CN111846251B - Sand-proof protection device for air inlet, exhaust and tail nozzle of engine - Google Patents
Sand-proof protection device for air inlet, exhaust and tail nozzle of engine Download PDFInfo
- Publication number
- CN111846251B CN111846251B CN202010661182.2A CN202010661182A CN111846251B CN 111846251 B CN111846251 B CN 111846251B CN 202010661182 A CN202010661182 A CN 202010661182A CN 111846251 B CN111846251 B CN 111846251B
- Authority
- CN
- China
- Prior art keywords
- exhaust
- engine
- aircraft engine
- air inlet
- support slide
- 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
- 230000000903 blocking effect Effects 0.000 claims abstract description 38
- 239000004576 sand Substances 0.000 claims abstract description 20
- 238000007789 sealing Methods 0.000 claims description 13
- 239000000463 material Substances 0.000 claims description 5
- 230000001681 protective effect Effects 0.000 claims description 5
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 239000000428 dust Substances 0.000 abstract description 7
- 238000005507 spraying Methods 0.000 abstract description 3
- 230000002265 prevention Effects 0.000 abstract 1
- 230000000694 effects Effects 0.000 description 4
- 230000017525 heat dissipation Effects 0.000 description 4
- 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
- 239000008358 core component Substances 0.000 description 3
- 239000003063 flame retardant Substances 0.000 description 3
- 239000007921 spray Substances 0.000 description 3
- 238000000034 method Methods 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
- 238000007599 discharging Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
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
A sand prevention protection device for engine air inlet, exhaust and tail nozzle is fixed in the both ends about the aircraft engine respectively with two support slide bars through fixed establishment, later inserts the intake duct blanking cover in the support slide bar through slide hole I, realizes through following support slide bar slip that the intake duct blanking cover lock is in the front side end of aircraft engine intake duct, effectively prevents that sand and dust from getting into its inside from the front end of aircraft engine, and the intake duct blanking cover is fixed through locking mechanism I relative support slide bar locking. And then, the exhaust protection cover is inserted into the support slide rod 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 rod, at the moment, the lower end of the hanging bracket is just inserted into the V-shaped slot, so that sand and dust are effectively prevented from entering the rear end of the aircraft engine, the exhaust fan works to extract and realize the discharge of hot air at the tail spraying part of the aircraft engine through the air passage hole, and the condition of ignition caused by overheat of the engine due to the protection of the blocking cover is effectively prevented.
Description
Technical Field
The invention relates to the technical field of aircraft engine protection, in particular to a sand-proof protection device for an air inlet, exhaust and tail nozzles of an engine.
Background
The engine is a core component of an aircraft, so that the stability of the performance of the engine is protected, and the pollution of foreign matters to the core component inside the engine is a serious problem in engine protection. If the aircraft is in a stop process in windy and sandy weather, the air inlet, the air outlet and the tail nozzle of the engine are sealed in time, so that the running risk of the engine caused by windy and sandy entering the core component inside the engine is prevented, and the ideal protection effect can be achieved by using the conventional protection blanking cap after the engine is completely cooled. The ignition event of the exhaust area of the 737 engine occurs in an airline company, specifically, because after a test run, an engine tail spray blocking cover is installed after the engine is not cooled enough, so that the engine is on fire, the EGT exhaust temperature indication is about 300 ℃ after the engine is just shut down, the exhaust area can be kept at more than 200 ℃ in a short time, the manufacturing material of the tail spray blocking cover belongs to flame retardant materials, after the engine is shut down, if the tail spray blocking cover is directly blocked, 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 of the surface of the blocking cover caused by long-term use can also have weakened effect on the flame retardant effect of the blocking cover, and therefore, great potential safety hazards are generated on the engine and the whole aircraft.
Disclosure of Invention
In order to overcome the defects of the technology, the invention provides a device which can protect the engine surface from being polluted by sand and dust and can also avoid the ignition of the engine caused by the combustion of the plugging cover protection device.
The technical scheme adopted for overcoming the technical problems is as follows:
a sand control protection device for an engine air intake, exhaust and tail nozzle comprising:
the two support slide bars are respectively arranged at the left side and the right side of the aircraft engine and are fixed on the aircraft engine through the fixing mechanism;
the air inlet blocking cover 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, and sliding holes I are formed in the supports I;
the exhaust protection cover is of a conical structure and internally provided with a conical cavity, the upper end of the exhaust protection cover is provided with a V-shaped slot which is matched with the lower end of a hanger of an aircraft engine and is in a V shape, the left end and the right end of the exhaust protection cover are respectively provided with a support II, sliding holes II are formed in the supports II, the left side and the right side of the head end of the exhaust protection cover are respectively provided with a mounting seat, the mounting seats are internally provided with air passage holes communicated with the cavity, and the exhaust fan is inserted into the air passage holes and is fixed on the mounting seats through screws;
the locking mechanism I is used for locking and fixing the air inlet blocking cover with the support sliding rod through the locking mechanism I when the head end of the support sliding rod is inserted into the sliding hole I corresponding to the same side and the air inlet blocking cover is buckled at the front side end of the air inlet of the aircraft engine;
and the locking mechanism II is used for inserting the tail end of the support sliding rod into a sliding hole II corresponding to the same side, and the lower end of the hanging bracket is inserted into the V-shaped slot when the exhaust protection cover is sleeved at the tail end of the aircraft engine, and the exhaust protection cover is locked and fixed with the support sliding rod through the locking mechanism II.
Further, the fixing mechanism comprises a fixing seat I, a fixing seat II, a nut I and a nut II, wherein the inner side end of the fixing seat I is axially provided with a screw rod I, the outer side end of the fixing seat I is axially provided with a screw rod II, the inner side end of the fixing seat II is axially provided with a screw rod III, the outer side end of the fixing seat II is axially provided with a screw rod IV, the supporting slide rod is respectively provided with a through hole I and a through hole II, the screw rod I is screwed in an air inlet channel ground service hole on the aircraft engine, the screw rod II is screwed and fixed through the nut I after passing through the through hole I, the screw rod III is screwed and fixed in a reverse thrust ground service hole on the aircraft engine after passing through the through hole II.
Further, the locking mechanism I comprises a pin hole III arranged on the support I and a pin hole I arranged on the support slide rod, when the air inlet channel blocking cover is buckled at the front side end of the air inlet channel of the aircraft engine, the pin hole III is coaxial with the pin hole I, the quick-release pin I is inserted into the pin hole I and the pin hole III, the locking mechanism II comprises a pin hole IV arranged on the support II and a pin hole II arranged on the support slide rod, when the air exhaust protective cover is sleeved at the tail end of the aircraft engine, the pin hole IV is coaxial with the pin hole II, and the quick-release pin II is inserted into the pin hole II and the pin hole IV.
In order to improve heat dissipation, the exhaust protection cover is provided with a plurality of heat dissipation fins at intervals along the circumferential direction.
In order to improve the tightness, 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 the air inlet of the aircraft engine, the boss is inserted into the air inlet of the aircraft engine.
In order to improve the tightness, the engine sealing device further comprises a sealing ring arranged between the exhaust protection cover and the aircraft engine.
In order to improve the tightness, the sealing strip is arranged between the hanging bracket and the V-shaped groove.
For convenient operation, a plurality of handles I are arranged on the fixing base I along the circumferential direction at intervals, and a plurality of handles II are arranged on the fixing base II along the circumferential direction at intervals.
For convenient 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 fixation firmness, the screw rod fixing device further comprises a gasket I and a gasket II sleeved on the screw rod II, and a gasket I and a gasket II sleeved on the screw rod IV, wherein the gasket I is positioned between the fixing seat I and the inner side surface of the support slide rod and between the fixing seat II and the inner side surface of the support slide rod, and the gasket II is positioned between the outer side surface of the support slide rod and the nut I and between the outer side surface of the support slide rod and the nut II.
The beneficial effects of the invention are as follows: two support slide bars are respectively fixed at the left end and the right end of the aircraft engine through the fixing mechanism, then the air inlet blocking cover is inserted into the support slide bars through the slide holes I, the air inlet blocking cover is buckled at the front side end of the air inlet of the aircraft engine by sliding along the support slide bars, sand dust is effectively prevented from entering the air inlet of the aircraft engine from the front end of the aircraft engine, and the air inlet blocking cover is relatively fixed by locking the support slide bars through the locking mechanism I. And then, the exhaust protection cover is inserted into the support slide rod 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 rod, at the moment, the lower end of the hanging bracket is just inserted into the V-shaped slot, so that sand and dust are effectively prevented from entering the rear end of the aircraft engine, the exhaust fan works to extract and realize the discharge of hot air at the tail spraying part of the aircraft engine through the air passage hole, and the condition of ignition caused by overheat of the engine due to the protection of the blocking cover is effectively prevented.
Drawings
FIG. 1 is a schematic perspective view of the present invention secured to an engine;
FIG. 2 is an exploded view of a three-dimensional structure of the present invention;
FIG. 3 is a schematic perspective view of the parts of the fixing base I and the fixing base II;
in the drawing, an aircraft engine 2, a hanger 3, an air inlet ground service hole 4, a reverse thrust ground service hole 5, a support slide 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 blocking cover 13, a boss 14, a support I15, a pin hole III 16, a sliding hole I17, an air exhaust protection cover 18, a mounting seat 19, an air passage 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 groove 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 39, a gasket I40, a gasket II 41, a handle III 42 and IV.
Detailed Description
The invention will be further described with reference to fig. 1, 2 and 3.
A sand control 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 sliding holes I16 are 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 shaped like a V 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, sliding holes II 24 are formed in the supports 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 which is communicated with the cavity is formed in the mounting seats 18, and an exhaust fan 20 is inserted into the air passage hole 19 and is fixed on the mounting seats 18 through screws 21; the locking mechanism I is used for locking and fixing the air inlet blocking cover 12 with the support slide rod 5 through the locking mechanism I when the head end of the support slide rod 5 is inserted into a slide hole I16 corresponding to the same side and the air inlet blocking cover is buckled at the front side end of an air inlet of the aircraft engine 1; the locking mechanism II is used for inserting the tail end of the support sliding rod 5 into a sliding hole II 24 corresponding to the same side, and when the exhaust protection cover 17 is sleeved on the tail end of the aircraft engine 1, the lower end of the hanging bracket 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, be fixed in the left and right sides both ends of aircraft engine 1 respectively through fixed establishment with two support slide bars 5, later insert the air inlet duct blanking cover 12 in supporting slide bar 5 through slide hole I16, realize through following support slide bar 5 slip that air inlet duct blanking cover 12 lock is in the front side end of aircraft engine 1 air inlet duct, effectively prevent sand and dust from getting into its inside from the front end of aircraft engine 1, air inlet duct blanking cover 12 is fixed through locking mechanism I relative support slide bar 5 locking. 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 hanging bracket 2 is just inserted into the V-shaped slot 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 realize discharging, and the condition that the engine is overheated due to blocking cover protection is effectively prevented.
The fixing mechanism can be of a structure that comprises a fixing seat I29, a fixing seat II 30, a nut I31 and a nut II 32, wherein a screw rod I33 is axially arranged at the inner side end of the fixing seat I29, a screw rod II 34 is axially arranged at the outer side end of the fixing seat I29, a screw rod III 35 is axially arranged at the inner side end of the fixing seat II 30, a screw rod 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 a support slide rod 5, the screw rod I33 is screwed into an air inlet channel ground service hole 3 on the aircraft engine 1, the screw rod II 34 is screwed and fixed through the nut I31 after penetrating through the through hole I6, the screw rod III 35 is screwed into a reverse thrust ground service hole 4 on the aircraft engine 1, and the screw rod IV 36 is screwed and fixed through the nut II 32 after penetrating through the through hole II 7. The supporting sliding rod 5 is quickly fixed on the aircraft engine 1 through the fixing seat I29 and the fixing seat II 30, and 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, so that the installation is convenient and simple.
The locking mechanism I can be of a structure comprising a pin hole III 15 formed in the support I14 and a pin hole I8 formed in the support slide rod 5, when the air inlet blocking cover 12 is buckled at the front side end of an air inlet of the aircraft engine 1, the pin hole III 15 is coaxial with the pin hole I8, the 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 formed in the support II 22 and a pin hole II 9 formed in the support slide rod 5, when the exhaust protective 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 the quick-release pin II 11 is inserted into the pin hole II 9 and the pin hole IV 23. The air inlet blocking cover 12 is quickly connected and fixed with the supporting slide rod 5 by the quick-release pin I10, the exhaust protection cover 17 is quickly and fixedly connected with the supporting slide rod 5 by 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 heat radiating fins 28 at intervals in the circumferential direction. By arranging a plurality of radiating fins 28, the radiating area is increased, and the arrangement of the radiating fins 28 along the axial direction of the exhaust protective cover 17 is also comprehensively considered as the main direction of the wind direction is mostly perpendicular to the longitudinal direction of the engine or in the same direction as the estimated longitudinal direction. Therefore, the heat dissipation fins 28 have the same trend as the wind direction, which can accelerate the heat convection and increase the heat dissipation efficiency.
Further, a cylindrical boss 13 is disposed at the inner side of the air inlet blocking cover 12, and when the air inlet blocking cover 12 is fastened to the front side 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 of the aircraft engine 1, so that the fixing firmness of the air inlet blocking cover 12 is improved, and the tightness between the air inlet blocking cover 12 and the air inlet of the aircraft engine 1 is further improved.
It may also comprise a sealing ring 26 arranged between the exhaust hood 17 and the aircraft engine 1 and a sealing strip 27 arranged between the pylon 2 and the V-shaped groove 25. The sealing between the exhaust hood 17 and the surface of the aft thrust reverser cowl portion of the aircraft engine 1 can be improved by adding a sealing ring 26. By adding the sealing strip 27, the tightness between the hanging bracket 2 and the V-shaped groove 25 can be improved, and meanwhile, the sealing strip 27 can play a role in buffering during installation, so that the hanging bracket 2 is prevented from being damaged during the process of sleeving the exhaust protective cover 17.
Further, a plurality of handles I37 are arranged on the fixing seat I29 along the circumferential direction at intervals, and a plurality of handles II 38 are arranged on the fixing seat II 30 along the circumferential direction at intervals. 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 rotation through handle I37, can conveniently drive fixing base II 30 rotation through handle II 38, can conveniently drive nut I31 rotation through handle III 41, can conveniently drive nut II 32 rotation through handle IV 42, improve the convenience when operating.
Further, the screw rod II 34 is provided with a gasket I39 and a gasket II 40 which are sleeved with the screw rod II 34, and a gasket I39 and a gasket II 40 which are sleeved with the screw rod IV 36, wherein the gasket I39 is positioned between the fixing seat I29 and the inner side surface of the support slide rod 5, between the fixing seat II 30 and the inner side surface of the support slide rod 5, and between the outer side surface of the support slide rod 5 and the nut I31, and between the outer side surface of the support slide rod 5 and the nut II 32. The firmness of connection between the fixing seat I29 and the fixing seat II 30 and the supporting slide rod 5 can be improved by arranging the gasket I39 and the gasket II 40, and the firmness of connection between the nut I31 and the nut II 32 and the supporting slide rod 5 can also be improved.
Claims (10)
1. A sand control 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 the 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 sliding holes I (16) are formed in the supports I (14);
the air exhaust protection cover (17) is of a conical structure, a conical cavity is formed in the air exhaust protection cover (17), V-shaped grooves (25) which are matched with the lower end of a hanging bracket (2) of the aircraft engine (1) and are in a V shape are formed in the upper end of the air exhaust protection cover (17), supports II (22) are respectively arranged at the left end and the right end of the air exhaust protection cover (17), sliding holes II (24) are formed in the supports II (22), mounting seats (18) are respectively arranged at the left side and the right side of the head end of the air exhaust protection cover (17), air passage holes (19) which are communicated with the cavity are formed in the mounting seats (18), and an air exhaust fan (20) is inserted into the air passage holes (19) and is fixed on the mounting seats (18) through screws (21);
the locking mechanism I is used for locking and fixing the air inlet blocking cover with the support sliding rod (5) through the locking mechanism I when the head end of the support sliding rod (5) is inserted into a sliding hole I (16) corresponding to 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 locking mechanism II is used for inserting the tail end of the supporting sliding rod (5) into a sliding hole II (24) corresponding to the same side, and the lower end of the hanging bracket (2) is inserted into the V-shaped groove (25) when the exhaust protection cover (17) is sleeved at the tail end of the aircraft engine (1), and the exhaust protection cover (17) is locked and fixed with the supporting sliding rod (5) through the locking mechanism II.
2. The sand control protection device for engine air intake, exhaust and tail nozzles 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), wherein a screw rod I (33) is axially arranged at the inner side end of the fixing seat I (29), a screw rod II (34) is axially arranged at the outer side end of the fixing seat I (29), a screw rod III (35) is axially arranged at the inner side end of the fixing seat II (30), a screw rod IV (36) is axially arranged at the outer side end of the fixing seat II, a through hole I (6) and a through hole II (7) are respectively arranged on the support slide rod (5), the screw rod I (33) is screwed into an air inlet channel ground service hole (3) on the aircraft engine (1), the screw rod II (34) is screwed and fixed through the nut I (31) after penetrating through the through hole I (6), and the screw rod III (35) is screwed into a reverse thrust ground service hole (4) on the aircraft engine (1), and the screw rod IV (36) is screwed and fixed through the nut II (32).
3. The sand control protection device for engine air intake, exhaust and tail nozzles of claim 1, wherein: the locking mechanism I comprises a pin hole III (15) arranged on the support II (14) and a pin hole I (8) arranged on the support slide rod (5), when the air inlet blocking cover (12) is buckled at the front side end of an air inlet of the aircraft engine (1), the pin hole III (15) is coaxial with the pin hole I (8), the quick-release pin I (10) is inserted into the pin hole I (8) and the pin hole III (15), the locking mechanism II comprises a pin hole IV (23) arranged on the support II (22) and a pin hole II (9) arranged on the support slide rod (5), when the air exhaust protective 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 the quick-release pin II (11) is inserted into the pin hole II (9) and the pin hole IV (23).
4. The sand control protection device for engine air intake, exhaust and tail nozzles 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 engine air intake, exhaust and tail nozzles of claim 1, wherein: the inner side end of the air inlet blocking cover (12) is provided with a cylindrical boss (13), and when the air inlet blocking cover (12) is buckled at the front side end of an air inlet of the aircraft engine (1), the boss (13) is inserted into the air inlet of the aircraft engine (1).
6. The sand control protection device for engine air intake, exhaust and tail nozzles of claim 1, wherein: the engine also comprises a sealing ring (26) arranged between the exhaust protection cover (17) and the aircraft engine (1).
7. The sand control protection device for engine air intake, exhaust and tail nozzles of claim 1, wherein: the sealing strip (27) is arranged between the hanging bracket (2) and the V-shaped groove (25).
8. The sand control protection device for engine air intake, exhaust and tail nozzles of 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 engine air intake, exhaust and tail nozzles of 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 engine air intake, exhaust and tail nozzles of claim 2, wherein: the novel screw rod is characterized by further comprising a gasket I (39) and a gasket II (40) sleeved on the screw rod II (34) and a gasket I (39) and a gasket II (40) sleeved on the screw rod IV (36), wherein the gasket I (39) is positioned between the inner side surfaces of the fixed seat I (29) and the support slide rod (5) and between the inner side surfaces of the fixed seat II (30) and the support slide rod (5), and the gasket II (40) is positioned between the outer side surfaces of the support slide rod (5) and the nut I (31) and between the outer side surfaces of the support 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 CN111846251A (en) | 2020-10-30 |
| CN111846251B true 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) |
Citations (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20040016227A (en) * | 2002-08-16 | 2004-02-21 | 한국항공우주산업 주식회사 | Joining apparatus for the nozzle fairing of aerospace |
| EP1452707A1 (en) * | 2003-02-28 | 2004-09-01 | Airbus France | Protective device for the air intake of a jet engine |
| WO2005024184A2 (en) * | 2003-08-29 | 2005-03-17 | The Nordam Group, Inc. | Variable cam exhaust nozzle |
| FR2931799A1 (en) * | 2008-05-30 | 2009-12-04 | Airbus France | Aircraft i.e. civil passenger transport aircraft, has reactors located inside envelope surface of theoretical fuselage, where lines of theoretical fuselage correspond to same dimension lines of aircraft fuselage with or without reactors |
| CN101678897A (en) * | 2007-06-01 | 2010-03-24 | 空中客车运作股份公司 | Propulsion assembly for aircraft with sliding nacelle |
| CN103153789A (en) * | 2010-10-15 | 2013-06-12 | 埃尔塞乐公司 | Assembly for attaching the hangers from which an aircraft propulsion unit is suspended |
| CN103429495A (en) * | 2011-02-11 | 2013-12-04 | 空中客车运营简化股份公司 | Airplane having a rear propulsion system |
| EP2672070A2 (en) * | 2012-06-08 | 2013-12-11 | General Electric Company | Nozzle Mounting and Sealing Assembly and Method of Mounting and Sealing a Nozzle Assembly |
| KR20160060317A (en) * | 2014-11-20 | 2016-05-30 | 주식회사 창민테크론 | Intake cover of aircraft |
| CN206071726U (en) * | 2016-09-30 | 2017-04-05 | 黄子生 | Aircraft turbine engine safty shield |
| CN106965944A (en) * | 2016-01-13 | 2017-07-21 | 王振牛 | A kind of method that anti-bird of jet plane air intake duct multi-buffer hits cover |
| CN206494131U (en) * | 2017-02-20 | 2017-09-15 | 张延林 | Aircraft engine protector |
| CA3013629A1 (en) * | 2017-09-25 | 2019-03-25 | The Boeing Company | Dual protection inner seal washer for electromagnetic effects (eme) fasteners |
| CN109927916A (en) * | 2017-12-18 | 2019-06-25 | 郭俊鸽 | A kind of military aircraft composite material radome fairing |
| CN110550227A (en) * | 2019-09-14 | 2019-12-10 | 山东威西特斯航空科技有限公司 | Installation method of aircraft engine air inlet protective cover |
| CN210106022U (en) * | 2019-02-22 | 2020-02-21 | 广州市司派克航空器材有限公司 | Model turbojet engine with protective mesh enclosure |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090101760A1 (en) * | 2007-03-26 | 2009-04-23 | Maahnchooh Donald Mundingo Ghogomu | Aircraft engine protection unit (A.E.P.U) |
| US9188025B2 (en) * | 2008-11-26 | 2015-11-17 | Mra Systems, Inc. | Apparatus for facilitating access to a nacelle interior |
| US20110011055A1 (en) * | 2009-07-17 | 2011-01-20 | Thomas Jay Troy | Jet engine air intake guard |
| US9446857B2 (en) * | 2012-02-08 | 2016-09-20 | The Boeing Company | Engine cowl and inlet cover |
| FR2998620B1 (en) * | 2012-11-29 | 2018-04-06 | Safran Aircraft Engines | TURBOMACHINE HOOD CAPABLE OF COVERING A BLOWER CONE |
| US9617009B2 (en) * | 2013-02-22 | 2017-04-11 | United Technologies Corporation | ATR full ring sliding nacelle |
| CN105814285B (en) * | 2013-12-17 | 2018-11-02 | 通用电气公司 | Composite fan inlet louver plug |
| CN204327338U (en) * | 2014-11-14 | 2015-05-13 | 中国商用飞机有限责任公司 | A kind of engine charge oral shield |
| FR3058127B1 (en) * | 2016-10-28 | 2022-02-25 | Safran Aircraft Engines | ASSEMBLY BETWEEN AN AIRCRAFT PYLONE AND A TURBOMACHINE |
-
2020
- 2020-07-10 CN CN202010661182.2A patent/CN111846251B/en active Active
- 2020-07-13 WO PCT/CN2020/101528 patent/WO2022006918A1/en active Application Filing
Patent Citations (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20040016227A (en) * | 2002-08-16 | 2004-02-21 | 한국항공우주산업 주식회사 | Joining apparatus for the nozzle fairing of aerospace |
| EP1452707A1 (en) * | 2003-02-28 | 2004-09-01 | Airbus France | Protective device for the air intake of a jet engine |
| WO2005024184A2 (en) * | 2003-08-29 | 2005-03-17 | The Nordam Group, Inc. | Variable cam exhaust nozzle |
| CN101678897A (en) * | 2007-06-01 | 2010-03-24 | 空中客车运作股份公司 | Propulsion assembly for aircraft with sliding nacelle |
| FR2931799A1 (en) * | 2008-05-30 | 2009-12-04 | Airbus France | Aircraft i.e. civil passenger transport aircraft, has reactors located inside envelope surface of theoretical fuselage, where lines of theoretical fuselage correspond to same dimension lines of aircraft fuselage with or without reactors |
| CN103153789A (en) * | 2010-10-15 | 2013-06-12 | 埃尔塞乐公司 | Assembly for attaching the hangers from which an aircraft propulsion unit is suspended |
| CN103429495A (en) * | 2011-02-11 | 2013-12-04 | 空中客车运营简化股份公司 | Airplane having a rear propulsion system |
| EP2672070A2 (en) * | 2012-06-08 | 2013-12-11 | General Electric Company | Nozzle Mounting and Sealing Assembly and Method of Mounting and Sealing a Nozzle Assembly |
| KR20160060317A (en) * | 2014-11-20 | 2016-05-30 | 주식회사 창민테크론 | Intake cover of aircraft |
| CN106965944A (en) * | 2016-01-13 | 2017-07-21 | 王振牛 | A kind of method that anti-bird of jet plane air intake duct multi-buffer hits cover |
| CN206071726U (en) * | 2016-09-30 | 2017-04-05 | 黄子生 | Aircraft turbine engine safty shield |
| CN206494131U (en) * | 2017-02-20 | 2017-09-15 | 张延林 | Aircraft engine protector |
| CA3013629A1 (en) * | 2017-09-25 | 2019-03-25 | The Boeing Company | Dual protection inner seal washer for electromagnetic effects (eme) fasteners |
| CN109927916A (en) * | 2017-12-18 | 2019-06-25 | 郭俊鸽 | A kind of military aircraft composite material radome fairing |
| CN210106022U (en) * | 2019-02-22 | 2020-02-21 | 广州市司派克航空器材有限公司 | Model turbojet engine with protective mesh enclosure |
| CN110550227A (en) * | 2019-09-14 | 2019-12-10 | 山东威西特斯航空科技有限公司 | Installation method of aircraft engine air inlet protective cover |
Non-Patent Citations (3)
| Title |
|---|
| 一种泄流式进气道堵盖方案技术研究;张国宏;贺永杰;曹军伟;;战术导弹技术;20120515(03);256-260 * |
| 固冲发动机进气道堵盖对起动性能影响;陈义;高波;董新刚;杨玉新;李璞;;固体火箭技术;20161031(05);569-572 * |
| 波音737-300飞机发动机油门杆错位排故分析;常城;山东工业技术;20130825;37-38 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111846251A (en) | 2020-10-30 |
| WO2022006918A1 (en) | 2022-01-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3216697B1 (en) | Shielded anti-icing system and methods | |
| US8132755B2 (en) | Engine exhaust system with directional nozzle | |
| US6463739B1 (en) | Afterburner heat shield | |
| CN100554085C (en) | The aero-engine assembly that comprises driving engine and be used for the base of this driving engine | |
| CA2344128C (en) | Method and apparatus for the cooling of jet-engine turbine casings | |
| US5623820A (en) | Flow control apparatus for gas turbine engine installation pressure relief doors | |
| EP1640565B1 (en) | Swirl-enhanced aerodynamic fastener shield for turbomachine | |
| US20130174572A1 (en) | Method for cooling a thermal protection floor of an aft aerodynamic fairing of a structure for mounting an aircraft propulsion system | |
| JP2008031983A (en) | Exhaust duct assembly and its assembling method | |
| EP3701171B1 (en) | Propulsion unit for aircraft | |
| US20160017804A1 (en) | Apparatus for protecting aircraft components against foreign object damage | |
| US20100300661A1 (en) | Device For Cooling Hot Gas To Be Discharged From An Aircraft | |
| US20140014792A1 (en) | Fastener assembly for a gas turbine | |
| CN111846251B (en) | Sand-proof protection device for air inlet, exhaust and tail nozzle of engine | |
| BR102017012071A2 (en) | THERMAL INSULATION COVER AND THERMAL INSULATION PLUG ASSEMBLY | |
| EP3087269B1 (en) | Aircraft with injection cooling system and injection cooling system | |
| JP3998494B2 (en) | Replaceable afterburner heat shield | |
| RU2500588C2 (en) | Turbojet nacelle | |
| US8448448B2 (en) | Cooling air bleed device in a turbomachine | |
| US8408009B2 (en) | Cooling air bleed device in a turbine engine | |
| EP2868870A1 (en) | Turbomachine housing a device in the engine compartment thereof and thermal protector for the device | |
| JP6317946B2 (en) | aircraft | |
| US20220154846A1 (en) | Valve assembly and lockout mechanism | |
| EP0794118B1 (en) | Flow control apparatus for gas turbine engine installation pressure relief doors | |
| EP4117992A1 (en) | Swirl anti-icing injector head nozzle configurations |
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 |