CN214533238U - Anti-icing subassembly of intake duct - Google Patents

Abstract

An object of the utility model is to provide an anti-icing subassembly of intake duct, it can avoid anti-icing steam backward flow to lead to the thermal radiation to the outer pipe, and then has avoided the destruction to anti-icing structure. The anti-icing component of the air inlet channel comprises a flute-shaped pipe and an air entraining pipe connected with the flute-shaped pipe, wherein the air entraining pipe comprises an outer layer protection pipe and an inner layer air entraining pipe, and further comprises a sealing ring, and the longitudinal section of the sealing ring is corrugated; and the inner peripheral side of one end of the air entraining pipe, which is close to the flute-shaped pipe, is in sealing connection with the inner layer air entraining pipe, and the outer peripheral side of the air entraining pipe is in sealing connection with the outer layer protection pipe.

Description

Anti-icing subassembly of intake duct

Technical Field

The utility model relates to an aircraft engine's anti-icing subassembly of intake duct.

Background

Icing of the aircraft engine inlet lip reduces the engine air intake, which can lose a portion of the engine thrust. Meanwhile, ice blocks are gathered to destroy the flow field profile of the air inlet channel of the engine, and the aerodynamic resistance is increased. When ice accumulates to some extent, engine surge may be caused. More seriously, ice that falls off the inlet lip may also be drawn into the engine and strike the damaged fan blades, causing mechanical damage. Therefore, an engine intake is usually designed with an anti-icing system to protect the ice formation area of the lip of the intake from ice.

For an active aircraft engine, the deicing mode of the lip of the air inlet channel is the hot air deicing of the lip of the engine. The hot air deicing mainly has two forms of a flute pipe and a direct injection type. Flute tube configurations are a more common form of anti-icing in hot gas anti-icing. Compared with the structural configuration of direct injection type hot air deicing, the flute-shaped pipe hot air deicing mode adopts point-to-point hot air jet flow in 360-degree annular direction of the lip mouth and in the icing area, so that the efficiency is higher, the requirement on the air entraining amount of an engine is lower, and the traditional machine type adopts the flute-shaped pipe hot air deicing mode in a large amount. However, according to the inventor's experience, there is at least one of the following problems with the flute tube hot gas deicing:

the hot gas backflow exists between the double-layer pipes of the flute-shaped pipe anti-icing structure, and the heat radiation is aggravated to easily damage the surrounding structure or cause the weight increase of the structure when extra protection is carried out.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an anti-icing subassembly of intake duct, it can avoid anti-icing steam backward flow to lead to the thermal radiation to the outer pipe, and then has avoided the destruction to anti-icing structure.

The anti-icing component of the air inlet channel comprises a flute-shaped pipe and an air entraining pipe connected with the flute-shaped pipe, wherein the air entraining pipe comprises an outer layer protection pipe and an inner layer air entraining pipe, and further comprises a sealing ring, and the longitudinal section of the sealing ring is corrugated; and the inner peripheral side of one end of the air entraining pipe, which is close to the flute-shaped pipe, is in sealing connection with the inner layer air entraining pipe, and the outer peripheral side of the air entraining pipe is in sealing connection with the outer layer protection pipe.

In one embodiment, the sealing ring is tapered, and the large end is connected with the outer protection tube in a sealing way, and the small end is connected with the inner bleed air tube in a sealing way.

In one embodiment, the partial section of the inner layer bleed air duct is a bellows.

In one embodiment, the outer protection tube comprises a protection tube front section for fixed mounting on the front partition and a protection tube rear section for fixed mounting on the rear partition, the protection tube front section and the protection tube rear section being axially movably fitted.

In one embodiment, the front section and the rear section of the protection tube comprise an annular matching surface on one side, a plurality of annular convex ribs which are matched with the annular matching surface in a sealing mode on the other side, and an annular groove which is used for spacing the plurality of annular convex ribs.

In an embodiment, the inner layer gas guide pipe comprises a front end gas guide pipe close to the flute-shaped pipe and a rear end gas guide pipe connected with the front end gas guide pipe, one of the rear end of the front end gas guide pipe and the front end of the rear end gas guide pipe is provided with a clamping male head, the other is provided with a clamping female head, the clamping male head and the clamping female head are fixedly connected through an outer hoop, and a clamping groove sealing ring is arranged between the clamping male head and the clamping female head.

In an embodiment, this inlet duct anti-icing subassembly still includes the fixed bolster, the fixed bolster includes the cantilever, the one end of cantilever is used for fixing on preceding baffle, and the other end is used for supporting this flute venturi tube, the cantilever is the flexible construction that has damping characteristic.

In one embodiment, the cantilever is undulating.

In one embodiment, the inlet duct anti-icing assembly further comprises a clamp and a shock pad, and the flute-shaped pipe is fixed on the cantilever by the clamp and spaced from the cantilever by the shock pad.

In an embodiment, the clamp includes outer clamp and interior clamp, interior clamp is the arch and is fixed in on this cantilever to provide this flute venturi tube of arc supporting part contact, this outer clamp encircles this flute venturi tube and superposes and is fixed in this cantilever with the both ends of this interior clamp again.

Corrugated sealing ring can be sealed with outer protection tube anti-icing steam, avoids the steam backward flow after the anti-icing uses to outer protection tube secondary heating, has avoided near structure that heat load heat radiation aggravation can damage, and it is scalable to utilize the corrugated geometric characteristics of sealing ring to realize the axial simultaneously to the displacement that compensation pipeline thermal energy produced reduces the tensile load of bleed pipe fixed department, improves anti-icing pipeline life.

Drawings

The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:

FIG. 1 is a schematic illustration of an inlet anti-icing assembly applied to an engine inlet.

FIG. 2 is a schematic view of an inlet anti-icing assembly.

Fig. 3 is a schematic illustration of the support of the flute tubes by the fixed support.

Fig. 4 is a schematic view of a clamp securing a flute tube to a cantilever.

Figure 5 is a schematic view of the bleed air duct mounted to the front and rear bulkheads.

Fig. 6 is a partial view of the left-hand portion of fig. 5.

Detailed Description

The present invention will be further described with reference to the following embodiments and drawings, and more details will be set forth in the following description in order to provide a thorough understanding of the present invention, but it is obvious that the present invention can be implemented in various other ways different from those described herein, and those skilled in the art can make similar generalizations and deductions according to the actual application without departing from the spirit of the present invention, and therefore, the scope of the present invention should not be limited by the contents of the embodiments.

It should be noted that these and other figures are given by way of example only and are not drawn to scale, and should not be construed as limiting the scope of the invention as it is actually claimed.

Fig. 1 shows the structure of hot gas deicing of an air inlet and a flute-shaped pipe. Wherein, air inlet anti-icing subassembly includes air inlet anti-icing subassembly 20, and air inlet anti-icing subassembly 20 includes flute venturi tube 21 and connects this flute venturi tube 21's bleed pipe 25. The air bleed pipe 25 of the air inlet anti-icing assembly 20 is positioned on the front partition plate 13 and the rear partition plate 15 of the air inlet 10, and the flute-shaped pipe 21 is fixed on the front partition plate 13 through a bracket. When a valve connected with the air guide pipe 25 is opened, hot air of an engine is guided into the air guide pipe 25, and the front edge of the lip skin 11 is heated by the hot air jetted by the flute-shaped pipe 21, so that the deicing effect is realized.

FIG. 2 illustrates the structure of an inlet anti-icing assembly. The air inlet anti-icing assembly 20 mainly comprises an anti-icing air guide pipe 25 and a flute-shaped pipe 21, wherein the flute-shaped pipe 21 is connected to the front partition plate 13 through a fixing support 234. The fixed support 23 is a flexible cantilever structure, has a certain displacement deformability, and is used for playing a role in damping and vibration reduction when the flute pipe vibrates. The number of the fixed brackets 23 is determined according to the vibration frequency of the engine and the natural frequency relation and the strength and rigidity deformation of the flute-shaped pipe, and in a typical embodiment, 8 fixed brackets 234 which are not uniformly arranged are adopted.

Fig. 3 shows a structure in which the flute-shaped pipe 21 is supported by a fixing bracket 234. The flute-shaped pipe 21 is connected to the front partition plate 13 of the air inlet 10 through a clamping hoop 23 and a fixing bracket 234. The fixed bracket 234 is generally a flexible structure having damping properties, and in one implementation, has a flexible structure 234b, i.e., the non-mechanical connection region of the fixed bracket 234 is a planar structure. In another embodiment, the fixing bracket 234 is a flexible structure 234a with a sinusoidal corrugated arc feature, which improves the rigidity of the fixing bracket 234 itself, and also has a flexible deformation to compensate the thermal expansion deformation displacement of the flute-shaped tube 21, reduce the internal stress level of the fixing bracket 234, and improve the fatigue life of the supporting structure of the anti-icing system 20.

FIG. 4 is an enlarged view of a portion of the flute tube and clamp connection. The clamp 23 for holding the flute tube 21 includes an outer clamp 231, an inner clamp 232, and a damping pad 233 also participates in holding the flute tube 21. The damping pad 233 has both high temperature and wear resistant properties. The inner band 232 is arcuately fixed to a fixed bracket 234 and provides an arcuate support portion for contacting the flute tube 21, and the outer band 231 surrounds the flute tube 21, for example, around at least half of a circumference, overlaps both ends of the inner band 232 and is fixed to the fixed bracket 234. The inner band 232 is provided in an arch shape so that the inner band 232 can also be constructed as a flexible structure having damping characteristics and compensate for thermal expansion deformation displacement of the flute tube 21 together with the damper pad 233.

Figure 5 shows a section of an anti-icing bleed duct structure. The bleed air duct 25 is fixedly connected, e.g. bolted, to the front 13 and rear 15 bulkheads via front and rear mounting flanges. The bleed air duct 25 comprises an outer protective tube 260 and an inner bleed air duct 250. Inner layer bleed air ducts 250 include a forward end bleed air duct 254 and a rearward end bleed air duct 255. The rear end of the front bleed conduit 254 adjacent the front bulkhead 13 is fixedly connected to the front end of the rear bleed conduit 255 by a removable outer clip 256. The inner layer bleed air ducts 250 are each provided with a bellows 257 near the front bulkhead 13 and the rear bulkhead 15, for example, with a bellows 257 provided at each of two locations of the rear bleed air duct 255. When the anti-icing system works, the air guide pipe thermally expands to compensate the axial extension displacement of the inner air guide pipe 250; similarly, when the aircraft engine is outside at-55 ℃ in an economical cruise condition, the bleed air duct 250 axially shortens the displacement compensation, thereby reducing the structural internal stress and increasing the thermal fatigue life of the inner bleed air duct structure 25.

Figure 6 shows part of the forward end of the anti-icing bleed air duct. The anti-icing bleed air duct 25 is sealed at the front bulkhead 13 by a sealing ring 261, the sealing ring 261 being corrugated, preferably of a high temperature alloy, as seen in longitudinal section in fig. 6, the front bulkhead 13 sealing the large opening 130 provided for the bleed air duct 250. The support ring 251 is welded to the outer periphery of the front end bleed air pipe 254, the seal ring 261 is welded to the outer periphery of the support ring 251 on the inner peripheral side thereof, the outer peripheral side of the seal ring 261 and the front flange 265 of the outer layer pipe 260 are bolted to the front bulkhead 13, and other methods than welding or bolting may be used for sealing. After the front-end air-entraining pipe 254 is welded with the female joint 252 in a combined manner, the male joint 253 is fixedly connected with a combined welding part of the corrugated pipe 257 through an outer clamp 256 and can be detached, and a clamp groove sealing ring 255 is arranged between the male joint 252 and the female joint 253.

When the anti-icing valve is opened and is in a working state, the flute-shaped pipe 21 moves forwards integrally along the axial direction of the engine due to thermal expansion, namely, is close to the inner wall of the lip skin 11, and simultaneously expands outwards integrally along the direction vertical to the engine, namely, expands and deforms along the outer skin 14 close to the air inlet 10 and the outer side of the lip skin 11 on one side of the connection area of the front clapboard 13. The inner bleed air tube 250 passes through the front partition 13, and takes into account the solid envelope area of the thermal expansion position offset in all possible ranges, where the structure of the inner bleed air tube cannot be hard-wired by using the conventional structural method, and further cannot achieve the air sealing of the hot air in the labial cavity (referred to as "D-duck cavity" in the industry) with the lumen of the bleed air tube 25 at the large opening 130 of the front partition 13. Conventionally, the inner layer bleed air ducts 250 are not constrained from offsetting near the large opening 130 of the front bulkhead 13, thereby avoiding the risk of premature failure of the front bulkhead 13 due to increased bulkhead in-plane stress caused by the connection of the bleed air ducts 25 to the front bulkhead 13. However, the obvious disadvantage of this solution is that the bleed air pipes 25 communicate with the D-Duct chamber at the opening of the front bulkhead 13, and the hot air backflow aggravates the thermal radiation load of the outer pipe 260, so that the air inlet Duct 10, which is usually made of composite material, requires an additional thermal blanket to be added to the outer skin 14 and the inner wall plate 16, resulting in a weight increase of the whole structure. The air-entraining pipe 25 shown in fig. 6 is provided with a sealing ring 261 at the opening of the front partition 13, and plays a role in sealing the cavity enclosed by the inner air-entraining pipe 250 and the outer pipe 260 from the D-Duct cavity and protecting the composite material outer skin 14 and the inner wall plate 16. It is preferable to make the sealing ring 261 have a tapered bellows shape as a whole, to further enhance the axial scalability of the sealing ring 261.

Adopt sealing ring 261 to seal to outer layer protection tube 260 and D-Duct chamber, avoid the steam backward flow after the anti-icing use to outer layer protection tube 260 secondary heating, avoid the thermal radiation aggravation of thermal load to damage near structure, it is scalable to utilize corrugate geometric characteristics to realize the axial simultaneously to the displacement that compensation pipeline thermal energy produced reduces the tensile load of bleed pipe fixed department, improves anti-icing pipeline life.

The bleed pipe 25 is for preventing the booster to destroy, installs outer protection tube 260 additional and protects structure on every side, and simultaneously, inlayer bleed pipe 250, outer protection tube 260 adopt the deformation compensation design respectively, reduce with around the baffle junction warp the fatigue stress corrosion problem that brings, avoid the condition that the joining region destroys in advance. For example, the inner layer bleed air tube 250 includes at least one length of bellows 257 therein. Fig. 6 also shows the deformation compensation design of the outer protection tube 260, the outer protection tube 260 includes a protection tube front end 261 and a protection tube rear end 262, the protection tube front end 261 is used for fixed mounting on the front partition plate 13, the protection tube rear end 262 is used for fixed mounting on the rear partition plate 15, the protection tube front end 261 and the protection tube rear end 262 can be axially movably matched, fig. 6 shows a specific matching mode, the outer peripheral surface of the protection tube front end 261 is provided with an annular convex rib 263, the annular grooves 264 are separated by 3 annular convex ribs, the inner peripheral surface corresponding to the protection tube rear end 262 is in sealing fit with the annular convex rib 263, the annular convex rib is contacted with the annular matching surface, a matching structure with better sealing performance can be provided, and the axial displacement deformation is allowed, so as to compensate the expansion caused by thermal load radiation. And, the inlayer bleed pipe is relatively independent with outer protection tube, only has detachable bolted connection and sliding connection, easy to assemble and dismantles and maintain.

Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent changes and modifications made to the above embodiments according to the technical spirit of the present invention, all without departing from the content of the technical solution of the present invention, fall within the scope of protection defined by the claims of the present invention.

Claims (10)

1. The anti-icing component of the air inlet comprises a flute-shaped pipe and an air-entraining pipe connected with the flute-shaped pipe, wherein the air-entraining pipe comprises an outer layer protection pipe and an inner layer air-entraining pipe;

and the inner peripheral side of one end of the air entraining pipe, which is close to the flute-shaped pipe, is in sealing connection with the inner layer air entraining pipe, and the outer peripheral side of the air entraining pipe is in sealing connection with the outer layer protection pipe.

2. The inlet ice protection assembly of claim 1, wherein the sealing ring is tapered, with a larger end sealingly connected to the outer protective tube and a smaller end sealingly connected to the inner bleed air tube.

3. The inlet anti-icing assembly of claim 1 wherein a section of said inner layer bleed air duct is a bellows.

4. The inlet duct anti-icing assembly of claim 1, wherein the outer protection tube comprises a protection tube front section and a protection tube rear section, the protection tube front section is fixedly mounted on the front partition plate, the protection tube rear section is fixedly mounted on the rear partition plate, and the protection tube front section and the protection tube rear section are axially movably engaged.

5. The inlet duct anti-icing assembly of claim 4, wherein the front section of the protection tube and the rear section of the protection tube include annular mating surfaces at the mating locations, and a plurality of annular ribs and annular grooves at the mating locations, wherein the annular mating surfaces are in sealing engagement with each other.

6. The air inlet anti-icing assembly according to claim 1 or 3, wherein the inner layer bleed air pipe comprises a front bleed air pipe close to the flute-shaped pipe and a rear bleed air pipe connected with the front bleed air pipe, one of the rear end of the front bleed air pipe and the front end of the rear bleed air pipe is provided with a clamping male head, the other is provided with a clamping female head, the clamping male head and the clamping female head are fixedly connected through an outer clamping hoop, and a clamping groove sealing ring is arranged between the clamping male head and the clamping female head.

7. The inlet duct anti-icing assembly of claim 1, further comprising a fixed bracket, wherein the fixed bracket comprises a cantilever, one end of the cantilever is used for being fixed on the front partition plate, the other end of the cantilever is used for supporting the flute-shaped pipe, and the cantilever is a flexible structure with damping characteristics.

8. The inlet scoop anti-icing assembly of claim 7, wherein said cantilever arm is undulating.

9. The inlet duct anti-icing assembly of claim 7, further comprising a clamp and a shock pad, wherein the flute tube is secured to the boom by the clamp and spaced from the boom by the shock pad.

10. The inlet duct anti-icing assembly of claim 9, wherein the clamp includes an outer clamp and an inner clamp, the inner clamp being arcuately secured to the boom and providing an arcuate support portion contacting the flute tube, the outer clamp surrounding the flute tube and overlying and secured to the boom at opposite ends of the inner clamp.

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