CN108252745B - Multi-stage turbine rotor - Google Patents
Multi-stage turbine rotor Download PDFInfo
- Publication number
- CN108252745B CN108252745B CN201710963593.5A CN201710963593A CN108252745B CN 108252745 B CN108252745 B CN 108252745B CN 201710963593 A CN201710963593 A CN 201710963593A CN 108252745 B CN108252745 B CN 108252745B
- Authority
- CN
- China
- Prior art keywords
- disc
- elastic member
- flange
- tension bolt
- shaped front
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
- F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
Abstract
The invention relates to a multistage turbine rotor comprising a first, a middle and a last disk connected to a shaft by a central tension bolt with a spherical washer and an elastic member inserted at its first surface into a Z-shaped front flange of the first disk and contacting it on the end face; mounted on the tension bolt at a second surface thereof; the Z-shaped front flange abutting against the first disc is fixed circumferentially with an axial pin; and is manufactured with an L-shaped annular flange having a tension bolt retainer circumferentially mounted thereon; while the third surface of the resilient member adjacent the first hub is made flat. Thus, the embodiments of the invention having the above-described features and the known features of the claimed invention make it possible to improve the reliability of the multistage turbine rotor of the gas turbine engine by preventing the elastic members from coming into contact with the disk hub and the web during operation of the rotor assembly within the gas power turbine.
Description
Technical Field
The invention relates to a multi-stage turbine rotor assembly in civil and terrestrial gas turbine engines.
Background
Gas turbine engine rotors are known in which the first, intermediate and final disks are axially fixed by means of tensioning bolts and mounting flanges (patent RU 2251010, IPC F02K3/06, publication date: 4/20/2005).
Such a configuration lacks reliability due to the higher stress applied to the tension bolts that may bend.
The closest claimed version and considered as prototype is the GT engine multi-stage turbine rotor, which comprises a disc axially fixed by means of a tension bolt comprising a spherical washer and a resilient member, such as a belleville spring washer mounted in series between the bolt head and the disc hub (patent RU 2230195, IPC F02K3/06, publication date: 4/20/2005).
A disadvantage of the known structure, which is considered as prototype, is its low reliability, since the elastic member is in contact with the disk hub or web, which may lead to damage of the disk in its area of maximum stress and further failure of the disk.
A technical challenge addressed by the claimed invention is to improve the reliability of a GT engine multi-stage turbine rotor assembly by avoiding contact of resilient members with the disk hub and webs during operation of the gas power turbine rotor.
Disclosure of Invention
The technical result is achieved by a multistage turbine rotor with discs connected to a shaft by a central tension bolt with a spherical washer and an elastic member, and the last disc is mounted on the shaft using a radial annular flange, while the first disc is made with a radial flange, according to the invention, the elastic member:
inserted at its first surface into the Z-shaped front flange of the first disc and brought into contact on the end face;
mounted on the tension bolt at a second surface thereof;
the elastic member abuts against the Z-shaped front flange of the first disc and is circumferentially fixed with the axial pin; and
manufactured with an L-shaped annular flange having a tension bolt retainer circumferentially mounted thereon;
while the third surface of the resilient member adjacent the first hub is made flat.
In contrast to the prototype, the present invention allows the resilient member to be mounted in the Z-shaped front flange of the first disc at its first surface and the flange to be in contact on the end face, which makes it possible to improve the reliability of the GT engine, as this design prevents the turbine first disc hub and the web, which are the most stress concentrated components, from coming into contact with the resilient member and also ensures that the resilient member is aligned with the turbine disc.
Mounting the resilient member on the tension bolt at its second surface improves the reliability of the gas free power turbine rotor assembly as this eliminates radial offset of the tension bolt from the disc.
Retaining the resilient member with the axial pin in the circumferential direction against the front flange of the first disk prevents circumferential movement of the resilient member that would cause rotor assembly imbalance within the gas power turbine.
The elastic member, which is manufactured to have an L-shaped flange and is circumferentially mounted on the tension bolt holder flange, prevents loss of axial fixation of the rotor disk due to circumferential movement of the tension bolts against the disk.
The flat third surface of the resilient member adjacent the first hub prevents the hub from catastrophic failure in the event of interference from the resilient member, such as in the event of increased axial thermal strain of the turbine disk.
Drawings
FIG. 1 is a longitudinal cross-section of a multi-stage turbine rotor;
fig. 2 is an enlarged view of section I.
Detailed Description
The multistage turbine rotor 1 comprises a first disc 2, an intermediate disc 3 and a last disc 4, which overhang the shaft 5 of the rotor 1 against a bearing 6 and are connected by a central tension bolt 7 passing through a spherical washer 8 and an elastic member 9. The last disc 4 with a radial flange 10 leading to the bearing 6 is attached to the shaft 5 by means of a bolted joint 11.
A resilient member 9 having a first surface 12 is mounted in the Z-shaped front flange 13 of the first disc 2 and is in contact with an end surface 14 of the Z-shaped front flange 13, while a second surface 15 of the resilient member 9 is in contact with a body 16 of the tension bolt 7. The elastic member 9 abuts against the Z-shaped front flange 13 of the first disc 2 and is fixed circumferentially with an axial pin 17 and is made with an L-shaped annular flange 18 on which a circumferential retainer 19 of the tensioning bolt 7 is mounted.
The third surface 21 of the elastic member 9 adjacent to the hub 20 of the first disc 2 is made flat to minimize damage to the hub 20 in case of contact of the elastic member with the hub, for example in case of excessive axial strain of the elastic member.
The assembly operates in the following manner.
During operation of the multi-stage turbine rotor assembly 1, the first, intermediate and final disks 2, 3 and 4 have a higher temperature than the central tension bolt 7, resulting in increased axial thermal strain of the disks 2, 3 and 4 compared to the less heated tension bolt 7, which will lead to disk failure. However, this does not occur because the elastic member 9 balances the difference in axial thermal strain between the first disc 2, the intermediate disc 3 and the last disc 4 and the tension bolt 7 due to its elasticity.
In the axial and radial directions, the elastic member 9 is in contact with only the Z-shaped front flange 13 of the first disk 2 in the region of minimum stress of the disk 2, thereby making it possible to improve the reliability of the multistage turbine rotor 1.
Accordingly, embodiments of the present invention having the above-described features and known features of the claimed invention enable the reliability of a multi-stage turbine rotor of a gas turbine engine to be improved by preventing the resilient member from contacting the disk hub and the web during operation of the rotor assembly within the gas power turbine.
Claims (1)
1. A multi-stage turbine rotor, wherein: -the first disc (2), the intermediate disc (3) and the last disc (4) are coupled with the shaft (5) by means of a central tension bolt (7) passing through a spherical washer (8) and an elastic member (9), -the last disc (4) is mounted on the shaft (5) by means of a radial annular flange (10), the first disc being made with a radial flange, characterized in that: the radial flange is a Z-shaped front flange (13); the elastic member (9) is inserted into the Z-shaped front flange (13) of the first disc at the first surface (12) thereof and is in contact with the end surface (14) of the Z-shaped front flange (13); the elastic member is mounted on the tensioning bolt at a second surface (15) thereof; the elastic member abuts against the Z-shaped front flange (13) of the first disc (2) and is fixed circumferentially with an axial pin (17); the elastic member (9) is manufactured to have an L-shaped annular flange (18), and a circumferential retainer (19) of the tension bolt (7) is mounted on the L-shaped annular flange (18); the third surface (21) of the elastic member (9) adjacent to the hub of the first disc is made flat.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2016152403A RU2661566C2 (en) | 2016-12-28 | 2016-12-28 | Multistage turbine rotor |
| RURU2016152403 | 2016-12-28 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108252745A CN108252745A (en) | 2018-07-06 |
| CN108252745B true CN108252745B (en) | 2020-05-05 |
Family
ID=62720836
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710963593.5A Active CN108252745B (en) | 2016-12-28 | 2017-10-17 | Multi-stage turbine rotor |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN108252745B (en) |
| RU (1) | RU2661566C2 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109538302B (en) * | 2018-10-19 | 2021-10-26 | 中国航发湖南动力机械研究所 | Turbine rotor structure and turbine engine |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH257836A (en) * | 1947-08-07 | 1948-10-31 | Sulzer Ag | Rotors for centrifugal machines, in particular for gas turbines. |
| RU2013569C1 (en) * | 1991-07-01 | 1994-05-30 | Лев Алексеевич Кудинов | Turbomachine rotor |
| RU2130124C1 (en) * | 1996-05-28 | 1999-05-10 | Акционерное общество "Авиадвигатель" | Multistage turbine rotor |
| RU2230195C2 (en) * | 2002-05-30 | 2004-06-10 | Открытое акционерное общество "Авиадвигатель" | Multistage turbine rotor |
| RU2506428C1 (en) * | 2012-10-15 | 2014-02-10 | Открытое акционерное общество "Авиадвигатель" | Multistage gas turbine |
| EP2938884B1 (en) * | 2012-12-31 | 2020-11-11 | Rolls-Royce Corporation | Interconnection of rotating components of a compressor of a gas turbine |
| CN203161306U (en) * | 2012-12-31 | 2013-08-28 | 北京全四维动力科技有限公司 | Multi-stage steam turbine adopting wheel disc drawbar structure |
| CN203476510U (en) * | 2013-08-22 | 2014-03-12 | 中国航空工业集团公司沈阳发动机设计研究所 | Connecting structure for power turbine disc of combustion gas turbine |
-
2016
- 2016-12-28 RU RU2016152403A patent/RU2661566C2/en active
-
2017
- 2017-10-17 CN CN201710963593.5A patent/CN108252745B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| RU2661566C2 (en) | 2018-07-17 |
| RU2016152403A (en) | 2018-06-28 |
| RU2016152403A3 (en) | 2018-06-28 |
| CN108252745A (en) | 2018-07-06 |
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