CN111846251A - Sand prevention protection device for air inlet, exhaust and tail nozzle of engine - Google Patents
Sand prevention protection device for air inlet, exhaust and tail nozzle of engine Download PDFInfo
- Publication number
- CN111846251A CN111846251A CN202010661182.2A CN202010661182A CN111846251A CN 111846251 A CN111846251 A CN 111846251A CN 202010661182 A CN202010661182 A CN 202010661182A CN 111846251 A CN111846251 A CN 111846251A
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- Prior art keywords
- exhaust
- aircraft engine
- engine
- air inlet
- cover
- Prior art date
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Links
- 239000004576 sand Substances 0.000 title claims abstract description 25
- 230000002265 prevention Effects 0.000 title abstract description 4
- 230000000903 blocking effect Effects 0.000 claims abstract description 38
- 238000007789 sealing Methods 0.000 claims description 20
- 239000000463 material Substances 0.000 claims description 5
- 239000000428 dust Substances 0.000 abstract description 7
- 238000005507 spraying Methods 0.000 abstract description 3
- 238000009434 installation Methods 0.000 description 4
- RNFJDJUURJAICM-UHFFFAOYSA-N 2,2,4,4,6,6-hexaphenoxy-1,3,5-triaza-2$l^{5},4$l^{5},6$l^{5}-triphosphacyclohexa-1,3,5-triene Chemical compound N=1P(OC=2C=CC=CC=2)(OC=2C=CC=CC=2)=NP(OC=2C=CC=CC=2)(OC=2C=CC=CC=2)=NP=1(OC=1C=CC=CC=1)OC1=CC=CC=C1 RNFJDJUURJAICM-UHFFFAOYSA-N 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 239000003063 flame retardant Substances 0.000 description 3
- 239000007921 spray Substances 0.000 description 3
- 239000008358 core component Substances 0.000 description 2
- 238000012856 packing Methods 0.000 description 2
- 230000000149 penetrating effect Effects 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
Abstract
The utility model provides a sand prevention protection device for engine air inlet, exhaust and tail nozzle, support the slide bar through fixed establishment with two and be fixed in aircraft engine's both ends about respectively, later insert the intake duct blanking cover through slide opening I and support in the slide bar, through along supporting the slide bar slip realization intake duct blanking cover lock in aircraft engine intake duct's front end, it is inside effectively to prevent that sand and dust from getting into from aircraft engine's front end, the intake duct blanking cover passes through locking mechanism I and supports the slide bar locking relatively and fix. And then the exhaust protection cover is inserted into the support slide bar through the slide hole II, the exhaust protection cover is sleeved at the tail end of the aircraft engine by sliding along the support slide bar, the lower end of the hanger is just inserted into the V-shaped groove, sand and dust are effectively prevented from entering the interior of the aircraft engine from the rear end of the aircraft engine, the exhaust fan works to extract hot air at the tail spraying part of the aircraft engine through the air passage hole and discharge the hot air outwards, and the condition that the engine is overheated to cause fire due to cover blocking protection is effectively prevented.
Description
Technical Field
The invention relates to the technical field of aircraft engine protection, in particular to a sand prevention protection device for an air inlet, an exhaust nozzle and a tail nozzle of an engine.
Background
The engine is a core component of the airplane, the performance stability of the engine is protected, and the phenomenon that foreign substances pollute the internal core component of the engine is the important factor for protecting the engine. If meeting the sand wind weather in the aircraft parking process, should seal the air inlet, gas vent and the tail nozzle of engine in time, prevent that the sand wind from getting into the inside core part of engine and causing the engine operation risk, use conventional protection blanking cover just can reach ideal protection effect after the engine cools off completely. After a certain airline company takes place of 737 engine exhaust area ignition events together, specifically, because after the test run, the engine tail spray blocking cover is installed before the engine is cooled enough, the ignition is caused, the EGT exhaust temperature of the engine after the shutdown of the engine indicates about 300 ℃, the temperature can be kept at more than 200 ℃ in a short time, the manufacturing material of the tail spray blocking cover belongs to a flame retardant material, if the tail spray blocking cover is directly blocked after the shutdown of the engine, the heat in the engine can not be dissipated, the heat is gathered, the blocking cover is always in a high temperature state, the flame retardant effect of the blocking cover can be weakened, in addition, the abrasion on the surface of the blocking cover caused by long-term use can also weaken the influence on the flame retardant effect, and therefore, the great potential safety hazard is generated on the engine and the whole airplane.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides a device which can not only protect the engine surface and sand dust pollution, but also avoid the ignition of the engine caused by the combustion of a blocking cover protection device.
The technical scheme adopted by the invention for overcoming the technical problems is as follows:
a sand protection device for an engine air intake, exhaust and tail nozzle comprising:
the two support sliding rods are respectively arranged at the left side and the right side of the aircraft engine and are fixed on the aircraft engine through a fixing mechanism;
the air inlet channel blocking cover is made of rubber materials, the left end and the right end of the air inlet channel blocking cover are respectively provided with a support I, and a sliding hole I is formed in the support I;
the exhaust protection cover is of a conical structure, a conical cavity is formed in the exhaust protection cover, a V-shaped groove matched with the lower end of a hanger of an aircraft engine is formed in the upper end of the exhaust protection cover, supports II are respectively arranged at the left end and the right end of the exhaust protection cover, a sliding hole II is formed in each support II, mounting seats are respectively arranged at the left side and the right side of the head end of the exhaust protection cover, air passage holes communicated with the cavity are formed in the mounting seats, and an exhaust fan is inserted into the air passage holes and fixed on the mounting seats through screws;
When the head end of the support sliding rod is inserted into the corresponding sliding hole I at the same side and the air inlet blocking cover is buckled at the front side end of the air inlet of the aircraft engine, the air inlet blocking cover is locked and fixed with the support sliding rod through the locking mechanism I;
and when the tail end of the support sliding rod is inserted into the sliding hole II corresponding to the same side and the exhaust protection cover is sleeved at the tail end of the aircraft engine, the lower end of the hanger is inserted into the V-shaped groove, and the exhaust protection cover is locked and fixed with the support sliding rod through the locking mechanism II.
Furthermore, the fixing mechanism comprises a fixing seat I, a fixing seat II, a nut I and a nut II, wherein a screw I is axially arranged at the inner side end of the fixing seat I, a screw II is axially arranged at the outer side end of the fixing seat I, a screw III is axially arranged at the inner side end of the fixing seat II, a screw IV is axially arranged at the outer side end of the fixing seat II, a through hole I and a through hole II are respectively arranged on the support slide bar, the screw I is screwed in an air inlet channel ground service hole on the aircraft engine, the screw II is screwed and fixed through the nut I after penetrating through the through hole I, the screw III is screwed in a reverse thrust ground service hole on the aircraft engine, and the screw IV is screwed and fixed through.
Furthermore, above-mentioned locking mechanism I is including setting up pinhole III on support I and setting up pinhole I on supporting the slide bar, and pinhole III is coaxial with pinhole I when the buckle of intake duct blanking cover is in aircraft engine intake duct's front end, and quick-release pin I cartridge is in pinhole I and pinhole III, locking mechanism II is including setting up pinhole IV on support II and setting up pinhole II on supporting the slide bar, and when the exhaust protection cover suit was in aircraft engine tail end, pinhole IV was the same axle with pinhole II, and quick-release pin II cartridge is in pinhole II and pinhole IV.
In order to improve the heat dissipation performance, the exhaust protection cover is provided with a plurality of radiating fins at intervals along the circumferential direction.
In order to improve the sealing property, the inner side end of the air inlet blocking cover is provided with a cylindrical boss, and when the air inlet blocking cover is buckled at the front side end of an aircraft engine air inlet, the boss is inserted into the aircraft engine air inlet.
In order to improve the sealing performance, the sealing device further comprises a sealing ring arranged between the exhaust protection cover and the aircraft engine.
In order to improve the sealing performance, the sealing device further comprises a sealing strip arranged between the hanging bracket and the V-shaped groove.
In order to facilitate operation, a plurality of handles I are arranged on the fixing seat I at intervals along the circumferential direction, and a plurality of handles II are arranged on the fixing seat II at intervals along the circumferential direction.
In order to facilitate operation, a plurality of handles III are arranged on the nut I at intervals along the circumferential direction, and a plurality of handles IV are arranged on the nut II at intervals along the circumferential direction.
In order to improve the fixing firmness, the fixing device further comprises a gasket I and a gasket II which are sleeved on the screw II, and a gasket I and a gasket II which are sleeved on the screw IV, wherein the gasket I is positioned between the fixing seat I and the inner side face of the supporting slide rod and between the fixing seat II and the inner side face of the supporting slide rod, and the gasket II is positioned between the outer side face of the supporting slide rod and the nut I and between the outer side face of the supporting slide rod and the nut II.
The invention has the beneficial effects that: two support slide bars are fixed at the left end and the right end of an aircraft engine respectively through a fixing mechanism, then an air inlet blocking cover is inserted into the support slide bars through slide holes I, the blocking cover of the air inlet is buckled at the front side end of an air inlet of the aircraft engine by sliding along the support slide bars, sand and dust are effectively prevented from entering the front end of the aircraft engine into the blocking cover of the air inlet, and the blocking cover of the air inlet is fixed through locking of a locking mechanism I relative support slide bar. And then the exhaust protection cover is inserted into the support slide bar through the slide hole II, the exhaust protection cover is sleeved at the tail end of the aircraft engine by sliding along the support slide bar, the lower end of the hanger is just inserted into the V-shaped groove, sand and dust are effectively prevented from entering the interior of the aircraft engine from the rear end of the aircraft engine, the exhaust fan works to extract hot air at the tail spraying part of the aircraft engine through the air passage hole and discharge the hot air outwards, and the condition that the engine is overheated to cause fire due to cover blocking protection is effectively prevented.
Drawings
FIG. 1 is a schematic perspective view of the present invention secured to an engine;
FIG. 2 is an exploded perspective view of the present invention;
FIG. 3 is a schematic perspective view of the fixing base I and the fixing base II of the present invention;
in the drawing, 1, an aircraft engine 2, a hanger 3, an air inlet channel ground service hole 4, a reverse thrust ground service hole 5, a support sliding rod 6, a through hole I7, a through hole II 8, a pin hole I9, a pin hole II 10, a quick release pin I11, a quick release pin II 12, an air inlet channel blocking cover 13, a boss 14, a support I15, a pin hole III 16, a sliding hole I17, an exhaust protection cover 18, a mounting seat 19, an air channel hole 20, an exhaust fan 21, a screw 22, a support II 23, a pin hole IV 24, a sliding hole II 25, a V-shaped notch 26, a sealing ring 27, a sealing strip 28, a radiating fin 29, a fixing seat I30, a fixing seat II 31, a nut I32, a nut II 33, a screw I34, a screw II 35, a screw III 36, a screw IV 37, a handle I38, a handle II, a gasket I40, a gasket II, a handle III.
Detailed Description
The invention will be further explained with reference to fig. 1, fig. 2 and fig. 3.
A sand protection device for an engine air intake, exhaust and tail nozzle comprising: the two support slide bars 5 are respectively arranged at the left side and the right side of the aircraft engine 1, and the support slide bars 5 are fixed on the aircraft engine 1 through a fixing mechanism; the air inlet blocking cover 12 is made of rubber materials, the left end and the right end of the air inlet blocking cover are respectively provided with a support I14, and a sliding hole I16 is formed in the support I14; the exhaust protection cover 17 is of a conical structure, a conical cavity is formed in the exhaust protection cover 17, a V-shaped groove 25 which is matched with the lower end of the hanger 2 of the aircraft engine 11 and is in a V shape is formed in the upper end of the exhaust protection cover 17, supports II 22 are respectively arranged at the left end and the right end of the exhaust protection cover 17, a sliding hole II 24 is formed in each support II 22, mounting seats 18 are respectively arranged at the left side and the right side of the head end of the exhaust protection cover 17, an air passage hole 19 communicated with the cavity is formed in each mounting seat 18, and an exhaust fan 20 is inserted into the air passage hole 19 and is fixed on; when the head end of the support sliding rod 5 is inserted into the corresponding sliding hole I16 on the same side and the air inlet blocking cover 12 is buckled at the front side end of the air inlet of the aircraft engine 1, the air inlet blocking cover is locked and fixed with the support sliding rod 5 through the locking mechanism I; and when the tail end of the support sliding rod 5 is inserted into the corresponding sliding hole II 24 on the same side and the exhaust protection cover 17 is sleeved at the tail end of the aircraft engine 1, the lower end of the hanger 2 is inserted into the V-shaped groove 25, and the exhaust protection cover 17 is locked and fixed with the support sliding rod 5 through the locking mechanism II. During the use, will two support slide bars 5 through fixed establishment and be fixed in aircraft engine 1's both ends about respectively, later insert support slide bar 5 with intake duct blanking cover 12 through slide opening I16 in, realize intake duct blanking cover 12 lock in aircraft engine 1 intake duct's front side end through sliding along supporting slide bar 5, prevent effectively that sand and dust from getting into inside from aircraft engine 1's front end, intake duct blanking cover 12 supports the slide bar 5 locking through locking mechanism I relatively and fixes. Then, the exhaust protection cover 17 is inserted into the support slide bar 5 through the slide hole II 24, the exhaust protection cover 17 is sleeved at the tail end of the aircraft engine 1 by sliding along the support slide bar 5, at the moment, the lower end of the hanger 2 is just inserted into the V-shaped groove 25, sand and dust are effectively prevented from entering the interior of the aircraft engine 1 from the rear end, the exhaust fan 20 works to extract hot air at the tail spraying part of the aircraft engine 1 through the air passage hole 19 and discharge the hot air outwards, and the condition that the engine is overheated to cause fire due to cover blocking protection is effectively prevented.
The fixing mechanism can be of a structure comprising a fixing seat I29, a fixing seat II 30, a nut I31 and a nut II 32, wherein a screw I33 is axially arranged at the inner side end of the fixing seat I29, a screw II 34 is axially arranged at the outer side end of the fixing seat II 30, a screw III 35 is axially arranged at the inner side end of the fixing seat II 30, a screw IV 36 is axially arranged at the outer side end of the fixing seat II, a through hole I6 and a through hole II 7 are respectively arranged on the support slide bar 5, the screw I33 is screwed in the air inlet channel ground service hole 3 on the aircraft engine 1, the screw II 34 is screwed and fixed through the nut I31 after penetrating through the through hole I6, the screw III 35 is screwed in the reverse thrust ground service hole 4 on the aircraft engine 1, and the screw IV 36 is. The supporting slide rod 5 is rapidly fixed on the aircraft engine 1 through the fixing seat I29 and the fixing seat II 30, the air inlet channel ground service hole 3 and the reverse thrust ground service hole 4 of the aircraft engine 1 are utilized for installation, and the installation is convenient and simple.
The locking mechanism I can be of a structure as follows, the locking mechanism I comprises a pin hole III 15 arranged on a support I14 and a pin hole I8 arranged on a support sliding rod 5, when an air inlet blocking cover 12 is buckled at the front side end of an air inlet of an aircraft engine 1, the pin hole III 15 is coaxial with the pin hole I8, a quick-release pin I10 is inserted into the pin hole I8 and the pin hole III 15, the locking mechanism II comprises a pin hole IV 23 arranged on a support II 22 and a pin hole II 9 arranged on the support sliding rod 5, when an exhaust protection cover 17 is sleeved at the tail end of the aircraft engine 1, the pin hole IV 23 is coaxial with the pin hole II 9, and a quick-release pin II 11 is inserted into the pin hole II 9. The air inlet channel blocking cover 12 and the supporting slide rod 5 are quickly connected and fixed through the quick-release pin I10, the exhaust protection cover 17 and the supporting slide rod 5 are quickly connected and fixed through the quick-release pin II 11, and the installation and the disassembly are simple and convenient.
Preferably, the exhaust protection cover 17 is provided with a plurality of radiating fins 28 at intervals in the circumferential direction. Through setting up a plurality of radiating fin 28, not only increased heat radiating area, radiating fin 28 also considers the wind direction problem along the axial setting of exhaust safety cover 17 comprehensively simultaneously, because the main part direction of wind direction is mostly with the vertical direction of engine or with send you to estimate vertical syntropy two kinds of circumstances. Therefore, the radiating fins 28 have the same direction as the wind direction, thereby accelerating the convection heat transfer and increasing the radiating efficiency.
Furthermore, a cylindrical boss 13 is arranged at the inner side end of the air inlet blocking cover 12, and when the air inlet blocking cover 12 is buckled at the front side end of the air inlet of the aircraft engine 1, the boss 13 is inserted into the air inlet of the aircraft engine 1. The boss 13 is inserted into the air inlet channel of the aircraft engine 1, so that the fixing firmness of the air inlet channel blocking cover 12 is improved, and the sealing performance between the air inlet channel blocking cover 12 and the air inlet channel of the aircraft engine 1 is further improved.
It may also comprise a sealing gasket 26 arranged between the exhaust protection cover 17 and the aircraft engine 1 and a sealing strip 27 arranged between the pylon 2 and the V-shaped slot 25. The sealing between the exhaust protection cover 17 and the surface of the rear thrust reverser region of the aircraft engine 1 can be improved by the addition of the sealing ring 26. By adding the sealing strip 27, the sealing performance between the hanger 2 and the V-shaped groove 25 can be improved, and the sealing strip 27 can play a role in buffering during installation, so that the condition that the hanger 2 is damaged when the exhaust protection cover 17 is sleeved is prevented.
Furthermore, a plurality of handles I37 are arranged on the fixing seat I29 at intervals along the circumferential direction, and a plurality of handles II 38 are arranged on the fixing seat II 30 at intervals along the circumferential direction. A plurality of handles III 41 are arranged on the nut I31 at intervals along the circumferential direction, and a plurality of handles IV 42 are arranged on the nut II 32 at intervals along the circumferential direction. Can conveniently drive fixing base I29 through handle I37 and rotate, can conveniently drive II 30 rotations of fixing base through handle II 38, can conveniently drive nut I31 through handle III 41 and rotate, can conveniently drive nut II 32 through handle IV 42 and rotate, convenience when having improved the operation.
Furthermore, the device also comprises a gasket I39 and a gasket II 40 sleeved on the screw II 34, and a gasket I39 and a gasket II 40 sleeved on the screw IV 36, wherein the gasket I39 is positioned between the fixed seat I29 and the inner side surface of the supporting slide rod 5 and between the fixed seat II 30 and the inner side surface of the supporting slide rod 5, and the gasket II 40 is positioned between the outer side surface of the supporting slide rod 5 and the nut I31 and between the outer side surface of the supporting slide rod 5 and the nut II 32. Through setting up packing ring I39 and packing ring II 40 can improve the firmness of the connection between fixing base I29 and fixing base II 30 and the support slide bar 5, also can improve the firmness of the connection between nut I31 and nut II 32 and the support slide bar 5.
Claims (10)
1. A sand control protection device for an engine air intake, exhaust and tail nozzle, comprising:
the two support sliding rods (5) are respectively arranged at the left side and the right side of the aircraft engine (1), and the support sliding rods (5) are fixed on the aircraft engine (1) through a fixing mechanism;
the air inlet blocking cover (12) is made of rubber materials, the left end and the right end of the air inlet blocking cover are respectively provided with a support I (14), and a sliding hole I (16) is arranged in the support I (14);
the exhaust protection cover (17) is of a conical structure, a conical cavity is formed in the exhaust protection cover, a V-shaped groove (25) which is matched with the lower end of a hanger (2) of an aircraft engine (11) and is in a V shape is formed in the upper end of the exhaust protection cover (17), supports II (22) are arranged at the left end and the right end of the exhaust protection cover (17) respectively, a sliding hole II (24) is formed in each support II (22), mounting seats (18) are arranged on the left side and the right side of the head end of the exhaust protection cover (17) respectively, an air channel hole (19) communicated with the cavity is formed in each mounting seat (18), and an exhaust fan (20) is inserted into each air channel hole (19) and fixed on each mounting seat (18) through;
When the head end of the supporting slide rod (5) is inserted into the corresponding slide hole I (16) at the same side and the air inlet blocking cover (12) is buckled at the front side end of an air inlet of the aircraft engine (1), the air inlet blocking cover is locked and fixed with the supporting slide rod (5) through the locking mechanism I;
and when the tail end of the support sliding rod (5) is inserted into the corresponding sliding hole II (24) on the same side and the exhaust protection cover (17) is sleeved at the tail end of the aircraft engine (1), the lower end of the hanger (2) is inserted into the V-shaped groove (25), and the exhaust protection cover (17) is locked and fixed with the support sliding rod (5) through the locking mechanism II.
2. The sand control protection device for an engine air intake, exhaust and tail nozzle of claim 1, wherein: the fixing mechanism comprises a fixing seat I (29), a fixing seat II (30), a nut I (31) and a nut II (32), a screw rod I (33) is arranged at the inner side end of the fixing seat I (29) along the axial direction, a screw II (34) is axially arranged at the outer end of the fixing seat II (30), a screw III (35) is axially arranged at the inner end of the fixing seat II (30), a screw IV (36) is axially arranged at the outer end of the supporting slide rod (5), a through hole I (6) and a through hole II (7) are respectively arranged on the supporting slide rod, the screw I (33) is screwed in an air inlet channel ground service hole (3) on the aircraft engine (1), the screw II (34) penetrates through the through hole I (6) and then is screwed and fixed through the nut I (31), the screw III (35) is screwed in the reverse thrust ground service hole (4) on the aircraft engine (1), and the screw IV (36) penetrates through the through hole II (7) and is screwed and fixed through the nut II (32).
3. The sand control protection device for an engine air intake, exhaust and tail nozzle of claim 1, wherein: locking mechanical system I is including setting up pinhole III (15) on support I (14) and setting up pinhole I (8) on supporting slide bar (5), and pinhole III (15) are coaxial with pinhole I (8) when intake duct blanking cover (12) lock is in aircraft engine (1) intake duct's front end, and quick-release pin I (10) cartridge is in pinhole I (8) and pinhole III (15), locking mechanical system II is including setting up pinhole IV (23) on support II (22) and setting up pinhole II (9) on supporting slide bar (5), when exhaust safety cover (17) suit in aircraft engine (1) tail end, pinhole IV (23) are coaxial with pinhole II (9), and quick-release pin II (11) cartridge is in pinhole II (9) and pinhole IV (23).
4. The sand control protection device for an engine air intake, exhaust and tail nozzle of claim 1, wherein: the exhaust protection cover (17) is provided with a plurality of radiating fins (28) at intervals along the circumferential direction.
5. The sand control protection device for an engine air intake, exhaust and tail nozzle of claim 1, wherein: the air inlet channel blocking cover is characterized in that a cylindrical boss (13) is arranged at the inner side end of the air inlet channel blocking cover (12), and when the air inlet channel blocking cover (12) is buckled at the front side end of an air inlet channel of an aircraft engine (1), the boss (13) is inserted into the air inlet channel of the aircraft engine (1).
6. The sand control protection device for an engine air intake, exhaust and tail nozzle of claim 1, wherein: the sealing ring device further comprises a sealing ring (26) arranged between the exhaust protection cover (17) and the aircraft engine (1).
7. The sand control protection device for an engine air intake, exhaust and tail nozzle of claim 1, wherein: the device also comprises a sealing strip (27) arranged between the hanger (2) and the V-shaped slot (25).
8. The sand control protection device for an engine air intake, exhaust and tail nozzle according to claim 2, wherein: a plurality of handles I (37) are arranged on the fixing seat I (29) at intervals along the circumferential direction, and a plurality of handles II (38) are arranged on the fixing seat II (30) at intervals along the circumferential direction.
9. The sand control protection device for an engine air intake, exhaust and tail nozzle according to claim 2, wherein: a plurality of handles III (41) are arranged on the nut I (31) at intervals along the circumferential direction, and a plurality of handles IV (42) are arranged on the nut II (32) at intervals along the circumferential direction.
10. The sand control protection device for an engine air intake, exhaust and tail nozzle according to claim 2, wherein: the screw rod I (29) and the screw rod II (34) are sleeved with a gasket I (39) and a gasket II (40) which are sleeved with a screw rod IV (36), the gasket I (39) is positioned between the fixing seat I (29) and the inner side face of the supporting slide rod (5) and between the fixing seat II (30) and the inner side face of the supporting slide rod (5), and the gasket II (40) is positioned between the outer side face of the supporting slide rod (5) and the nut I (31) and between the outer side face of the supporting slide rod (5) and the nut II (32).
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010661182.2A CN111846251B (en) | 2020-07-10 | 2020-07-10 | Sand-proof protection device for air inlet, exhaust and tail nozzle of engine |
| PCT/CN2020/101528 WO2022006918A1 (en) | 2020-07-10 | 2020-07-13 | Sand-control protection device for engine air inlet, exhaust and nozzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010661182.2A CN111846251B (en) | 2020-07-10 | 2020-07-10 | Sand-proof protection device for air inlet, exhaust and tail nozzle of engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111846251A true CN111846251A (en) | 2020-10-30 |
| CN111846251B CN111846251B (en) | 2024-03-19 |
Family
ID=73153687
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010661182.2A Active CN111846251B (en) | 2020-07-10 | 2020-07-10 | Sand-proof protection device for air inlet, exhaust and tail nozzle of engine |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN111846251B (en) |
| WO (1) | WO2022006918A1 (en) |
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| CN111846251B (en) | 2024-03-19 |
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