EP1111246A1 - Partie de virole rigidifiée - Google Patents
Partie de virole rigidifiée Download PDFInfo
- Publication number
- EP1111246A1 EP1111246A1 EP99870274A EP99870274A EP1111246A1 EP 1111246 A1 EP1111246 A1 EP 1111246A1 EP 99870274 A EP99870274 A EP 99870274A EP 99870274 A EP99870274 A EP 99870274A EP 1111246 A1 EP1111246 A1 EP 1111246A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- ferrule
- rectifier
- ferrules
- rectifier stage
- sheet
- 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
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
- F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
Definitions
- the present invention relates to a part of the shell provided with a device which allows the stiffen.
- This ferrule can be the inner ferrule or the outer shell of a compressor, preferably a coaxial compressor.
- Coaxial compressors are well known in itself, and are used in several types of application. In particular, they are used in double motors body, turbofans or turbojets. We also note their presence in power plants. These compressors low or high pressure basically consist of several stages of rotating blades separated by stages rectifiers which aim to reposition the vector speed of the fluid leaving the previous stage before send it to the next compartment.
- rectifier stages are made up essentially fixed vanes connecting an outer shell to an inner shell, both concentric.
- the problem is that these rectifier stages are subject to relatively significant efforts due inter alia to vibrations which quickly cause wear and tear tired.
- the present invention aims to provide a new solution that would stiffen the floor rectifier, and in particular the first floor of the compressor, which does not require the use of a excess material and which therefore reduces the cost Manufacturing.
- the present invention relates to a ferrule consisting of a sheet adhering to a part elastomer, characterized in that said elastomer part includes one or more independent metallic elements of the sheet of the ferrule which are at least partially embedded in said elastomeric part. These elements metallic stiffen said ferrule and are thereby called “stiffeners”.
- the present invention also relates to a rectifier stage comprising two ferrules, a ferrule inner and outer shell, at least one of these ferrules being a ferrule according to the invention. These ferrules are connected to each other by a series of fixed vanes.
- said ferrule is the inner ferrule which comprises at minus a metallic element possibly completely submerged in said elastomeric part.
- said ferrule is the outer ferrule which comprises at at least one metallic element partially embedded in said elastomeric part.
- the present invention relates to the use of this rectifier stage as the first stage rectifier in a coaxial compressor, present for example in a turbofan.
- Figure 1 shows a general view of the compression stage of a turbofan.
- Figure 2 shows a detail of the figure 1 showing the stiffening device of the rectifiers at the inner shell.
- FIG. 3 represents a device for stiffening of an inner ferrule of a rectifier according to a first preferred form of the invention.
- FIG. 4 represents a device for stiffening of the outer shell of a rectifier according to another preferred form of the invention.
- Figure 1 shows the compression stage of a turbofan.
- This compression stage is composed of two types of parts: on the one hand, moving parts which are essentially constituted by the rotor 1 provided with blades mobile 3, on the other hand the fixed parts constituting the rectifier stages 2 which are essentially constituted by an inner ferrule 4, an outer ferrule 5 and a series of fixed vanes 6 connecting said ferrules 4 and 5.
- the outer shell 5 is common to several successive rectifier stages, while that the inner ferrules 4 and 4 'are specific to each rectifier stage 2, 2 ', ...
- these interior ferrules 4 are in the form of shaped metal sheets rings, while the fixed blades 6 correspond to simple metal sheets radially connecting a ferrule inner 4 to an outer shroud 5.
- a room elastomer 7 is present so as to secure the blade fixed 6 to the inner shell 4.
- This elastomer part 7 also acts as a joint between two floors successive.
- the gas first passes through the first stage rectifier 2 of the compressor where its speed vector is repositioned to be driven by the first floor rotating blades 3 before reaching the second stage rectifier 2 'to be repositioned again.
- the gas thus undergoes a training cycle - repositioning at after which its kinetic energy decreases gradually as its pressure increases.
- stairs 8 are machined in the sheet of the inner shell 4 to stiffen said ferrule, and in particular the first stage rectifier 2.
- the alternative proposed by this invention consists in stiffening a ferrule by proposing to use a simple sheet for this one (therefore without bandage or stairs).
- FIG 3 shows the principle of stiffening of an inner shell according to a first embodiment of the present invention.
- an elastomer part 7 playing the role of seal and support at fixed dawn 6 is conventionally arranged on said inner ferrule 4.
- elastomer 7 playing the role of seal and support at fixed dawn 6 is conventionally arranged on said inner ferrule 4.
- elastomer 7 is embedded in at least one metallic element 10 which thus indirectly stiffen said ferrule interior 4 and therefore the entire rectifier stage 2 in its together. Therefore, this metallic element is called more commonly stiffener.
- this metal element 10 is independent of the sheet of the inner shell 4.
- the elastomer part 7 which allows conventionally securing a fixed vane 6 of the rectifier to said inner ferrule 4 without direct contact is maintained. This avoids potential faults in the air flow from a weld or rivet.
- the first important advantage of the device according to the invention resides in the machining of the ferrule itself, which is therefore particularly simplified. Indeed, it is no longer necessary to offer bandages or stairs. Because of this, the device is less expensive and safer than the solutions proposed according to the state of the art.
- Another advantage of such a device is that it minimizes checks, in particular by compared to a solution requiring soldering.
- Such a device using an element stiffener according to the present invention offers a large choice in the material that can be used.
- the metal element 10 is completely embedded in the elastomer part 7 present under the sheet of the ferrule interior 4, but it may only be partially embedded in the elastomeric part.
- FIG. 4 represents a device for stiffening of the outer shell 5 of a stage rectifier according to a second preferred embodiment according to the invention.
- a piece in elastomer 17 playing the role of joint allows to join the fixed blade 6 at the outer shell 5 of the stage rectifier 2.
- this elastomer part 17 is partially embedded at least one metallic element 12 which allows to indirectly stiffen this outer shell 5 and therefore the rectifier stage as a whole.
- the element metallic 12 is independent of the sheet of the ferrule exterior 5.
- the element metallic 12 is partially embedded in the room elastomer 17 under the sheet of the outer shell 5, but he could also be completely drowned.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Physical Or Chemical Processes And Apparatus (AREA)
- Exhaust Gas After Treatment (AREA)
Abstract
Description
Claims (6)
- Virole (4,5) constituée d'une tôle à laquelle adhère une pièce élastomère (7,17), caractérisée en ce que ladite pièce élastomère (7,17) comprend un ou plusieurs éléments métalliques (10,12) indépendants de la tôle de la virole (4,5) et au moins partiellement noyés dans ladite pièce élastomère (7,17) et qui permettent de rigidifier ladite virole.
- Etage redresseur (2) comprenant deux viroles, une virole intérieure (4) et une virole extérieure (5) reliées par une aube fixe (6), caractérisé en ce qu'au moins l'une de ces viroles est une virole selon la revendication 1.
- Etage redresseur selon la revendication 2, caractérisé en ce que ladite virole est la virole intérieure (4).
- Etage redresseur selon la revendication 2, caractérisé en ce que ladite virole est la virole extérieure (5).
- Etage redresseur selon la revendication 2, caractérisé en ce que les deux viroles sont des viroles selon la revendication 1.
- Utilisation de l'étage redresseur selon l'une des revendications 2 à 5 comme un étage redresseur dans un compresseur coaxial, de préférence présent dans un turbofan.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP19990870274 EP1111246B1 (fr) | 1999-12-21 | 1999-12-21 | Partie de virole rigidifiée |
DE69910408T DE69910408T2 (de) | 1999-12-21 | 1999-12-21 | Steifes Ringteil |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP19990870274 EP1111246B1 (fr) | 1999-12-21 | 1999-12-21 | Partie de virole rigidifiée |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1111246A1 true EP1111246A1 (fr) | 2001-06-27 |
EP1111246B1 EP1111246B1 (fr) | 2003-08-13 |
Family
ID=8243946
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19990870274 Expired - Lifetime EP1111246B1 (fr) | 1999-12-21 | 1999-12-21 | Partie de virole rigidifiée |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP1111246B1 (fr) |
DE (1) | DE69910408T2 (fr) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1081335A2 (fr) * | 1999-08-09 | 2001-03-07 | United Technologies Corporation | Stator pour une turbomachine et méthode pour la fabrication |
EP1293645A1 (fr) * | 2001-09-14 | 2003-03-19 | Techspace Aero S.A. | Compresseur axial de turbomachine comprenant un dispositif de séparation de flux et procédé d'assemblage de ce dispositif |
EP1426559A1 (fr) * | 2002-12-03 | 2004-06-09 | Techspace Aero S.A. | Virole interieure pour compresseur axial |
GB2442300A (en) * | 2006-09-27 | 2008-04-02 | Rolls Royce Plc | Sheet material gas turbine engine casing components |
EP2194230A1 (fr) * | 2008-12-05 | 2010-06-09 | Siemens Aktiengesellschaft | Agencement d'aube directrice pour une turbomachine axiale |
US8870543B2 (en) | 2010-06-23 | 2014-10-28 | Techspace Aero S.A. | Lightened axial compressor rotor |
EP3095963A1 (fr) * | 2015-05-27 | 2016-11-23 | Techspace Aero S.A. | Aube et virole à fourreau de compresseur de turbomachine axiale |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102009034025A1 (de) * | 2009-07-21 | 2011-01-27 | Mtu Aero Engines Gmbh | Einlaufbelag zur Anordnung an einem Gasturbinenbauteil |
EP2803822B1 (fr) * | 2013-05-13 | 2019-12-04 | Safran Aero Boosters SA | Système de prélèvement d'air de turbomachine axiale |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB991357A (en) * | 1963-12-04 | 1965-05-05 | Rolls Royce | Axial fluid flow machine such as a compressor or turbine |
US3268207A (en) * | 1964-05-07 | 1966-08-23 | Rolls Royce | Bladed structure |
DE1626031A1 (de) * | 1967-08-31 | 1971-01-14 | Daimler Benz Ag | Gehaeuse fuer ein Gasturbinentriebwerk |
DE2706110A1 (de) * | 1977-02-14 | 1978-08-17 | Kuehnle Kopp Kausch Ag | Verdichtergehaeuse vorzugsweise fuer abgasturbolader |
EP0277884A2 (fr) * | 1987-02-05 | 1988-08-10 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Turboréacteur multiflux à couronne externe de redresseur de soufflante frettée sur le carter |
-
1999
- 1999-12-21 DE DE69910408T patent/DE69910408T2/de not_active Expired - Fee Related
- 1999-12-21 EP EP19990870274 patent/EP1111246B1/fr not_active Expired - Lifetime
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB991357A (en) * | 1963-12-04 | 1965-05-05 | Rolls Royce | Axial fluid flow machine such as a compressor or turbine |
US3268207A (en) * | 1964-05-07 | 1966-08-23 | Rolls Royce | Bladed structure |
DE1626031A1 (de) * | 1967-08-31 | 1971-01-14 | Daimler Benz Ag | Gehaeuse fuer ein Gasturbinentriebwerk |
DE2706110A1 (de) * | 1977-02-14 | 1978-08-17 | Kuehnle Kopp Kausch Ag | Verdichtergehaeuse vorzugsweise fuer abgasturbolader |
EP0277884A2 (fr) * | 1987-02-05 | 1988-08-10 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Turboréacteur multiflux à couronne externe de redresseur de soufflante frettée sur le carter |
Cited By (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1081335A2 (fr) * | 1999-08-09 | 2001-03-07 | United Technologies Corporation | Stator pour une turbomachine et méthode pour la fabrication |
SG97911A1 (en) * | 1999-08-09 | 2003-08-20 | United Technologies Corp | Stator assembly for a rotary machine and method for making the stator assembly |
EP1081335A3 (fr) * | 1999-08-09 | 2004-03-17 | United Technologies Corporation | Stator pour une turbomachine et méthode pour la fabrication |
EP1293645A1 (fr) * | 2001-09-14 | 2003-03-19 | Techspace Aero S.A. | Compresseur axial de turbomachine comprenant un dispositif de séparation de flux et procédé d'assemblage de ce dispositif |
EP1426559A1 (fr) * | 2002-12-03 | 2004-06-09 | Techspace Aero S.A. | Virole interieure pour compresseur axial |
GB2442300B (en) * | 2006-09-27 | 2009-01-28 | Rolls Royce Plc | Casing for a gas turbine engine |
GB2442300A (en) * | 2006-09-27 | 2008-04-02 | Rolls Royce Plc | Sheet material gas turbine engine casing components |
US8057170B2 (en) | 2006-09-27 | 2011-11-15 | Rolls-Royce Plc | Intermediate casing for a gas turbine engine |
EP2194230A1 (fr) * | 2008-12-05 | 2010-06-09 | Siemens Aktiengesellschaft | Agencement d'aube directrice pour une turbomachine axiale |
US8870543B2 (en) | 2010-06-23 | 2014-10-28 | Techspace Aero S.A. | Lightened axial compressor rotor |
CN106168229A (zh) * | 2015-05-21 | 2016-11-30 | 航空技术空间股份有限公司 | 用于轴向涡轮机的压缩机的有插座的叶片和护罩 |
CN106168229B (zh) * | 2015-05-21 | 2019-02-15 | 赛峰航空助推器股份有限公司 | 用于轴向涡轮机的压缩机的有插座的叶片和护罩 |
US10280940B2 (en) | 2015-05-21 | 2019-05-07 | Safran Aero Boosters Sa | Blade and shroud with socket for a compressor of an axial turbomachine |
EP3095963A1 (fr) * | 2015-05-27 | 2016-11-23 | Techspace Aero S.A. | Aube et virole à fourreau de compresseur de turbomachine axiale |
BE1023134B1 (fr) * | 2015-05-27 | 2016-11-29 | Techspace Aero S.A. | Aube et virole a fourreau de compresseur de turbomachine axiale |
Also Published As
Publication number | Publication date |
---|---|
DE69910408D1 (de) | 2003-09-18 |
DE69910408T2 (de) | 2004-06-24 |
EP1111246B1 (fr) | 2003-08-13 |
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