CN111911314A

CN111911314A - Sealed explosion-proof blanking cover of aircraft side-push engine

Info

Publication number: CN111911314A
Application number: CN202010881430.4A
Authority: CN
Inventors: 杨正富; 毛义锋; 易斌
Original assignee: Mianyang Jiatai Intelligent Manufacturing Co ltd
Current assignee: Mianyang Jiatai Intelligent Manufacturing Co ltd
Priority date: 2020-08-27
Filing date: 2020-08-27
Publication date: 2020-11-10

Abstract

The invention discloses a sealed explosion-proof blanking cover of an aircraft side-push engine, which is fixed at the upper end of a power output port of the side-push engine, the sealed explosion-proof blanking cover comprises an aluminum alloy insert and a blanking cover body made of PEEK (polyether-ether-ketone) material, the aluminum alloy insert comprises a cylindrical barrel and a flange plate, the blanking cover body comprises a cover surface and a cover wall, the lower end surface of the cover wall is provided with a circle of annular groove extending towards the cover surface, the cylindrical barrel is embedded into the annular groove, the second cover wall at the other side of the annular groove is bonded with the outer wall of the cylindrical barrel, and a circle of annular release groove is arranged on the cover wall right above the cylindrical barrel. The blocking cover is isolated and sealed from external interference factors when the side-push engine of the aircraft does not start to work, once the side-push engine works, when the pressure in the cavity is greater than a design required value, the bottom of the annular release groove is broken by internal pressure, so that the top of the blocking cover is pushed out completely, and the requirement of kinetic energy output is met.

Description

Sealed explosion-proof blanking cover of aircraft side-push engine

Technical Field

The invention relates to the technical field of matched blocking covers of aircraft side-thrust turning engines, in particular to a sealed type explosion-proof blocking cover of an aircraft side-thrust engine.

Background

The aircraft main propulsion engine provides forward power, and when the flight direction and the flight attitude of the aircraft need to be adjusted, the side propulsion engine is required to enter a working state to provide kinetic energy. When the side-thrust engine does not provide kinetic energy output, deformation larger than the design requirement amount is not generated when the side-thrust engine needs to bear external design pressure, and sealing between the outside and the inside of the aircraft is also needed to be realized so as to avoid external environmental factors from interfering with normal operation of the engine.

Disclosure of Invention

The invention aims to solve the defects in the prior art and provides a sealed type explosion-proof blanking cover of an aircraft side-push engine, so that the side-push engine is protected from being interfered by external conditions when not entering a working state and a kinetic energy output window can be smoothly opened when entering the working state.

In order to achieve the purpose, the invention is implemented according to the following technical scheme:

a sealed explosion-proof blanking cover of an aircraft side-push engine is fixed at the upper end of a power output port of the side-push engine, the sealed explosion-proof blanking cover comprises an aluminum alloy insert and a blanking cover body made of PEEK (polyether-ether-ketone) material, the aluminum alloy insert comprises a cylindrical barrel and a flange fixed at the outer ring of the bottom of the cylindrical barrel, the lower end face of the flange is fixed on the power output port of the side-push engine, a sealing element is arranged between the lower end face of the flange and the power output port of the side-push engine, the blanking cover body covers the cylindrical barrel and comprises a cover face and a cover wall, the lower end face of the cover wall is provided with a ring-shaped groove extending towards the cover face, the top of the ring-shaped groove is positioned above the lower end face of the cover face, one side of the ring-shaped groove forms a first cover wall, the other side of the ring-shaped groove forms a second cover wall, the thickness of the first cover, the second cover wall on the other side of the annular groove is bonded with the outer wall of the cylindrical barrel, and the bottom of the second cover wall on the other side of the annular groove is fixed on the upper end face of the flange plate; and a circle of annular release groove is arranged on the cover wall right above the cylindrical barrel, and the distance between the bottom of the annular release groove and the top end of the cylindrical barrel is 0.5 mm.

Furthermore, a center column is vertically fixed in the center of the lower end face of the cover face, a plurality of reinforcing ribs are uniformly distributed along the circumference of the outer wall of the center column, and the end parts of the reinforcing ribs are fixed on the inner wall of the first cover wall.

Preferably, the bottom of the second cover wall is bonded to the upper end face of the flange.

Preferably, the second cover wall and the flange are mounted on the power output port of the side-push engine through fixing screws, and the fixing screws sequentially penetrate through the second cover wall and the flange and then are connected with the outer wall of the power output port of the side-push engine through threads.

Preferably, the sealing element between the lower end face of the flange plate and the power output port of the side-thrust engine is an annular sealing ring.

Preferably, the surface roughness of the outer wall of the cylindrical barrel is Ra3.2, and the surface roughness of the inner wall of the cylindrical barrel is Ra0.8.

Compared with the prior art, the blocking cover disclosed by the invention is isolated and sealed from external interference factors when the aircraft side-push engine does not start to work, once the side-push engine works, when the pressure in the cavity is greater than a design requirement value, the inside of the blocking cover is pressed, and the bottom of the annular release groove is broken by the internal pressure, so that the top of the blocking cover is completely pushed out, and the requirement of kinetic energy output is met.

Drawings

FIG. 1 is a cross-sectional view of one embodiment of the present invention.

FIG. 2 is a top view of one embodiment of the present invention.

FIG. 3 is a schematic structural view of the aluminum alloy insert of the present invention.

Fig. 4 is an enlarged view of fig. 1 at a.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail with reference to the following embodiments. The specific embodiments described herein are merely illustrative of the invention and do not limit the invention.

As shown in fig. 1-4, the sealed explosion-proof cap of the aircraft side-push engine of the present embodiment is fixed to the upper end of the power output port 1 of the side-push engine, and includes an aluminum alloy insert 3 and a cap body 4 made of PEEK material, where in the present embodiment, the PEEK material is carbon fiber reinforced by 30%, and has a tensile strength of 220MPa, a tensile modulus of 23GPa, a tensile elongation of 1.8%, a bending strength of 298MPa, and a bending modulus of 21GPa, compressive strength of 240MPa and impact strength of 46KJ/m²Rockwell hardness HRR 121, melting point 343 ℃, thermal deformation temperature 315 ℃, continuous use temperature 260 ℃ and density 1.4 +/-0.01; aluminum alloy insert 3 includes cylindricality barrel 32 and fixes the ring flange 31 at cylindricality barrel 32 bottom outer lane, the terminal surface is fixed on side push engine power delivery outlet 1 under ring flange 31, terminal surface and side push are equipped with sealing member 2 between the engine power delivery outlet 1 under the ring flange 31, and sealing member 2 in this embodiment can adopt rubber seal in order to realize the isolation of side push engine power delivery outlet 1 internal and external environment, blanking cover body 4 covers on cylindricality barrel 3, and blanking cover body 4 includes capping 45 and geyser, and the annular groove (not seen in the picture) that the round extended towards the capping is seted up to the lower terminal surface of capping, and the top of annular groove is located capping 45 terminal surface's top, and annular groove one side forms first capping 41, annular groove opposite side formation second capping 42, and the thickness of first capping 41 is less than capping 45, cylindricality barrel 32 embedding annular groove and cylindricality barrel 32's top and annular groove's top contact The second cover wall 42 at the other side of the annular groove is coated with DG-4 epoxy resin adhesive to be bonded with the outer wall of the cylindrical barrel 32, and because the thickness of the DG-4 epoxy resin adhesive is not suitable to be controlled to be consistent, a ring of annular glue overflow grooves 7 are arranged at the lower part of the second cover wall 42 and the upper part of the flange plate 31, so that redundant glue flows into the glue overflow grooves 7 during extrusion, and the effect of primary sealing is achieved; the surface roughness of the outer wall of the cylindrical barrel 32 is Ra3.2, the uneven state of the surface of the outer wall of the cylindrical barrel 32 enables the DG-4 epoxy resin system cementing agent and the annular groove corresponding to the PEEK blanking cover to have better bonding performance, and meanwhile, the secondary sealing of the blanking cover body 4 is realized; the surface roughness Ra0.8 of the inner wall of the cylindrical barrel 32 can effectively reduce the friction force between the PEEK blanking cover and the inner wall of the cylindrical barrel 32 when a release region at the top of the blanking cover needs to fall off under the output pressure of an engine so as to realize successful falling off; the bottom of the second cover wall 42 at the other side of the annular groove is fixed on the upper end surface of the flange plate 31; a ring of annular release grooves 5 are formed in the cover wall right above the cylindrical barrel 32, and the annular release grooves 5 are arranged for the purpose that when the side-push engine works, when the pressure in the cavity is higher than the design pressureWhen the pressure is evaluated, the inner part of the blocking cover is pressed, and the bottom of the annular release groove can be broken under the internal pressure; the distance between the bottom of the annular release groove 5 and the top end of the cylindrical barrel 32 is 0.5mm, and the distance between the bottom of the annular release groove 5 and the top end of the cylindrical barrel 32 can be adjusted to achieve the purpose of opening the kinetic energy output port by pressure according to different power of side-thrust engines of each type of aircraft.

As shown in figure 1, when the aircraft side-push engine does not start working, the whole sealed type explosion-proof blanking cover is isolated and sealed from external interference factors, once the side-push engine works, pressure is pushed to the cover surface 45 along the arrow direction shown in the drawing, due to the factor of shearing force, when the internal pressure is greater than the self shearing-resistant index of the material between the bottom of the annular release groove 5 and the top end of the cylindrical barrel 32, the bottom of the annular release groove 5 is broken, the top of the blanking cover falls outwards due to the internal pressure of the side-push engine, and the purpose of completely opening the kinetic energy output port is achieved.

As shown in fig. 1, a center post 43 is vertically fixed at the center of the lower end surface of the cover surface 45, a plurality of reinforcing ribs 44 are uniformly distributed along the circumference of the outer wall of the center post 43, and the end portions of the reinforcing ribs 44 are fixed on the inner wall of the first cover wall 41. When the side-push engine does not enter a working state, the top of the cover surface 45 is subjected to external pressure, the pressure is subjected to primary pressure dispersion on the top of the cylindrical barrel 32 of the aluminum alloy insert 3, and the residual pressure disperses the force to the periphery of the cover wall along the central column 43 and the reinforcing ribs 44, so that the requirement of the deformation amount of the external pressure is met.

In this embodiment, the bottom of the second cover wall 42 and the upper end surface of the flange 31 may be bonded together by a DG-4 epoxy adhesive; of course, the second cover wall 42 and the flange 31 may be mounted on the side-push engine power output port 1 by fixing screws 6, and the fixing screws 6 may sequentially penetrate through the second cover wall 42 and the flange 31 and then be screwed to the outer wall of the side-push engine power output port 1. Mainly in order to prevent the blanking cap body 4 from falling off from the aluminium alloy insert 3 when the aircraft side thrust engine is not starting to operate.

As shown in fig. 1, the working principle of the present invention is:

when the aircraft side-push engine does not start working, the aluminum alloy insert 3 and the plug cover body 4 made of PEEK material are completely plugged at the power output port 1 of the side-push engine, so that the power output port 1 of the side-push engine is isolated and sealed from external interference factors; when the side-push engine works, pressure is pushed to the cover surface 45 along the arrow direction of the figure, due to the factor of shearing force, when the internal pressure is greater than the self anti-shearing index of the PEEK material between the bottom of the annular release groove 5 and the top end of the cylindrical barrel 32, the bottom of the annular release groove 5 is broken, the top of the blocking cover falls outwards due to the relation of the internal pressure of the side-push engine, and the purpose that the kinetic energy output port is completely opened is achieved.

The technical solution of the present invention is not limited to the limitations of the above specific embodiments, and all technical modifications made according to the technical solution of the present invention fall within the protection scope of the present invention.

Claims

1. The utility model provides an explosion-proof blanking cover of canned type of aircraft side-push engine, its characterized in that fixes in side-push engine power delivery outlet upper end, explosion-proof blanking cover of canned type includes the aluminum alloy inserts and the blanking cover body of being made by the PEEK material, the aluminum alloy inserts includes cylindricality barrel and fixes the ring flange in cylindricality barrel bottom outer lane, the terminal surface is fixed on side-push engine power delivery outlet under the ring flange, be equipped with the sealing member between terminal surface and the side-push engine power delivery outlet under the ring flange, blanking cover body lid is on the cylindricality barrel, and blanking cover body includes capping and gecko wall, and the lower terminal surface of gecko wall is seted up the annular groove that the round extends towards the capping, and the top of annular groove is located capping below the terminal surface, and annular groove one side forms first capping, and the annular groove opposite side forms the second capping, and the thickness of first capping is lighter, the cylindrical barrel is embedded into the annular groove, the top of the cylindrical barrel is in contact with the top of the annular groove, the second cover wall on the other side of the annular groove is bonded with the outer wall of the cylindrical barrel, and the bottom of the second cover wall on the other side of the annular groove is fixed on the upper end face of the flange plate; and a circle of annular release groove is arranged on the cover wall right above the cylindrical barrel, and the distance between the bottom of the annular release groove and the top end of the cylindrical barrel is 0.5 mm.

2. The sealed type explosion proof cover for an aircraft side thrust engine according to claim 1, characterized in that: a central column is vertically fixed in the center of the lower end face of the cover face, a plurality of reinforcing ribs are uniformly distributed along the circumference of the outer wall of the central column, and the end parts of the reinforcing ribs are fixed on the inner wall of the first cover wall.

3. The sealed type explosion proof cover for an aircraft side thrust engine according to claim 1, characterized in that: the bottom of the second cover wall is bonded with the upper end face of the flange.

4. The sealed type explosion proof cover for an aircraft side thrust engine according to claim 1, characterized in that: and the second cover wall and the flange plate are arranged on the power output port of the side-push engine through fixing screws, and the fixing screws sequentially penetrate through the second cover wall and the flange plate and then are connected with the outer wall of the power output port of the side-push engine through threads.

5. The sealed type explosion proof cover for an aircraft side thrust engine according to claim 1, characterized in that: and a sealing element between the lower end surface of the flange plate and a power output port of the side-thrust engine is an annular sealing ring.

6. The sealed type explosion proof cover for an aircraft side thrust engine according to claim 1, characterized in that: the surface roughness of the outer wall of the cylindrical barrel is Ra3.2, and the surface roughness of the inner wall of the cylindrical barrel is Ra0.8.