CN218467717U

CN218467717U - Adopt fine grain aeroengine rectification extension board of K465 alloy

Info

Publication number: CN218467717U
Application number: CN202222589321.2U
Authority: CN
Inventors: 剧亚东; 厉福海; 贾婷; 王艳平; 王佳伟
Original assignee: Suzhou Hanwei Material Technology Co ltd
Current assignee: Suzhou Hanwei Material Technology Co ltd
Priority date: 2022-09-29
Filing date: 2022-09-29
Publication date: 2023-02-10
Anticipated expiration: 2032-09-29

Abstract

The utility model provides an adopt fine grained aeroengine rectification extension board of K465 alloy, include: plate body, heat-circulating pipe, splitter box and heat conduction inner chamber, the air inlet duct has been seted up to the plate body upper end, the heat conduction inner chamber has been seted up to plate body inside, the air inlet duct includes set casing, connecting seat, interior guide plate and guiding gutter, the connecting seat is installed to the set casing inboard, the guide plate in the connecting seat lower extreme is installed, the guiding gutter has all been seted up to interior guide plate both sides, the splitter box has been seted up to heat-circulating pipe right-hand member, the tee bend is installed to the splitter box right-hand member, the heat pipe is installed to the tee bend right-hand member, fire-retardant layer is installed in the heat pipe outside, compares with prior art, the utility model discloses following beneficial effect has: through using interior guide plate and guiding gutter, can be to the inboard support of plate body when to make the air current pass through fast, through using heat-circulating pipe and heat pipe, can make things convenient for the staff to heat the rectification extension board.

Description

Adopt fine grain aeroengine rectification extension board of K465 alloy

Technical Field

The utility model belongs to the technical field of the aeroengine, a adopt fine grain aeroengine rectification extension board of K465 alloy is related to.

Background

When an airplane flies under low-temperature, humid and meteorological conditions containing supercooled water drops, an air inlet component at the front end of an engine of the airplane is frozen, a rectifying support plate is easy to freeze, the ice accumulation causes reduction of air inlet quantity of the engine, reduction of thrust and reduction of air inlet quality of the engine, meanwhile, the engine is damaged or even destroyed due to ice accumulation falling, the safety of airplane flying is seriously affected by the ice, and therefore a safe and reliable ice prevention system is needed.

In chinese patent CN114876638A (a hot gas anti-icing structure of an aircraft engine rectifying support plate), an anti-icing component is included; the anti-icing component is provided with a hot air inlet along the middle part of the upper end surface, and extends to the lower end of the anti-icing component along the spanwise equal section of the rectifying support plate to form a hot air cavity; the anti-icing component is provided with a third hot air outlet along the lower end surface; the front end of the interior of the anti-icing component is provided with a support plate front cavity, and hot air flow in the hot air cavity is injected into the support plate front cavity through the upper row of fine channels along the tangential direction and flows into the rear end air collection cavity through the lower row of fine channels; the upper row of fine passages are a passage set which is uniformly arranged at intervals along the spanwise direction of the rectification support plate, and the lower row of fine passages and the upper row of fine passages are correspondingly arranged in a sequential or staggered arrangement mode; the middle part of the gas collection cavity is provided with a plurality of sections of flow distribution plates along the vertical direction, and the wall surface of the rear section of the flow distribution plate is provided with a plurality of air outlet holes; the support plate front cavity extends from the upper end surface to the lower end surface along the spreading direction of the rectification support plate, the upper end surface forms a first hot gas outlet, and the lower end surface forms a second hot gas outlet.

However, when the rectifying support plate is used in an actual flight task, it is found that although the device can be used in a low-temperature and humid environment and accumulated ice falls off, the temperature inside the hot air cavity is high, the pipeline of the hot air cavity is easily damaged, and meanwhile, the airflow is disturbed due to the excessively thick rectifying support plate, and the air intake effect of the hot air cavity is reduced, so that the rectifying support plate for the aero-engine adopting the K465 fine grains is urgently needed to solve the problems.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing an adopt fine grained aeroengine rectification extension board of K465 alloy, solve the problem of proposing among the above-mentioned background art to the not enough that prior art exists.

The utility model discloses a following technical scheme realizes: an aircraft engine rectifying support plate adopting K465 alloy fine grains comprises: the heat-conducting plate comprises a plate body, an air inlet groove and a heat-conducting inner cavity, wherein the air inlet groove is formed in the upper end of the plate body, and the heat-conducting inner cavity is formed in the plate body;

the air inlet groove comprises a fixed shell, a connecting seat, an inner guide plate and guide grooves, the connecting seat is installed on the inner side of the fixed shell, the inner guide plate is installed at the lower end of the connecting seat, and the guide grooves are formed in the two sides of the inner guide plate;

the heat conduction inner chamber includes heat-circulating pipe, splitter box, tee bend, heat pipe and fire-retardant layer, the splitter box has been seted up to the heat-circulating pipe right-hand member, the tee bend is installed to the splitter box right-hand member, the heat pipe is installed to the tee bend right-hand member, fire-retardant layer is installed in the heat pipe outside.

As a preferred embodiment, the cross section of the plate body is of an arc structure, the cross section of the inner side of the air inlet groove is of a triangular structure, and the inner part of the plate body is of a hollow structure, so that air flow can be conveniently divided at the outer side of the plate body and the inner side of the air inlet groove.

As a preferred embodiment, the inside of the air inlet duct is communicated with the guide groove, the guide groove is provided with a plurality of groups, the cross section of the inner guide plate is in an i-shaped structure, and the inner guide plate can support the inner side of the plate body and enable air flow to pass through rapidly.

As a preferred embodiment, the inner deflectors are fixedly connected with the connecting seats, two groups of connecting seats are correspondingly installed on one group of inner deflectors, and the connecting seats are fixedly connected with the fixed shell.

In a preferred embodiment, the fixed shell, the inner guide plate and the plate body are all made of K465 alloy fine grains, and the heat circulation pipe is connected with an external engine.

As a preferred embodiment, the interior of the heat circulation pipe, the diversion trench, the tee joint and the heat conduction pipe are all communicated with each other, the manufacturing materials of the circulation pipe, the diversion trench, the tee joint and the heat conduction pipe are all zirconium diboride, the flame retardant layer wraps the outer side of the heat conduction pipe, and the flame retardant layer is made of SVT expandable graphite.

After the technical scheme is adopted, the beneficial effects of the utility model are that: through using interior guide plate and guiding gutter, can be to the inboard support of plate body when to make the air current pass through fast, through using heat-circulating pipe and heat pipe, can make things convenient for the staff to heat the rectification extension board.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the description below are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without inventive labor.

FIG. 1 is a schematic structural view of an aircraft engine rectification support plate adopting K465 alloy fine grains according to the present invention;

FIG. 2 is a top view structural diagram of the interior of a heat conducting inner cavity in a rectification support plate of an aero-engine adopting K465 fine crystal alloy of the present invention;

FIG. 3 is a right side view structure diagram of the inside of an air inlet duct in the rectification support plate of the aero-engine adopting K465 fine grain;

in the figure: the heat-conducting plate comprises a plate body 1, an air inlet groove 2, a heat-conducting inner cavity 3, a fixing shell 2a, a connecting seat 2b, an inner guide plate 2c, a guide groove 2d, a heat-circulating pipe 3a, a flow dividing groove 3b, a tee joint 3c, a heat-conducting pipe 3d and a flame-retardant layer 3e.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by a person skilled in the art without making creative efforts belong to the protection scope of the present invention.

Referring to fig. 1-3, an aircraft engine rectifying support plate adopting fine grains of K465 alloy includes: the plate comprises a plate body 1, an air inlet groove 2 and a heat conduction inner cavity 3, wherein the air inlet groove 2 is formed in the upper end of the plate body 1, and the heat conduction inner cavity 3 is formed in the plate body 1;

the air inlet groove 2 comprises a fixed shell 2a, a connecting seat 2b, an inner guide plate 2c and guide grooves 2d, the connecting seat 2b is installed on the inner side of the fixed shell 2a, the inner guide plate 2c is installed at the lower end of the connecting seat 2b, and the guide grooves 2d are formed in the two sides of the inner guide plate 2 c;

the heat conduction inner cavity 3 comprises a heat circulation pipe 3a, a flow distribution groove 3b, a tee joint 3c, a heat conduction pipe 3d and a flame-retardant layer 3e, the flow distribution groove 3b is formed in the right end of the heat circulation pipe 3a, the tee joint 3c is installed at the right end of the flow distribution groove 3b, the heat conduction pipe 3d is installed at the right end of the tee joint 3c, and the flame-retardant layer 3e is installed on the outer side of the heat conduction pipe 3 d.

The cross section of the plate body 1 is of an arc structure, the cross section of the inner side of the air inlet groove 2 is of a triangular structure, and the inner part of the plate body 1 is of a hollow structure, so that air flow can be conveniently divided in the outer side of the plate body 1 and the inner side of the air inlet groove 2.

Inside and the guiding gutter 2d intercommunication each other of air inlet duct 2, a plurality of groups have been seted up to guiding gutter 2d, and interior guide plate 2c cross section is an I-shaped structure, and interior guide plate 2c can be to the inboard support of plate body 1 the time, can make the air current pass through fast.

Interior guide plate 2c is connected fixedly with connecting seat 2b, and two sets of connecting seats 2b are installed to a set of interior guide plate 2c correspondence, and connecting seat 2b is connected fixedly with set casing 2a, can increase the air current and pass through efficiency.

The fixed shell 2a, the inner guide plate 2c and the plate body 1 are all made of K465 alloy fine grains, and the heat circulation pipe 3a is connected with an external engine, so that the strength of the rectification support plate can be improved.

The heat circulation pipe 3a, the diversion trench 3b, the tee joint 3c and the heat conduction pipe 3d are all communicated with each other, the circulation pipe, the diversion trench 3b, the tee joint 3c and the heat conduction pipe 3d are made of zirconium diboride, the flame retardant layer 3e wraps the outer side of the heat conduction pipe 3d, and the flame retardant layer 3e is made of SVT expandable graphite and can improve the heat-resisting effect of the rectifying support plate.

As a first embodiment of the present invention: in order to solve the problem that although the device can be used in a low-temperature humid environment and can simultaneously drop accumulated ice, the temperature in the hot air cavity is high, and pipelines of the hot air cavity are extremely easy to damage, firstly, heat in the aircraft engine enters the inside of the diversion channel 3b through the hot circulation pipe 3a, then, the heat is conducted to the inside of the two groups of heat conduction pipes 3d through the tee joint 3c, heat is provided for the plate body 1 through the heat conduction pipes 3d, and the flame-retardant layer 3e is made of SVT expandable graphite, so that the phenomenon of spontaneous combustion caused by the fact that the temperature of the heat conduction pipes 3d is too high can be effectively prevented.

As a second embodiment of the present invention: in order to solve the problem that the airflow is disordered and the air intake effect of the rectification support plate is reduced due to the fact that the rectification support plate is too thick, firstly, when the aviation flight works, high-speed air rapidly flows at the upper end of the plate body 1 and inside the air intake duct 2, the high-speed air flowing inside the air intake duct 2 can effectively stabilize the stability of the rectification support plate, and the air drainage efficiency entering from the air intake duct 2 can be accelerated through the plurality of groups of guide grooves 2d, so that the rectification support plate is kept stable.

The above description is only for the preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. An aircraft engine rectifying support plate adopting K465 alloy fine grains comprises: plate body (1), air inlet duct (2) and heat conduction inner chamber (3), its characterized in that: an air inlet groove (2) is formed in the upper end of the plate body (1), and a heat conduction inner cavity (3) is formed in the plate body (1);

the air inlet groove (2) comprises a fixed shell (2 a), a connecting seat (2 b) and guide grooves (2 d), the connecting seat (2 b) is installed on the inner side of the fixed shell (2 a), an inner guide plate (2 c) is installed at the lower end of the connecting seat (2 b), and the guide grooves (2 d) are formed in the two sides of the inner guide plate (2 c);

heat conduction inner chamber (3) include heat-circulating pipe (3 a), splitter box (3 b) and fire-retardant layer (3 e), splitter box (3 b) have been seted up to heat-circulating pipe (3 a) right-hand member, tee bend (3 c) are installed to splitter box (3 b) right-hand member, heat pipe (3 d) are installed to tee bend (3 c) right-hand member, fire-retardant layer (3 e) are installed in heat pipe (3 d) outside.

2. The aircraft engine rectifying support plate adopting K465 alloy fine crystals as claimed in claim 1, wherein: the cross section of the plate body (1) is of an arc structure, the cross section of the inner side of the air inlet groove (2) is of a triangular structure, and the inside of the plate body (1) is of a hollow structure.

3. The aircraft engine rectifying support plate adopting K465 alloy fine crystals as claimed in claim 2, wherein: the inside of the air inlet groove (2) is communicated with the guide grooves (2 d), a plurality of groups of the guide grooves (2 d) are arranged, and the cross section of the inner guide plate (2 c) is of an I-shaped structure.

4. The aircraft engine rectifying support plate adopting K465 alloy fine grains as claimed in claim 3, wherein: the inner guide plate (2 c) is fixedly connected with the connecting seats (2 b), one group of the inner guide plate (2 c) is correspondingly provided with two groups of connecting seats (2 b), and the connecting seats (2 b) are fixedly connected with the fixed shell (2 a).

5. The aircraft engine rectifying support plate adopting K465 alloy fine grains as claimed in claim 4, wherein: the fixed shell (2 a), the inner guide plate (2 c) and the plate body (1) are all manufactured by K465 alloy fine grains, and the heat circulation pipe (3 a) is connected with an external engine.

6. The aircraft engine rectifying support plate adopting K465 alloy fine grains as claimed in claim 5, wherein: the interiors of the heat circulation pipe (3 a), the flow distribution groove (3 b), the tee joint (3 c) and the heat conduction pipe (3 d) are communicated with each other;

the circulating pipe, the splitter box (3 b), the tee joint (3 c) and the heat-conducting pipe (3 d) are made of zirconium diboride, the flame-retardant layer (3 e) wraps the outer side of the heat-conducting pipe (3 d), and the flame-retardant layer (3 e) is made of SVT expandable graphite.