EP2459884B1 - Secteur de virole exterieure pour couronne aubagee de stator de turbomachine d'aeronef, comprenant des cales amortisseuses de vibrations - Google Patents

Secteur de virole exterieure pour couronne aubagee de stator de turbomachine d'aeronef, comprenant des cales amortisseuses de vibrations Download PDF

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Publication number
EP2459884B1
EP2459884B1 EP10739591.5A EP10739591A EP2459884B1 EP 2459884 B1 EP2459884 B1 EP 2459884B1 EP 10739591 A EP10739591 A EP 10739591A EP 2459884 B1 EP2459884 B1 EP 2459884B1
Authority
EP
European Patent Office
Prior art keywords
sector
outer shell
wedge
sectors
friction surfaces
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
Application number
EP10739591.5A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2459884A2 (fr
Inventor
Laurent Gilles Dezouche
Patrick Edmond Kapala
Samir Zaidi
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 Aircraft Engines SAS
Original Assignee
SNECMA SAS
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Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP2459884A2 publication Critical patent/EP2459884A2/fr
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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • F01D25/06—Antivibration arrangements for preventing blade vibration
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
    • 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 generally to an aircraft turbomachine, preferably of the turbojet or turboprop type.
  • the invention relates to the compressor or turbine stator of such a turbomachine, and more specifically to a bladed crown sector comprising a plurality of stator vanes as well as two concentric ferrules carrying the vanes and intended to delimit radially a primary flow through the turbomachine, respectively inwardly and outwardly.
  • a bladed crown generally made using several sectors arranged end to end, is generally used in the compressor or the turbine as a rectifier or distributor.
  • Turbomachines generally comprise in series a low pressure compressor, a high pressure compressor, a combustion chamber, a high pressure turbine and a low pressure turbine.
  • the compressors and turbines comprise several rows of circumferentially spaced apart blades, these rows being separated by rows of blades that are also circumferentially spaced apart.
  • rectifiers and distributors are subject to high dynamic loads. Indeed, the technological evolution leads to a reduction of the number of floors for equal or higher performances, which results in a higher load for each floor.
  • the evolution of production technologies leads to reducing the number of parts, which leads to the reduction of the damping effect of the connections between the parts. This is the case, in particular, when adopting a soldering technology of the abradable cartridge that eliminates a significant source of dissipation of vibration energy.
  • the invention therefore aims to remedy at least partially the problems mentioned above, relating to the achievements of the prior art.
  • the invention firstly relates to a bladed crown sector according to claim 1.
  • each vibration damping wedge has a substantially identical profile to that of the elementary sectors.
  • a support shims against the friction surfaces of the elementary sectors allows a perfect seal between these elements, independent of the pressure differential between the aerodynamic stream and the outside of the compressor or the turbine. Indeed, this seal is obtained by construction, with shims exerting substantially oriented efforts in the tangential direction against the friction surfaces of the elementary sectors. It is noted that this seal is further enhanced in operation, since the plating forces between the friction surfaces and the wedges are accentuated by the application, on the elementary sectors, of the tangential component of the aerodynamic forces exerted on the vanes. of stator.
  • said wedge is in abutment against two plane parallel friction surfaces and facing each other in said tangential direction and respectively provided on said two elementary sectors associated with said wedge, and said wedge has two friction surfaces. complementary planes parallel to each other and cooperating respectively with the two friction surfaces of the elementary sectors.
  • the planar contacts between the friction surfaces and the complementary friction surfaces make it possible to ensure a satisfactory damping of the vibrations by friction.
  • the manufacture of the assembly according to the invention is greatly simplified, which provides a significant gain in terms of cost and time.
  • said wedge has hooks for its maintenance on the stator of compressor or turbine, these hooks thus having the same profile than those of the brackets worn by the elementary sectors.
  • said damping damping wedges extend substantially in an axial or oblique direction of said assembly. It is expected that each elementary sector carries a single stator vane, or possibly several blades, without departing from the scope of the invention.
  • the bladed crown can constitute a compressor rectifier, or a turbine distributor.
  • the ring sector preferably extends over an angular extent of between 5 and 60 °, but can be up to 360 ° in order to constitute the entire bladed crown.
  • the subject of the invention is also an aircraft turbine engine comprising a stator of compressor or turbine equipped with at least one sector of bladed crown as described above.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP10739591.5A 2009-07-31 2010-07-29 Secteur de virole exterieure pour couronne aubagee de stator de turbomachine d'aeronef, comprenant des cales amortisseuses de vibrations Active EP2459884B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0955439A FR2948736B1 (fr) 2009-07-31 2009-07-31 Secteur de virole exterieure pour couronne aubagee de stator de turbomachine d'aeronef, comprenant des cales amortisseuses de vibrations
PCT/EP2010/061037 WO2011012679A2 (fr) 2009-07-31 2010-07-29 Secteur de virole exterieure pour couronne aubagee de stator de turbomachine d'aeronef, comprenant des cales amortisseuses de vibrations

Publications (2)

Publication Number Publication Date
EP2459884A2 EP2459884A2 (fr) 2012-06-06
EP2459884B1 true EP2459884B1 (fr) 2018-06-27

Family

ID=41800367

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10739591.5A Active EP2459884B1 (fr) 2009-07-31 2010-07-29 Secteur de virole exterieure pour couronne aubagee de stator de turbomachine d'aeronef, comprenant des cales amortisseuses de vibrations

Country Status (9)

Country Link
US (1) US20120128482A1 (zh)
EP (1) EP2459884B1 (zh)
JP (1) JP5697667B2 (zh)
CN (1) CN102472297A (zh)
BR (1) BR112012002304A2 (zh)
CA (1) CA2769217A1 (zh)
FR (1) FR2948736B1 (zh)
RU (1) RU2537997C2 (zh)
WO (1) WO2011012679A2 (zh)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2971022B1 (fr) 2011-02-02 2013-01-04 Snecma Etage redresseur de compresseur pour une turbomachine
US9610644B2 (en) * 2011-02-08 2017-04-04 United Technologies Corporation Mate face brazing for turbine components
US9546557B2 (en) * 2012-06-29 2017-01-17 General Electric Company Nozzle, a nozzle hanger, and a ceramic to metal attachment system
US9334756B2 (en) 2012-09-28 2016-05-10 United Technologies Corporation Liner and method of assembly
EP2971659B1 (en) 2013-03-15 2021-09-22 Raytheon Technologies Corporation Acoustic liner with varied properties
DE102013212252A1 (de) * 2013-06-26 2014-12-31 Siemens Aktiengesellschaft Turbine und Verfahren zur Anstreiferkennung
FR3008455B1 (fr) * 2013-07-09 2015-08-21 Snecma Redresseur pour compresseur comportant des moyens de rattrapage de jeu
CN104440153B (zh) * 2014-11-04 2017-06-06 中国南方航空工业(集团)有限公司 机匣内叶片加工阻尼装置
FR3029242B1 (fr) 2014-11-28 2016-12-30 Snecma Aube de turbomachine, comprenant des cloisons entrecroisees pour la circulation d'air en direction du bord de fuite
US10655482B2 (en) * 2015-02-05 2020-05-19 Rolls-Royce Corporation Vane assemblies for gas turbine engines
JP6689117B2 (ja) * 2016-03-31 2020-04-28 三菱日立パワーシステムズ株式会社 軸流回転機械に装備される静翼環及び軸流回転機械
CN106988794B (zh) * 2017-06-02 2018-12-14 中国航发南方工业有限公司 静子组合件夹紧方法及静子组合件
CN107747563B (zh) * 2017-09-30 2020-04-10 中国航发沈阳发动机研究所 带阻尼的风扇机匣
US11242762B2 (en) * 2019-11-21 2022-02-08 Raytheon Technologies Corporation Vane with collar
FR3115819B1 (fr) * 2020-11-02 2023-04-14 Safran Aircraft Engines Ensemble de stator de turbomachine d’aéronef, comprenant une structure externe formée de deux tronçons annulaires entourant une couronne aubagée de stator
FR3119196B1 (fr) * 2021-01-27 2022-12-23 Safran Aircraft Engines Rangée annulaire sectorisée d’aubes fixes

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US2661147A (en) * 1949-01-19 1953-12-01 Ingersoll Rand Co Blower blade fastening device
SU453486A1 (ru) * 1973-04-11 1974-12-15 УСТРОЙСТВО дл ДЕМПФИРОВАНИЯ КОЛЕБАНИЙ РАБОЧИХ ЛОПАТОК ОСЕВОЙ ТУРБОМАШИНЫ
JPS5239807A (en) * 1975-09-25 1977-03-28 Mitsubishi Heavy Ind Ltd Moving vane vibration controlling apparatus
US5201850A (en) * 1991-02-15 1993-04-13 General Electric Company Rotor tip shroud damper including damper wires
DE4436731A1 (de) * 1994-10-14 1996-04-18 Abb Management Ag Verdichter
FR2831615B1 (fr) * 2001-10-31 2004-01-02 Snecma Moteurs Redresseur fixe sectorise pour compresseur d'une turbomachine
US6984108B2 (en) * 2002-02-22 2006-01-10 Drs Power Technology Inc. Compressor stator vane
US6733237B2 (en) * 2002-04-02 2004-05-11 Watson Cogeneration Company Method and apparatus for mounting stator blades in axial flow compressors
EP1510654A1 (de) * 2003-08-25 2005-03-02 Siemens Aktiengesellschaft Einstückige Turbinenbeschaufelungseinheit und Verfahren zur Herstellung einer einstückigen Turbinenbeschaufelungseinheit
US7104752B2 (en) * 2004-10-28 2006-09-12 Florida Turbine Technologies, Inc. Braided wire damper for segmented stator/rotor and method
FR2902843A1 (fr) * 2006-06-23 2007-12-28 Snecma Sa Secteur de redresseur de compresseur ou secteur de distributeur de turbomachine
US7591634B2 (en) * 2006-11-21 2009-09-22 General Electric Company Stator shim welding
US7806655B2 (en) * 2007-02-27 2010-10-05 General Electric Company Method and apparatus for assembling blade shims

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Also Published As

Publication number Publication date
CN102472297A (zh) 2012-05-23
EP2459884A2 (fr) 2012-06-06
FR2948736B1 (fr) 2011-09-23
WO2011012679A3 (fr) 2011-04-21
JP5697667B2 (ja) 2015-04-08
US20120128482A1 (en) 2012-05-24
RU2537997C2 (ru) 2015-01-10
RU2012107522A (ru) 2013-09-10
BR112012002304A2 (pt) 2016-05-31
JP2013501181A (ja) 2013-01-10
CA2769217A1 (en) 2011-02-03
WO2011012679A2 (fr) 2011-02-03
FR2948736A1 (fr) 2011-02-04

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