RU2194177C1 - Two gas turbine engine support - Google Patents

Abstract

FIELD: mechanical engineering. SUBSTANCE: invention relates to gas turbine engine. Said support for two rotor gas turbine engine has high pressure rotor journal, pre-oil space, oil space and intershaft space formed by journal and shaft of high pressure rotor. Bearing inner race and labyrinth seal separating pre-oil and oil spaces is installed on outer surface of journal. Impeller made in form of hub with ribbed disk is installed between spaces. Ring groove is made on inner surface of journal from side of intershaft space. Ring space forms open cavity in journal which communicates with oil space through holes in journal and holes in impeller. EFFECT: improved reliability of support and increased service life owing to prevention of coking of support members. 4 cl, 5 dwg

Description

 The invention relates to the field of gas turbine engine manufacturing, and in particular to the construction of engine mounts.

 A known support for a two-rotor gas turbine engine (GTE), comprising a high-pressure rotor pin, a pre-oil and oil cavity formed by a low-pressure rotor shaft and a shaft-to-shaft cavity separated by an oil seal from the oil cavity, and an inner bearing race and a labyrinth placed on the outer surface of the pin separating pre-oil and oil cavities / 1 /.

 In the known construction, when oil is supplied from the low-pressure rotor to the oil bath of the high-pressure rotor, oil is sprayed, which makes it possible to get it from the oil cavity through the movable seal into the pre-oil cavity. Once in the pre-oil cavity, the oil can coke, which reduces the reliability of the engine, and can also enter the environment through the air system in the form of drops and steam, which increases the oil consumption on the engine and affects the environment.

 The present invention solves the problem of eliminating the possibility of coking of oil in the pre-oil cavity of the support by preventing oil from entering the air channels of the support.

 To achieve the specified technical result in the support of a two-rotor gas turbine engine containing a pin of a high-pressure rotor, an inner bearing race and a labyrinth seal formed on the surface by a pin and a shaft of a low-pressure rotor, an inter-cavity, a pre-oil cavity and separated from it by a labyrinth cavity, and from the inter-cavity an oil cavity with movable seals; an impeller made in the form of a hub is mounted on the trunnion between the labyrinth seal and the inner race of the bearing with a ribbed disk, and an annular groove is made on the inner surface of the axle from the side of the pre-oil cavity, forming an open niche in the axle, connected to the oil cavity by a system of holes sequentially made in the axle and impeller, the impeller opening being in communication with the axle opening.

 In addition, the outlet cross sections of the holes can be located on the impeller hub between the finned disk and the labyrinth seal, or the holes can be made in the finned disk and the impeller hub, and a connector can be made in the radial plane along the finned disk and the impeller hub, and the holes can be placed on at least one of its surfaces.

 The presence of an impeller in the form of a hub with a ribbed disk allows the droplets of the high-pressure rotor to efficiently evacuate oil droplets from the bearing area and the labyrinth seal into the oil cavity during rotation.

 The presence of an annular groove on the inner surface of the trunnion of the high-pressure rotor from the side of the inter-shaft cavity, which forms an open niche in the trunnion, allows you to capture the oil that has leaked from the oil cavity through the movable seal and not let it pass further into the pre-oil cavity of the air engine venting system.

 The presence of holes sequentially made in the trunnion of the high-pressure rotor and impeller connected with the oil cavity allows the oil to be returned from the open niche to the oil cavity.

 The presence of exit cross sections of openings made in the impeller’s hub between the labyrinth seal and the ribbed disk allows oil droplets to be evacuated to the oil system area separated from the bearing, which excludes particles of coke and “waste” oil from entering the bearing area directly.

 When making through holes in the radial plane in the finned disk and the impeller hub, the inlet of which is connected with the outlet of the holes in the journal and the outlet is with the oil cavity, the effect of evacuation of leaked oil drops is enhanced.

 If there is a connector on the ribbed disk and the impeller hub, when placing through holes on at least one of the connector surfaces, the manufacturing system and overhaul preventative maintenance are simplified.

 The proposed support is illustrated by the drawings shown in figures 1-5.

 Figure 1 shows a longitudinal section of the support of a two-rotor gas turbine engine.

 Figure 2 is a longitudinal section of the impeller.

 Figure 3 is a longitudinal section of the impeller with through holes in the radial plane.

 In FIG. 4 is a longitudinal section through an impeller with a connector in the radial plane.

 Figure 5 is a view A of figure 4.

 The support of a two-rotor gas turbine engine contains a pin 1 of a high-pressure rotor, a pre-oil cavity 2, an oil cavity 3, an inter-cavity 4 formed by a pin 1 and a shaft 5 of the high pressure rotor and separated from the oil cavity 3 by a movable seal 6.

 On the outer surface 7 of the pin 1, an inner bearing race 8 and a labyrinth seal 9 are located, separating the pre-oil 2 and oil 3 cavities. An impeller 10 is mounted on the pin 1 between the labyrinth seal 9 and the inner race of the bearing 6. The impeller 10 is made in the form of a hub 11 with a finned disk 12.

 An annular groove is made on the inner surface of the axle 1 from the side of the inter-cavity 4, forming an open niche 13 in the axle 1, connected with the oil cavity 3 by the holes 14 in the axle 1 and the holes 15 in the impeller 10. The inlets of the openings 15 are communicated with the outlets of the openings 14.

 The holes 15 of the impeller 10 can be made in the hub 11 with the location of their output sections between the finned disk 12 and the labyrinth seal 9.

 The holes 15 can also be made in the ribbed disk 12 and the hub 11 of the impeller 10 in the radial plane 16.

 The impeller 10 can be made with a radial connector 17. In this case, the holes 15 can be placed on one of the surfaces of this connector.

 Support two-rotor GTE works as follows.

 When oil penetrates from the oil cavity 3 through the movable seal 6 into the inter-cavity 4, it is pressed by the centrifugal forces to the inner surface of the pin 1. Under the action of these forces, the oil film moves along this surface and when it reaches the annular groove made in the pin 1, it gets into the open niche 13, from which through holes 14 in the pin 1 and holes 15 in the impeller 10 is thrown into the zone of the oil cavity 3. The labyrinth seal 9 separating the pre-oil cavity 2 and the oil cavity 3, prevent the ingress of oil into the cavity 2, and due to the placement of the impeller 10 with the ribbed disk 12 on the outer surface 7 of the pin 1 between the labyrinth seal 9 and the inner race of the bearing 8, the oil exiting the holes 15 cannot directly enter the area of the bearing 6, since the ribbed on both sides, the disk 12 throws the oil into the evacuation zone of the oil cavity 3. This reduces the risk of oil escaping through the pre-oil cavities 2 into the environment.

 Particularly relevant is the operation of the proposed support in variable modes and on the engine start and stop modes, since it is precisely at these modes that the oil is most often released into the inter-cavity 4. When the engine is stopped, the remaining oil is evacuated directly to the oil cavity 3, which prevents the coke formation process support structures, thereby increasing its reliability and resource.

Sourse of information
1. US patent N 5160251, CL. NKI 6 F 01 D 85/16, 1992

Claims (4)

 1. The support of a two-rotor gas turbine engine, comprising a pin of a high pressure rotor, an inner bearing race and a labyrinth seal, an axle cavity, a pre-oil cavity and a movable oil cavity separated from it by a spindle and a labyrinth cavity, and a labyrinth cavity separated from it, and a movable oil seal characterized in that on the trunnion between the labyrinth seal and the inner race of the bearing there is an impeller made in the form of a hub with a ribbed disk, and on the inside An annular groove is made in the trunnion on the front surface of the trunnion, forming an open niche in the trunnion, connected to the oil cavity by a system of through holes sequentially made in the trunnion and impeller, the inputs of the impeller openings communicating with the outputs of the trunnion openings.  2. Support according to claim 1, characterized in that the outlet cross sections of the holes are located on the impeller hub between the finned disk and the labyrinth seal.  3. Support according to claim 1, characterized in that the holes are made in the ribbed disk and the impeller hub in a radial plane.  4. Support according to claim 3, characterized in that a connector is made in the radial plane along the ribbed disk and the impeller hub, with the holes placed on at least one of the surfaces of the connector.

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