Spring for shield of netlike thrust reverse of aircraft turbojet engine

FIELD: machine building.

SUBSTANCE: leaf spring (17) has two branches (19, 21) that form U-shaped part. The ends (19a, 19b, 21a, 21b) of these branches are made with the possibility of interaction with reverse shield and actuating rod (15) of this shield correspondingly.

EFFECT: reduction of spring mass.

10 cl, 4 dwg

 

The invention relates to a spring for flap lattice of reverse thrust turbojet engine aircraft.

Specialists in this field it is known that lattice reverse thrust turbojet engine aircraft is equipped with, as a rule, near plates rigidly connected with a sliding hood of this reverse, which interact with special rods connected with a fixed internal structure of the thrust reverser.

When the reverse thrust mode direct thrust, flaps are held by the rods on the continuation of the inner wall of the sliding hood.

When he works in the reverse thrust mode, the flaps using the rods are driven, with the result that they block the chamber circulation secondary air flow turbojet engine, thereby rejecting this thread in the forward direction, which allows the reverse thrust and, hence, the braking of an aircraft having such reverse.

It is also known that between rods and plates put the spring in order to compensate for deviations from tolerances and deformation of the structure when the panels are in position corresponding to the mode of direct thrust in one of the bars at the same time creates the possibility of providing sufficient pressure on these plates at the specified position.

On who's day is known for different types of springs - screw or plate.

The purpose of the invention is in the development of the spring, which would be easier than that used in known systems.

To achieve this goal the proposed plate spring for the flap of reverse thrust, characterized in that it has two branches, forming a U-shaped piece, and the ends of these branches are made interoperable, respectively, with the flap of the specified reverse and drive rod of the flap.

Due to this special form, the ends of the considered spring less prone to bending moments or not exposed to any bending loads, which allows you to work with a spring, which when given the mass demonstrates the best elastic properties.

According to other optional characteristics of this spring,

- these all are essentially opposite to each other;

thanks to this special location, you can access both branches of the U-shaped parts along their entire length and, consequently, an even greater improvement in the elastic properties of the spring at a given mass;

at least one of these branches has two forked parts;

- branch specified spring made interoperable with the specified rod has a cross section decreasing in the direction from neither is as specified U-shaped details to the end of this branch; since the bending moment, which is undergoing this branch, decreases in the direction from its end to the bottom of the U-shaped parts, it is obvious that in practice there is no need to perform this branch with the same cross-section along the entire length, so that in the result it is possible to reduce the weight of the spring;

- branch specified spring made interoperable with the above post, has on its end bends, forming a support platform for the specified rod; such bends formed in the body of the spring, allow to avoid the use of additional parts as reference sites and thereby reduce the weight of the structure;

- branch specified spring made interoperable with the specified plate has on its end mounting flat areas;

this spring is at least partially made of an alloy based on titanium; this allows for weight reduction;

this spring is at least partially made of a composite material;

this is achieved weight reduction.

The invention also covers lattice thrust reversal, characterized in that it has at least one spring of the type described above.

The subject of the invention is also a nacelle for a turbojet engine, characterized in that it is provided with reverse tahitia described above.

Other characteristics and advantages of the invention made it clear from the following description given with reference to the attached drawings, where:

figure 1 is a view in side section of the grid thrust reverser equipped with at least one spring according to the invention, where the specified reverse is shown in the position corresponding to the mode of direct thrust;

figure 2 is a view similar to that shown in figure 1, where the reverse is shown in the position corresponding to the reverse thrust mode;

figure 3 is a view in the perspective view of area III of figure 2;

figure 4 - illustration of this zone III in the form similar to that shown in figure 1 and 2.

As can be seen in figure 1, there is a lattice thrust reverser equipped, as in all traditional systems, the engine 1, which is slidable relative to some fixed structure including a fixed front frame 3 and the fixed internal structure 5.

As in all known systems, sliding between the engine and the fixed internal structure 5 is formed a circular path 7 of a cold air stream.

In the normal mode, that is in flight, the cold air circulates inside the specified path 7, as shown in figure 1 by the arrow 9, that is, along the inner wall of the hood 1 and the fixed internal structure 5.

In this operating mode, the flux is specified cold air 9 is formed with a stream of hot air, coming out of the turbojet engine (not shown), thereby creating thrust of the aircraft (not shown).

During reverse thrust, as shown in figure 2, the sliding engine 1 is shifted under the influence of any type actuator hydraulic power cylinder 11 toward the rear part of the turbojet engine, i.e. to the right in figure 2.

The consequence of this slide is the overlap of the ring highway 7 near distributed throughout its volume plates 13 (figures 1 and 2 seen just one of these shields) and redirect the flow of fresh air towards the front of the gondola (arrow 9' in figure 2).

Each of the plates 13 pivotally mounted on the sliding doors 1, with its movement from the position shown in figure 1, in which it is a continuation of the inner wall of the sliding doors 1, in the position of the overlap shown in figure 2, in which it is located across highway 7 cold air is achieved through the operation rod 15, the ends of which are made with the possibility of rotation, respectively, on the stationary inner structure 5 and the flap 13.

Specifically (this can be seen, however, in figure 3 and 4), the rod 15 communicates with the plate 13 by means of the spring 17.

This spring is made in the form of a U-shaped parts, that is, has two branches 19, 21, connected the other curved section 23.

Each of these two branches is, in fact, a forked end, that is consisting of two parts, respectively, 19a, 19b and 21A, 21b.

Parts 21A, 21b branch 21 is fixed by their respective ends to the plate 13 by means of special tools type rivets 23a, 23b.

In a preferred embodiment, as seen in figure 3 and 4, each part 21A, 21b branch 21 has on its end a corresponding flat section 25A, 25b, forming a small angle with the rest of this branch.

It is preferable that two parts 19a, 19b branch 19 was shaped, pointed in the direction from the curved section 23 of the spring to the end of this branch 19.

At the end of each of these parts 19a, 19b formed bend 27b, made in one piece with the rest of the spring 17 and forming a support platform for end 29 of the rod 15.

For this purpose provided by the axis 31 passing between the two bends 27A, 27b through the end 29 of the rod 15, and this axis can be maintained with the help of pins 33.

As more clearly seen in figure 4, the ends of the branches 19 and 21 that communicates with the rod 15 and the plate 13 are preferably opposite each other, i.e. essentially in the plane P containing the specified ends and perpendicular to the flap 13.

It is advisable that the spring 17 was at least partially made of titanium alloy and/or any compositng the material.

As can be seen from the table below, only the good characteristics of the spring can be obtained, in particular, when using a titanium alloy type TV866 or composite materials such as glass epoxy or carbon-epoxy UD (unidirectional) tissue.

In this table the letter Δ indicated allowable fatigue stress of the material, the letter E is the modulus of elasticity of the material, the Energy is equal to Δ2/E, the Density corresponds to the density of the material, and "Efficiency" is the ratio of Energy Density.

Spring steelTitanium alloy TAD4ETitanium alloy TV866The aluminum. alloy A28GVGlass epoxy UD fabricKevlar-epoxy UD fabricCarbon-epoxy UD fabric
Δ (MPa)1200120014005008005001100
E (MPa)205000116000 10600070000450008500013000
Energy7,0212,418,53,5714,222,94of 9.30
Density84,54,52,722,51,61,8
Efficiency0,92,84,11,3the 5.71,85,2

The above spring can compensate for deviations from tolerances and deformation of the structure when the flap 13 is in the position corresponding to the mode of direct thrust, shown in figure 1, where it should remain within the volume of a given size, limited, on the one hand, sliding the engine 1 and, on the other hand, the front frame 3.

In addition to providing such compensation of deviations from tolerances, pru is in 17 allows the rod 15 to provide sufficient pressure on the flap 13 to hold it in position, shown in figure 1.

As mentioned earlier, due to the U-shaped springs, the location of its two branches opposite each other, tapering cross-sections of these branches and the appropriate choice of material for manufacture of the springs is possible to achieve a very effective compromise between performance and weight, which in this design is significantly reduced.

As an example, you can specify that when using such springs can achieve savings in 150 g compared with springs, known from the prior art.

Given that in lattice reverse thrust is used about a dozen of these springs, the total gain in weight can be up to 1800 grams for each reverse.

But, as is known to all specialists of aircraft, each additional gram weight costs $ 1 extra expenses.

This case achieved through the proposed spring gain in weight can be estimated at us $ 1,800 on each thrust reverser.

If we assume that the spring is made of titanium, which is somewhat more expensive than the traditionally used materials, the win will come down to about $ 1,500 on the reverse.

Of course, the invention is in no way limited to the above described and illustrated in the drawings, the var is the ant implementation which was given only as an example.

1. The plate spring (17) for the flap (13) of reverse thrust, characterized in that it has two branches (19, 21), forming a U-shaped piece, and the ends (19a, 19b, 21A, 21b) of these branches are made interoperable, respectively, with the flap (13) of the specified reverse and drive rod (15) of this flap.

2. The plate spring (17) according to claim 1, characterized in that the ends (19a, 19b, 21A, 21b) are located essentially opposite each other.

3. The plate spring (17) according to any one of claims 1 and 2, characterized in that at least one of these branches (19, 21) has two forked portions (19a, 19b, 21a, 21b).

4. The plate spring (17) according to any one of claims 1 and 2, characterized in that the branch (19) of the said springs are made with the possibility of interaction with the specified rod (15)has a cross section decreasing in the direction from the Foundation of the specified U-shaped details to the end of this branch.

5. The plate spring (17) according to any one of claims 1 and 2, characterized in that the branch (19) of the said springs are made with the possibility of interaction with the specified rod (15)has at its end bends (27A, 27b), forming a support for the specified rod (15).

6. The plate spring (17) according to any one of claims 1 and 2, characterized in that the branch specified spring made interoperable with the specified plate has on its end mounting flat areas.

7. The plate spring (17) according to any one of claims 1 and 2, characterized in that it at least partially made of an alloy based on titanium.

8. The plate spring (17) according to any one of claims 1 and 2, characterized in that it at least partially made of a composite material.

9. Lattice thrust reversal, characterized in that it has at least one plate spring (17), performed according to any one of the preceding paragraphs.

10. Nacelle for a turbojet engine, characterized in that it is equipped with a thrust reverser according to claim 9.



 

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