FR2050550A5 - Governor for turbine rotors - Google Patents
Governor for turbine rotorsInfo
- Publication number
- FR2050550A5 FR2050550A5 FR6920186A FR6920186A FR2050550A5 FR 2050550 A5 FR2050550 A5 FR 2050550A5 FR 6920186 A FR6920186 A FR 6920186A FR 6920186 A FR6920186 A FR 6920186A FR 2050550 A5 FR2050550 A5 FR 2050550A5
- Authority
- FR
- France
- Prior art keywords
- governor
- turbine
- turbine rotors
- mixed
- fibres
- 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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/006—Arrangements of brakes
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Governor consists of a coaxial crown of suitable frictional material mounted within the the turbine box facing the blades. The material may be of graphite, or mineral powder or fibres mixed with thermosetting resin, e.g. glass fibres or asbestos mixed with phenolic resin. The governor limits the speed of the turbine to prevent breakdown due to excessive temperature.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR6920186A FR2050550A5 (en) | 1969-06-17 | 1969-06-17 | Governor for turbine rotors |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR6920186A FR2050550A5 (en) | 1969-06-17 | 1969-06-17 | Governor for turbine rotors |
Publications (1)
Publication Number | Publication Date |
---|---|
FR2050550A5 true FR2050550A5 (en) | 1971-04-02 |
Family
ID=9035886
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR6920186A Expired FR2050550A5 (en) | 1969-06-17 | 1969-06-17 | Governor for turbine rotors |
Country Status (1)
Country | Link |
---|---|
FR (1) | FR2050550A5 (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1503042A1 (en) * | 2003-07-31 | 2005-02-02 | BorgWarner Inc. | Braking system in a turbocharger |
FR2916482A1 (en) * | 2007-05-25 | 2008-11-28 | Snecma Sa | Turbine braking system for gas turbine engine, has two braking units integrated to stator and rotor, respectively and abrasive element eroded with ring shaped element, where braking units are contacted by axial displacement of rotor |
EP2971600A4 (en) * | 2013-03-13 | 2016-12-14 | United Technologies Corp | Geared architecture to protect critical hardware during fan blade out |
-
1969
- 1969-06-17 FR FR6920186A patent/FR2050550A5/en not_active Expired
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1503042A1 (en) * | 2003-07-31 | 2005-02-02 | BorgWarner Inc. | Braking system in a turbocharger |
FR2916482A1 (en) * | 2007-05-25 | 2008-11-28 | Snecma Sa | Turbine braking system for gas turbine engine, has two braking units integrated to stator and rotor, respectively and abrasive element eroded with ring shaped element, where braking units are contacted by axial displacement of rotor |
EP2071136A3 (en) * | 2007-05-25 | 2010-03-10 | Snecma | Braking device for a turbine in a gas turbine motor in the event of shaft breakage |
US8161727B2 (en) | 2007-05-25 | 2012-04-24 | Snecma | System providing braking in a gas turbine engine in the event of the turbine shaft breaking |
EP2971600A4 (en) * | 2013-03-13 | 2016-12-14 | United Technologies Corp | Geared architecture to protect critical hardware during fan blade out |
US10107134B2 (en) | 2013-03-13 | 2018-10-23 | United Technologies Corporation | Geared architecture to protect critical hardware during fan blade out |
EP3575561A1 (en) * | 2013-03-13 | 2019-12-04 | United Technologies Corporation | A turbofan engine |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
ST | Notification of lapse |