IMPROVED DEVICE FOR SUPPORTING EQUIPMENT ON AN AIRCRAFT TURBOMACHINE HOUSING

Abstract

The invention relates to an aircraft turbomachine assembly (60) comprising a turbomachine casing (28), and equipment (62) fixed to the casing by means of an equipment support device (64a) comprising: - a first support portion (68a) fixed to the casing (28) by means of a first fastening member (69a), the first support portion forming a base of the support device; - a second support portion (80a) fixed to the equipment (62) by means of a second fastening member (81a), the second portion forming a support arm for the equipment; - an intermediate portion (82a) connecting the first and second support portions; the first support portion (68a) taking the form of a support wire having a fastening end (70a) pressed against the casing, and a bent area (72a) extending from the fastening end and bearing against the casing. Figure for the abbreviation: Figure 2

Description

Title of the invention: IMPROVED DEVICE SUPPORT FOR EQUIPMENT ON AN AIRCRAFT TURBOMACHINE HOUSING technical field

[0001] The present invention relates to the field of equipment supports on aircraft turbomachine housings.

[0002] It applies to all types of equipment, and to all types of aircraft turbomachinery, such as turbojets and turboprops. PREVIOUS STATE OF THE ART

[0003] Aircraft turbomachine housings support equipment for this turbomachine, such as fuel supply equipment, heat exchangers, pumps, pipes, etc.

[0004] This equipment is conventionally supported using deformed sheet metal, bosses, or more complex and bulky devices when there is a need to dampen the vibrations of the turbomachine. When greater forces need to be absorbed, solutions using clevises and connecting rods are also implemented.

[0005] On turbomachine housings, the number of equipment is often significant. Therefore, when new equipment needs to be installed in an already dense environment, installation difficulties can arise. These difficulties stem from the size of the equipment itself, but also from the size of its support structures.

[0006] There is therefore a need to optimize these support devices, in order to be able to further increase the number of equipment on aircraft turbomachine housings. Description of the invention

[0007] To meet this need, the invention relates to an aircraft turbomachine assembly comprising a turbomachine casing, as well as equipment fixed to the casing using an equipment support device.

[0008] According to the invention, the equipment support device comprises:

[0009] - a first support portion fixed to the housing by means of a first member of fixing, the first portion of support forming a base of the support device;

[0010] - a second support portion fixed to the equipment using a second component of attachment, the second portion of support forming a support arm for the equipment;

[0011] - an intermediate portion connecting the first and second support portions;

[0012] and the first support portion takes the form of a support wire having a fixing end cooperating with the first fixing member in order to be pressed against the housing, as well as an angled area extending the fixing end, the angled area comprising at least one elbow bearing against the housing.

[0013] The invention is advantageous in that it is based on the use of a support wire to form all or part of the equipment support device. Such a wire has the advantage of being compact and can be positioned, at least partially, between the equipment and the housing, thus facilitating the installation of other adjacent equipment.

[0014] Furthermore, providing an elbow extending the mounting end of the first support portion, and placing it against the housing, simply and effectively prevents rotation of the mounting end, and therefore rotation of the supported equipment. This equipment can thus be supported by a single support device according to the invention, or by a reduced number of such devices.

[0015] The invention is also advantageous in that the use of a support wire gives the device a flexibility that helps to limit the stresses induced on the equipment during assembly. Furthermore, this flexibility is beneficial for damping the vibrations of the turbomachine.

[0016] During assembly and / or design, the support wire can advantageously be plastically deformed as desired, to adapt to surrounding space constraints, to adjust the flexibility of the equipment support arm, etc. The support wire used can indeed be easily deformed to adapt to many different equipment mounting situations.

[0017] The invention preferably provides for at least one of the following optional technical features, taken individually or in combination.

[0018] Preferably, the angled area comprises two elbows, each supported on the housing, the two elbows together having a general S shape. This arrangement further limits the risks of rotation of the fastening end, and therefore contributes to the proper retention of the equipment, in a simple, low mass, and efficient manner.

[0019] Preferably, the second support portion takes the form of a support wire, preferably straight.

[0020] Preferably, the intermediate portion takes the form of a support wire, curved in shape, preferably in the shape of an elbow, a semicircle or a U.

[0021] Preferably, the first and second support portions, as well as the intermediate portion, are formed from a single support wire. The support device is therefore advantageously simple, economical, and lightweight.

[0022] Preferably, at least part of the equipment support device is arranged between the housing and the equipment, along a radial direction of the turbomachine. This arrangement further reduces the overall size and facilitates the installation of other equipment in the immediate vicinity.

[0023] Preferably, the second fastening element is a nut cooperating with a threaded end of the second support portion.

[0024] Preferably, the first fastening element comprises a clamp in the general shape of a U.

[0025] Preferably, the assembly comprises two equipment support devices for fixing said equipment to the housing, the two devices being of different shapes and / or orientations, and of any designs among all those described below, specific to the present invention.

[0026] Finally, the invention relates to an aircraft turbomachine, comprising at least one such assembly, and preferably several assemblies of this type.

[0027] Other advantages and features of the invention will become apparent in the detailed, non-limiting description below. Brief description of the drawings

[0028] The following detailed description refers to the attached drawings on which:

[0029] [Fig.1] is a schematic half view in longitudinal section of an aircraft turbojet engine;

[0030] [Fig.2] is a perspective view of an assembly of the turbojet of the preceding figure, comprising a turbomachine casing and equipment mounted on this casing using equipment support devices, the assembly being in the form of a first preferred embodiment of the invention;

[0031] [Fig.3] is a top view of the assembly shown in the previous figure;

[0032] [Fig.4] is a rear view of the assembly shown in Figures 2 and 3;

[0033] [Fig.5] is a side view of part of one of the two support devices of equipment shown in the previous figures;

[0034] [Fig.6] is a top view of part of the equipment support device shown in the previous figure;

[0035] [Fig.7] is a side view of one part of the other of the two equipment support devices shown in the preceding figures;

[0036] [Fig.8] is a top view of part of the equipment support device shown in the previous figure;

[0037] [Fig.9] is a top view of the assembly similar to that of [Fig.3], with the assembly being presented in the form of a second preferred embodiment of the invention;

[0038] [Fig. 10] is a rear view of the assembly shown in [Fig. 9];

[0039] [Fig. 11] is a perspective view of part of one of the two devices of equipment support shown in Figures 9 and 10; and

[0040] [Fig. 12] is a perspective view of a portion of either of the two equipment support devices, according to an alternative. DETAILED EXPLANATION OF PREFERRED METHODS OF IMPLEMENTATION

[0041] Figure 1 illustrates an aircraft turbojet engine 10, for example a twin-spool, twin-flow type, intended for example for the propulsion of an aircraft capable of supersonic flight. However, the invention applies to other types of aircraft turbomachinery, such as turboprops or turbojets with different architectures.

[0042] In the description, the axial direction X is the direction of the longitudinal axis 11 of the turbojet engine. Unless otherwise specified, the radial direction R is at every point a direction orthogonal to and passing through the longitudinal axis 11, and the circumferential direction C (sometimes called the tangential, azimuthal, or ortho-radial direction) is at every point a direction orthogonal to the radial direction R and to the longitudinal axis 11. The terms "upstream" and "downstream" are defined with reference to a general direction D of the gas flow in the turbojet engine 10, in normal direct thrust configuration.

[0043] By way of illustration, such a turbojet 10 comprises, from upstream to downstream, an air inlet 12, a low pressure compressor 14, a high pressure compressor 16, a combustion chamber 18, a high pressure turbine 20, a low pressure turbine 22, an afterburner 24, and a variable geometry nozzle 26, for example of the convergent-divergent type.

[0044] As is well known, the high-pressure compressor 16, the combustion chamber 18, and the high-pressure turbines 20 and low-pressure turbines 22 define a primary flow PV. This primary flow is surrounded by a secondary flow SV of the turbojet engine. At the outlet of the low-pressure turbine 22 is a turbine rear frame 27, sometimes referred to as the "TRF frame" according to the Anglo-Saxon terminology "Turbine Rear Frame".

[0045] Downstream of the turbine rear casing 27, there is a rear casing 28 surrounding the downstream end of the secondary flow SV and, further downstream, the afterburner channel 24. This rear casing 28 is also called the external afterburner casing, or diffusion casing.

[0046] Furthermore, a confluence ferrule 30, sometimes called a "confluence plate" or simply "confluence", extends downstream in line with the rear turbine casing 27, inside an upstream portion of the rear casing 28 concentrically with the latter, so as to externally delimit the downstream end of the primary flow PV and to internally delimit the downstream end of the secondary vein SV. The secondary vein SV thus extends from upstream to downstream, from an outlet of the low pressure compressor 14 to a downstream edge 32 of the confluence ferrule 30.

[0047] Finally, a diffusion cone 38 extends downstream in line with the rear turbine casing 27, so as to internally delimit the downstream end of the primary PV stream.

[0048] Thus, during operation, air Fl, which entered through the air inlet 12 and was compressed by the low-pressure compressor 14, then splits into a primary flow F2 circulating in the primary stream PV and a secondary flow F3 circulating in the secondary stream SV. The primary flow F2 is then further compressed in the high-pressure compressor 16, then mixed with fuel and ignited in the combustion chamber 18, before undergoing expansion in the high-pressure turbine 20 and then in the low-pressure turbine 22.

[0049] Part of the secondary flow F3, and the combustion gases which constitute the primary flow F2 at the outlet of the low pressure turbine 22, mix within the afterburner channel 24 in a so-called confluence zone, at and beyond the downstream edge 32 of the confluence ferrule 30, and thus constitute an exhaust gas flow F4 which continues its circulation in the afterburner channel 24 and then escapes from the turbojet 10 through the outlet delimited by the nozzle 26.

[0050] In afterburner operation, for example to propel an aircraft to supersonic speeds, fuel is injected into the gas stream within the downstream end of the primary PV stream and / or the afterburner channel 24, and the resulting mixture is ignited within this channel to generate additional thrust. A flame-attachment device 50 is provided for this purpose.

[0051] With reference now to [Fig. 2], an assembly 60 forming an integral part of the turbojet engine described above is shown, comprising the casing 28 and a component 62 fixed to the outer surface of this casing. This component 62 can be of various types, and here it is preferably a component for the afterburner function, for supplying fuel. Of course, the invention applies to other types of components, and it can also relate to other turbojet casings, all those intended to support components, either internally or externally.

[0052] In [Fig.2], the assembly 60 comprises two equipment support devices 64a, 64b, allowing the attachment of the equipment 62 to the radially outer surface of the housing 28. These equipment support devices are specific to the present invention, and a first preferred embodiment of the invention will now be described with reference to Figures 2 to 8.

[0053] Each of the two support devices 64a, 64b has a support wire type design, in that they are essentially based on the use of a deformed wire, having a certain flexibility capable of damping the vibrations of the housing, and facilitating the installation of the equipment 62. The support wire used is thus comparable to a plastically deformed spring wire, preferably made of metallic material or metallic alloy, preferably having a diameter of the order of 2 to 8 mm, depending on the mass of the equipment to be supported, and the load applied to the motor.

[0054] In the first preferred embodiment, a single, continuous wire, plastically deformed so as not to be entirely straight, is used to produce a large part of each equipment support device 64a, 64b. Indeed, for the first equipment support device 64a, a single support wire 66a is used to form the following three continuous portions.

[0055] First, there is a first support portion 68a fixed to the housing 28 by means of a first fastening member 69a. The first support portion 68a forms a base of the support device, being made by a portion of the support wire having a preferably straight fastening end 70a, and cooperating with the first fastening member in order to be pressed against the outer surface of the housing 28. The first support portion 68a also includes a bent section 72a extending from the fastening end 70a, the bent section comprising two successive bends 74a, 76a, each bearing against the outer surface of the housing 28. The two bends have opposite directions, so as to present together a general S shape. The S then continues with another straight section 78a, for example parallel to the fastening end 70a, or substantially parallel to it.Preferably, the fixing end 70a, the two elbows 74a, 76a, as well as the straight section 78a, are crossed by the same imaginary plane, for example parallel to the directions X and C.

[0056] This then consists of a second support portion 80a, fixed to the equipment 62 by means of a second fastening element 81a. This second support portion 80a, also wire-based, forms a support arm for the equipment 62, preferably straight. For this first support device 64a, the support arm 80a extends, for example, parallel to the X direction, or substantially parallel to it.

[0057] The third portion corresponds to an intermediate portion 82a, connecting the first and second support portions 68a, 80a. The corresponding wire portion is curved, here semicircular or U-shaped for the first support device 64a. This intermediate portion 82a is located, for example, in a radial imaginary plane, while the second support portion 80a is arranged radially outwards with respect to the fixing end 70a of the first support portion 68a, for example by being parallel or substantially parallel to this end 70a.

[0058] The first fastening member 69a comprises a clamping collar 84a, generally U-shaped, which presses the fastening end 70a of the first support portion 68a against the outer surface of the housing 28. The collar 84a is tightened using screws or similar elements, for example, screws 86a. Thus, the fastening end 70a is held on the housing by tightening the collar 84a, and rotation of this end about its own axis is cleverly prevented by the contact between the elbows 74a, 76a, and this same outer surface of the housing 28.

[0059] Furthermore, the second fastening member 81a is a nut cooperating with a threaded end of the second support portion 80a. For example, the nut 81a bears against a fastening lug 88a of the equipment 62, this lug being traversed by the threaded end of the second support portion 80a.

[0060] Thanks to this design of the first support device 64a, at least a part of it can be arranged radially between the outer surface of the housing 28 and the supported equipment 62. This reduces the size of the device 64a and facilitates the installation of other adjacent equipment on the housing 28.

[0061] During the assembly of the equipment 62, the wire 66a can be plastically deformed to obtain the desired final shape. Another possibility is to perform this deformation of the spring wire before the assembly of the equipment 62.

[0062] Furthermore, during assembly or design, the flexibility of the support can be easily adjusted by adjusting the length of the support arm, formed by the second support portion 80a. This effectively amounts to adjusting the reach of the first support device 64a.

[0063] The second equipment support device 64b is of identical or similar design to that described for the first device 64a. Moreover, in the figures, the identical or similar elements have the same numerical references, the extension "a" used for the elements of the first device 64a being replaced by the extension "b" for the identical or similar elements of the second device 64b.

[0064] In this first preferred embodiment of the invention, the second support device 64b, although having a design similar to the first device 64a due to the use of the same and unique deformed spring wire 66b, nevertheless has a different shape and / or orientation.

[0065] More precisely, the fixing end 70b can be parallel to the fixing end 70a, but the two bends 74b, 76b are respectively in opposite directions to the bends 74a, 76a of the first device. The two S-shapes, formed by these four bends, thus tend to move closer together, going upstream. Furthermore, in the second device 64b, the intermediate portion 82b takes the form of an elbow, preferably at 90°, thus carrying the second support portion 80b in an orientation parallel to the direction R, or substantially parallel to it.

[0066] The combination of the two support devices 64a, 64b allows for a large number of degrees of freedom of movement. Indeed, translations along the X, R, and C directions are accommodated by the first support device 64a, while rotations along the X and R directions are accommodated by the combination of the two devices 64a, 64b. Rotation along the C direction can, for its part, be accommodated by the interfaces with surrounding parts (not shown), such as other equipment fixed to the housing 28.

[0067] According to a second preferred embodiment shown in Figures 9 to 11, the first support device 64a is identical to that described in the first preferred embodiment, but the second support device 64b differs slightly from that of the first device 64a of the first embodiment. Indeed, the intermediate portion 82b is no longer a simple bend in a fictitious plane parallel to the X and R directions, but a second 90° bend, in a fictitious plane parallel to the R and C directions, brings the support arm 80b into the C direction, or substantially parallel to it.

[0068] The combination of the two support devices 64a, 64b allows for a large number of degrees of freedom of movement. Indeed, translations along the X, R, and C directions are accommodated by the first support device 64a, while rotations along the X and R directions are accommodated by the combination of the two devices 64a, 64b. As in the first preferred embodiment of the invention, rotation along the C direction can be accommodated by the interfaces with surrounding parts (not shown), such as other equipment fixed to the housing 28.

[0069] Finally, [Fig. 12] represents an alternative for the implementation of the equipment support devices 64a, 64b described above. Instead of a single, continuous spring wire, two separate spring wires form the first and second support portions 68a, 68b, 80a, 80b, respectively. The intermediate portion 82a, 82b that connects these two wires is then formed by a flexible sheet metal, for example, crimped at its two opposite ends onto the spring wires. This allows, if necessary, for an even greater increase in the flexibility of the support devices 64a, 64b.

[0070] Various modifications can be made by a person skilled in the art to the invention just described, solely by way of non-limiting examples, and the scope of which is defined by the appended claims. Furthermore, all the features disclosed above, in the various preferred embodiments and their alternatives, are combinable. Moreover, it is noted that on all the figures that have been described above, elements that bear the same numerical references correspond to identical or similar elements.

Claims

Demands

1. Aircraft turbomachine assembly (60) comprising a turbomachine casing (28), and equipment (62) fixed to the casing by means of an equipment support device (64a, 64b), characterized in that the equipment support device comprises: - a first support portion (68a, 68b) fixed to the casing (28) by means of a first fastening member (69a, 69b), the first support portion forming a base of the support device; - a second support portion (80a, 80b) fixed to the equipment (62) by means of a second fastening member (81a, 81b), the second support portion forming a support arm for the equipment; - an intermediate portion (82a, 82b) connecting the first and second support portions;and in that the first support portion (68a, 68b) takes the form of a support wire having a fixing end (70a, 70b) cooperating with the first fixing member (69a, 69b) in order to be pressed against the housing, as well as an angled area (72a, 72b) extending from the fixing end, the angled area comprising at least one elbow (74a, 76a, 74b, 76b) bearing against the housing (28).

2. Assembly according to claim 1, characterized in that the angled area (72a, 72b) comprises two elbows (74a, 76a, 74b, 76b), each supported on the housing (28), the two elbows together having a general S shape.

3. Assembly according to claim 1 or claim 2, characterized in that the second support portion (80a, 80b) takes the form of a support wire, preferably straight.

4. Assembly according to claim 1 or claim 2, characterized in that the intermediate portion (82a, 82b) takes the form of a support wire, curved in shape, preferably in the shape of an elbow, a semicircle or a U.

5. Assembly according to the preceding claim, combined with claims 2 and 3, characterized in that the first and second support portions (68a, 68b, 80a, 80b), as well as the intermediate portion (82a, 82b), are formed by the same and unique support wire (66a, 66b).

6. Assembly according to any one of the preceding claims, characterized in that at least a part of the equipment support device (64a, 64b) is arranged between the housing (28) and the equipment (62), along a radial direction (R) of the turbomachine.

7. Assembly according to any one of the preceding claims, characterized in that the second fastening member (81a, 81b) is a nut cooperating with a threaded end of the second support portion (80a, 80b).

8. Assembly according to any one of the preceding claims, characterized in that the first fastening member (69a, 69b) comprises a clamp generally in the shape of a U.

9. Assembly according to any one of the preceding claims, characterized in that it comprises two equipment support devices (64a, 64b) for fixing said equipment (62) to the housing (28), the two devices being of different shapes and / or orientations.

10. Aircraft turbomachine (10), comprising at least one assembly (60) according to any one of the preceding claims.

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