CN216077334U

CN216077334U - A radome fairing structure for engine anti-icing

Info

Publication number: CN216077334U
Application number: CN202122660465.8U
Authority: CN
Inventors: 程俊; 赵熙; 梁湘华; 林莉; 吴帝佳; 程享
Original assignee: AECC Guiyang Engine Design Research Institute
Current assignee: AECC Guiyang Engine Design Research Institute
Priority date: 2021-11-02
Filing date: 2021-11-02
Publication date: 2022-03-18
Anticipated expiration: 2031-11-02

Abstract

The utility model discloses a fairing structure for anti-icing of an engine, which comprises: the surface of the convex front end of the fairing is provided with a plurality of through holes; one end of the anti-icing air guide pipe is fixedly connected with the inner surface of the front end of the bulge of the fairing correspondingly, and the other end of the anti-icing air guide pipe extends to the space at the rear end of the engine fan. The engine fan introduces the cold air in the environment into the engine, the cold air is compressed by the engine fan, the temperature and the pressure are increased, then the high-temperature high-pressure gas is introduced into the anti-icing guide pipe of the engine, the pressure in the anti-icing guide pipe is higher than the external atmospheric pressure, so the high-temperature high-pressure gas is discharged from the plurality of through holes of the main part and the auxiliary part, the high-temperature high-pressure gas can also play a reverse force role on the facing supercooled water drops, the airflow coming out from the through holes of the fairing can cover the surface of the fairing, the contact area of the fairing and the supercooled water drops is reduced, the possibility of icing is effectively reduced, and the problem that partial icing can exist on the outer side surface of the outer wall of the bonnet is solved.

Description

A radome fairing structure for engine anti-icing

Technical Field

The utility model relates to a fairing structure for engine ice prevention, and belongs to the technical field of engine fairings.

Background

The engine is used as a core power component of the airplane, and can cause serious consequences in case of failure. When an aircraft is flying at high altitudes, there are often a large number of liquid droplets in the cloud that remain unfrozen below freezing, i.e., "supercooled droplets". Supercooled water drops collide with a fairing at the front end of the engine and are accumulated and frozen on the surface of the fairing to generate an ice accumulation phenomenon, and if ice removal measures are not taken in time, airflow is separated, so that compressor blades in the engine are forced to vibrate; if the fallen ice layer collides with the blade rotating at a high speed, stability and safety of the engine are affected. Therefore, the icing of the engine often brings great harm to the flight safety, and the need of an efficient and reliable anti-icing technical means is a fundamental measure for ensuring the safety of the engine.

In the engine hood with the rectification boss disclosed in the chinese patent publication No. CN212202252U, a heat dissipation channel is established between the outer wall of the hood and the inner wall of the hood, and hot air is introduced from the diffusion tube and enters the heat dissipation channel to heat the outer wall of the hood and the inner wall of the hood, so that although the ice-proof effect can be achieved, the air temperature is lower than zero during high-altitude flight, and during continuous high-altitude flight, the problem of partial icing exists on the outer side surface of the outer wall of the hood.

SUMMERY OF THE UTILITY MODEL

In order to solve the technical problem, the utility model provides a fairing structure for anti-icing of an engine.

The utility model is realized by the following technical scheme.

The utility model provides a fairing structure for engine anti-icing, comprising:

the surface of the convex front end of the fairing is provided with a plurality of through holes;

one end of the anti-icing air guide pipe corresponds to the inner face of the front end of the protrusion of the fairing and is fixedly connected with the inner face of the front end of the protrusion of the fairing, the hollow space inside the anti-icing air guide pipe is communicated with the through hole, and the other end of the anti-icing air guide pipe extends to the space at the rear end of the engine fan.

One end of the anti-icing air guide conduit is fixedly connected with the inner surface of the front end of the bulge of the fairing in a corresponding gluing mode.

One end of the anti-icing air guide pipe is correspondingly welded and fixedly connected with the inner surface of the front end of the bulge of the fairing.

The anti-icing bleed pipe is the stereoplasm body, and stereoplasm body one end welded fastening is at protruding front end internal surface and corresponds the intercommunication with a plurality of through-holes, and the other end of stereoplasm body extends to engine fan rear end space.

The orientation of each through-hole of a plurality of through-holes is all inequality for a plurality of through-holes are equallyd divide and are outwards gone out on protruding front end, and what like this can be more even is equallyd divide the water conservancy diversion with high temperature high pressure gas to the radome fairing surface formation steam rete.

The through hole is a circular through hole, so that the processing and the gas flowing in the through hole are convenient.

The utility model has the beneficial effects that: the engine fan introduces cold air in the environment into the engine, the temperature and the pressure of the cold air are increased after the cold air is compressed by the engine fan, then high-temperature high-pressure gas is introduced into the anti-icing guide pipe of the engine, the pressure in the anti-icing guide pipe is higher than the external atmospheric pressure, so that the high-temperature high-pressure gas is discharged from a plurality of through holes arranged on the surfaces of the front ends of the protrusions of the main fairing and the auxiliary fairing, and under the common action of the high-temperature high-pressure gas and the atmospheric pressure, the high-temperature high-pressure gas can diffuse along the surface of the fairing to heat the surface of the fairing around the through holes, so that the surface temperature of the fairing is increased, and supercooled water drops are difficult to accumulate and freeze on the surface of the fairing; meanwhile, the high-temperature and high-pressure gas can also play a role of reverse force for the facing supercooled water drops, and the airflow coming out of the through hole of the fairing can cover the surface of the fairing, so that the contact area of the fairing and the supercooled water drops is reduced, the icing possibility is effectively reduced, and the problem that part of the outer side surface of the outer wall of the cap cover is iced is solved.

Drawings

FIG. 1 is a schematic view of the present invention;

in the figure: 1-a fairing; 11-raised front end; 12-a through hole; 2-an engine fan; 3-anti-icing air-entraining duct.

Detailed Description

The technical solution of the present invention is further described below, but the scope of the claimed invention is not limited to the described.

As shown in fig. 1.

The utility model relates to a fairing structure for anti-icing of an engine, comprising:

the surface of a convex front end 11 of the fairing 1 is provided with a plurality of through holes 12;

one end of the anti-icing air guide pipe 3 is correspondingly welded or fixedly connected with the front end 11 of the protrusion of the fairing 1 in a gluing mode, the hollow space inside the anti-icing air guide pipe 3 is communicated with the through hole 12, and the other end of the anti-icing air guide pipe 3 extends to the space at the rear end of the engine fan 2.

When the aircraft flies at high altitude, the engine fan 2 introduces cold air in the environment into the engine, and the temperature and the pressure of the cold air are increased after the cold air is compressed by the engine fan 2. Then, high-temperature and high-pressure gas is introduced into the anti-icing guide pipe 3 of the engine, and the pressure in the anti-icing guide pipe 3 is higher than the external atmospheric pressure, so that the high-temperature and high-pressure gas is discharged from a plurality of through holes 12 arranged on the surface of the front end 11 of the protrusion of the main fairing and the auxiliary fairing 1. Under the common action of the high-temperature high-pressure gas and the atmosphere, the high-temperature high-pressure gas diffuses along the surface of the fairing 1 to heat the surface of the fairing 1 around the through hole 12, so that the surface temperature of the fairing 1 is increased, and supercooled water drops are difficult to accumulate and freeze on the surface of the fairing 1; meanwhile, the high-temperature and high-pressure gas can also play a role of reverse force for the facing supercooled water drops, and the airflow coming out of the through holes 12 of the fairing 1 can cover the surface of the fairing 1, so that the contact area of the fairing 1 and the supercooled water drops is reduced, the icing possibility is effectively reduced, and the problem that part of the outer side surface of the outer wall of the hood is iced is solved.

The anti-icing air guide pipe 3 is a hard pipe body, one end of the hard pipe body is welded and fixed on the inner surface of the front end 11 of the protrusion and correspondingly communicated with the through holes 12, and the other end of the hard pipe body extends to the space at the rear end of the engine fan 2.

The inner diameter of the anti-icing air guide conduit 3 is circular, so that air flow can conveniently flow in the conduit.

The inner diameter and the outer diameter of the anti-icing air guide pipe 3 are both circular, so that water chestnuts or edges are prevented from appearing on the inner diameter and the outer diameter of the anti-icing air guide pipe 3, and the safety is improved.

The orientation of each through hole 12 of a plurality of through holes 12 is all different for a plurality of through holes 12 are all outwards gone out on protruding front end 11, and the high temperature high pressure gas that can be more even like this is equallyd divide the water conservancy diversion to fairing 1 surface and is formed the steam rete.

The through holes 12 are circular through holes, which facilitates processing and provides for the flow of gas through the through holes 12.

Claims

1. The fairing structure for the anti-icing of the engine is characterized in that a plurality of through holes (12) are formed in the surface of a convex front end (11) of a fairing (1);

one end of the anti-icing air guide pipe (3) corresponds to the inner surface of the front protruding end (11) of the fairing (1) and is fixedly connected with the inner surface of the air guide pipe (3), the hollow space inside the anti-icing air guide pipe (3) is communicated with the through hole (12), and the other end of the anti-icing air guide pipe (3) extends to the rear end space of the engine fan (2).

2. The fairing structure for engine anti-icing of claim 1, wherein: one end of the anti-icing air guide conduit (3) is correspondingly glued and fixedly connected with the inner surface of the raised front end (11) of the fairing (1).

3. The fairing structure for engine anti-icing of claim 1, wherein: one end of the anti-icing air guide conduit (3) is correspondingly welded and fixedly connected with the inner surface of the raised front end (11) of the fairing (1).

4. The fairing structure for engine anti-icing of claim 1, wherein: the anti-icing air guide conduit (3) is a hard pipe body.

5. The fairing structure for engine anti-icing of claim 4, wherein: the inner diameter of the anti-icing air guide conduit (3) is circular.

6. The fairing structure for engine anti-icing of claim 5, wherein: the inner diameter and the outer diameter of the anti-icing air guide conduit (3) are both circular.

7. The cowling structure for engine anti-icing of claim 1 or 6, wherein: the orientation of each through hole (12) of the through holes (12) is different, so that the through holes (12) are uniformly distributed on the protruding front end (11) and outwards face out, and high-temperature and high-pressure gas is uniformly spread and guided to the surface of the fairing (1) to form a hot gas film layer.

8. The fairing structure for engine anti-icing of claim 7, wherein: the through hole (12) is a circular through hole.