (21), wherein the upper elastic member (23) and the lower elastic member (25) are both composed of elastic elements, the upper elastic member is arranged at the outer side of the outer cylinder body (1), the distance sleeve is used as an inner guide mandrel between the sealing gasket (24) and the compression gasket (22) and is compressed by the compression nut (21) to form a pre-pressing force, the lower elastic member (25) is arranged between the outer cylinder body and the heat shield, the distance sleeve is used as the inner guide mandrel and is used as an assembly distance between the outer cylinder body and the heat shield to form the pre-pressing force, and the sealing gasket (24) is directly compressed with the outer wall surface of the outer cylinder body to tightly seal the gas in the cooling; the air guide hole (2) is positioned at the axial middle position of the outer cylinder body (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711428587.6A CN108678871B (en) | 2017-12-26 | 2017-12-26 | Jet pipe heat insulation structure for thrust steering jet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711428587.6A CN108678871B (en) | 2017-12-26 | 2017-12-26 | Jet pipe heat insulation structure for thrust steering jet engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108678871A CN108678871A (en) | 2018-10-19 |
| CN108678871B true CN108678871B (en) | 2020-12-29 |
Family
ID=63799207
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711428587.6A Active CN108678871B (en) | 2017-12-26 | 2017-12-26 | Jet pipe heat insulation structure for thrust steering jet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108678871B (en) |
Families Citing this family (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111707473B (en) * | 2020-06-19 | 2022-05-13 | 中航工程集成设备有限公司 | Engine test run injection cylinder with tile type lining plate protection structure and design method thereof |
| CN112139436A (en) * | 2020-09-27 | 2020-12-29 | 中国人民解放军第五七一九工厂 | Quick replacement device for heat shield of tail nozzle of aircraft engine |
| CN112412654B (en) * | 2020-11-05 | 2022-09-20 | 中国航发四川燃气涡轮研究院 | Screw rod adjusting type binary vectoring nozzle structure and adjusting method |
| CN112431687B (en) * | 2020-11-12 | 2022-07-08 | 太原科技大学 | Foldable rail accuse engine high temperature heat-proof mechanism |
| CN112539117B (en) * | 2020-11-12 | 2022-07-08 | 太原科技大学 | High-temperature heat insulation mechanism of multidirectional swing rail control engine |
| CN113217224B (en) * | 2021-06-21 | 2022-10-28 | 中国航发沈阳发动机研究所 | Spray tube adjusting sheet and heat shield integrated structure |
| CN113944565B (en) * | 2021-10-19 | 2022-06-28 | 中国科学院工程热物理研究所 | Tail nozzle structure for improving vibration characteristic |
| CN113700572B (en) * | 2021-10-28 | 2022-02-01 | 中国航发四川燃气涡轮研究院 | Lateral combined movement sealing structure for convergence section of binary vector nozzle |
| CN114013669B (en) * | 2021-11-23 | 2023-08-04 | 中国航发沈阳发动机研究所 | Aeroengine capable of realizing short-time strong infrared stealth |
| CN115013841B (en) * | 2022-05-12 | 2023-10-31 | 中国航发四川燃气涡轮研究院 | Afterburner double-layer floating seal round-to-square heat shield structure and rear exhaust system |
| CN115143847A (en) * | 2022-07-28 | 2022-10-04 | 西安现代控制技术研究所 | Long-range bullet arrow bullet tail heat-proof seal composite construction |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2076937C1 (en) * | 1994-10-04 | 1997-04-10 | Конструкторское бюро приборостроения | Solid-propellant rocker engine |
| CN2839037Y (en) * | 2005-06-30 | 2006-11-22 | 中集车辆（集团）有限公司 | Connecting device for tank truck secondary fram and chassis cross member |
| RU2339829C1 (en) * | 2007-04-02 | 2008-11-27 | Государственное унитарное предприятие "Конструкторское бюро приборостроения" | Solid-propellant rocket engine |
| CN102536514A (en) * | 2012-01-17 | 2012-07-04 | 南京航空航天大学 | Binary plug nozzle of turbofan engine with afterburning |
| CN204783323U (en) * | 2015-07-09 | 2015-11-18 | 中国航空工业集团公司沈阳发动机设计研究所 | Spray tube adjustment sheet heat screen coupling mechanism |
| CN105443269A (en) * | 2014-08-25 | 2016-03-30 | 中国航空工业集团公司沈阳发动机设计研究所 | Cooling structure of contracting nozzle |
-
2017
- 2017-12-26 CN CN201711428587.6A patent/CN108678871B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2076937C1 (en) * | 1994-10-04 | 1997-04-10 | Конструкторское бюро приборостроения | Solid-propellant rocker engine |
| CN2839037Y (en) * | 2005-06-30 | 2006-11-22 | 中集车辆（集团）有限公司 | Connecting device for tank truck secondary fram and chassis cross member |
| RU2339829C1 (en) * | 2007-04-02 | 2008-11-27 | Государственное унитарное предприятие "Конструкторское бюро приборостроения" | Solid-propellant rocket engine |
| CN102536514A (en) * | 2012-01-17 | 2012-07-04 | 南京航空航天大学 | Binary plug nozzle of turbofan engine with afterburning |
| CN105443269A (en) * | 2014-08-25 | 2016-03-30 | 中国航空工业集团公司沈阳发动机设计研究所 | Cooling structure of contracting nozzle |
| CN204783323U (en) * | 2015-07-09 | 2015-11-18 | 中国航空工业集团公司沈阳发动机设计研究所 | Spray tube adjustment sheet heat screen coupling mechanism |
Non-Patent Citations (1)
| Title |
|---|
| 三轴承转向喷管转向机构工作原理及运动规律;王中荣等;《燃气涡轮试验与研究》;20150630;第28卷(第3期);第25-29页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108678871A (en) | 2018-10-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108678871B (en) | Jet pipe heat insulation structure for thrust steering jet engine | |
| CN100554085C (en) | The aero-engine assembly that comprises driving engine and be used for the base of this driving engine | |
| US8777164B2 (en) | Air intake structure for an aircraft nacelle | |
| US20100040466A1 (en) | Bypass turbojet engine nacelle | |
| EP2792597B1 (en) | Inner cowl structure for aircraft turbine engine | |
| CN101903244B (en) | Device for cooling hot gas to be discharged from an aircraft | |
| CN112431694B (en) | Expandable spray pipe using flexible material and external truss structure | |
| JP6462042B2 (en) | Insulation blanket and insulation blanket assembly | |
| US10900368B2 (en) | Seal systems for use with aircraft | |
| US8925332B2 (en) | Anti-fire seal assembly and nacelle comprising such a seal | |
| US8753072B2 (en) | Turbojet engine nacelle | |
| US20140202169A1 (en) | Assembly formed by a turbine engine and a system for attaching it to an aircraft structure | |
| US8157267B2 (en) | Free-floating gas seal | |
| CN110886667B (en) | Binary adjustable spray pipe adopting spring power seal | |
| CN109436373B (en) | High-ultrasonic rapid force and heat combined test cabin | |
| WO2018133640A1 (en) | Low-wind-resistance tubular track, stratosphere-simulating low-wind-resistance tube having built-in track, carrier rocket spacecraft launching system, and method for reducing resistance of tubular track | |
| CN112727634B (en) | Rectangular cross-section spray pipe | |
| EP3284917B1 (en) | Active clearance control collector to manifold insert | |
| CN111114771A (en) | Ultrahigh-temperature end heat sealing structure of hypersonic aircraft | |
| CN115585073B (en) | Test device for dynamic sealing performance of metal elastic sealing structure | |
| CN114483381B (en) | Variable structure engine spray pipe using combined dynamic seal | |
| CN109080837A (en) | Small-sized unmanned aircraft | |
| Lennard | Design Features of the CF6 Engine Thrust Reverser and Spoiler | |
| CN115095445A (en) | Tail jet pipe with sandwich structure | |
| CN110877746A (en) | Auxiliary power device blast pipe supports supporting device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |