FR3116305B1 - CONNECTING SHAFT OF A HIGH PRESSURE BODY OF A TURBOMACHINE - Google Patents
CONNECTING SHAFT OF A HIGH PRESSURE BODY OF A TURBOMACHINE Download PDFInfo
- Publication number
- FR3116305B1 FR3116305B1 FR2011813A FR2011813A FR3116305B1 FR 3116305 B1 FR3116305 B1 FR 3116305B1 FR 2011813 A FR2011813 A FR 2011813A FR 2011813 A FR2011813 A FR 2011813A FR 3116305 B1 FR3116305 B1 FR 3116305B1
- Authority
- FR
- France
- Prior art keywords
- connecting shaft
- turbomachine
- pressure body
- high pressure
- annular flange
- 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.)
- Active
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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/026—Shaft to 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
- 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
- F05D2250/00—Geometry
- F05D2250/60—Structure; Surface texture
- F05D2250/61—Structure; Surface texture corrugated
-
- 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
- F05D2250/00—Geometry
- F05D2250/60—Structure; Surface texture
- F05D2250/61—Structure; Surface texture corrugated
- F05D2250/611—Structure; Surface texture corrugated undulated
Abstract
L’invention concerne un arbre de liaison (200) d’un corps haute pression de turbomachine, ledit arbre de liaison (200) étant configuré pour coupler en rotation un module rotatif, ledit arbre de liaison (200) comportant un corps (220) présentant au niveau de l’une de ses extrémités une bride annulaire (210) configurée pour être couplée au module rotatif (100), ledit arbre de liaison (200) étant caractérisé en ce qu’il comporte une première gorge circonférentielle (230) ménagées au niveau de la paroi du corps (220) dans une région voisine de ladite bride annulaire (210) et s’étendant au moins partiellement sur une portion circonférentielle de la paroi du corps (220). Figure de l’abrégé : Figure 1.The invention relates to a connecting shaft (200) of a turbomachine high-pressure body, said connecting shaft (200) being configured to couple in rotation a rotary module, said connecting shaft (200) comprising a body (220) having at one of its ends an annular flange (210) configured to be coupled to the rotary module (100), said connecting shaft (200) being characterized in that it comprises a first circumferential groove (230) provided at the body wall (220) in a region adjacent to said annular flange (210) and extending at least partially over a circumferential portion of the body wall (220). Abstract Figure: Figure 1.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR2011813A FR3116305B1 (en) | 2020-11-18 | 2020-11-18 | CONNECTING SHAFT OF A HIGH PRESSURE BODY OF A TURBOMACHINE |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR2011813 | 2020-11-18 | ||
FR2011813A FR3116305B1 (en) | 2020-11-18 | 2020-11-18 | CONNECTING SHAFT OF A HIGH PRESSURE BODY OF A TURBOMACHINE |
Publications (2)
Publication Number | Publication Date |
---|---|
FR3116305A1 FR3116305A1 (en) | 2022-05-20 |
FR3116305B1 true FR3116305B1 (en) | 2023-06-30 |
Family
ID=75339815
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR2011813A Active FR3116305B1 (en) | 2020-11-18 | 2020-11-18 | CONNECTING SHAFT OF A HIGH PRESSURE BODY OF A TURBOMACHINE |
Country Status (1)
Country | Link |
---|---|
FR (1) | FR3116305B1 (en) |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3072749B1 (en) * | 2017-10-24 | 2020-01-03 | Safran Transmission Systems | EPICYCLOIDAL GEAR TRAIN |
FR3086343B1 (en) * | 2018-09-24 | 2020-09-04 | Safran Aircraft Engines | TURBOMACHINE WITH REDUCER FOR AN AIRCRAFT |
-
2020
- 2020-11-18 FR FR2011813A patent/FR3116305B1/en active Active
Also Published As
Publication number | Publication date |
---|---|
FR3116305A1 (en) | 2022-05-20 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PLFP | Fee payment |
Year of fee payment: 2 |
|
PLSC | Publication of the preliminary search report |
Effective date: 20220520 |
|
PLFP | Fee payment |
Year of fee payment: 3 |
|
PLFP | Fee payment |
Year of fee payment: 4 |