FR3107077B1 - RIGIDIFIED TURBOMACHINE PLATFORM - Google Patents
RIGIDIFIED TURBOMACHINE PLATFORM Download PDFInfo
- Publication number
- FR3107077B1 FR3107077B1 FR2001381A FR2001381A FR3107077B1 FR 3107077 B1 FR3107077 B1 FR 3107077B1 FR 2001381 A FR2001381 A FR 2001381A FR 2001381 A FR2001381 A FR 2001381A FR 3107077 B1 FR3107077 B1 FR 3107077B1
- Authority
- FR
- France
- Prior art keywords
- platform
- main wall
- turbomachine
- stiffener
- rigidified
- 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
- 239000003351 stiffener Substances 0.000 abstract 3
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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
- F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
-
- 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)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
L'invention concerne une plateforme (18) de soufflante (12) de turbomachine (10), qui est destinée à être montée sur un moyeu (14) de la soufflante (12) entre deux aubes (16) adjacentes, la plateforme (18) comportant une paroi principale (20) qui est de forme cintrée selon la direction longitudinale en ayant des bords (24, 26) courbés, un raidisseur (34) qui est monté sur une face interne (36) de la paroi principale (20), caractérisée en ce que le raidisseur (34) comporte au moins deux tronçons (38) rectilignes qui sont inclinés l'un par rapport à l'autre et inclinés par rapport à la direction principale longitudinale, les parois d’extrémité transversales (44, 46) de chacun desdits tronçons (38) ayant leurs tranches externes situées à l’opposé de la paroi principale (20) qui sont libres de manière que la section du raidisseur soit ouverte à l’opposé de la paroi principale (20). Figure pour l’abrégé : Figure 3The invention relates to a platform (18) for a fan (12) of a turbomachine (10), which is intended to be mounted on a hub (14) of the fan (12) between two adjacent blades (16), the platform (18 ) comprising a main wall (20) which is of curved shape in the longitudinal direction having curved edges (24, 26), a stiffener (34) which is mounted on an internal face (36) of the main wall (20) , characterized in that the stiffener (34) comprises at least two rectilinear sections (38) which are inclined relative to each other and inclined relative to the main longitudinal direction, the transverse end walls (44, 46) of each of said sections (38) having their outer edges located opposite the main wall (20) which are free so that the section of the stiffener is open opposite the main wall (20). Figure for abstract: Figure 3
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR2001381A FR3107077B1 (en) | 2020-02-12 | 2020-02-12 | RIGIDIFIED TURBOMACHINE PLATFORM |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR2001381 | 2020-02-12 | ||
FR2001381A FR3107077B1 (en) | 2020-02-12 | 2020-02-12 | RIGIDIFIED TURBOMACHINE PLATFORM |
Publications (2)
Publication Number | Publication Date |
---|---|
FR3107077A1 FR3107077A1 (en) | 2021-08-13 |
FR3107077B1 true FR3107077B1 (en) | 2022-12-23 |
Family
ID=71111525
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR2001381A Active FR3107077B1 (en) | 2020-02-12 | 2020-02-12 | RIGIDIFIED TURBOMACHINE PLATFORM |
Country Status (1)
Country | Link |
---|---|
FR (1) | FR3107077B1 (en) |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6447250B1 (en) * | 2000-11-27 | 2002-09-10 | General Electric Company | Non-integral fan platform |
WO2013104853A2 (en) * | 2012-01-09 | 2013-07-18 | Snecma | Pi-section reinforcing piece made of composite material, notably turbomachine fan platform, and method of manufacturing same |
FR3084104B1 (en) * | 2018-07-20 | 2020-10-23 | Safran Aircraft Engines | RIGIDIFIED PLATFORM |
-
2020
- 2020-02-12 FR FR2001381A patent/FR3107077B1/en active Active
Also Published As
Publication number | Publication date |
---|---|
FR3107077A1 (en) | 2021-08-13 |
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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: 20210813 |
|
PLFP | Fee payment |
Year of fee payment: 3 |
|
PLFP | Fee payment |
Year of fee payment: 4 |
|
PLFP | Fee payment |
Year of fee payment: 5 |