GB1336808A - Arrangement of bearings in a gas turbine jet engine - Google Patents
Arrangement of bearings in a gas turbine jet engineInfo
- Publication number
- GB1336808A GB1336808A GB1000072A GB1000072A GB1336808A GB 1336808 A GB1336808 A GB 1336808A GB 1000072 A GB1000072 A GB 1000072A GB 1000072 A GB1000072 A GB 1000072A GB 1336808 A GB1336808 A GB 1336808A
- Authority
- GB
- United Kingdom
- Prior art keywords
- turbine
- housing
- rotor
- shaft
- secured
- 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.)
- Expired
Links
Classifications
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
1336808 Gas turbine engines - arrangements of bearings SOC NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION 3 March 1972 [3 March 1971] 10000/72 Heading FIG [Also in Division F2] The invention relates to a method of mounting a thrust bearing of a compressor and turbine assembly of a gas turbine engine whereby in the event of shaft failure, the turbine rotor and the thrust bearing may move axially rearwardly whereby the turbine rotor blades engage the stator blades so preventing excessive speed of the rotor. The invention is described with reference to a gas turbine ducted fan engine, the turbine rotor being indicated at 4, the compressor and turbine shaft at 3, and the thrust bearing assembly at 13. The inner race 15 is secured to the shaft 3 by screwed ring 16 and the outer race 20 is secured within a housing 21 by a screwed ring 20a, a member 22 against which the outer race 20 abuts being secured to the housing 21 by means 22a. The housing 21 is formed integrally with a thin disc portion 21c so that it is axially movable, the outer periphery of the disc portion being secured to fixed structure 14 at 23. In normal operation the axial thrust on the compressor and turbine assembly is forward so that a projection 21a of the housing 21 abuts against a projection 14c of the fixed structure 14. In the event of shaft failure the shaft 3 and turbine rotor 4 are permitted to move axially rearwardly by flexing of the thin disc 21c whereby the rotor blades contact the stator blades so preventing excessive rotational speed of the rotor; the housing 21 moves axially rearwardly so that the abutting portions 21a, 14c disengage. The member 21 is guided within the structure 14 at the points 14b, 14d.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US00245446A US3795779A (en) | 1972-04-19 | 1972-04-19 | Steering shaft, gear shift lever switch assembly |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR7107283A FR2131797B1 (en) | 1971-03-03 | 1971-03-03 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1336808A true GB1336808A (en) | 1973-11-14 |
Family
ID=9072813
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1000072A Expired GB1336808A (en) | 1971-03-03 | 1972-04-19 | Arrangement of bearings in a gas turbine jet engine |
Country Status (3)
Country | Link |
---|---|
DE (1) | DE2209713C3 (en) |
FR (1) | FR2131797B1 (en) |
GB (1) | GB1336808A (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3705703A1 (en) * | 2013-03-15 | 2020-09-09 | United Technologies Corporation | Shield for arranging between a bearing and a rotating seal element |
CN112888868A (en) * | 2018-09-13 | 2021-06-01 | 赛峰飞机发动机公司 | System for axial retention of a ring of a rolling element bearing |
CN114688100A (en) * | 2022-05-31 | 2022-07-01 | 成都中科翼能科技有限公司 | Assembly method of gas compressor of gas turbine engine |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2639073B1 (en) * | 1988-11-17 | 1990-12-21 | Snecma | BEARING ENCLOSURE HAVING A DEFLECTOR SCREEN |
FR2640684B1 (en) * | 1988-12-15 | 1994-01-28 | Snecma | TURBOMACHINE COMPRISING A BRAKING DEVICE BETWEEN TURBINE ROTOR AND EXHAUST CASING |
DE10358953A1 (en) | 2003-12-15 | 2005-07-28 | Man Turbo Ag | Storage of the rotor of a gas turbine |
-
1971
- 1971-03-03 FR FR7107283A patent/FR2131797B1/fr not_active Expired
-
1972
- 1972-03-01 DE DE19722209713 patent/DE2209713C3/en not_active Expired
- 1972-04-19 GB GB1000072A patent/GB1336808A/en not_active Expired
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3705703A1 (en) * | 2013-03-15 | 2020-09-09 | United Technologies Corporation | Shield for arranging between a bearing and a rotating seal element |
US11255272B2 (en) | 2013-03-15 | 2022-02-22 | Raytheon Technologies Corporation | Shield for arranging between a bearing and a rotating seal element |
CN112888868A (en) * | 2018-09-13 | 2021-06-01 | 赛峰飞机发动机公司 | System for axial retention of a ring of a rolling element bearing |
CN114688100A (en) * | 2022-05-31 | 2022-07-01 | 成都中科翼能科技有限公司 | Assembly method of gas compressor of gas turbine engine |
Also Published As
Publication number | Publication date |
---|---|
DE2209713A1 (en) | 1972-09-21 |
DE2209713B2 (en) | 1977-08-18 |
FR2131797B1 (en) | 1975-02-21 |
DE2209713C3 (en) | 1978-04-13 |
FR2131797A1 (en) | 1972-11-17 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed | ||
PCNP | Patent ceased through non-payment of renewal fee |