EP1213483A1 - Statorstufe eines Verdichters - Google Patents

Statorstufe eines Verdichters Download PDF

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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
Application number
EP00870290A
Other languages
English (en)
French (fr)
Other versions
EP1213483B1 (de
Inventor
Mathieu Bos
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.)
Filing date
Publication date
Application filed by Techspace Aero SA filed Critical Techspace Aero SA
Priority to DE60026686T priority Critical patent/DE60026686T2/de
Priority to EP00870290A priority patent/EP1213483B1/de
Priority to US10/001,122 priority patent/US6655912B2/en
Publication of EP1213483A1 publication Critical patent/EP1213483A1/de
Application granted granted Critical
Publication of EP1213483B1 publication Critical patent/EP1213483B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • 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)
EP00870290A 2000-12-06 2000-12-06 Statorstufe eines Verdichters Expired - Lifetime EP1213483B1 (de)

Priority Applications (3)

Application Number Priority Date Filing Date Title
DE60026686T DE60026686T2 (de) 2000-12-06 2000-12-06 Statorstufe eines Verdichters
EP00870290A EP1213483B1 (de) 2000-12-06 2000-12-06 Statorstufe eines Verdichters
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 (de) 2000-12-06 2000-12-06 Statorstufe eines Verdichters

Publications (2)

Publication Number Publication Date
EP1213483A1 true EP1213483A1 (de) 2002-06-12
EP1213483B1 EP1213483B1 (de) 2006-03-15

Family

ID=8175867

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00870290A Expired - Lifetime EP1213483B1 (de) 2000-12-06 2000-12-06 Statorstufe eines Verdichters

Country Status (3)

Country Link
US (1) US6655912B2 (de)
EP (1) EP1213483B1 (de)
DE (1) DE60026686T2 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2072760A1 (de) 2007-12-21 2009-06-24 Techspace aero Vorrichtung zur Befestigung von Leitschaufeln an einen Stufenring des Stators einer Strömungsmaschine und entsprechendes Befestigungsverfahren
US9771815B2 (en) 2012-12-24 2017-09-26 Safran Aero Boosters Sa Blade-retaining plate with internal cut-outs for a turbomachine stator
EP3406854A1 (de) * 2017-05-26 2018-11-28 United Technologies Corporation Statoranordnung mit halteclip für gasturbinenmotor
EP3412873A1 (de) * 2017-06-09 2018-12-12 United Technologies Corporation Statoranordnung mit halteclip für gasturbinenmotor

Families Citing this family (14)

* Cited by examiner, † Cited by third party
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
US10533456B2 (en) 2017-05-26 2020-01-14 United Technologies Corporation Stator assembly with contoured retention clip for gas turbine engine
US10655502B2 (en) 2017-05-26 2020-05-19 United Technologies Corporation Stator assembly with 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)

* Cited by examiner, † Cited by third party
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)

* Cited by examiner, † Cited by third party
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

Patent Citations (4)

* Cited by examiner, † Cited by third party
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)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2072760A1 (de) 2007-12-21 2009-06-24 Techspace aero Vorrichtung zur Befestigung von Leitschaufeln an einen Stufenring des Stators einer Strömungsmaschine und entsprechendes Befestigungsverfahren
US9771815B2 (en) 2012-12-24 2017-09-26 Safran Aero Boosters Sa Blade-retaining plate with internal cut-outs for a turbomachine stator
EP3406854A1 (de) * 2017-05-26 2018-11-28 United Technologies Corporation Statoranordnung mit halteclip für gasturbinenmotor
US10590783B2 (en) 2017-05-26 2020-03-17 United Technologies Corporation Stator assembly with retention clip for gas turbine engine
EP3412873A1 (de) * 2017-06-09 2018-12-12 United Technologies Corporation Statoranordnung mit halteclip für gasturbinenmotor
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
DE60026686T2 (de) 2006-10-05
EP1213483B1 (de) 2006-03-15
US6655912B2 (en) 2003-12-02
DE60026686D1 (de) 2006-05-11
US20020085913A1 (en) 2002-07-04

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