EP2199544A1 - Aufbau eines Leitschaufelgitters - Google Patents

Aufbau eines Leitschaufelgitters Download PDF

Info

Publication number: EP2199544A1
Authority: EP; European Patent Office
Prior art keywords: outer shell; turbomachine; stage according; plane; straightener
Prior art date: 2008-12-22
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

Application number

EP20080172599

Other languages

English (en)

French (fr)

Other versions

EP2199544B1 (de

Inventor

Rodolphe Lebrun

Alain Derclaye

Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)

Safran Aero Boosters SA

Original Assignee

Techspace Aero SA

Priority date (The priority date 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 date listed.)

2008-12-22

Filing date

2008-12-22

Publication date

2010-06-23

2008-12-22 Application filed by Techspace Aero SA filed Critical Techspace Aero SA

2008-12-22 Priority to EP08172599.6A priority Critical patent/EP2199544B1/de

2009-12-03 Priority to CA2686988A priority patent/CA2686988C/en

2009-12-17 Priority to US12/640,062 priority patent/US8469662B2/en

2010-06-23 Publication of EP2199544A1 publication Critical patent/EP2199544A1/de

2016-03-30 Application granted granted Critical

2016-03-30 Publication of EP2199544B1 publication Critical patent/EP2199544B1/de

Status Active legal-status Critical Current

2028-12-22 Anticipated expiration legal-status Critical

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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

Definitions

the present invention relates to turbomachine stators. It relates more particularly to a rectifier architecture in an axial compressor of a turbomachine.
Axial compressors are well known per se and are used in several types of applications. In particular, they are used in turbojet engines.
These low or high pressure compressors comprise several stages of rotating blades which are separated by rectifier stages which are intended to reposition the velocity vector of the fluid leaving the preceding stage before sending it to the next stage.
rectifier stages consist essentially of fixed vanes connecting an outer ferrule to an inner ferrule, both concentric and delimiting the air flow zone or aerodynamic vein.
the contacts between the platform of the blade and the outer shell may be of planar-curve, curve-curve or plane-plane respectively.
planar-curve or curve-curve assemblies do not marry perfectly.
plane-curve type contact it can be easily understood that the two surfaces do not marry perfectly.
curve-curve type contact the manufacturing tolerances are such that the two surfaces do not have exactly the same radius of curvature and, therefore, do not fit perfectly one of the other.
a plane-plane type contact where the two surfaces fit perfectly with each other makes it possible to reduce the stresses induced during assembly and to avoid instability of the positioning of the blade around the point of attachment. .
Requirement EP 1 801 357 A1 has a turbomachine stator vane comprising a blade crown fixed, mounted on an outer shell, each blade having a platform for attachment to the outer shell.
Blading is characterized in that the outer shell comprises a plurality of individual housings for the platforms, machined in the thickness of the ferrule, the shape of each housing being complementary to that of the corresponding platform.
the housings are in the form of flat-bottomed recesses and the platforms are in the form of a plate.
the patent US 6,543,995 B1 has a rectifier where the contact between the platform of the blade and the outer shell is of plane-plane type.
Flat facets are machined on the outer shell and disposed circumferentially on the side opposite to the aerodynamic stream, and the blade platforms have a flat surface on their inner side (on the blade side).
the contact between the platform of the blade and the outer shell is on the opposite side to the aerodynamic vein.
Such an assembly architecture requires machining a series of large openings in the outer shell to allow the passage of the blade through it.
the disclosed rectifier architecture requires the use of an elastomeric material to fill the interstices between the blade profile and the openings in the outer shell; this in order to obtain a perfectly smooth surface on the side of the aerodynamic vein.
the present invention aims to provide a solution that makes it possible to overcome the disadvantages of the state of the art.
the present invention more specifically aims to provide an outer dawn-ferrule assembly architecture where the assembly constraints are reduced.
Another object of the present invention is to provide an exterior dawn-ferrule assembly architecture where the only openings in the outer shell are those required by the fastening systems (rivets, bolts, "lockbolt”, etc.).
the present invention also aims to provide an outer dawn-ferrule assembly architecture where the platforms are arranged to improve aerodynamic performance.
the present invention discloses a turbomachine rectifying stage comprising a set of fixed vanes connecting an inner ferrule to an outer ferrule, said fixed vanes having attachment platforms having flat surfaces cooperating with a plurality of juxtaposed plane facets, said facets planes on the inner face of the outer shell to ensure a fixation with a contact plane / plane between the blades and the outer shell.
the present invention also discloses a method for manufacturing a turbomachine rectifier stage according to claim 4 comprising a resin transfer molding step or a resin transfer cocuring step for the assembly of the outer shell with fixed vanes.
the figure 1 represents a section of a part of a turbocharger.
the figure 2 represents a three-dimensional view of two types of exterior dawn-ferrule assembly according to the state of the art.
the figure 3 represents two three-dimensional views of a contact between a blade platform and an outer shell according to the invention.
the figure 4 represents a three-dimensional view of the bolting of the blade platform to the outer shell according to the invention.
the figure 5 represents a three-dimensional view of the bolting of the blade platform to the outer shell according to another embodiment of the invention.
the figure 6 represents a three-dimensional view of the blade platforms fixed to the outer shell by means of "lockbolts" according to the invention.
the present invention relates to an architecture for assembling the stator vanes to the outer ferrule in a turbocharger.
the figure 1 shows a section of a part of a turbocharger where one can see the rotating blades 3 driven by the compressor shaft and the stator vanes 2 attached to the inner ring 4 and outer 5.
the outer shell instead of being a continuous curved surface, consists of a plurality of plane facets disposed on the side of the aerodynamic stream; the plane facets being juxtaposed.
the outer shell is formed of a plurality of plane facets on the side of the aerodynamic vein and the opposite side to the aerodynamic stream.
an outer shell consisting of a plurality of flat segments, the latter being also juxtaposed.
the outer shell is made of composite material and obtained by a Resin Transfer Molding (RTM) technique.
RTM Resin Transfer Molding
the blades comprise a platform having a flat surface on the opposite side to the blade of the blade.
the contact between the platform of the blade and the plane facets or plane segments of the outer shell is made exclusively on the side of the aerodynamic vein.
the figure 3 illustrates the planplane type contact between the platform 7 of the blade 2 and the planar segments 10 of the outer shell on the inner face of the outer shell.
the platforms 7 are arranged side by side to provide a smooth continuous surface to the flow of air which improves the aerodynamic performance compared to a welded configuration where the weld bead opens into the vein.
the only openings required in the outer shell are those for the attachment systems of the platform of the blade to the inner face of the outer shell.
the fastening system is a bolted fastener 11 (see FIG. Figures 4 and 5 ). Bolting takes place at the plane facets or flat segments of the outer shell or at the flanges provided for the assembly of ferrules together.
the figure 4 presents the first configuration.
a threaded rod integral with the blade passes through the ferrule and is bolted to the outer shell by a nut on the opposite side to the aerodynamic vein.
an L-shaped flange 8 is integral with the platform of the blade and bolted by connection with the assembly flange 1 of the outer rings 5 (see also FIG. figure 1 ).
a lockbolt 9 also maintains the platform of dawn in contact with the facet or plane segment of the outer shell.
the platforms of the blades are assembled to the facets or flat segments of the outer shell only by means of "lockbolts".
each platform is fixed to the plane segment 10 of the outer shell by means of two "lockbolts" 9.
the platforms are fixed by means of rivets (not shown).
the vanes can be secured by means of fastening systems that combine bolted fasteners, rivets and "lockbolts".
the invention has the advantage that only one or two fasteners, namely the bolted fastener, the rivet or the "lockbolt", are required to attach a blade platform to a flat facet or segment. plan of the outer shell.
the platforms are glued to the outer shell or the platform of the blade is assembled to the outer shell by co-molding ("cocuring" in English).
co-molding in English.
the latter assembly technique is based on the RTM process and consists in simultaneously making the composite parts (blade and outer shell) and the junction between the two parts.
the plane-plane contact allows a reduction of assembly constraints.
plane facets or planar segments are directly molded to finished dimensions, which greatly reduces machining operations relative to to the state-of-the-art manufacturing ranges US 6,543,995 B1 where the plane facets or flat segments are milled out of a part roughed by turning and where it is necessary to mill the openings and drillings.
junction lines between blade platforms are not parallel to the velocity vector of the air flow, the latter being biased relative to the junction lines.
This has the advantage of restricting the creepage distances with respect to a configuration where the velocity vector of the air flow is parallel to the connecting lines, as is the case in the state of the art. US 6,543,995 B1 , and therefore minimize aerodynamic disturbances.
the only openings required in the outer shell are those for the mounting holes.
the outer shell is free of any opening.
the removal of large openings in the outer shell has the advantage of not reducing the structural strength of the shell. This presents more particularly an advantage for the long fiber composite ferrules where the openings in the ferrule sever the fibers and therefore particularly reduce the mechanical strength of the material.
the blade assembly is perfectly interchangeable, that is to say that the platform and the fastening system can be identical while having blade profiles or materials. different.

Landscapes

Engineering & Computer Science (AREA)
Mechanical Engineering (AREA)
General Engineering & Computer Science (AREA)
Structures Of Non-Positive Displacement Pumps (AREA)

EP08172599.6A 2008-12-22 2008-12-22 Aufbau einer Leitschaufelstufe Active EP2199544B1 (de)

Priority Applications (3)

Application Number	Priority Date	Filing Date	Title
EP08172599.6A EP2199544B1 (de)	2008-12-22	2008-12-22	Aufbau einer Leitschaufelstufe
CA2686988A CA2686988C (en)	2008-12-22	2009-12-03	Guide vane architecture
US12/640,062 US8469662B2 (en)	2008-12-22	2009-12-17	Guide vane architecture

Applications Claiming Priority (1)

Application Number	Priority Date	Filing Date	Title
EP08172599.6A EP2199544B1 (de)	2008-12-22	2008-12-22	Aufbau einer Leitschaufelstufe

Publications (2)

Publication Number	Publication Date
EP2199544A1 true EP2199544A1 (de)	2010-06-23
EP2199544B1 EP2199544B1 (de)	2016-03-30

Family

ID=40668391

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
EP08172599.6A Active EP2199544B1 (de)	2008-12-22	2008-12-22	Aufbau einer Leitschaufelstufe

Country Status (3)

Country	Link
US (1)	US8469662B2 (de)
EP (1)	EP2199544B1 (de)
CA (1)	CA2686988C (de)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
EP2199544B1 (de) *	2008-12-22	2016-03-30	Techspace Aero S.A.	Aufbau einer Leitschaufelstufe
EP2211023A1 (de) *	2009-01-21	2010-07-28	Siemens Aktiengesellschaft	Leitschaufelsystem für eine Strömungsmaschine mit segmentiertem Leitschaufelträger
EP2696042B1 (de) *	2012-08-09	2015-01-21	MTU Aero Engines GmbH	Strömungsmaschine mit mindestens einem Leitschaufelkranz
EP2930308B1 (de) *	2014-04-11	2021-07-28	Safran Aero Boosters SA	Facettengehäuse einer axialen Turbomaschine
US10301951B2 (en)	2016-05-20	2019-05-28	United Technologies Corporation	Turbine vane gusset
CN112709716A (zh) *	2020-12-29	2021-04-27	中国航发沈阳发动机研究所	一种压气机静子叶片结构
US11828197B2 (en)	2021-12-03	2023-11-28	Rolls-Royce North American Technologies Inc.	Outlet guide vane mounting assembly for turbine engines
US12398655B2 (en)	2023-03-17	2025-08-26	Rolls-Royce North American Technologies Inc.	Segmented variable fan outlet guide vane with segment interface components
US12398648B2 (en)	2023-03-17	2025-08-26	Rolls-Royce North American Technologies Inc.	Segmented variable fan outlet guide vane with cam assembly and pass through actuation mechanisms
US12320260B2 (en)	2023-03-17	2025-06-03	Rolls-Royce North American Technologies Inc.	Segmented variable fan outlet guide vane with cam assembly and unique actuation mechanisms
US12480422B2 (en)	2023-03-17	2025-11-25	Rolls-Royce North American Technologies Inc.	Segmented variable fan outlet guide vane with pass through actuation mechanisms
US12292056B2 (en)	2023-03-17	2025-05-06	Rolls-Royce North American Technologies Inc.	Segmented variable fan outlet guide vane with gear assembly
US12428974B2 (en)	2023-03-17	2025-09-30	Rolls-Royce North American Technologies Inc.	Segmented variable fan outlet guide vane with unique actuation mechanisms

Citations (9)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
DE1476928A1 (de) *	1965-05-29	1969-07-31	Bergmann Borsig Veb	Leitschaufelfuss fuer Turbinen mit hoher Eintrittstemperatur
US5474419A (en)	1992-12-30	1995-12-12	Reluzco; George	Flowpath assembly for a turbine diaphragm and methods of manufacture
US5584654A (en)	1995-12-22	1996-12-17	General Electric Company	Gas turbine engine fan stator
EP1167693A2 (de) *	2000-06-30	2002-01-02	General Electric Company	Leitschaufelplattformen
US6543995B1 (en)	1999-08-09	2003-04-08	United Technologies Corporation	Stator vane and stator assembly for a rotary machine
EP0953729B1 (de)	1998-05-01	2003-06-25	Techspace aero	Leitbeschaufelung für eine Turbomaschine
EP1801357A1 (de)	2005-12-22	2007-06-27	Techspace aero	Schaufelleitring einer Strömungsmaschine, Strömungsmaschine mit einem solchen Leitring und Leitschaufel
WO2008000014A2 (de) *	2006-06-30	2008-01-03	Facc Ag	Leitschaufelanordnung für ein triebwerk
EP1936121A1 (de)	2006-12-22	2008-06-25	Techspace aero	Winkelfixierung für Leitschaufeln von Turbomachinen

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
US3004750A (en) *	1959-02-24	1961-10-17	United Aircraft Corp	Stator for compressor or turbine
FR2654463A1 (fr) *	1989-11-15	1991-05-17	Snecma	Element de stator de turbomachine.
US6343912B1 (en) *	1999-12-07	2002-02-05	General Electric Company	Gas turbine or jet engine stator vane frame
US6969239B2 (en) *	2002-09-30	2005-11-29	General Electric Company	Apparatus and method for damping vibrations between a compressor stator vane and a casing of a gas turbine engine
EP1433925A1 (de) *	2002-12-24	2004-06-30	Techspace Aero S.A.	Befestigungsverfahren von einer Schaufel mit einem Statorring
EP2199544B1 (de) *	2008-12-22	2016-03-30	Techspace Aero S.A.	Aufbau einer Leitschaufelstufe
EP2339120B1 (de) *	2009-12-22	2015-07-08	Techspace Aero S.A.	Leitschaufelstufe einer Strömungsmaschine und zugehöriger Verdichter

2008
- 2008-12-22 EP EP08172599.6A patent/EP2199544B1/de active Active
2009
- 2009-12-03 CA CA2686988A patent/CA2686988C/en not_active Expired - Fee Related
- 2009-12-17 US US12/640,062 patent/US8469662B2/en not_active Expired - Fee Related

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
DE1476928A1 (de) *	1965-05-29	1969-07-31	Bergmann Borsig Veb	Leitschaufelfuss fuer Turbinen mit hoher Eintrittstemperatur
US5474419A (en)	1992-12-30	1995-12-12	Reluzco; George	Flowpath assembly for a turbine diaphragm and methods of manufacture
US5584654A (en)	1995-12-22	1996-12-17	General Electric Company	Gas turbine engine fan stator
EP0953729B1 (de)	1998-05-01	2003-06-25	Techspace aero	Leitbeschaufelung für eine Turbomaschine
US6543995B1 (en)	1999-08-09	2003-04-08	United Technologies Corporation	Stator vane and stator assembly for a rotary machine
EP1167693A2 (de) *	2000-06-30	2002-01-02	General Electric Company	Leitschaufelplattformen
EP1801357A1 (de)	2005-12-22	2007-06-27	Techspace aero	Schaufelleitring einer Strömungsmaschine, Strömungsmaschine mit einem solchen Leitring und Leitschaufel
WO2008000014A2 (de) *	2006-06-30	2008-01-03	Facc Ag	Leitschaufelanordnung für ein triebwerk
EP1936121A1 (de)	2006-12-22	2008-06-25	Techspace aero	Winkelfixierung für Leitschaufeln von Turbomachinen

Also Published As

Publication number	Publication date
US8469662B2 (en)	2013-06-25
US20100158685A1 (en)	2010-06-24
CA2686988A1 (en)	2010-06-22
EP2199544B1 (de)	2016-03-30
CA2686988C (en)	2016-02-16

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