UA62518A - Rear belt of suspension of a gas turbine bypass engine - Google Patents

Abstract

A rear belt of suspension of a gas turbine engine to the pylon of an aircraft contains hinges, two rods whose one side ends are connected by a bracket in place of its fastening to the aircraft, and the other ends of the specified rods are attached to the edges of the engine from both sides with respect to the longitudinal axis of the latter. Fastening to the engine is ensured by threaded connections through the ears of rods and plates and contains on the latter two parallel edges and two ears of each specified ear. Between specified ears and edges is located an insert with apertures for the specified threaded connections. From both sides of insert between edges are additionally located the redundant plates with apertures, in some of them is introduced a threaded connection, and the safety fingers together with apertures of ears are additionally introduced into other apertures.

Description

Description of the invention

The claimed technical solution relates to aviation technology, namely to the design of nodes 2 for fastening the power plant and its placement on the aircraft.

A known device for mounting a two-circuit turbojet engine (see Russian patent Mo 849694, class v64027/26, filed: 03/12/1980, published: 09/20/1996, Bull. Mo2b6).

Its rear fastening belt is a connection of the engine and the aircraft pylon with the help of three tubular rods, the plane of which is perpendicular to the axis of the gas generator of the engine. The hinged rods are fixed on the 70 shell of the gas generator of the engine and the aircraft pylon. Two rods perform the main working function, and the third, located between the main rods, performs the function of a backup rod and comes into operation in case of failure of one of the main rods.

The shortcomings of the considered design include the fact that there are no spare fasteners in the nodes for attaching the rods to the engine and the aircraft pylon. Although the spare rods ensure the safety of the 12 structure, they complicate the installation of the engine to the aircraft pylon due to the large number of attachment points, both to the aircraft pylon and to the engine itself.

The known rear suspension belt of a gas turbine engine (see Russian patent "Samara State Scientific and Production Enterprise "Practsia" Mo 2005667 cl. Ub4027/26, filed: 06/05/1992, published: 01/15/1994, Bull. Mo1).

The known device includes a spike located between the aircraft pylon and the spherical bearing of the rear suspension belt, two main side rods with one end hinged to the engine housing and the other to the pylon with a conical pin. In the common plane between them, there are two additional rods, which are hinged to the side rods in the engine housing. The upper ends of the additional rods are connected to a common node together with the rear end of the thrust. The above-mentioned assembly is a sleeve in which a spherical bearing is placed, which 22 covers the spike of the pylon. Additional rods perform the role of backups and come into operation in case of failure of one of the main rods.

The considered device is of interest from the point of view of safety in an emergency situation, but the large number of hinged joints complicates the design and its installation on the aircraft pylon, even with the presence of a spike used as a lock. co

The closest in design is the rear mounting device for an aircraft engine (see US patent "United Zyrkaft" Mo 3.397.855, class B64027/26, filed: 12.1.1966, priority application Mo 598.373, published: 08.20.1968). at

The known device is a structure containing two rods that are joined together at the point of articulation with the pylon of the aircraft at one point. 3o The unit of attachment of the rear suspension to the engine body, more precisely, on the flange of the gas generator body, contains ee, connecting plates consisting of two halves. The connecting plate embraces the flange of the gas generator body and is fixed on it with the help of bolts. Inserts are inserted between the two lugs of the connecting plate. The connection between the insert and the connecting plate is made using a bolt. The bolt " penetrates the connecting plate and the insert through the coaxial holes made in the eye of the insert and the eyes C 50 of the connecting plate. In the hole made in the eye of the insert, a hinged bearing is installed to compensate for the axial thermal expansion of the motor housing.

From" Rods are attached to the inserts at one end by butt welding. The other end of the rods is connected by butt welding to the connecting bracket, which is inserted into the hole made in the wall of the fan duct housing. The connecting bracket is pressed against the surface of the wall of the fan duct housing with a ring flange installed in the groove made in the connecting bracket. For reliable installation of the b flange in the connecting bracket, a clamping ring is used that presses the flange to the connecting bracket.

A grommet is pressed into the housing of the connecting bracket and welded along the contour. A hole is made in the ear of the mother-in-law, into which a hinged bearing is pressed, which acts as a compensator for axial -k 70 temperature expansions of the engine housing. The axis of the bearing is parallel to the longitudinal axis of the engine.

A safety flange is attached to the surface of the fan duct housing by its edges and is attached with rivets. The flange acts as a fuse against damage to the suspension attachment unit to the fan duct housing.

The design of the engine suspension ensures not only the upper location of the engine, but also the side (on 29 horizontal pylons). The design of the suspension provides an oscillating type of connection, which slightly reduces the noise from the vibrations, minimal weight. The installation of an aircraft engine to the aircraft pylon is quite technological, because the fastening is carried out at one point.

This design is easy to maintain. Safety measures are proposed in the spare fastening parts in the design of connecting the suspension to the flange of the gas generator body. But there are a number of disadvantages, namely: - due to a change in the distance between the points of attachment of the rods to the engine due to the accumulation of tolerances during the manufacture and thermal expansion of the engine housings, assembly and temperature stresses arise in the rods, which can lead to the destruction of the rods; - Due to the lack of spare rods in the design, in addition to the backup mount, in case of failure of one of the rods under the action of the resulting stresses, the remaining suspension rods may collapse, which will lead to the loss of the engine.

However, the design considered above was chosen as a prototype of the claimed device, because it provides a simplified installation of the engine on the aircraft, because the engine is mounted in the rear plane at one point, it allows to fasten, in particular, a gas turbine two-circuit engine to the ribs located on the engine body, while passing through the second circuit of the gas-air path of the engine, the two suspension core assemblies have a minimal effect on gas-dynamic losses, and the reliability of mounting the engine on the aircraft.

The proposed rear mounting belt is designed for mounting a gas turbine two-circuit engine to an aircraft. 70 The technical task of the claimed invention is to create such a design of the rear belt of the gas turbine two-circuit engine, which would give an overall technical result, which consists in simultaneously ensuring the simplicity and low weight of the design of the rear belt of the gas turbine two-circuit engine, its manufacturability in manufacturing and assembly- disassembly, while ensuring the reliability of the engine mounting on the aircraft and safety during operation.

This overall technical result must be ensured both with lateral (on horizontal pylons) and upper mounting of the engine on the aircraft.

The set technical problem is solved by the fact that in the known design of the rear belt for fastening the gas turbine engine to the aircraft pylon, which contains hinges, two rods, where one end of the rods is united by a bracket in the place of its attachment to the aircraft, and the other ends of the said rods are attached to the ribs of the engine on both sides relative to the longitudinal axis of the latter, and the attachment to the engine is provided with threaded connections through the lugs of the rods and plates, improvements have been made. These improvements are as follows.

The attachment to the engine contains on the latter two parallel ribs and two lugs of each rod. An insert with holes for threaded connections is placed between the mentioned lugs and ribs. Duplicating plates with holes are additionally installed on both sides of the insert between the 2g5 ribs, in one of which a threaded connection is introduced, and in the other, together with the holes of the lugs, safety fingers are additionally introduced. In this way, a firmer and more reliable fastening of the suspension attachment unit to the engine body is achieved, and the use of duplicate plates together with safety fingers ensures the safety of operation - when the eye of the insert is destroyed, the safety fingers and duplicate plates come into operation. зо зо Pivot bearings, located, one in the eye of the insert, and the others - in the connecting plate. Thus, the axial temperature expansion of the motor housing is compensated. -

The rods have the form of a channel. The rods are made of two longitudinal halves, fastened together by threaded connections, for example, bolts. This design of the rod ensures safety in operation - when one of the halves of the rod breaks, the reserve half comes into operation. with

Part of each rod is made in the form of a fairing. The front part of the fairing is formed by a part of the cylinder, and the rear part is formed by two intersecting planes tangent to the latter. Thus, gas-dynamic losses from the passage of the rear fastening belt assembly through the second circuit of the engine are reduced.

All this ensures the aforementioned technical results of the proposed device.

The invention is illustrated by sketches, where: "Fig. 1. shows the general view of the rear belt unit together with the engine for attaching the latter to the pylon in c of the aircraft with top mounting; Fig. 2. element A of Fig. 1 is shown, which relates specifically to the rear fastening belt; ;" Fig. 3 shows a general view of attaching the engine to the aircraft pylon with side mounting; Fig. A4 shows a cross-section along B-B of Fig. 3 (general view of the rear unit of attachment to the aircraft with lateral attachment);

Fig. 5 shows an enlarged view of element Г of Fig. 4 at the point of attachment to the aircraft; fig. b6 shows a cross-section from DD (fastening of the rear belt of the suspension to the bracket located right on the pylon) fig. 5; Fig. 7 shows the cross-section E-E (connection of the rods with the connecting plate) Fig. 5; Fig. 8 shows a cross-section along Fig. 4 (structure of rods;) - Fig. 9 shows element B (fastening of rods together with engine ribs) Fig. 5; with fig. 10 shows a cross section according to 3-3 of Fig. 7; Fig. 11 shows element B in the axonometric projection of Fig. 4.

The claimed back belt device has a mounting on the pylon 1 of the aircraft, through the bracket 2 dv | contains the connecting plate C, two rods 4 and 5, fastening nodes 6 and 7 to the motor housing 8 (see Fig. 1, 2).

Fastening of the connecting plate C and the bracket 2 located on the pylon 1 of the aircraft,

P is carried out by bolts 9 and 10. Bolt 10 penetrates the connecting plate Z through the hole 11 with a gap (see Fig. 4).

The design of the connecting plate Z is a node that consists of two longitudinal halves - the connecting plate 12 and 13, and the connection of these plates is carried out with the help of rivets 14. Rods 4 and 5 are equivalent. The rods consist of two longitudinal halves each. Rod 4 consists of rods 15 and 16, and rod 5 consists of rods 17 and 18, connected to each other by bolts 19 (see fig.5 and fig.b).

The rods 4 and 5 are connected to the connecting plate C with bolts 20, 21, 22, 23. The bolt 22 penetrates the rods 16, 17 and the connecting plate C and is installed with a gap in the hole 24 made in the connecting plate 3.

Attachment nodes b and 7 of the rear belt to the engine housing 8 are identical in design. The attachment unit b 65 contains an insert 25, to which the rod 4 is attached with a bolt 26, two duplicating plates 27, identical in shape and located between the insert and the lugs of the rib located on the turbine support housing, with fingers 28 installed on them. Insert 25 and duplicating plates 27 are attached to the ribs 29 of the motor housing 8 with bolts 30, 31 and nuts 32. Installed on duplicate plates 27, the fingers 28 are inserted with a gap into the hole 33, made in the form of a rod 4 with forked lugs (see Fig. 7, Fig. 8, Fig. 9).

Pivot bearings 34 and 35 are installed in the connecting plate C and in the eye of the insert 25, respectively.

Fairings 36 are installed on rods 4 and 5. Fairing 36 is a structure whose front part is formed by a part of a cylinder, and the rear part is formed by two intersecting planes that touch the latter.

In the place of passage of the rear fastening belt through the hood of the second circuit, sealing elements of 37 M - prominent profile are installed. 70 In flight, the proposed technical solution - the rear mounting belt, perceives and transmits vertical and lateral loads from the engine to the aircraft pylon through the mounting nodes b and 7, fixed on the power ribs made on the engine turbine support 8, on rods 4 and 5.

The latter, in turn, transmit the indicated loads to the connecting plate C, through which the loads are transferred to the bracket 2, and then to the pylon 1 of the aircraft.

In addition, the rear mounting belt perceives the torque from lateral inertial loads, as well as the component of mass (inertial) forces and loads from traction and gyroscopic moments.

To reduce gas-dynamic losses from the passage of the rear fastening belt assembly through the second circuit of the engine 8, fairings 36 are installed on rods 4 and 5.

Depending on the force of the moments acting on the engine, both tensile and 2o compressive stresses occur in rods 4 and 5.

Axial thermal expansion of the engine housings is compensated by installing pivot bearings 34 in the connecting plate Z and bearings Z5 in the insert eye 25.

Mounting the engine 8 to the aircraft is simplified by the fact that it is carried out after the assembly of the rear mounting belt is attached to the engine and the connection of the rear mounting belt to the pylon 1 of the aircraft is carried out at the point of its attachment to the aircraft.

Under the calculated operating conditions, reserve power elements and fastening elements do not come into operation. In the event of unexpected (accidental) damage: - if bolt 9 breaks, the backup bolt 10 (see fig. 4) takes over. - when one of the halves of the rod 4 or 5 is destroyed - their reserve elements come into operation (see Fig. 5); so z - when the insert 25 is destroyed or the bolt 26 is destroyed - the backup fingers 28 and plates 27 come into operation (see Fig. 7, 8). --

Thus, damage or destruction of each of the power parts of the rear suspension unit will not lead to the loss of the engine.

The improvement ensures the simplicity of the design with a minimum number of hinged bearings and the introduction of redundancy elements into the suspension design

The manufactured experimental sample was designed to attach the Ai-22 engine to the Tu-324 aircraft of Tupolev JSC and was tested by hanging the engine on a stand.

Claims (6)

The formula of the invention h - c 1. The rear belt of fastening of the gas turbine engine to the aircraft pylon, containing hinges, two :z" rods, one end of which is united by a bracket in the place of its attachment to the aircraft, and the other ends of the mentioned rods are attached to the ribs of the engine on both sides relative to the longitudinal axis of the latter, and the attachment to the engine is provided with threaded connections through the lugs of the rods and plates, a FO which differs in that the attachment to the engine contains on the latter two parallel ribs and two lugs of each mentioned rod, and between the mentioned lugs and ribs there is an insert with holes under the mentioned threaded connections, while on both sides of the insert between the ribs, duplicate plates with holes are additionally installed, in one of which a threaded connection is introduced, and in the others, together with the holes of the lugs, additional safety 5r fingers are introduced. 2. The rear belt for fastening the gas turbine engine to the aircraft pylon according to claim 1, which is characterized by the fact that at the point of attachment to the aircraft pylon, each said rod has additional two lugs, between which there is a connecting plate with holes through which it connected by threaded connections to the lugs of the rod. 3. The rear belt of fastening of the gas turbine engine to the pylon of the aircraft according to claim 1, which is characterized by the fact that the mentioned hinges are located, one - in the mentioned insert together with the threaded connection of the latter with the eyes of the rods, and the other - in the connecting plate. 4. The rear belt for fastening the gas turbine engine to the pylon of the aircraft according to claims 1-3, which is characterized by the fact that each mentioned rod has the shape of a channel. in 5. The rear belt for fastening the gas turbine engine to the aircraft pylon according to claim 4, which is characterized by the fact that each mentioned channel is made of two longitudinal parts, fastened together by threaded connections. 6. The rear belt for fastening the gas turbine engine to the aircraft pylon according to claims 4, 5, which is characterized by the fact that at least a part of each rod is made in the form of a fairing, the front part of which is formed by a part of a cylinder, and its rear part is formed by two intersecting planes that touch the last