JP2009203956A - Bracket and liner support structure having the same - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a bracket and a liner support structure having the same, capable of absorbing a thermal expansion difference and vibration between two elements. <P>SOLUTION: The bracket 21 has a displacement absorbing structure part 22 curved in a U shape or a C shape, formed of a plate-like member in the whole, and constituting a part up to a joining part between the bracket 21 and a liner 10 being a second element from a joining part between the bracket 21 and an engine casing 13 being a first element. <P>COPYRIGHT: (C)2009,JPO&INPIT

Description

  The present invention relates to a bracket for fixing a second element to a first element by being arranged between the first element and the second element facing each other and being joined to each of the first element and the second element. More particularly, the present invention relates to a bracket suitable as a part for supporting a liner of an afterburner of an aircraft engine and a liner support structure including the same.

  FIG. 4 is a diagram showing a schematic configuration of a conventional general aircraft engine. In FIG. 4, the aircraft engine 1 includes a fan 2 that rotates to take in air, a compressor 3 that compresses air, a combustor 4 that mixes and burns air and fuel, and a high-temperature gas generated in the combustor 4. The high-pressure turbine 5 and the low-pressure turbine 6 driven by the engine, the mixer 7 that mixes the high-temperature gas (turbine exhaust gas) from the low-pressure turbine 6 and the low-temperature air discharged from the bypass passage 8, and fuel in the turbine exhaust gas And an afterburner 9 that increases engine thrust by reburning (see, for example, Patent Document 1 below).

  The afterburner 9 includes a hollow cylindrical liner 10 supported by an engine casing 13, a fuel sprayer 11 that injects combustion, and a flame holder 12 that forms a vortex flow of the mixed gas. In order to support the liner 10 by the engine casing 13, conventionally, as shown in FIG. 5, a boss 15 having a bolt hole is welded to the outer periphery of the liner 10, and the liner 10 is casing by a bolt 17 through the boss 15. 13 was fixed. In addition, the code | symbol 16 in FIG. 5 shows a welding part.

  In the aircraft engine 1, the engine casing 13 has a relatively low temperature, but the liner 10 of the afterburner 9 exposed to the high-temperature gas has a high temperature, and a difference in thermal expansion occurs due to the temperature difference. Further, vibration due to engine operation is transmitted to the engine casing 13.

Japanese Patent Laying-Open No. 2006-10179 (FIG. 5)

However, the conventional liner support structure using the boss 15 shown in FIG. 5 cannot absorb the difference in thermal expansion between the engine casing 13 and the liner 10 described above because the rigidity of the boss 15 is too high. The vibration from the casing 13 is transmitted to the liner 10 as it is without being absorbed. For this reason, there is a concern that a large stress acts on the welded portion 16 between the liner 10 and the boss 15 to shorten the life of the welded portion 16.
In addition, such a problem is not limited to the support structure of the liner 10, and can also occur when two elements that cause a difference in thermal expansion or one of them vibrates are coupled.

  This invention is made | formed in view of said problem, and makes it a subject to provide the bracket support structure provided with the bracket which can absorb the thermal expansion difference and vibration between two elements, and this.

In order to solve the above-mentioned problems, the following technical means are adopted for the bracket of the present invention and the liner support structure including the bracket.
(1) The present invention is arranged between a first element and a second element facing each other, and is fixed to each of the first element and the second element, thereby fixing the second element to the first element. The bracket is formed of a plate-like member as a whole, and is formed into a U-shape or C that forms a part from the joint portion between the bracket and the first element to the joint portion between the bracket and the second element. It has the displacement absorption structure part curved in character shape, It is characterized by the above-mentioned.

In the bracket of the present invention described above, the entire bracket is formed of a plate-like member, and forms a U-shape or C-shape that forms from the joint portion between the bracket and the first element to the joint portion between the bracket and the second element. Unlike the conventional highly rigid boss, it has a function (flexibility) to expand and contract in the separating direction of the first element and the second element. For this reason, the thermal expansion difference and vibration of the first element and the second element can be absorbed.
In addition, since the displacement absorbing structure portion has a U-shaped or C-shaped curved shape, there is no inflection point in the range from the joint portion between the bracket and the first element to the joint portion between the bracket and the second element. It is bent to. For this reason, the stress is not concentrated on a specific part, and the effect that the stress is dispersed throughout the displacement absorbing structure part is produced, so that the fatigue life of the bracket itself can be extended.

(2) Further, in the bracket described above, the two displacement absorbing structures are provided, and the two displacement absorbing structures are either one of the first element side and the second element side with the concave sides facing each other. The ends are joined together in both.

  According to said structure, since the bracket which integrally provided the two displacement absorption structure parts is comprised, when providing a several bracket between a 1st element and a 2nd element, a number of parts can be reduced.

(3) Further, the present invention is a liner support structure for fixing an afterburner liner in an aircraft engine to an engine casing surrounding the liner, and includes a plurality of brackets according to the above (1) or (2). The plurality of brackets are disposed between the engine casing and the liner at circumferential intervals, and are fixed to each of the engine casing and the liner.

  According to the liner support structure of the present invention, the fatigue life of the liner support structure of the afterburner of an aircraft engine can be extended.

  According to the present invention, the difference in thermal expansion and vibration between the first element and the second element can be absorbed, and the life of the support structure can be extended.

  Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. In addition, the same code | symbol is attached | subjected to the common part in each figure, and the overlapping description is abbreviate | omitted.

  FIG. 1 is a diagram showing a configuration of a bracket 21 and a liner support structure 20 including the bracket 21 according to the first embodiment of the present invention. In the following, an embodiment applied to the liner support structure 20 for an aircraft engine will be described. However, the present invention is not limited to this, and two elements that cause a difference in thermal expansion or one of which vibrates are combined. Can be widely applied to brackets.

In the liner support structure 20 shown in FIG. 1, a bracket 21 is disposed between an engine casing 13 as a first element and a liner 10 as a second element.
The engine casing 13 and the liner 10 are respectively an engine casing 13 and an afterburner liner 10 in an aircraft engine, and the applied aircraft engine is, for example, the aircraft engine 1 shown in FIG. It may be an aircraft engine of the form. In the present embodiment, the plurality of brackets 21 are disposed between the engine casing 13 and the liner 10 at intervals in the circumferential direction.

  In FIG. 1, a bracket 21 is fixed to each of a hollow cylindrical engine casing 13 as a first element and a hollow cylindrical liner 10 as a second element, thereby fixing the liner 10 to the engine casing 13. The whole is formed of a plate-like member. That is, the bracket 21 is a plate-like member.

  As shown in FIG. 1, the bracket 21 has a U shape that forms a part from a joint portion between the bracket 21 and the engine casing 13 as the first element to a joint portion between the bracket 21 and the liner 10 as the second element. Or it has the displacement absorption structure part 22 curved in C shape. The displacement absorbing structure 22 has a function (flexibility) of expanding and contracting in the separating direction between the engine casing 13 as the first element and the liner 10 as the second element. That is, the liner 10 is elastically supported by the bracket 21 with respect to the engine casing 13.

The displacement absorbing structure 22 can appropriately absorb the difference in thermal expansion between the engine casing 13 and the liner 10, can appropriately attenuate the vibration from the engine casing 13, and has a proper rigidity (hardness). The material, size, shape, etc. are preferably set so that 10 can be supported.
In addition, the curved part in the displacement absorption structure part 22 is not restricted to circular arc shape with a constant curvature, The curved shape from which a curvature changes with positions may be sufficient.

  In the present embodiment, the bracket 21 is joined to the engine casing 13 by a bolt 23 and a nut 24. A bolt insertion hole 10 a is formed in the liner 10 so that a bolt can be inserted from the inside of the liner 10. Note that the bracket 21 and the engine casing 13 may be joined by other joining means such as rivets and welding, if possible.

  In the configuration example of FIG. 1, the bracket 21 is joined to the liner 10 by a rivet 25. Note that the bracket 21 and the liner 10 may be joined by other joining means such as bolts, nuts, and welding, if possible.

  In the configuration example of FIG. 1, the bracket 21 includes two displacement absorbing structure portions 22. The two displacement absorbing structure portions 22 are arranged with their concave sides facing each other, and the engine casing 13 as the first element. The ends are joined on the side. In addition, instead of the configuration example of FIG. 1, the two displacement absorbing structure portions 22 may be connected to each other at the liner 10 side, which is the second element, and between the engine casing 13 side and the liner 10 side. Both ends may be connected to each other. Further, the bracket 21 may be entirely circular or a circular shape close thereto, or an elliptical shape or an elliptical shape close thereto.

  Next, the operation and effect of this embodiment will be described.

  According to the present embodiment, the entire bracket 21 is formed by a plate-like member, and the joint between the bracket 21 and the liner 10 as the second element is joined from the joint portion between the bracket 21 and the engine casing 13 as the first element. Unlike the conventional rigid boss 15 shown in FIG. 4, the engine casing 13 that is the first element and the liner that is the second element are provided. 10 has a function (flexibility) of expanding and contracting in the separating direction. For this reason, the difference in thermal expansion and vibration between the engine casing 13 as the first element and the liner 10 as the second element can be absorbed. Moreover, the fatigue life of the liner support structure 20 can be extended by applying to the liner support structure 20 of the afterburner of an aircraft engine like this embodiment.

  Here, as in the reference example shown in FIG. 3, for example, the portions that form the joint portion on the engine casing 13 side to the joint portion on the liner 10 side have straight portions 30 a to 30 c and a relatively small radius of curvature. A trapezoidal shaped bracket 30 composed of the curved portions 30d and 30e is also conceivable. However, in such a configuration, when a load is applied to the bracket 30, stress concentrates on the curved portions 30 d and 30 e having a small radius of curvature, which is a factor that greatly reduces the fatigue life of the bracket 30. On the other hand, according to the present embodiment shown in FIG. 1, the displacement absorbing structure portion 22 has a U-shaped or C-shaped shape, so that the joint portion between the bracket 21 and the engine casing 13 as the first element. In the range of the joint portion between the bracket 21 and the liner 10 as the second element, it is smoothly bent without an inflection point. For this reason, since stress does not concentrate on a certain specific part and the effect that stress is disperse | distributed to the whole displacement absorption structure part 22 arises, the fatigue life of bracket 21 itself can be lengthened.

  According to the configuration of the present embodiment, since the bracket 21 integrally including the two displacement absorbing structure portions 22 is configured, a plurality of brackets 21 are provided between the engine casing 13 and the liner 10 as in the present embodiment. The number of parts can be reduced even when providing.

FIG. 2 is a diagram showing a configuration of the bracket 21 and the liner support structure 20 including the bracket 21 according to the second embodiment of the present invention.
Unlike the first embodiment described above, in this embodiment, one bracket 21 has one displacement absorbing structure 22. About another structure and its modification, it is the same as that of 1st Embodiment.

  Also with the configuration of the present embodiment, the displacement absorbing structure 22 can absorb the difference in thermal expansion and vibration between the engine casing 13 as the first element and the liner 10 as the second element. Moreover, the fatigue life of the liner support structure 20 can be extended by applying to the liner support structure 20 of the afterburner of an aircraft engine like this embodiment.

  Although the embodiments of the present invention have been described above, the embodiments of the present invention disclosed above are merely examples, and the scope of the present invention is not limited to these embodiments. . The scope of the present invention is indicated by the description of the scope of claims, and further includes meanings equivalent to the description of the scope of claims and all modifications within the scope.

It is a figure which shows the structure of this bracket of 1st Embodiment of this invention, and a liner support structure provided with the same. It is a figure which shows the structure of this bracket of 2nd Embodiment of this invention, and a liner support structure provided with the same. It is a figure which shows the structure of the liner support structure of a reference example. It is a figure which shows schematic structure of the conventional common aircraft engine. It is a figure which shows the conventional liner support structure.

Explanation of symbols

10 Liner (second element)
10a Bolt insertion hole 13 Engine casing (first element)
20 Liner support structure 21 Bracket 22 Displacement absorption structure 23 Bolt 24 Nut 25 Rivet

Claims (3)

A bracket for fixing the second element to the first element by being arranged between the first element and the second element facing each other and being fixed to each of the first element and the second element,
The bracket is entirely formed of a plate-shaped member,
A bracket having a displacement absorption structure curved in a U shape or a C shape constituting a portion from a joint portion between the bracket and the first element to a joint portion between the bracket and the second element.   Two displacement absorbing structures are provided, and the two displacement absorbing structures are joined to each other at one or both of the first element side and the second element side with the concave sides facing each other. The bracket according to claim 1. A liner support structure for fixing an afterburner liner in an aircraft engine to an engine casing surrounding the liner.
A plurality of brackets according to claim 1 or 2,
The plurality of brackets are disposed between the engine casing and the liner at a circumferential interval, and are fixed to each of the engine casing and the liner.

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