RU2596899C1 - Support of low-pressure compressor of turbomachine - Google Patents

Abstract

FIELD: energy.

SUBSTANCE: invention relates to power engineering. Support of low-pressure compressor of turbomachine, comprising intermediate shaft, in which is installed a compressor rotor journal and connected to it in circumferential direction by means of spline joint, and in axial direction by means of coupling pipes, successively mounted on intermediate shaft ball bearing, graphite seal, labyrinth seal, wherein seals and inner ring of ball bearing are locked relative to intermediate shaft in axial direction by means of thrust face and nut.

EFFECT: invention increases efficiency, reliability and manufacturability of support due to additional control of alignment and convenience of flaw detection of bearing and seals.

1 cl, 1 dwg

Description

The invention relates to the field of turbomachinery, and in particular to the design of an angular contact support with a compression device of a compressor and a low-pressure rotor turbine of a gas turbine engine.

As the closest analogue (prototype), the support of a low-pressure compressor of a turbomachine is selected, containing an intermediate shaft, in which the axle of the compressor rotor is installed and connected to it in the circumferential direction by means of a splined joint, and in the axial direction by means of a coupling pipe, ball-mounted in series on the intermediate shaft a bearing, the outer ring of which is connected to its housing by means of a flange connection, a graphite seal, the housing of which is connected to the ball housing a bearing, a labyrinth seal, said seals and the inner ring of the ball bearing being axially fixed relative to the intermediate shaft by means of a thrust end and a nut, made and threaded on the intermediate shaft, respectively, an oil supply visor forming a ring oil supply cavity with the outer surface of the intermediate shaft, diametrically located below the bore diameter of the inner ring of the ball bearing and communicated with the annular and axial oil supply grooves made on the intermediate shaft and connected to the inner ring of the ball bearing (see fig. 3.4, p. 118, “Technology of operation, diagnostics and repair of gas turbine engines: Textbook. allowance. / Yu.S. Eliseev, V.V. Krymov, K.A. Malinovsky, V.G. Popov. - M .: Higher. school; 2002. - 355 p .; ill.).

The known technical solution has the following disadvantages. Due to the fact that, in the known construction, the compression nut of the inner ring of the ball bearing is installed on the turbine side, the thrust end is made on the compressor side relative to the ball bearing, and the flange of the outer ring of the ball bearing is joined to the flange of the bearing housing on the turbine side, the ball bearing can be inserted into the turbomachine only as part of an assembled support, including housing, seals and countershaft. Therefore, after mounting the support in the turbomachine, it is impossible to control the end runout of the inner ring of the bearing relative to the outer ring. The presence of increased heartbeat, i.e. loss of alignment, negatively affects the performance of the bearing with the release of increased heat and subsequent destruction of the bearing. Also, the graphite seal housing is connected to the ball bearing housing by means of a non-separable connection. In the process of fault detection of graphite compaction, the support must be completely disassembled. In this case, it is necessary to keep the turbine rotor in the axial direction, this requires access to the turbine support. This complicates and increases the cost of defective seals and bearings, reduces the manufacturability of the turbomachine. The presence of oil-supplying channels passing along the joint thread of the nut and the intermediate shaft reduces the strength of the threaded connection due to additional stress concentrators, which also reduces the resource of the support as a whole. In this case, the nut thread to reduce the coefficient of friction during tightening, as a rule, is lubricated with graphite grease, which clogs the oil supply channels and clogs the oil. Since the oil-supply cavity is made on a nut, it cannot be diametrically located much lower than the bearing without increasing the radial channels passing through the thread. This reduces the centrifugal effect of supplying oil to the bearing.

The technical result achieved by using the present invention is to increase the operability, reliability and manufacturability of the support due to additional control of the alignment and convenience of defective bearings and seals.

The specified technical result is achieved by the fact that in the known support of the low-pressure compressor of a turbomachine containing an intermediate shaft, in which the axle of the compressor rotor is mounted and connected to it in the circumferential direction by means of a spline connection, and in the axial direction by means of a shrink tube, a ball joint is sequentially mounted on the intermediate shaft a bearing, the outer ring of which is connected to its housing by means of a flange connection, a graphite seal, the housing of which is connected to the housing of the bearing, a labyrinth seal, said seals and the inner ring of the ball bearing being axially fixed relative to the intermediate shaft by means of a thrust end and a nut made and threaded on the intermediate shaft, respectively, an oil supply visor forming an annular oil supply cavity with the outer surface of the intermediate shaft, diametrically located below the bore diameter of the inner ring of the ball bearing and communicated with the annular and axial oil-grooves made on the intermediate shaft and connected to the inner ring of the ball bearing, according to the present invention, the nut is mounted on the compressor side with respect to the ball bearing, and the thrust end is made integrally on the turbine side with the intermediate shaft, while in the said flange connection of the outer ring of the ball bearing with ball bearing housing, the flange of the outer ring of the ball bearing is located on the compressor side relative to the housing flange a ball bearing mustache, and the oil supply visor is made on the thrust end, while the connection of the graphite seal housing with the ball bearing housing is collapsible.

This embodiment of the device allows, on an installed support in the turbomachine, to check the end runout of the inner ring of the bearing relative to the outer ring in the absence of a compressor rotor, seals and with technological fixing of the bearing on the countershaft. This was made possible thanks to the additional flange connection of the graphite seal housing to the support housing. This protects against possible misalignment errors and provides predictable bearing performance during operation. Also, when sealing and bearing are faulty, it is not necessary to dismantle the bearing housing with the intermediate shaft holding the turbine rotor, it is enough to fix it with the intermediate shaft on the compressor side, while the axial alignment of the turbine rotor is not disturbed.

In addition, the oil supply cavity is in communication with the annular and axial oil supply grooves through holes in the intermediate shaft, made at an angle to the longitudinal axis of the support.

In this case, the oil supply channels do not pass through the threaded connection of the nut with the intermediate shaft (as in the prototype), as a result of this, the strength of the threaded connection is increased. Solid lubricant applied to the threads of the nut does not contaminate the oil. Holes made at an angle to the longitudinal axis of the support allow the oil supply cavity to be arranged at a smaller diameter than in the prototype, while the efficiency of oil supply to the bearing will increase due to an increase in the centrifugal force of the oil.

The essence of the present invention is illustrated in the drawing, which shows a longitudinal section of the claimed support of the compressor low pressure turbomachine.

The support of the low-pressure compressor of the turbomachine contains an intermediate shaft 1 in which the axle of the rotor of the compressor 2 is mounted and connected to it in the circumferential direction by means of a spline connection 3, and in the axial direction by means of a shrink tube 4, a ball bearing 5, an outer ring, mounted in series on the intermediate shaft 1 6 of which is connected to its housing 7 by means of a flange connection, a graphite seal 8, the housing 9 of which is connected to the housing 7 of a ball bearing 5, a labyrinth seal 10, wherein the crushed seals 8, 10 and the inner ring 11 of the ball bearing 5 are axially fixed relative to the intermediate shaft 1 by means of a thrust end 12 and a nut 13 made and threaded on the intermediate shaft 1, respectively, an oil supply visor 14 forming with the outer surface of the intermediate shaft 1 an annular oil-supply cavity 15, diametrically located below the bore diameter of the inner ring 11 of the ball bearing 5 and in communication with the annular and axial oil-supply grooves and 16, 17, made on the intermediate shaft 1 and connected to the inner ring 11 of the ball bearing 5, while relative to the ball bearing 5, the nut 13 is mounted on the compressor side, and the thrust end 12 is made integrally on the turbine side with the intermediate shaft 1, while said flange connection of the outer ring 6 of the ball bearing 5 with the housing 7 of the ball bearing 5 the flange of the outer ring 6 of the ball bearing 5 is located on the compressor side relative to the flange of the housing 7 of the ball bearing 5, and the oil the visor 14 is made on the abutment end 12, while the connection of the housing 9 of the graphite seal 8 with the housing 7 of the ball bearing 5 is made collapsible, for example, by means of a flange connection, where the flange 18 of the housing 9 of the graphite seal 8 relative to the flange 19 of the housing 7 of the ball bearing 5 is made with side of the compressor.

In this case, the oil supply cavity 15 is in communication with the annular and axial oil supply grooves 16, 17 by means of holes 20 in the intermediate shaft 1, made obliquely to the longitudinal axis of the support.

The operation of the declared support of the rotor of the turbomachine is as follows.

The torque from the turbine rotor is transmitted to the compressor rotor 2 through an intermediate shaft 1 and a spline connection 3. In this case, the compressor rotor 2 is axially fixed by means of a shrink tube 4. The total axial load from the rotors is transmitted through the ball bearing 5 to the housing 7. Axial locking of the ball bearing 5 relative to the intermediate shaft 1 is provided by a nut 13 and a thrust end 12 through the parts of the seals 10 and 8.

If the seals and bearing are faulty with the compressor rotor 2 absent, it is enough to remove the nut 13, the labyrinth seal 10 and the graphite seal housing 9. In this case, it is possible to inspect the ball bearing 5, replace it without dismantling the housing 7, or check the end runout of the inner ring 11 of the ball bearing 5 relative to the outer ring 6 when assembling the turbomachine. All this increases the reliability, availability and manufacturability of the support and turbomachine as a whole.

Claims (2)

1. Support of a low-pressure compressor of a turbomachine, comprising an intermediate shaft in which the axle of the compressor rotor is mounted and connected to it in the circumferential direction by means of a spline connection, and in the axial direction by means of a shrink tube, a ball bearing, the outer ring of which is connected to its housing by means of a flange connection, a graphite seal, the housing of which is connected to the ball bearing housing, a labyrinth seal, wherein the grooves and the inner ring of the ball bearing are axially fixed relative to the intermediate shaft by means of a thrust end and a nut made and threaded on the intermediate shaft, respectively, an oil supply visor forming an annular oil supply cavity with an outer surface of the intermediate shaft diametrically lower than the bore diameter of the inner ring of the ball bearing and communicated with annular and axial oil supply grooves made in between shaft and connected to the inner ring of the ball bearing, characterized in that the nut is installed on the compressor side relative to the ball bearing, and the thrust end is made integrally with the intermediate shaft on the turbine side, while the flange in the said flange connection of the outer ring of the ball bearing with the ball bearing housing the outer ring of the ball bearing is located on the compressor side relative to the flange of the ball bearing housing, and the oil supply visor is made on a thrust RCE, wherein the compound body graphite seal ball bearing housing configured collapsible. 2. The support of the low-pressure compressor of a turbomachine according to claim 1, characterized in that the oil-supply cavity is in communication with the annular and axial oil-supply grooves through holes in the intermediate shaft made obliquely to the longitudinal axis of the support.

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