EP1213483A1 - Etage redresseur d'un compresseur - Google Patents
Etage redresseur d'un compresseur Download PDFInfo
- Publication number
- EP1213483A1 EP1213483A1 EP00870290A EP00870290A EP1213483A1 EP 1213483 A1 EP1213483 A1 EP 1213483A1 EP 00870290 A EP00870290 A EP 00870290A EP 00870290 A EP00870290 A EP 00870290A EP 1213483 A1 EP1213483 A1 EP 1213483A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blades
- retention
- openings
- ferrule
- stiffening
- 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
- 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
-
- 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
Definitions
- the present invention relates to a stage rectifier of a compressor comprising a succession rectifier or stator stages separated by stages rotor blades, each rectifier stage consisting of fixed vanes connecting an inner ferrule to an outer shell.
- 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 or rotor stages separated by stator stages or rectifiers which have to reposition (straighten) the speed vector of the fluid leaving the previous stage before sending it to the next compartment.
- Each of these rectifier stages is essentially consisting of fixed vanes connecting a ferrule exterior to an interior ferrule, both concentric.
- stiffening solutions have been considered.
- stiffeners in bandage shape machined on the inner shell or on the outer shell and on the non-functional side has been proposed.
- These bandages or stairs can also be made of an insert by welding or riveting.
- the blades are joined to the ferrules, both interior and exterior, by rivets or welds.
- the use of these means of solidarity has the major drawback of disturbing flow and generate a pressure drop in the vein aerodynamic.
- the present invention aims to provide a solution which allows to combine the functions of stiffening of the inner shell and retention of blades of a rectifier stage of an axial compressor.
- the present invention aims to allow a solution that offers great simplicity of assembly and does not require assembly operations additional.
- the present invention also aims to propose a solution in which the aerodynamic vein flux is not affected by the presence of welds or rivets at the ferrule.
- the present invention also aims to allow the realization of a solution of a low cost Student.
- the present invention relates to a stage rectifier of a compressor comprising two ferrules, one inner ferrule and outer ferrule, both concentric and preferably circular and connected one to the other by a series of fixed vanes. At least the ferrule interior has lights or openings that allow the passage of said blades in these lights. Dawn themselves have at their end which will be arranged on the side of the inner shell a second opening intended for allow the passage of a retention part and stiffening having an elastic function. This retention and stiffening piece will allow advantageously the joining of the blades two by two on the non-functional side, i.e. on the side of the face internal, from the inner shell.
- this retention and stiffening part is present in the form of a cut, formed and folded sheet in two and is provided with two flat studs intended to be housed in the openings of two successive blades.
- this piece is folded allows it to provide a spring function for example a spring type " hair pin ".
- the assembly will be quick and easy, and will be carried out by applying precompression to said part of retention and stiffening that we will position then in the two openings of two successive blades and which we will then simply release. Once this part is mounted, the spring effect spreads the two blades successive linked.
- the placement of said piece will be against the edge of the openings of the shell.
- these parts will then be embedded in an elastomeric element.
- Figure 1 shows a general view of the compression stage of a turbofan with a stiffening of the ferrules according to the state of the art.
- Figure 2 shows a detail of the figure 1 showing the stiffening device according to the state of the technique including stiffeners at the inner ferrule.
- FIG. 3 represents the device for retention used in the solution according to this invention.
- FIG. 4 represents the device for retention according to the invention arranged at a ferrule interior and two successive blades so as to allow the stiffening of said inner shell and the blade retention function on this ferrule.
- Each rectifier stage 2,2 ', 2 ", ... is essentially consisting of an inner shell respectively 4.4 ', 4 ", ..., an outer ferrule respectively 5.5 ', 5 “, ... and a series of fixed blades respectively 6.6 ', 6 ", ... connecting said ferrule inner and outer ferrule.
- said interior ferrules 4.4 ', 4 ", ... and said outer ferrules 5.5', 5", ... are specific to each of the rectifier stages 2,2 ', 2 ", ... More specifically, the interior ferrules 4,4 ', 4 ", ... and the outer ferrules 5.5 ', 5 ", ... are presented under the form of metal sheets in the form of rings while the series of fixed blades 6,6 ', 6 ", ... correspond to metal sheets radially connecting an inner ferrule to an outer shell for each series.
- 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 rotor of rotating vanes 3 before joining the second rectifier stage 2 'to be again repositioned in 3 ', etc.
- the gas thus undergoes a cycle training - repositioning after which its kinetic energy gradually decreases while 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 while ensuring a retention function of the vanes at said ferrule.
- the blade retention piece 100 is described in detail in Figure 3. We observe that it is mainly in the form of a cut sheet, formed and folded 110 provided with two flat tenons 117 and 119.
- the shape and composition of the sheet 110 are such that the part 100 can be assimilated to a spring of "hairpin" type.
- Figure 4 shows the basic principle of the present invention and explains how the part of retention and stiffening 100 is arranged at level a ferrule and two successive blades to ensure the both the stiffening of this shell and the retention of two successive blades at this shell.
- the ferrule and preferably the inner ferrule 4
- the ends 51, 51 'of said blades themselves have openings 52.52 '.
- Said blades 60,61,62, ... are secured to the ferrule 4 using the retention and stiffening part 100.
- the flat studs 117 and 119 of said piece of retention and stiffening 100 are housed in openings 52, 52 'of the two successive blades 60,61,62, ...
- the retention and stiffening part 100 thus makes it possible to joining the blades two by two (60 and 61, 62 and 63, etc.) at the level of the rectifier stages.
- we exert on it precompression see arrows in Figure 3 as we would do this using sugar tongs.
- piece 100 so that its flattened studs 117, 119 come to stay in the openings respectively 52 and 52 'of successive blades 60,61,62, ...
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
- d'une part, des pièces mobiles qui sont essentiellement constituées par le rotor 1 muni de plusieurs séries d'aubes mobiles 3,3',3",... correspondant à plusieurs étages rotoriques successifs, et
- d'autre part des pièces fixes constituant les étages statoriques redresseurs 2,2',2",... séparant les étages rotoriques 3,3',3",...
Claims (4)
- Etage redresseur (2) d'un compresseur (1) comprenant une virole extérieure (5) et une virole intérieure (4), toutes deux concentriques et de préférence circulaires et reliées l'une à l'autre par une série d'aubes fixes (60,61,62,...), caractérisé en ce que, au moins la virole intérieure (4) étant pourvue de lumières ou ajours (42,42') qui permettent le passage d'une des extrémités (51,51') desdites aubes (60,61,62,...) dans ces lumières ou ajours (42,42'), les aubes (60,61,62,...) présentent à leur extrémité (51,51') un second ajour (52,52') destiné à permettre le passage d'une pièce de rétention et de rigidification (100) présentant une fonction élastique afin de les maintenir deux par deux.
- Etage redresseur selon la revendication 1, caractérisé en ce que ladite pièce de rétention et de rigidification (100) est un ressort de type «épingle à cheveux» et se présente essentiellement sous la forme d'une tôle découpée, formée et repliée (110) munie de deux tenons plats (117 et 119) qui sont dimensionnés de manière à permettre leur localisation dans les ajours (52,52') de deux aubes successives (60,61;61,62;...).
- Etage redresseur selon la revendication 1 ou 2, caractérisé en ce que l'extrémité (51,51') des aubes fixes (60,61,62,...) est noyée dans un élément élastomère (200).
- Procédé de montage au niveau d'un étage redresseur d'une pièce de rétention et de rigidification (100) présentant une fonction élastique, l'étage redresseur comprenant une virole extérieure (5) et une virole intérieure (4), toutes deux concentriques et de préférence circulaires et reliées l'une à l'autre par une série d'aubes fixes (60,61,62,...), ladite pièce de rétention et de rigidification (100) se présentant essentiellement sous la forme d'une tôle découpée, formée, repliée (110) et munie de deux tenons plats (117 et 119) qui sont dimensionnés de manière à permettre leur localisation dans les ajours (52,52') de deux aubes successives (60,61;61;62;...), caractérisé en ce que l'on exerce une précompression sur ladite pièce de rétention et de rigidification (100), on la place au niveau des aubes successives (60,61,62,...) de manière à ce que les deux tenons (117 et 119) viennent se loger dans les ajours (52, 52') desdites aubes (60,61,62,...), puis on relâche la pression exercée sur ladite pièce de rétention et de rigidification (100).
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE60026686T DE60026686T2 (de) | 2000-12-06 | 2000-12-06 | Statorstufe eines Verdichters |
EP00870290A EP1213483B1 (fr) | 2000-12-06 | 2000-12-06 | Etage redresseur d'un compresseur |
US10/001,122 US6655912B2 (en) | 2000-12-06 | 2001-11-30 | Guide vane stage of a compressor |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP00870290A EP1213483B1 (fr) | 2000-12-06 | 2000-12-06 | Etage redresseur d'un compresseur |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1213483A1 true EP1213483A1 (fr) | 2002-06-12 |
EP1213483B1 EP1213483B1 (fr) | 2006-03-15 |
Family
ID=8175867
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00870290A Expired - Lifetime EP1213483B1 (fr) | 2000-12-06 | 2000-12-06 | Etage redresseur d'un compresseur |
Country Status (3)
Country | Link |
---|---|
US (1) | US6655912B2 (fr) |
EP (1) | EP1213483B1 (fr) |
DE (1) | DE60026686T2 (fr) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2072760A1 (fr) | 2007-12-21 | 2009-06-24 | Techspace aero | Dispositif de fixation d'aubes a une virole d'étage de stator d'une turbomachine et procède de fixation associe |
US9771815B2 (en) | 2012-12-24 | 2017-09-26 | Safran Aero Boosters Sa | Blade-retaining plate with internal cut-outs for a turbomachine stator |
EP3406854A1 (fr) * | 2017-05-26 | 2018-11-28 | United Technologies Corporation | Ensemble stator comportant un clip de rétention pour moteur à turbine à gaz |
EP3412873A1 (fr) * | 2017-06-09 | 2018-12-12 | United Technologies Corporation | Ensemble de stator avec clip de rétention pour moteur à turbine à gaz |
Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6984108B2 (en) * | 2002-02-22 | 2006-01-10 | Drs Power Technology Inc. | Compressor stator vane |
US7651319B2 (en) * | 2002-02-22 | 2010-01-26 | Drs Power Technology Inc. | Compressor stator vane |
US7108480B2 (en) * | 2004-05-28 | 2006-09-19 | General Electric Company | Method and apparatus for balancing turbine rotors |
US20090110552A1 (en) * | 2007-10-31 | 2009-04-30 | Anderson Rodger O | Compressor stator vane repair with pin |
US9045985B2 (en) | 2012-05-31 | 2015-06-02 | United Technologies Corporation | Stator vane bumper ring |
US9777594B2 (en) | 2015-04-15 | 2017-10-03 | Siemens Energy, Inc. | Energy damping system for gas turbine engine stationary vane |
DE102016210454A1 (de) * | 2016-06-14 | 2017-12-14 | MTU Aero Engines AG | Wuchtgewicht für eine Laufschaufel einer Turbinenstufe |
US10655502B2 (en) | 2017-05-26 | 2020-05-19 | United Technologies Corporation | Stator assembly with retention clip for gas turbine engine |
US10533456B2 (en) | 2017-05-26 | 2020-01-14 | United Technologies Corporation | Stator assembly with contoured retention clip for gas turbine engine |
US10557412B2 (en) | 2017-05-30 | 2020-02-11 | United Technologies Corporation | Systems for reducing deflection of a shroud that retains fan exit stators |
US10724389B2 (en) * | 2017-07-10 | 2020-07-28 | Raytheon Technologies Corporation | Stator vane assembly for a gas turbine engine |
US20190078469A1 (en) * | 2017-09-11 | 2019-03-14 | United Technologies Corporation | Fan exit stator assembly retention system |
US10808559B2 (en) | 2018-06-01 | 2020-10-20 | Raytheon Technologies Corporation | Guide vane retention assembly for gas turbine engine |
CN111734499B (zh) * | 2020-04-21 | 2022-08-19 | 中国航发沈阳发动机研究所 | 一种增压级静子叶片限位块及具有其的增压级静子部件 |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB748912A (en) * | 1950-08-01 | 1956-05-16 | Rolls Royce | Improvements in or relating to blade assemblies of compressors and turbines and likemachines |
US2812159A (en) * | 1952-08-19 | 1957-11-05 | Gen Electric | Securing means for turbo-machine blading |
FR2671140A1 (fr) * | 1990-12-27 | 1992-07-03 | Snecma | Aubage redresseur pour compresseur de turbomachine. |
US5569019A (en) * | 1993-12-22 | 1996-10-29 | Alliedsignal Inc. | Tear-away composite fan stator vane |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4452564A (en) * | 1981-11-09 | 1984-06-05 | The Garrett Corporation | Stator vane assembly and associated methods |
FR2697285B1 (fr) * | 1992-10-28 | 1994-11-25 | Snecma | Système de verrouillage d'extrémités d'aubes. |
US6409472B1 (en) * | 1999-08-09 | 2002-06-25 | United Technologies Corporation | Stator assembly for a rotary machine and clip member for a stator assembly |
-
2000
- 2000-12-06 EP EP00870290A patent/EP1213483B1/fr not_active Expired - Lifetime
- 2000-12-06 DE DE60026686T patent/DE60026686T2/de not_active Expired - Fee Related
-
2001
- 2001-11-30 US US10/001,122 patent/US6655912B2/en not_active Expired - Fee Related
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB748912A (en) * | 1950-08-01 | 1956-05-16 | Rolls Royce | Improvements in or relating to blade assemblies of compressors and turbines and likemachines |
US2812159A (en) * | 1952-08-19 | 1957-11-05 | Gen Electric | Securing means for turbo-machine blading |
FR2671140A1 (fr) * | 1990-12-27 | 1992-07-03 | Snecma | Aubage redresseur pour compresseur de turbomachine. |
US5569019A (en) * | 1993-12-22 | 1996-10-29 | Alliedsignal Inc. | Tear-away composite fan stator vane |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2072760A1 (fr) | 2007-12-21 | 2009-06-24 | Techspace aero | Dispositif de fixation d'aubes a une virole d'étage de stator d'une turbomachine et procède de fixation associe |
US9771815B2 (en) | 2012-12-24 | 2017-09-26 | Safran Aero Boosters Sa | Blade-retaining plate with internal cut-outs for a turbomachine stator |
EP3406854A1 (fr) * | 2017-05-26 | 2018-11-28 | United Technologies Corporation | Ensemble stator comportant un clip de rétention pour moteur à turbine à gaz |
US10590783B2 (en) | 2017-05-26 | 2020-03-17 | United Technologies Corporation | Stator assembly with retention clip for gas turbine engine |
EP3412873A1 (fr) * | 2017-06-09 | 2018-12-12 | United Technologies Corporation | Ensemble de stator avec clip de rétention pour moteur à turbine à gaz |
US10767503B2 (en) | 2017-06-09 | 2020-09-08 | Raytheon Technologies Corporation | Stator assembly with retention clip for gas turbine engine |
Also Published As
Publication number | Publication date |
---|---|
EP1213483B1 (fr) | 2006-03-15 |
DE60026686D1 (de) | 2006-05-11 |
DE60026686T2 (de) | 2006-10-05 |
US20020085913A1 (en) | 2002-07-04 |
US6655912B2 (en) | 2003-12-02 |
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