SU1354834A1 - Rotor bearing support of two-stage gas-turbine engine - Google Patents

Abstract

This invention relates to a power plant industry. The invention makes it possible to increase the reliability of the support and to reduce axial and radial dimensions for use in an engine (D) located between the stages of an auxiliary drive with bevel gears. The upward displacement of the axis 15 relative to the longitudinal axis D ensures the alignment of the axes of the bearing surfaces of the bearings (and) 7 and 8 during assembly D and its operation due to the elasticity of the housing (K) 3. The latter is due to the introduction of through and longitudinal 126 Fig.Z27 J5

Description

groove 13 and the presence of elastic Papochek, formed tgazami. Three work D is carried out lubrication P.-On the channel

23 stator to channel 22 K 3 the oil enters the drilling Ik and the nozzle 26 to D 7. Simultaneously from drilling

24 by the removable tube 21, the oil enters the drilling 25 K 3 and further - on

one

The invention relates to energy-efficient construction, in particular to the supports of the rotors of gas turbine engines.

The aim of the invention is to increase the operational reliability of the support and to reduce the axial and radial dimensions when using an auxiliary drive with conical testers placed between the stages in the engine.

Nyamio

Figure 1 shows a two-stage gas turbine engine with a rotor support., Longitudinal section; in Fig. 2, section A-A in Fig. 1 (on the support the rotor of the two-stage gas turbine engine); on fig.Z - partial tearing support; 4 shows the support of the rotor from May to the line of dampers.

The support of the rotor 1 of the two-stage gas turbine engine contains elastic casing 3 connected to the stator 2 of the engine with a flange 4 and cylindrical bearing surfaces of 5 tb and bearings in the casing 3 of bearings 9 and 8 of shafts 9, 10 of stages 1t and 12 that are in contact with support surfaces 5 and 6. The housing 3 in the zone between the supporting surfaces 5 and 6 is provided with through-length longitudinal grooves 13, forming elastic balochki.1 and the axis 15 of the supporting surface 6 of the bearing 8, placed on the side opposite to the flange 4, is displaced upwards from 1 longitudinal B engine.

When used in a gas turbine. The motor located between the cascades 1 1 and 12 of the auxiliary drive 16 with bevel gears 17, 18, 19, housing 3 in the area of the grooves 13 is provided with openings 20 for accommodating a six-way break.

The nozzle 27 to P 8, Gib 28 and rings 29, possibly with Tf, free radial and axial displacement of the 2 K tube. Use the auxiliary drive 16 K 3 in the area of the grooves 13 with holes 20 to accommodate gears, 2 O, p. 4 il.

5 g

0

2

The support is equipped with a detachable pipe 21 for supplying oil through the channels 22, 23 of the housing 3 and the stator 2 to the drills 24 and 25 of the housing 3 to the nozzles 26 and 27 to the bearings 7 and 8. The removable pipe 21 has a bend 28 and is fixed movably in drilling of the housing 24 and 25 with the help and sealing rings 29 and the lock 30 ..

Above the bearings 7 and 8, two oil or one damper 31, 32 can be installed (figure 2) (figure 4).

When a two-stage gas turbine engine is operating, the radial forces of the bearing axis 7 and 8 are transmitted to the elastic housing 3 and through the drive housing, the nozzle to the power unit, the engine housing (not indicated in the drawing). flange 4, which allows EXCLUDE additional oil joints.

The upward displacement of the axis 15 relative to the longitudinal axis of the engine, in the case of the general assembly of the engine and its operation, is the alignment of the axes of the supporting surfaces of the bearings. 7 and 8 due to the elasticity of the housing 3, due to the introduction of through and longitudinal grooves 13 and the presence of beams 14.

The deformation of the casings of the 1T and 12s cascades due to the operation of the two-stage gas turbine engine, temperature change and force effects, is also closed to the mounting flange 4, thereby maintaining the position of the supports of the cascades 11 and 12 relative to each other.

When the engine is running, bearings 7 and 8 are lubricated in the following way: By channel 23 of the stator and channel 22 of the housing 3, oil is reached and drilling 2 of the housing 3 is fed to the bearing 7 on the nozzle 26 to the bearing 7. drilling 25 of the housing 3 and further on the nozzle 27 to the bearing 8. There are several drilling holes 2A and 25, as well as the pipes 21.

The bend 28 and sealing rings 29 make the support operation reliable due to the possibility of free radial and axial movement of the tube 21.

Claims (3)

1. The rotor support of a two-stage gas turbine engine, comprising a housing connected to the stator of the engine with a flange and cylindrical bearing surfaces, bearings of the cascade shafts placed in the housing, in contact with the supporting surfaces, which in order to increase the reliability of operation, the housing in the zone between the bearing surfaces is provided with through longitudinal grooves, and the axis of the bearing surface of the bearing located on the side opposite to the flange is offset relative to the axis of the engine 0 in order to reduce axial and radial dimensions, 2. Bearing on p. 1, I differ. Scha and with the fact that when using-. Research institutes in the engine located between 5 stages of an auxiliary drive with bevel gears, body c. the slot area is provided with holes for accommodating gears, Q 3. The support according to claim 1, in which it is equipped with a detachable tube for supplying oil to the bearings, which is fixed in the housing by means of sealing rings. 8 6 SW Editor A.Kondrahina FIG. Compiled by E. Craidin Tehred M. Khodanych Order 4347 Circulation 442 Subscription VNIIPI USSR State Committee. for inventions and discoveries 113035, Moscow, Zh-35, Raushsk nab., 4/5 Proevodptvens-polygraphic enterprise, Uzhgorod, st. Project, 4 Corrector S.Cherni