GB670665A - Improvements in or relating to compressors and turbines - Google Patents
Improvements in or relating to compressors and turbinesInfo
- Publication number
- GB670665A GB670665A GB1991349A GB1991349A GB670665A GB 670665 A GB670665 A GB 670665A GB 1991349 A GB1991349 A GB 1991349A GB 1991349 A GB1991349 A GB 1991349A GB 670665 A GB670665 A GB 670665A
- Authority
- GB
- United Kingdom
- Prior art keywords
- platforms
- blades
- july
- engagement
- platform
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Supercharger (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
670,665. Axial-flow compressors and turbines. ROLLS-ROYCE, Ltd., July 12, 1950. [July 28, 1949] No. 19913/49. Classes 110(i) and 110(iii). Each rotor blade 10 has, towards its root end, a platform 10b which forms, together with the platforms of the other blades, a substantially continuous annular wall, relative vibration between the platforms being frictionally damped by metal pads 14, each of which is pressed by centrifugal force against adjacent platforms. Each pad 14 is retained axially by the engagement of a flange 14a between the associated platforms 10b and an interstage spacer ring 12, and retained radially by engagement with an annular shoulder 15, but with sufficient freedom of movement to allow it to bear against the platforms under the action of centrifugal force. To permit relative movement, adjacent platforms 10b are slightly spaced apart, and each platform is joined to a fir-tree root 10c by a flexible stem 10d. If, however, the blades are pivotally attached to the rotor disc 11, as by means of a pin, the flexible stems may be shortened or eliminated. To prevent adjacent blades from vibrating in unison their flexible stems may be of differing crosssection. According to the Provisional Specification, platforms may be provided at the blade tips or between the tips and the roots, in which case the pads 14 can be formed with retaining tags which are bent over to engage the radially outer side.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1991349A GB670665A (en) | 1949-07-28 | 1949-07-28 | Improvements in or relating to compressors and turbines |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1991349A GB670665A (en) | 1949-07-28 | 1949-07-28 | Improvements in or relating to compressors and turbines |
Publications (1)
Publication Number | Publication Date |
---|---|
GB670665A true GB670665A (en) | 1952-04-23 |
Family
ID=10137229
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1991349A Expired GB670665A (en) | 1949-07-28 | 1949-07-28 | Improvements in or relating to compressors and turbines |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB670665A (en) |
Cited By (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2836392A (en) * | 1953-06-03 | 1958-05-27 | United Aircraft Corp | Disc vibration damping means |
US2912222A (en) * | 1952-08-02 | 1959-11-10 | Gen Electric | Turbomachine blading and method of manufacture thereof |
US2916257A (en) * | 1953-12-30 | 1959-12-08 | Gen Electric | Damping turbine buckets |
US2948505A (en) * | 1956-12-26 | 1960-08-09 | Gen Electric | Gas turbine rotor |
US2957675A (en) * | 1956-05-07 | 1960-10-25 | Gen Electric | Damping means |
US2985426A (en) * | 1954-07-15 | 1961-05-23 | Rolls Royce | Bladed rotor construction for axialflow fluid machine |
US2997274A (en) * | 1953-04-13 | 1961-08-22 | Morgan P Hanson | Turbo-machine blade vibration damper |
US3037741A (en) * | 1958-12-29 | 1962-06-05 | Gen Electric | Damping turbine buckets |
US3047268A (en) * | 1960-03-14 | 1962-07-31 | Stanley L Leavitt | Blade retention device |
US3396905A (en) * | 1966-09-28 | 1968-08-13 | Gen Motors Corp | Ducted fan |
FR2376958A1 (en) * | 1977-01-11 | 1978-08-04 | Rolls Royce | MOBILE COMPRESSOR STAGE |
FR2527260A1 (en) * | 1982-05-18 | 1983-11-25 | Snecma | RETRACTABLE DAMPING DEVICE FOR AUBES OF A TURBOMACHINE |
US4455122A (en) * | 1981-12-14 | 1984-06-19 | United Technologies Corporation | Blade to blade vibration damper |
US4723889A (en) * | 1985-07-16 | 1988-02-09 | Societe Nationale D'etude Et De Constructions De Moteur D'aviation "S.N.E.C.M.A." | Fan or compressor angular clearance limiting device |
EP0297120A1 (en) * | 1986-12-29 | 1989-01-04 | United Technologies Corp | Interblade seal for turbomachine rotor. |
GB2227192A (en) * | 1988-12-29 | 1990-07-25 | Gen Electric | Damped gas turbine engine airfoil row |
US5156528A (en) * | 1991-04-19 | 1992-10-20 | General Electric Company | Vibration damping of gas turbine engine buckets |
US5318405A (en) * | 1993-03-17 | 1994-06-07 | General Electric Company | Turbine disk interstage seal anti-rotation key through disk dovetail slot |
WO1994012773A1 (en) * | 1992-11-24 | 1994-06-09 | United Technologies Corporation | Gas turbine blade damper |
EP2418356A1 (en) * | 2010-08-10 | 2012-02-15 | Siemens Aktiengesellschaft | Turbine inter-platform damper and corresponding turbine blade |
US10196896B2 (en) | 2015-04-13 | 2019-02-05 | Rolls-Royce Plc | Rotor damper |
FR3075284A1 (en) * | 2017-12-18 | 2019-06-21 | Safran Aircraft Engines | SHOCK ABSORBER DEVICE |
US11536157B2 (en) | 2017-12-18 | 2022-12-27 | Safran Aircraft Engines | Damping device |
-
1949
- 1949-07-28 GB GB1991349A patent/GB670665A/en not_active Expired
Cited By (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2912222A (en) * | 1952-08-02 | 1959-11-10 | Gen Electric | Turbomachine blading and method of manufacture thereof |
US2997274A (en) * | 1953-04-13 | 1961-08-22 | Morgan P Hanson | Turbo-machine blade vibration damper |
US2836392A (en) * | 1953-06-03 | 1958-05-27 | United Aircraft Corp | Disc vibration damping means |
US2916257A (en) * | 1953-12-30 | 1959-12-08 | Gen Electric | Damping turbine buckets |
US2985426A (en) * | 1954-07-15 | 1961-05-23 | Rolls Royce | Bladed rotor construction for axialflow fluid machine |
US2957675A (en) * | 1956-05-07 | 1960-10-25 | Gen Electric | Damping means |
US2948505A (en) * | 1956-12-26 | 1960-08-09 | Gen Electric | Gas turbine rotor |
US3037741A (en) * | 1958-12-29 | 1962-06-05 | Gen Electric | Damping turbine buckets |
US3047268A (en) * | 1960-03-14 | 1962-07-31 | Stanley L Leavitt | Blade retention device |
US3396905A (en) * | 1966-09-28 | 1968-08-13 | Gen Motors Corp | Ducted fan |
FR2376958A1 (en) * | 1977-01-11 | 1978-08-04 | Rolls Royce | MOBILE COMPRESSOR STAGE |
US4455122A (en) * | 1981-12-14 | 1984-06-19 | United Technologies Corporation | Blade to blade vibration damper |
US4516910A (en) * | 1982-05-18 | 1985-05-14 | S.N.E.C.M.A. | Retractable damping device for blades of a turbojet |
EP0095409A1 (en) * | 1982-05-18 | 1983-11-30 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Damping device for the vanes in the rotor of a turbo machine |
FR2527260A1 (en) * | 1982-05-18 | 1983-11-25 | Snecma | RETRACTABLE DAMPING DEVICE FOR AUBES OF A TURBOMACHINE |
US4723889A (en) * | 1985-07-16 | 1988-02-09 | Societe Nationale D'etude Et De Constructions De Moteur D'aviation "S.N.E.C.M.A." | Fan or compressor angular clearance limiting device |
EP0297120A1 (en) * | 1986-12-29 | 1989-01-04 | United Technologies Corp | Interblade seal for turbomachine rotor. |
EP0297120A4 (en) * | 1986-12-29 | 1990-09-05 | United Technologies Corporation | Interblade seal for turbomachine rotor |
GB2227192A (en) * | 1988-12-29 | 1990-07-25 | Gen Electric | Damped gas turbine engine airfoil row |
US5156528A (en) * | 1991-04-19 | 1992-10-20 | General Electric Company | Vibration damping of gas turbine engine buckets |
WO1994012773A1 (en) * | 1992-11-24 | 1994-06-09 | United Technologies Corporation | Gas turbine blade damper |
US5318405A (en) * | 1993-03-17 | 1994-06-07 | General Electric Company | Turbine disk interstage seal anti-rotation key through disk dovetail slot |
EP2418356A1 (en) * | 2010-08-10 | 2012-02-15 | Siemens Aktiengesellschaft | Turbine inter-platform damper and corresponding turbine blade |
US10196896B2 (en) | 2015-04-13 | 2019-02-05 | Rolls-Royce Plc | Rotor damper |
US10385696B2 (en) | 2015-04-13 | 2019-08-20 | Rolls-Royce Plc | Rotor damper |
FR3075284A1 (en) * | 2017-12-18 | 2019-06-21 | Safran Aircraft Engines | SHOCK ABSORBER DEVICE |
US11421534B2 (en) | 2017-12-18 | 2022-08-23 | Safran Aircraft Engines | Damping device |
US11536157B2 (en) | 2017-12-18 | 2022-12-27 | Safran Aircraft Engines | Damping device |
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