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multi-stage turbine rotor

A turbine rotor and disc technology, applied in the field of multi-stage turbine rotor components, can solve problems such as disc failure, disc damage, and low reliability

Active Publication Date: 2020-05-05
奥德克航空发动机股份公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The disadvantage of the known structure, considered a prototype, is its low reliability, since the elastic members are in contact with the disc hub or the web, which can lead to damage of the disc in its area of ​​greatest stress and further failure of the disc

Method used

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Embodiment Construction

[0020] The multi-stage turbine rotor 1 comprises a first disc 2 , an intermediate disc 3 and a final disc 4 , which overhang the shaft 5 of the rotor 1 against a bearing 6 and pass through the center of a spherical washer 8 and an elastic member 9 Tension bolt 7 is connected. The last disc 4 with a radial flange 10 leading to the bearing 6 is attached to the shaft 5 by a bolt joint 11 .

[0021] The elastic member 9 having the first surface 12 is installed in the Z-shaped front flange 13 of the first disc 2 and is in contact with the end face 14 of the Z-shaped front flange 13, while the second surface 15 of the elastic member 9 is in contact with the tensioned The body 16 of the bolt 7 is in contact. The elastic member 9 rests against the Z-shaped front flange 13 of the first disc 2 and is fixed circumferentially with axial pins 17 and is manufactured with an L-shaped annular flange 18 on which is mounted The circumferential retainer 19 of the tension bolt 7 .

[0022] The...

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Abstract

The invention relates to a multi-stage turbine rotor comprising first, middle and last disks connected to a shaft by a central tensioning bolt with a spherical washer and an elastic member inserted at its first surface into the first in the Z-shaped front flange of the disc and bringing it into contact with the end face; mounted on a tensioning bolt at its second surface; circumferentially fixed with an axial pin against the Z-shaped front flange of the first disc ; and is manufactured with an L-shaped annular flange having a tensioning bolt holder circumferentially mounted thereon; while the third surface of the elastic member adjacent to the first disc hub is made flat. Accordingly, embodiments of the invention having the characteristics described above and known features of the claimed invention make it possible to improve the performance of the invention by preventing contact of said elastic members with the disc hub and web during operation of the rotor assembly within a gas power turbine. Reliability of the multi-stage turbine rotor of the gas turbine engine.

Description

technical field [0001] This invention relates to multi-stage turbine rotor assemblies within commercial and land-based gas turbine engines. Background technique [0002] Gas turbine engine rotors are known in which the first, middle and last discs are axially fixed by means of tension bolts and mounting flanges (patent RU 2 251 010, IPC F02K3 / 06, date of publication: 20 April 2005 day). [0003] Such a configuration suffers from a lack of reliability due to the relatively high stresses applied to the possibly bent tension bolts. [0004] The closest to the claimed version and believed to be the prototype is the GT engine multi-stage turbine rotor comprising a disc axially secured by tension bolts consisting of spherical washers and elastic members such as mounted in series on the bolt Belleville spring washer between head and disc hub (patent RU2 230 195, IPC F02K3 / 06, publication date: April 20, 2005). [0005] The disadvantage of the known structure, considered a protot...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/06
CPCF01D5/06F01D5/066F02C7/36
Inventor 弗拉基米尔·米哈维洛维奇·亚兹夫谢尔盖·伊万诺维奇·法捷耶夫弗拉基米尔·康斯坦丁诺维奇·索契夫瓦列里·阿列克谢维奇·库兹涅佐夫
Owner 奥德克航空发动机股份公司
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