Turbine engine comprising means for supporting at least one item of equipment

Abstract

Turbine engine, comprising means for absorbing the thrust forces from its engine, which comprise longitudinal connecting rods, the ends of which are connected to structural annular casings of the turbine engine, characterized in that it comprises means for supporting at least one item of equipment on said thrust-absorbing connecting rods and/or for suspending at least one item of equipment from said thrust-absorbing connecting rods.

Claims

1. A turbine engine, comprising: a system for suspending a downstream end of the turbine engine to an aircraft strut, said system absorbing thrust forces and comprising two longitudinal thrust-absorbing connecting rods, upstream ends of the thrust-absorbing connecting rods being connected to an upstream structural annular casing of the turbine engine, and downstream ends of the thrust-absorbing connecting rods being connected to a downstream structural annular casing of the turbine engine, wherein a support is fixed on the two longitudinal thrust-absorbing connecting rods and extends substantially therebetween, the support carrying or supporting at least one item of equipment which is fixed to or suspended from said thrust-absorbing connecting rods.

2. The turbine engine according to claim 1, wherein the support comprises a support plate substantially coplanar with the thrust-absorbing connecting rods.

3. The turbine engine according to claim 2, wherein the support plate is fixed on the connecting rods by clamping collars or bolted connections.

4. The turbine engine according to claim 2, wherein the support plate carries at least two items of equipment.

5. The turbine engine according to claim 1, wherein the thrust-absorbing connecting rods present an angle therebetween.

6. The turbine engine according to claim 1, wherein the connecting rods have a circular, square or rectangular cross section.

7. The turbine engine according to claim 1, wherein the upstream ends of the thrust-absorbing connecting rods are connected to the upstream structural annular casing of the turbine engine which includes a hub of an intermediate casing, and the downstream ends of the thrust-absorbing connecting rods are connected to the downstream structural annular casing of the turbine engine which includes a downstream suspension connected to a ring mounted around an inter-turbine casing.

8. The turbine engine according to claim 2, wherein the item of equipment passes through the support plate.

9. The turbine engine according to claim 2, wherein sides of the support plate abut the connecting rods.

10. The turbine engine according to claim 2, wherein the support plate is trapezoidal in shape.

11. The turbine engine according to claim 2, wherein the support plate is located at a distance from ends of the thrust-absorbing connecting rods.

Description

DESCRIPTION OF THE FIGURES

(1) The invention will be better understood and other details, features and advantages of the invention will emerge from reading the following description, given by way of non-limiting example and with reference to the accompanying drawings, in which:

(2) FIG. 1 is a schematic view of an aircraft turbine engine according to the prior art, seen from the side,

(3) FIG. 2 is a partial schematic view in perspective of a turbine engine according to the invention,

(4) FIG. 3 is a larger-scale view of the thrust-absorbing means and support means according to the invention of the turbine engine of FIG. 2.

DETAILED DESCRIPTION

(5) Reference is made first of all to FIG. 1, which is a turbine engine 10 according to the prior art, this turbine engine 10 here being a bypass turbojet engine.

(6) The turbine engine 10 comprises, from upstream to downstream in the direction of flow of the gases, a fan 12 that generates a flow that divides into two coaxial flows, the primary flow supplying the engine, which comprises a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, a low-pressure turbine and an exhaust nozzle 14 for ejecting the combustion gases.

(7) These engine modules (fan, compressors, combustion chamber, turbines) are surrounded by structural annular casings. The turbine engine 10 thus comprise a plurality of successive annular casings including an intermediate casing 16, a high-pressure compressor casing 18, a combustion chamber casing 20, an inter-turbine casing 22 and an exhaust casing 24.

(8) As shown by FIG. 1, in order to mount and fix the turbine engine 10 on an aircraft strut 26 under its wings, two suspensions 28, 30, respectively upstream and downstream, are provided, so as to form an interface between the turbine engine 10 and the strut 26. The upstream suspension 28 is arranged between the strut 26 and the intermediate casing 16 and the downstream suspension is arranged between the strut 26 and the inter-turbine casing 22.

(9) The suspensions 28, 30 are arranged and contained in two suspension planes P1 and P2 of the turbine engine, which are parallel to each other and orthogonal to the longitudinal axis L-L thereof.

(10) The turbine engine 10 of FIG. 1 further comprises means for absorbing the thrust forces of the engine, which comprise here two longitudinal connecting rods 32, the upstream ends of which are articulated on the intermediate casing 16 and the downstream ends of which are articulated on the downstream suspension 30.

(11) However, this technology has drawbacks, including a complex integration of the equipment in the region extending around the engine through which the thrust-absorbing connecting rods 32 pass.

(12) The invention makes it possible to remedy this drawback by conferring an equipment-supporting function on the thrust-absorbing connecting rods 32.

(13) FIGS. 2 and 3 are an embodiment of the invention in which the thrust-absorbing connecting rods 32 support two items of equipment 34, 36. These items of equipment 34, 36 are here fixed to a support plate 38 that extends between the connecting rods 32 and is fixed thereto.

(14) In the example shown, the connecting rods 32 are not parallel but form an angle between them. The support plate 38 has a substantially trapezoidal shape and occupies an inter-rod space, situated at a distance from the longitudinal ends of the connecting rods. The plate 38 may be metal and has for example a thickness of between 1 and 5 millimeters.

(15) The plate 38 comprises, at its corners, means 40 for fixing to the connecting rods 32, these fixing means comprising here clamping collars that grip the flanges 32 and are locked thereon by means of bolts (not shown).

(16) The items of equipment 34, 36 may be fixed or mounted on the plate 38 by any suitable means, and for example by means of damping studs. In the example shown, the items of equipment 34, 36 are aligned one behind the other along the longitudinal axis LL of the turbine engine, and each comprise a top part 42 extending above the plate 38 (or radially outside the plate with respect to the axis LL) and a bottom part 44 that extends below the plate 38 (or radially inside the plate with respect to the axis LL).

(17) The plate 38 may be metallic and has for example a thickness of a few millimeters.

(18) In the example shown, the connecting rods 32 are mounted downstream of the intermediate casing 16 and their upstream ends are articulated thereon. More precisely, the intermediate casing 16 comprises a hub 50 surrounded by a cylindrical wall (not shown) and connected thereto by radial arms. The upstream ends of the connecting rods 32 are articulated on the hub 50 of the intermediate casing 16.

(19) The downstream ends of the connecting rods 32 are articulated on the ends of a beam 52 that is itself articulated on the downstream suspension 30, as described in the patent application FR 12/51813. The downstream suspension 30 is here connected by connecting rods to a ring 54 mounted around the inter-turbine casing 22.