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EP2526301B1 - Diffusor-gleichrichter-anschluss für einen radialverdichter - Google Patents

Diffusor-gleichrichter-anschluss für einen radialverdichter Download PDF

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Publication number
EP2526301B1
EP2526301B1 EP11704655.7A EP11704655A EP2526301B1 EP 2526301 B1 EP2526301 B1 EP 2526301B1 EP 11704655 A EP11704655 A EP 11704655A EP 2526301 B1 EP2526301 B1 EP 2526301B1
Authority
EP
European Patent Office
Prior art keywords
diffuser
assembly
flange
guide vane
disk
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
EP11704655.7A
Other languages
English (en)
French (fr)
Other versions
EP2526301A1 (de
Inventor
Jacques Marcel Arthur Bunel
Sandrine Gandelot
Guy Vieillefond
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
Safran Aircraft Engines SAS
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 Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP2526301A1 publication Critical patent/EP2526301A1/de
Application granted granted Critical
Publication of EP2526301B1 publication Critical patent/EP2526301B1/de
Active legal-status Critical Current
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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
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/62—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps
    • F04D29/624—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • 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
    • 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
    • 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
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • 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
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet

Definitions

  • the field of the present invention is that of turbomachines and, in particular, that of the compressors of these turbomachines.
  • the aeronautical turbomachines are conventionally constituted by a set of assembled modules, comprising in the direction of air circulation, one or more compressors, a combustion chamber, one or more turbines which drive the compressor or compressors via drive shafts by drawing power on the gases leaving the combustion chamber, and at the outlet, a nozzle in which the exhaust gases are ejected to produce thrust, or a free turbine which recovers the energy of the gas to produce mechanical power.
  • the compressors are conventionally either of the axial type where the flow of air passing through them follows a substantially axial direction from the inlet to the outlet, or of the so-called centrifugal type where the air enters axially to come out in a radial direction.
  • a centrifugal compressor the air is collected at the outlet of the compression wheel by a radial part, called a diffuser, then transferred to a second part, called a rectifier, which brings back the flow of compressed air in a direction substantially axial, before its introduction into the combustion chamber.
  • One-piece rectifiers are also known which are fixed by bolting on flanges connected to the structure of the engine, but these configurations are characterized by additional pieces that induce a penalty in terms of mass. Moreover, these flanges can deform under the action of vibration or thermal expansion and do not ensure perfect continuity of the vein between the diffuser and the rectifier.
  • the present invention aims to overcome these disadvantages by providing a connection device between the diffuser and the rectifier that does not have at least some of the disadvantages of the prior art and, in particular, which is lightweight, simple to mount and to disassemble and which ensures a good alignment of the air circulation ducts at the outlet of the compressor.
  • the subject of the invention is an assembly consisting of a diffuser and a rectifier of the air flow at the outlet of a centrifugal compressor of a turbomachine, said diffuser having substantially the shape of a double disk. annular radially oriented, and said rectifier being a double O-piece, positioned in the extension of the double disk of the diffuser and curved to deflect the air flow downstream of the turbomachine, characterized in that said rectifier is fixed on said diffuser by a link positioned at immediate proximity of the contact surface of the two parts and dismountable using standard tools, excluding any other means of support.
  • a standard tooling must be understood as a tool transportable by the operator that is adapted to be implemented on the mounting station or disassembly of the turbomachine.
  • connection is a connection by screw and nut.
  • the diffuser comprises on one of its disks, at its contact surface with said rectifier, a flange parallel to said disk and delimiting with it a groove adapted to receive the head of said screw and having at least one notch adapted to let the rod of said screw.
  • the rectifier comprises, at its contact surface with said diffuser, a ring-shaped ring whose section comprises a first portion L, which envelops the end of the diffuser, followed by a second part having the form of a flange that comes to wrap the corresponding flange of the diffuser.
  • the rectifier at its surface intended to cooperate with the disk of the diffuser opposite to the disk carrying said flange, comprises a ring-shaped ring with L. section.
  • the diffuser comprises, on its disc opposite the one carrying said flange, an L-shaped flange, which extends axially towards the outside of the diffuser and projects radially so as to form a flange. cross stop for the rectifier.
  • the screw comprises on its head a truncated portion so as to constitute an anti-rotation member by cooperation with the bottom of the groove.
  • the invention also relates to a compressor module for a turbomachine, comprising a diffuser-rectifier assembly as described above and, finally, a turbomachine comprising such a diffuser-rectifier assembly positioned at the outlet of a centrifugal compressor.
  • the diffuser 1 placed at the outlet of the mobile wheel of a centrifugal compressor, not shown, and a rectifier 2 which causes the flow of compressed air a deflection of about 120 ° to send it towards a combustion chamber, not shown also.
  • the diffuser 1 is substantially in the form of a radially oriented double annular disk in the center of which the compressor wheel is inserted and which forms a conduit for collecting the compressed air.
  • the rectifier 2 is a two-sided O-piece, positioned in the extension of the double disk of the diffuser and which is bent to deflect the flow of air towards the downstream of the engine (the downstream being represented to the right on the figure 1 ).
  • the downstream disk 3 of the diffuser comprises, positioned outside the diffuser, a flange 4 parallel to the downstream disk 3 and running over its entire circumference, which is connected to the downstream disk by a bridge so as to create a groove 5 between the flange 4 and the downstream disk 3.
  • the flange 4 is positioned against the disc located downstream, that is to say the disc accessible last during assembly in the presented configuration; it is obvious that this type of connection may include a flange 4 mounted on the upstream disk, if it is the latter which is accessible last during the assembly of the engine.
  • the disk of the diffuser 1 terminates in an L-shaped flange 6, which extends first axially towards the outside of the diffuser so as not to disturb the flow of the air flow at the interior of said diffuser and which then projects radially so as to constitute a transverse stop flange for the rectifier.
  • L-shaped flange 6 extends first axially towards the outside of the diffuser so as not to disturb the flow of the air flow at the interior of said diffuser and which then projects radially so as to constitute a transverse stop flange for the rectifier.
  • the rectifier 2 terminates at its junction with the diffuser 1, on the upstream side, by an upstream ring 7 of L-shaped section whose axial extension cooperates with the flange L 6 of the diffuser and, on the downstream side by a downstream ferrule 8 also of toric form.
  • the section of the downstream ferrule 8 comprises a first portion 8a, L, which envelops the end of the diffuser, and continues with a second portion 8b in the form of a flange which caps the corresponding flange 4 of the diffuser 1.
  • Maintaining the rectifier 2 on the diffuser 1 is provided by a screw 9 whose head is placed in the groove 5 and which extends perpendicularly to the wall of the downstream disc 3.
  • This screw passes through, on the one hand, the flange 4 of the diffuser at a notch 11 formed in said flange and secondly the second portion 8b of the downstream ferrule 8 at a bore 12.
  • the assembly is tightened by means of a nut 10 which cooperates with the screw 9 and which is based on the second part 8b.
  • FIGS. 3 and 4 show the screw 9 whose head is truncated to reveal a flat portion 13 and the notch 11 formed in the wall of the flange 4 of the diffuser.
  • the Figures 5 to 7 show the sequence of operations for mounting a rectifier 2 on a diffuser 1.
  • the head of the screw 9 is positioned in the groove 5 of the diffuser 1, with its flat 13 against the bottom of the groove to provide an anti-rotation function during clamping.
  • the rod of the screw 9 is positioned perpendicular to the flange 4 and passes through the notch 11 formed in this flange.
  • the rectifier 2 has been installed on the diffuser 1, by an axial translation movement.
  • the downstream ferrule 8 is here represented in transparency.
  • the first part 8a of the shell extends in the background, in the extension of the downstream disc 3, while the second part 8b covers the flange 4 of the diffuser.
  • the rod of the screw 9 passes through the second portion 8b by the bore 12 made for this purpose.
  • the figure 7 shows the assembled diffuser-rectifier assembly.
  • the nut 10 is screwed onto the rod of the screw 9 and secures the ferrule 8 of the rectifier with the flange 4 of the diffuser.
  • the diffuser 1 is preferably made from a piece cut in the mass, the groove 5 being machined in an extra thickness left on the downstream disc 3.
  • the groove being machined, notches are then performed in the flange 4 of the diffuser, being distributed a priori regularly on the circumference of said flange.
  • the rectifier 2 is, for its part, made by an attached sheet which reconstructs the air stream, on which is reported by welding or brazing the upstream and downstream ferrules 7 8 which provide the connection with the diffuser 1.
  • This method of realization allows to realize the rectifier independently of the other parts of the turbomachine and in particular to resume the weld seam ferrules in case of overflow of the cord, before mounting the rectifier 2 on the diffuser 1. It can thus s ensure that no burrs from welding protrude into the airstream and disturbs flow by causing pressure drops or unwanted turbulence.
  • the first improvement provided by the invention lies in a perfect alignment of the two parts, which remain aligned regardless of the operating conditions and, in particular, regardless of the level of vibration or thermal deformation of the parts. This characteristic results from the fitting of the ferrule 8 of the rectifier between one side the radial extension of the flange L 6 and the other side flange 4 of the diffuser.
  • the tightening of the screw 9 further provides a stressing of this shell which is retained by the L-shaped flange and which is pushed against the flange 4 by the nut 10. This stressing ensures a good holding of the shell 8 and the perfect alignment of the ducts that channel the vein of air.
  • the rectifier 2 is mounted directly on the diffuser 1, without connection by flanges with the engine structure, which avoids the deformations due to the flexibility of these holding flanges, as found in the prior art.
  • the positioning of the clamping means of the rectifier 2 as close as possible to its connection with the diffuser 1 contributes to this improvement in the rigidity of the assembly and to the constant alignment of the conduits. This avoids the multiplicity of devices for maintaining the rectifier and the mass associated therewith.

Landscapes

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

Claims (9)

  1. Anordnung, bestehend aus einem Diffusor (1) und einem Gleichrichter (2) des aus einem Radialverdichter einer Turbomaschine austretenden Luftstroms, wobei der Diffusor im Wesentlichen die Form einer ringförmigen radial ausgerichteten Doppelscheibe aufweist, und der Gleichrichter ein doppeltes torisches Teil ist, das in der Verlängerung der Doppelscheibe des Diffusors angeordnet ist und gekrümmt ist, um den Luftstrom zur stromabwärtigen Seite der Turbomaschine umzuleiten,
    dadurch gekennzeichnet, dass der Gleichrichter auf dem Diffusor durch eine Verbindung befestigt ist, die in unmittelbarer Nähe der Kontaktoberfläche der zwei Teile positioniert ist und mithilfe eines Standardwerkzeugs unter Ausschluss von jeglichem anderen Stützmittel zerlegbar ist.
  2. Anordnung nach Anspruch 1, wobei die Verbindung eine Verbindung durch Schraube (9) und Mutter (10) ist.
  3. Anordnung nach Anspruch 2, wobei der Diffusor (1) auf einer seiner Scheiben (3) in Höhe seiner Kontaktoberfläche mit dem Gleichrichter einen Flansch (4) enthält, der parallel zur Scheibe ist und mit dieser eine Nut (5) definiert, die geeignet ist, den Kopf der Schraube (9) aufzunehmen und mindestens eine Kerbe (11) enthält, die geeignet ist, das Gewinde der Schraube durchzulassen.
  4. Anordnung nach Anspruch 3, wobei der Gleichrichter (2) auf Höhe seiner Kontaktoberfläche mit dem Diffusor eine Halterung (8) von torischer Form enthält, deren Sektion einen ersten Abschnitt (8a) in L-Form enthält, der das Ende des Diffusors (1) umgibt, gefolgt von einem zweiten Abschnitt (8b), der die Form eines Flansches aufweist, der den entsprechenden Flansch (4) des Diffusors umhüllt.
  5. Anordnung nach einem der Ansprüche 3 oder 4, wobei der Gleichrichter (2) auf Höhe seiner Oberfläche, die zur Zusammenarbeit mit der Scheibe des Diffusors vorgesehen ist, die der Scheibe (3), die den Flansch (4) trägt, gegenüberliegt, eine Halterung (7) von torischer bis sektionsartiger bis L-Form enthält.
  6. Anordnung nach einem der Ansprüche 3 bis 5, wobei der Diffusor (1) auf seiner Scheibe, die der Scheibe, die den Flansch (4) trägt, gegenüberliegt, einen Flansch in L-Form (6) enthält, der sich axial zur Außenseite des Diffusors erstreckt und der so radial hervorsteht, dass für den Gleichrichter ein transversaler Anschlagflansch gebildet wird.
  7. Anordnung nach einem der Ansprüche 3 bis 6, wobei die Schraube (9) auf ihrem Kopf einen Abschnitt enthält, der so trunkiert ist, dass ein Antirotationsorgan durch Zusammenarbeit mit dem Boden der Nut (5) gebildet wird.
  8. Verdichtermodul für eine Turbomaschine, enthaltend eine Diffusor-Gleichrichter-Anordnung nach einem der Ansprüche 1 bis 7.
  9. Turbomaschine, enthaltend eine Diffusor-Gleichrichter-Anordnung am Austritt eines Radialverdichters nach einem der Ansprüche 1 bis 7.
EP11704655.7A 2010-01-19 2011-01-19 Diffusor-gleichrichter-anschluss für einen radialverdichter Active EP2526301B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1050328A FR2955364B1 (fr) 2010-01-19 2010-01-19 Liaison diffuseur-redresseur pour un compresseur centrifuge
PCT/FR2011/050092 WO2011089355A1 (fr) 2010-01-19 2011-01-19 Liaison diffuseur-redresseur pour un compresseur centrifuge

Publications (2)

Publication Number Publication Date
EP2526301A1 EP2526301A1 (de) 2012-11-28
EP2526301B1 true EP2526301B1 (de) 2019-03-06

Family

ID=42330989

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11704655.7A Active EP2526301B1 (de) 2010-01-19 2011-01-19 Diffusor-gleichrichter-anschluss für einen radialverdichter

Country Status (9)

Country Link
US (1) US9291171B2 (de)
EP (1) EP2526301B1 (de)
JP (1) JP5755250B2 (de)
CN (1) CN102713308B (de)
BR (1) BR112012017995B1 (de)
CA (1) CA2787480C (de)
FR (1) FR2955364B1 (de)
RU (1) RU2561790C2 (de)
WO (1) WO2011089355A1 (de)

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DE102015219556A1 (de) 2015-10-08 2017-04-13 Rolls-Royce Deutschland Ltd & Co Kg Diffusor für Radialverdichter, Radialverdichter und Turbomaschine mit Radialverdichter
US10041377B2 (en) * 2015-11-24 2018-08-07 General Electric Company System and method for turbine diffuser
US10041365B2 (en) 2015-11-24 2018-08-07 General Electric Company System of supporting turbine diffuser
US10287920B2 (en) 2015-11-24 2019-05-14 General Electric Company System of supporting turbine diffuser
US10036267B2 (en) 2015-11-24 2018-07-31 General Electric Company System of supporting turbine diffuser outlet
US10036283B2 (en) 2015-11-24 2018-07-31 General Electric Company System and method for diffuser AFT plate assembly
US10837364B2 (en) 2017-01-27 2020-11-17 Raytheon Technologies Corporation Thermal shield for gas turbine engine diffuser case
US11603852B2 (en) 2018-01-19 2023-03-14 General Electric Company Compressor bleed port structure
CN109129267B (zh) * 2018-10-13 2024-01-23 中国航发常州兰翔机械有限责任公司 一种环形箍带装配用工装及其工作方法
US11098730B2 (en) 2019-04-12 2021-08-24 Rolls-Royce Corporation Deswirler assembly for a centrifugal compressor
US11441516B2 (en) 2020-07-14 2022-09-13 Rolls-Royce North American Technologies Inc. Centrifugal compressor assembly for a gas turbine engine with deswirler having sealing features
US11286952B2 (en) 2020-07-14 2022-03-29 Rolls-Royce Corporation Diffusion system configured for use with centrifugal compressor
US11578654B2 (en) 2020-07-29 2023-02-14 Rolls-Royce North American Technologies Inc. Centrifical compressor assembly for a gas turbine engine

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Also Published As

Publication number Publication date
RU2012135461A (ru) 2014-02-27
BR112012017995B1 (pt) 2022-08-30
JP2013517426A (ja) 2013-05-16
CN102713308A (zh) 2012-10-03
EP2526301A1 (de) 2012-11-28
CA2787480C (fr) 2017-11-21
CN102713308B (zh) 2017-07-18
BR112012017995A2 (pt) 2016-05-03
CA2787480A1 (fr) 2011-07-28
US9291171B2 (en) 2016-03-22
WO2011089355A1 (fr) 2011-07-28
US20120308374A1 (en) 2012-12-06
RU2561790C2 (ru) 2015-09-10
FR2955364B1 (fr) 2012-11-16
FR2955364A1 (fr) 2011-07-22
JP5755250B2 (ja) 2015-07-29

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