FR2411959A1 - Perfectionnements aux turbomachines - Google Patents
Perfectionnements aux turbomachinesInfo
- Publication number
- FR2411959A1 FR2411959A1 FR7835354A FR7835354A FR2411959A1 FR 2411959 A1 FR2411959 A1 FR 2411959A1 FR 7835354 A FR7835354 A FR 7835354A FR 7835354 A FR7835354 A FR 7835354A FR 2411959 A1 FR2411959 A1 FR 2411959A1
- Authority
- FR
- France
- Prior art keywords
- radius
- disc
- audit
- rim
- extending
- 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.)
- Granted
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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
- F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
-
- 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
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/55—Seals
- F05D2240/56—Brush seals
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
L'INVENTION CONCERNE UN DISQUE DE TURBINE COMPRENANT UNE PLURALITE DE FENTES AGENCEES POUR RECEVOIR LES TALONS DES AUBES DE ROTOR, LES SURFACES RADIALEMENT LES PLUS INTERIEURES DE TOUTES LESDITES FENTES SE TROUVANT A UN PREMIER RAYON. CE DISQUE COMPORTE UN REBORD CIRCONFERENTIEL CONTINU S'ETENDANT CIRCONFERENTIELLEMENT A PARTIR DE LA BORDURE DU DISQUE SUR AU MOINS L'UNE DE SES FACES, LEDIT REBORD FORMANT UNE SURFACE CONTINUE S'ETENDANT CIRCONFERENTIELLEMENT A UN RAYON INFERIEUR AUDIT PREMIER RAYON, ET ETANT RELIE AU DISQUE A UN RAYON SUPERIEUR AUDIT PREMIER RAYON, ET UN CANAL CONTINU D'AIR DE REFROIDISSEMENT S'ETENDANT CIRCONFERENTIELLEMENT, OUVERT VERS LE COTE RADIALEMENT INTERIEUR DU REBORD ET S'ETENDANT RADIALEMENT VERS L'EXTERIEUR ENTRE LE REBORD ET LADITE FACE DU DISQUE.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB5259777 | 1977-12-17 |
Publications (2)
Publication Number | Publication Date |
---|---|
FR2411959A1 true FR2411959A1 (fr) | 1979-07-13 |
FR2411959B1 FR2411959B1 (fr) | 1982-02-19 |
Family
ID=10464535
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR7835354A Granted FR2411959A1 (fr) | 1977-12-17 | 1978-12-15 | Perfectionnements aux turbomachines |
Country Status (4)
Country | Link |
---|---|
US (1) | US4275990A (fr) |
JP (1) | JPS54116514A (fr) |
DE (1) | DE2853586C2 (fr) |
FR (1) | FR2411959A1 (fr) |
Families Citing this family (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4807433A (en) * | 1983-05-05 | 1989-02-28 | General Electric Company | Turbine cooling air modulation |
FR2603333B1 (fr) * | 1986-09-03 | 1990-07-20 | Snecma | Rotor de turbomachine comportant un moyen de verrouillage axial et d'etancheite d'aubes montees dans des brochages axiaux du disque et procede de montage |
US4923370A (en) * | 1988-11-28 | 1990-05-08 | Allied-Signal Inc. | Radial turbine wheel |
DE19705442A1 (de) * | 1997-02-13 | 1998-08-20 | Bmw Rolls Royce Gmbh | Turbinen-Laufradscheibe mit Kühlluftkanälen |
US6234756B1 (en) | 1998-10-26 | 2001-05-22 | Allison Advanced Development Company | Segmented ring blade retainer |
GB0227745D0 (en) * | 2002-11-28 | 2003-01-08 | Rolls Royce Plc | Blade cooling |
US7192245B2 (en) * | 2004-12-03 | 2007-03-20 | Pratt & Whitney Canada Corp. | Rotor assembly with cooling air deflectors and method |
ES2321862T3 (es) * | 2006-09-25 | 2009-06-12 | Siemens Aktiengesellschaft | Rotor de turbina con placas de bloqueo y correspondiente procedimiento de montaje. |
US8459954B2 (en) * | 2010-01-19 | 2013-06-11 | United Technologies Corporation | Torsional flexing energy absorbing blade lock |
FR3000763B1 (fr) * | 2013-01-04 | 2016-07-15 | Snecma | Disque de rotor muni d’une pluralite de crochets |
BR102013021427B1 (pt) * | 2013-08-16 | 2022-04-05 | Luis Antonio Waack Bambace | Turbomáquinas axiais de carcaça rotativa e elemento central fixo |
EP2843196B1 (fr) * | 2013-09-03 | 2020-04-15 | Safran Aero Boosters SA | Compresseur de turbomachine et turboachine associée |
FR3091722B1 (fr) * | 2019-01-11 | 2020-12-25 | Safran Aircraft Engines | Rotor, turbine équipée d’un tel rotor et turbomachine équipée d’une telle turbine |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR990770A (fr) * | 1949-05-09 | 1951-09-26 | Procédé pour l'augmentation de la puissance de moteurs a turbine à gaz, en particulier de moteurs d'aviation dont l'aubage de la turbine est constitué par des aubes creuses refroidies par air et appareils pour la mise en oeuvre de ce procédé | |
FR1526683A (fr) * | 1967-06-12 | 1968-05-24 | United Aircraft Corp | Disque de turbine refroidi |
FR1599371A (fr) * | 1967-12-21 | 1970-07-15 | ||
FR2028539A1 (fr) * | 1969-01-17 | 1970-10-09 | Westinghouse Electric Corp | |
US3768921A (en) * | 1972-02-24 | 1973-10-30 | Aircraft Corp | Chamber pressure control using free vortex flow |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CA590470A (en) * | 1960-01-12 | Rolls-Royce Limited | Bladed rotor for axial-flow fluid machines | |
US2647368A (en) * | 1949-05-09 | 1953-08-04 | Hermann Oestrich | Method and apparatus for internally cooling gas turbine blades with air, fuel, and water |
US2951340A (en) * | 1956-01-03 | 1960-09-06 | Curtiss Wright Corp | Gas turbine with control mechanism for turbine cooling air |
GB1152331A (en) * | 1966-05-18 | 1969-05-14 | Rolls Royce | Improvements in Gas Turbine Blade Cooling |
US3575528A (en) * | 1968-10-28 | 1971-04-20 | Gen Motors Corp | Turbine rotor cooling |
DE1957614C3 (de) * | 1969-11-15 | 1974-03-14 | Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen | Laufschaufelkranz für Gasturbinentriebwerke mit hoher DrehzahL |
US3826084A (en) * | 1970-04-28 | 1974-07-30 | United Aircraft Corp | Turbine coolant flow system |
US3703808A (en) * | 1970-12-18 | 1972-11-28 | Gen Electric | Turbine blade tip cooling air expander |
US3689176A (en) * | 1971-04-02 | 1972-09-05 | Gen Electric | Turbomachinery rotor consturction |
US3748060A (en) * | 1971-09-14 | 1973-07-24 | Westinghouse Electric Corp | Sideplate for turbine blade |
US3849025A (en) * | 1973-03-28 | 1974-11-19 | Gen Electric | Serpentine cooling channel construction for open-circuit liquid cooled turbine buckets |
US3853425A (en) * | 1973-09-07 | 1974-12-10 | Westinghouse Electric Corp | Turbine rotor blade cooling and sealing system |
US3888601A (en) * | 1974-05-23 | 1975-06-10 | Gen Electric | Turbomachine with balancing means |
US4033705A (en) * | 1976-04-26 | 1977-07-05 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Blade retainer assembly |
US4221542A (en) * | 1977-12-27 | 1980-09-09 | General Electric Company | Segmented blade retainer |
-
1978
- 1978-11-30 US US05/965,057 patent/US4275990A/en not_active Expired - Lifetime
- 1978-12-12 DE DE2853586A patent/DE2853586C2/de not_active Expired
- 1978-12-15 JP JP15566978A patent/JPS54116514A/ja active Granted
- 1978-12-15 FR FR7835354A patent/FR2411959A1/fr active Granted
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR990770A (fr) * | 1949-05-09 | 1951-09-26 | Procédé pour l'augmentation de la puissance de moteurs a turbine à gaz, en particulier de moteurs d'aviation dont l'aubage de la turbine est constitué par des aubes creuses refroidies par air et appareils pour la mise en oeuvre de ce procédé | |
FR1526683A (fr) * | 1967-06-12 | 1968-05-24 | United Aircraft Corp | Disque de turbine refroidi |
FR1599371A (fr) * | 1967-12-21 | 1970-07-15 | ||
FR2028539A1 (fr) * | 1969-01-17 | 1970-10-09 | Westinghouse Electric Corp | |
US3768921A (en) * | 1972-02-24 | 1973-10-30 | Aircraft Corp | Chamber pressure control using free vortex flow |
Also Published As
Publication number | Publication date |
---|---|
JPS54116514A (en) | 1979-09-10 |
DE2853586C2 (de) | 1984-01-05 |
FR2411959B1 (fr) | 1982-02-19 |
JPS6211163B2 (fr) | 1987-03-11 |
DE2853586A1 (de) | 1979-07-19 |
US4275990A (en) | 1981-06-30 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
ST | Notification of lapse |