WO2013011235A1 - Aube de turbomachine et procédé de fabrication de cette aube - Google Patents
Aube de turbomachine et procédé de fabrication de cette aube Download PDFInfo
- Publication number
- WO2013011235A1 WO2013011235A1 PCT/FR2012/051690 FR2012051690W WO2013011235A1 WO 2013011235 A1 WO2013011235 A1 WO 2013011235A1 FR 2012051690 W FR2012051690 W FR 2012051690W WO 2013011235 A1 WO2013011235 A1 WO 2013011235A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- plate
- main part
- seal
- blade
- ribs
- Prior art date
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
- F01D5/12—Blades
- F01D5/14—Form or construction
-
- 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
-
- 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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- 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
-
- 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
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- 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
- 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
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
Definitions
- the subject of the invention is a turbomachine blade of the kind comprising a plate attached to a main structural part of the blade and which can find particular use for OGV (outlet guide vane).
- OGV outlet guide vane
- the invention has been designed to obviate these disadvantages, and it is indicated by an excellent positional accuracy between the main part and the plate prior to their assembly, and by a much safer obtaining of the sealing of the cavity after assembly. Another advantage is that the level of vibration of which the dawn is the seat is reduced.
- the invention can be defined as a turbomachine blade comprising a main part containing a cavity and ribs extending into the cavity, and a plate joined to the main part by closing the cavity and resting on the ribs, characterized in that the plate is joined to the main part resting on a bearing surface of the main part, set back with respect to an outer face of the main part which surrounds it, by a region adjacent to a outer edge of the plate.
- the plate is flush with the outer surface of the main part, and the blade thus has a surface of perfect or almost perfect continuity, without final machining.
- the support of the plate on the ribs reduces its ability to vibrate.
- the interlocking of the plate in the bearing surface set back from the outer surface of the main part makes it possible not to expose the sealing means to the outer surface and thus reduces the risk of them being accidentally damaged, or eliminated by a final machining of dawn, which is not essential in the invention.
- Another advantage of the nesting of the plate in the main part is that it can be placed in the correct position without care during assembly.
- the outer edge of the plate extends over a groove of the main portion which surrounds the bearing surface and is filled by a seal of elastic material, the seal being compressed by the outer edge. .
- the seal is guaranteed by the compression of the seal by the outer edge of the plate.
- Positioning the plate and the main part is advantageously provided by centering pins penetrating into aligned bores; it is then advantageous for the seal to extend into these bores once the centering pins have been removed.
- the holes may extend to the ribs, near their connection to the main part itself.
- Another aspect of the invention is a method characterized in that it consists, after having laid the plate on the ribs and before fixing the plate on the main part, to introduce centering pins in the aligned bores.
- FIG 1 is a turbomachine part where the invention is present
- FIG. 2 is an exploded view of a blade according to the invention
- FIG. 3 is a section of the dawn
- FIG. 4 is a detail of FIG. 3;
- FIGS. 5 and 6 are details of the main part of the blade,
- FIGS. 7 to 9 illustrate alternative embodiments for the ribs of the blades.
- FIG. 1 represents an intermediate casing of a turbomachine comprising an outer shell 1, an inner shell 2 and a circle of blades 3 placed between the ferrules 1 and 2.
- a few radial arms 4 further connect the ferrules 1 and 2 in order to reinforce assembly.
- the blades 3 are arranged through a gas flow they contribute to straighten between two stages of blades, as is usual in this type of devices.
- FIG. 2 illustrates the constituents of the blades 3: first there is a main part 5, comprising the greater part of the structure of the blade 3 as well as legs 6 or platforms 7 of bolted connection to ferrules 1 and 2; the main part 5 is continuous on one face of the blade 3 but has a cavity 8 which opens on the other side. Ribs 9 extend into this cavity 8; their number and their arrangement are not very important and there is shown here a single rib 9, which extends from the inner edge to the outer edge of the cavity 8; ribs that do not completely traverse the cavity would also be possible.
- the other elements of the blade 3 are a smooth plate 10 which assembles with the main part 5 by closing the cavity 8 and an elastomer seal 11 whose shape corresponds to the contour of the plate 10.
- the plate 10 rests on the ribs 9 as well as on a bearing surface 12 of the main part 5 when it is installed; the bearing surface 12 is set back relative to the outer face 13 of the main part 5, so that the plate 10 is flush with the outer face 13 and the blade is smooth and allows a good flow of gas.
- the seal 11 is housed in a groove 14 of the main part 5 which extends around the bearing surface 12. The outer edge of the plate 10 compresses the seal 11, which is made of elastomer or other elastic material, extending above the groove 14, and it is therefore a part adjacent to this outer edge 29 which rests on the bearing surface 12.
- FIGS. 5 and 6 show further details of the invention.
- the groove 14 has a projection 15 where it extends in front of the connections of the rib 9 to the edge of the main part 5, and the end of the projection 15, which extends on the rib 9, has a bore blind 16.
- Holes 17 are also established at corresponding locations through the plate 10 to the assembly of the plate 10 on the main part 5, the alignment of the holes 16 and 17, and the introduction of centering pins 18 in these alignments ensures a good invariable position of the plate 10 until it is permanently fixed to the main part 5 ( Figure 2).
- the fixing method can be accomplished by gluing, or any brazing or welding process: electron beam welding at the location of the bearing surface 12 and the rib 9 can be envisaged.
- the joining surfaces have been coated with binder as is known in the art.
- the centering pins 18 are removed after fixation. Note in Figure 2 that the seal 11 has bulges 19 at the location of the projections 15, these bulges 19, previously compressed by the centering pins 18, penetrate the bottom projections 15 as soon as these pins have been removed, closing holes 16 and 17 so as to strengthen the seal and improve the appearance of the blade.
- Figures 7 to 9 illustrate some other possible arrangements for the ribs: respectively a rib 20 in the transverse direction of the blade 3, invariable radius in the machine; a cross arrangement comprising both the ribs 9 and 20; and another arrangement in cross, available in X from which two ribs 21 and 22 extend diagonally through the cavity 8.
- the other features of the invention are not modified, except possibly the position assembly points using the centering pins 18, which it is always advantageous to establish at the connection between the ribs and the main part 5 by bores located in the rib (for the main part) and in front of her (for the plate); but the precision the assembly remains.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Control Of Turbines (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1400052.5A GB2505845B (en) | 2011-07-20 | 2012-07-17 | Turbine engine vane plate seal |
US14/233,549 US9556745B2 (en) | 2011-07-20 | 2012-07-17 | Turbine engine vane plate seal |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1156594A FR2978196B1 (fr) | 2011-07-20 | 2011-07-20 | Aubes de turbomachine comprenant une plaque rapportee sur une partie principale |
FR1156594 | 2011-07-20 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2013011235A1 true WO2013011235A1 (fr) | 2013-01-24 |
Family
ID=46639620
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2012/051690 WO2013011235A1 (fr) | 2011-07-20 | 2012-07-17 | Aube de turbomachine et procédé de fabrication de cette aube |
Country Status (4)
Country | Link |
---|---|
US (1) | US9556745B2 (fr) |
FR (1) | FR2978196B1 (fr) |
GB (1) | GB2505845B (fr) |
WO (1) | WO2013011235A1 (fr) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2764951A1 (fr) * | 2013-02-08 | 2014-08-13 | Rolls-Royce plc | Fabrication d'une aube creuse |
FR3034131A1 (fr) * | 2015-03-24 | 2016-09-30 | Snecma | Etage d'aubes de stator pour une turbomachine |
EP3323979A1 (fr) * | 2016-11-17 | 2018-05-23 | United Technologies Corporation | Profil aérodynamique avec panneau présentant un joint périphérique |
FR3109962A1 (fr) * | 2020-05-06 | 2021-11-12 | Safran Aircraft Engines | Aube directrice de sortie pour turbomachine d’aeronef, comprenant un passage de refroidissement de lubrifiant equipe de parois ondulees |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3005693B1 (fr) | 2013-05-16 | 2017-12-22 | Snecma | Turbomachine d'aeronef a double flux comprenant une virole inter-veine a maintien aval simplifie |
FR3006367B1 (fr) * | 2013-05-28 | 2015-07-03 | Snecma | Aube creuse, et son procede de fabrication |
US10371165B2 (en) * | 2013-10-30 | 2019-08-06 | United Technologies Corporation | Fan blade composite ribs |
WO2015099861A2 (fr) | 2013-10-30 | 2015-07-02 | United Technologies Corporation | Segments composites de pale de soufflante |
US20180038386A1 (en) * | 2016-08-08 | 2018-02-08 | United Technologies Corporation | Fan blade with composite cover |
FR3071008B1 (fr) * | 2017-09-11 | 2019-09-13 | Safran Aircraft Engines | Aube directrice de sortie pour turbomachine, comprenant un passage de refroidissement de lubrifiant equipe d'une matrice de conduction thermique comprimee entre les parois d'intrados et d'extrados |
FR3078100B1 (fr) | 2018-02-16 | 2020-03-20 | Safran Aircraft Engines | Couronne aubagee pour stator de turbomachine dont les aubes sont reliees a la virole externe par appui conique et pion frangible |
US10919116B2 (en) * | 2018-06-14 | 2021-02-16 | Raytheon Technologies Corporation | Installation of laser vent holes into vertical walls of cavity-back airfoils |
FR3091730B1 (fr) * | 2019-01-14 | 2021-04-02 | Safran Aircraft Engines | Bras aerodynamique de carter pour une turbomachine d’aeronef |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1557529A2 (fr) | 2004-01-26 | 2005-07-27 | United Technologies Corporation | Aube creuse de soufflante pour turbomachine |
US7736131B1 (en) * | 2008-07-21 | 2010-06-15 | Florida Turbine Technologies, Inc. | Turbine blade with carbon nanotube shell |
US20100247322A1 (en) | 2009-03-31 | 2010-09-30 | United Technologies Corporation | Internally supported airfoil and method for internally supporting a hollow airfoil during manufacturing |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
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FR2754478B1 (fr) * | 1996-10-16 | 1998-11-20 | Snecma | Procede de fabrication d'une aube creuse de turbomachine |
US6039542A (en) * | 1997-12-24 | 2000-03-21 | General Electric Company | Panel damped hybrid blade |
US6454536B1 (en) * | 2000-02-09 | 2002-09-24 | General Electric Company | Adhesion enhancers to promote bonds of improved strength between elastomers metals in lightweight aircraft fan blades |
US6471484B1 (en) * | 2001-04-27 | 2002-10-29 | General Electric Company | Methods and apparatus for damping rotor assembly vibrations |
US7189064B2 (en) * | 2004-05-14 | 2007-03-13 | General Electric Company | Friction stir welded hollow airfoils and method therefor |
US8083489B2 (en) * | 2009-04-16 | 2011-12-27 | United Technologies Corporation | Hybrid structure fan blade |
US8616834B2 (en) * | 2010-04-30 | 2013-12-31 | General Electric Company | Gas turbine engine airfoil integrated heat exchanger |
US8944773B2 (en) * | 2011-11-01 | 2015-02-03 | United Technologies Corporation | Rotor blade with bonded cover |
US10215027B2 (en) * | 2012-01-04 | 2019-02-26 | United Technologies Corporation | Aluminum fan blade construction with welded cover |
WO2014055110A1 (fr) * | 2012-10-01 | 2014-04-10 | United Technologies Corporation | Aube directrice statique à canaux internes creux |
GB201302262D0 (en) * | 2013-02-08 | 2013-03-27 | Rolls Royce Plc | Manufacture of hollow aerofoil |
GB201316732D0 (en) * | 2013-09-20 | 2013-11-06 | Rolls Royce Plc | Manufacture of filled aerofoil |
US9896941B2 (en) * | 2014-01-16 | 2018-02-20 | United Technologies Corporation | Fan blade composite cover with tapered edges |
-
2011
- 2011-07-20 FR FR1156594A patent/FR2978196B1/fr active Active
-
2012
- 2012-07-17 WO PCT/FR2012/051690 patent/WO2013011235A1/fr active Application Filing
- 2012-07-17 GB GB1400052.5A patent/GB2505845B/en active Active
- 2012-07-17 US US14/233,549 patent/US9556745B2/en active Active
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1557529A2 (fr) | 2004-01-26 | 2005-07-27 | United Technologies Corporation | Aube creuse de soufflante pour turbomachine |
US7736131B1 (en) * | 2008-07-21 | 2010-06-15 | Florida Turbine Technologies, Inc. | Turbine blade with carbon nanotube shell |
US20100247322A1 (en) | 2009-03-31 | 2010-09-30 | United Technologies Corporation | Internally supported airfoil and method for internally supporting a hollow airfoil during manufacturing |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2764951A1 (fr) * | 2013-02-08 | 2014-08-13 | Rolls-Royce plc | Fabrication d'une aube creuse |
US9879545B2 (en) | 2013-02-08 | 2018-01-30 | Rolls-Royce Plc | Manufacture of hollow aerofoil |
FR3034131A1 (fr) * | 2015-03-24 | 2016-09-30 | Snecma | Etage d'aubes de stator pour une turbomachine |
EP3323979A1 (fr) * | 2016-11-17 | 2018-05-23 | United Technologies Corporation | Profil aérodynamique avec panneau présentant un joint périphérique |
US10731495B2 (en) | 2016-11-17 | 2020-08-04 | Raytheon Technologies Corporation | Airfoil with panel having perimeter seal |
FR3109962A1 (fr) * | 2020-05-06 | 2021-11-12 | Safran Aircraft Engines | Aube directrice de sortie pour turbomachine d’aeronef, comprenant un passage de refroidissement de lubrifiant equipe de parois ondulees |
Also Published As
Publication number | Publication date |
---|---|
GB201400052D0 (en) | 2014-02-19 |
GB2505845B (en) | 2018-02-21 |
FR2978196B1 (fr) | 2016-12-09 |
US20140193250A1 (en) | 2014-07-10 |
GB2505845A (en) | 2014-03-12 |
US9556745B2 (en) | 2017-01-31 |
FR2978196A1 (fr) | 2013-01-25 |
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