EP2901021B2 - Turbomaschinengehäuse und laufrad - Google Patents

Turbomaschinengehäuse und laufrad Download PDF

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Publication number
EP2901021B2
EP2901021B2 EP13779269.3A EP13779269A EP2901021B2 EP 2901021 B2 EP2901021 B2 EP 2901021B2 EP 13779269 A EP13779269 A EP 13779269A EP 2901021 B2 EP2901021 B2 EP 2901021B2
Authority
EP
European Patent Office
Prior art keywords
groove
casing
strip
downstream
blades
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
EP13779269.3A
Other languages
English (en)
French (fr)
Other versions
EP2901021A1 (de
EP2901021B1 (de
Inventor
Vincent Paul Gabriel Perrot
Sébastien COCHON
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
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Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP2901021A1 publication Critical patent/EP2901021A1/de
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Publication of EP2901021B2 publication Critical patent/EP2901021B2/de
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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • 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
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • 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
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips

Definitions

  • the invention relates to an assembly comprising a turbomachine casing and a blade wheel disposed therein.
  • the casing can house one or more impellers, mounted for relative rotation inside the casing.
  • the blades are generally arranged in such a way that their ends pass as close as possible to the internal wall of the casing.
  • the internal surface of the casings of turbomachines is in certain cases equipped with a strip of abradable material (that is to say, intended to undergo abrasion), arranged inside the housing to the right of the end of the blades.
  • the length of the blades is then determined such that the blades, at full speed of the turbomachine, come into contact with the strip of abradable material.
  • the strip of abradable material wears until it reaches a shape which allows it to no longer come into contact with the blades.
  • the shape thus obtained is that which allows a minimum clearance between the end of the blades and the casing.
  • the international application WO2012/025357 presented a casing comprising a blade wheel, and in which the end of the blades is arranged so as to be substantially shorter on the downstream side than on the upstream side. This solution makes it possible to guarantee the existence of a clearance at least between the downstream part of the end of the blades and the casing.
  • turbomachines comprising moving blades inside fixed casings are moreover disclosed by the documents GB2361747 , EP1344895 , US 2012/163967 And JP 2009/174429 .
  • the object of the invention is therefore to propose an arrangement of casing and/or blades which makes it possible to minimize the play between the blades and the casing, which limits as much as possible the contacts and friction between the blades and the casing, and keeps the blades at maximum efficiency.
  • the casing/impeller assembly defined above which comprises, in line with the ends of the blades, a strip of abradable material on the upstream side, and a circumferential groove on the downstream side, has the following advantages.
  • the strip of abradable material is placed in line with the blade ends, on an upstream part thereof. However, it is at the level of the part upstream of the end of the blades that the reduction of the play between the end of the blades and the casing is the most useful.
  • the casing comprises a groove provided immediately downstream of the strip of abradable material.
  • the bottom of the groove is therefore recessed with respect to the strip of abradable material.
  • the groove has a larger radius than the strip of abradable material (more precisely, than the inner surface thereof).
  • This radius difference means that blades having a substantially constant radius from the leading edge to the trailing edge, may have ends having an upstream part very close to the strip of abradable material, so as to wear this strip when implementation of the turbomachine, in a manner known per se, and a downstream part not or very unlikely to come into contact with the surfaces of the groove and therefore the casing.
  • the downstream limit of the circumferential groove can be located to the right, or substantially to the right, of the downstream limit of the blade tips.
  • the downstream limit of the circumferential groove to be arranged axially downstream of the trailing edge of the blades.
  • the downstream limit of the circumferential groove is then preferably placed at an axial distance, relative to the trailing edge of the blades, of between 5 and 20% of the axial chord of the blade taken at the tip of the blade. This distance allows the circumferential groove to have a sufficient range of movement of the tip of the blade with respect to its nominal position.
  • the casing has an optimized contact surface, and advantageously comprises a strip of abradable material of minimum axial extent, which makes it possible to minimize the contacts and friction between the blades and the casing.
  • the invention further relates to a turbomachine axial flow compressor, comprising a casing or the assembly (casing and blade wheel) defined above.
  • the invention finally relates to a turbomachine comprising at least one casing as defined above.
  • FIG. 1 represents a turbomachine axial flow compressor 10.
  • This comprises a casing 12, inside which is mounted a blade wheel 14.
  • the blade wheel 14 itself comprises a rotor disc 16, on which are fixed manner known per se radial vanes 18, axisymmetrically.
  • the impeller is arranged so as to be able to rotate along an axis of rotation A inside the casing 12.
  • the casing 12 has an internal wall 20 delimiting a gas passage vein.
  • This internal wall forms a surface of revolution, which has a substantially conical general shape, and in the present case cylindrical, at the level (axially) of the blade wheel 14.
  • the upstream side of the casing 12 (with respect to the intended direction of circulation of the gases in the casing) is arranged on the left side of the figure.
  • Each of the vanes 18 has a leading edge 18A, a trailing edge 18B, and a tip 19.
  • the radially internal part of the casing 12 consists mainly of two parts: a substantially cylindrical sleeve 22 made of metal or metal alloy (alloy of titanium, aluminum, steel, etc.), and a strip 24 of abradable material, different from the material of part 22, for example an Al-Si based alloy.
  • the sleeve 22 Upstream and downstream of the blades 18, the sleeve 22 has a radially inner surface 23 that is substantially cylindrical.
  • the radius R of the latter is slightly greater than the maximum radius of the blade wheel 14, measured at the end of the blades 18.
  • the sleeve 22 does not include any internal channel or passage serving to ensure gas circulation at the right of the paddle wheel 14.
  • the sleeve 22 comprises a housing 26.
  • This has the shape of a circular circumferential groove, having a shape of revolution around the axis A, and formed hollow in the sleeve 22.
  • This housing 26 has a bottom surface 27 which is generally substantially cylindrical in shape.
  • the strip 24 which is also in the form of a sleeve, is placed in the housing 26 and occupies the upstream part thereof.
  • the housing has upstream, the strip 24 of abradable material, and downstream, a circumferential groove 30, which is simply the downstream part of the housing 26.
  • the band 24 has a radially inner surface 25.
  • the thickness (in the radial direction) of the sleeve 24 is determined in such a way that when the sleeve 24 is placed in the housing 26, the inner surfaces 23 of the sleeve 22 and 25 of the band 24 are continuous with each other, and have the same radius R ( figure 2 ).
  • the difference in radius between the surface 23 (inside the sleeve 22) and the bottom surface 27 of the housing 26, at the level of the strip 24, is thus equal to the thickness of the strip 24.
  • the upstream limit of the surface 25 of the strip 24 is arranged axially substantially in line with the leading edge 18A of the blades 18, or even slightly upstream of the latter.
  • the surface 25 of the strip 24 may have a discontinuity (of position and/or tangency) with respect to the surface 23.
  • the strip 24 could have a slightly smaller inside radius. , or slightly greater than the radius R of the surface 23 of the sleeve 22.
  • the downstream limit of the strip 24 is located approximately halfway (along the axis A) between the leading edge 18A and the trailing edge 18B of the blade 18.
  • the strip 24 of abradable material covers at least 30% of the axial extent of the blades. On the other hand, it is of little use for it to occupy more than 70% of the axial extent of the blades.
  • the groove 30 Immediately downstream of the strip 24 is the groove 30. This is delimited upstream by the strip 24, and at the bottom and on the downstream side by the sleeve 22.
  • the groove 30 generally comprises, from upstream to downstream, three successive parts: An upstream part 32 delimited by the strip 24, a bottom 34, and a downstream part 36.
  • the upstream part is formed by the downstream surface of the strip 24. Conversely, the bottom 34 and the downstream part 36 are not formed from an abradable material.
  • this surface is arranged in a plane transverse to the axis A of the housing 12.
  • the upstream surface 32 forms at the upstream end of the groove 30 an 'outgoing' staircase step, at the level of which the diameter fluid passage increases sharply.
  • the bottom surface 34 is a portion of the bottom surface of the housing 26.
  • the housing 26 has a cylindrical bottom surface and therefore in these embodiments, the bottom surfaces 27 are cylindrical.
  • downstream surface 36 of the groove 30 can be, like the surface 32, arranged in a plane transverse to the axis A of the housing 12 (embodiment of the picture 2 ).
  • the downstream surface 36 of the groove 30 forms at the downstream end of the groove 30 an 'inward' stair step, at the level of which the fluid passage diameter suddenly decreases to become equal to that of the surface. interior of room 22.
  • the downstream limit of the surface 36 of the groove 30 is arranged axially substantially in line with the trailing edge 18B of the blades 18, or even slightly downstream of the latter.
  • the groove 30 therefore has a concave axial section.
  • the axial extent of the bottom surface 34 is smaller than in the first embodiment, and conversely the axial extent of the downstream surface 36 is increased.
  • the surface 34 ends upstream of the trailing edge of the blades 18, and not to the right of this one.
  • the downstream surface 36 of the groove 30 therefore extends from the downstream limit of the bottom surface 34 upstream of the trailing edge of the blades 18, up to the level (axially) of this trailing edge or downstream of it. this.
  • downstream limit of the circumferential groove is arranged not in line with the trailing edge 18B of the blades, but downstream from the latter.
  • the downstream limit of the circumferential groove is thus arranged at an axial distance along the axis A, counted from the trailing edge 18B of the blades, comprised between 5 and 20% of the axial chord of the blades. taken at the top of dawn.
  • the value of the “axial chord of the blades” corresponds to the distance along the axis A, as shown in the figures, between the leading edge 18A and the trailing edge 18B of the blades.
  • the embodiment of the figure 5 is close to that of the figure 4 .
  • the only difference lies in the shape of the bottom of housing 26.
  • the bottom of the housing 26 is divided into two parts: an upstream part which receives the strip 24, and a downstream part which forms the groove 30. These two parts are both cylindrical in shape; the upstream part has a larger internal diameter than the downstream part, and consequently these two parts are separated by a shoulder 38.
  • This shoulder 38 serves to maintain the strip 34 in position, in particular in the axial direction.
  • This surface 40 has a strictly concave axial section (locally) at any point from upstream to downstream and consequently this surface section does not include a straight segment.
  • Its shape is any shape, which ideally is determined by use or by calculation so as to ensure that in all operating modes of the turbomachine, the surfaces 34 and 36 (and therefore the surface 40) remain without contact with the vanes 18.
  • figure 7 presents an embodiment which differs from that presented by the picture 3 by the shape of the upstream surface 32 of the groove 30.
  • the upstream surface 32 is frustoconical, with axis A. It forms with the latter an apex angle ⁇ of 45°.
  • the angle ⁇ is preferably at least equal to 45°.
  • the end 19 of the vanes 18 is located radially strictly inside the wall 20.
  • the length of the vanes is constant.
  • the blades may have a length (measured in the radial direction) which varies according to the position considered on the axis of the blade wheel.
  • the blades can thus have a total radius (overall radius of the blades mounted on the blade wheel) that is axially variable.
  • the blades can moreover have a total radius possibly greater or at least locally greater (that is to say only over a certain axial interval along the axis of the blade wheel) than the radius of the inner surface of the housing immediately upstream or downstream of the impeller.
  • the end of the blades then penetrates at least locally inside the wall of the casing.
  • the vanes can also present a non-uniform radial clearance with the casing, as shown by the embodiments presented above.
  • the overall radius of the vanes may be less or greater than the inside radius (R) of the housing surface immediately upstream or downstream of the vanes.
  • the total radius of the vanes can also vary between one and the other of these configurations depending on the position on the axis of the vane wheel.

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)
  • Polishing Bodies And Polishing Tools (AREA)

Claims (9)

  1. Einheit, umfassend ein Turbomaschinengehäuse (12) und ein radiales Laufrad (14), das in dem genannten Gehäuse angeordnet ist, wobei das Laufrad (14) eine Rotationsachse (A) aufweist und eine Rotorscheibe (16) umfasst, auf der die Schaufeln (18) achsensymmetrisch befestigt sind, wobei das Gehäuse (12) eine Innenwand (20) aufweist, umfassend ein Umfangsband (24) aus abreibbarem Material, wobei
    gegenüber den Enden der Schaufeln das Gehäuse stromaufwärts das Band aus abreibbarem Material, um ein minimales Spiel zwischen den Enden der Schaufeln und dem Gehäuse zu erhalten, und stromabwärts eine Umfangsrille (30) aufweist,
    wobei das Band aus abreibbarem Material stromabwärts von der Umfangsrille (30) begrenzt wird,
    wobei eine stromabwärtige Begrenzung der Umfangsrille (30) axial rechts oder stromabwärts von der Hinterkante (18B) der Schaufeln (18) angeordnet ist,
    wobei die Umfangsrille (30) von stromaufwärts nach stromabwärts drei aufeinanderfolgende Teile umfasst, nämlich einen stromaufwärtigen Teil (32), der von dem Band (24) begrenzt wird, einen Boden (34) und einen stromabwärtigen Teil (36), und
    wobei der Boden (34) der Umfangsrille (30) zylindrisch ist.
  2. Einheit nach Anspruch 1, wobei die Rille, mit Ausnahme einer Fläche (32) der Rille, die aus dem Band aus abreibbarem Material gebildet ist, einen konkaven axialen Querschnitt aufweist.
  3. Einheit nach Anspruch 1 oder 2, wobei die Rille auf der stromabwärtigen Seite mit der Innenwand (20) des Gehäuses durch eine konkave Anschlussformung (36) verbunden ist, insbesondere mit einem Abschnitt eines Kreisbogens.
  4. Einheit nach einem der Ansprüche 1 bis 3, wobei die Rille auf der stromabwärtigen Seite mit der Innenwand des Gehäuses durch eine im Wesentlichen kegelstumpfförmige Fläche (36) verbunden ist.
  5. Einheit nach einem der Ansprüche 1 bis 4, wobei ein Boden (34) der Rille einen Radius aufweist, der kleiner ist als der maximale Radius des Bands aus abreibbarem Material.
  6. Einheit nach einem der Ansprüche 1 bis 5, wobei eine Fläche der Rille, die aus dem Band aus abreibbarem Material gebildet ist, kegelstumpfförmig ist, wobei der Winkel (α) des Kegelstumpfs mindestens 45° und vorzugsweise mindestens 60° beträgt.
  7. Einheit nach einem der Ansprüche 1 bis 6, wobei die Rille (30) einen dichten Boden aufweist.
  8. Einheit nach einem der Ansprüche 1 bis 7, wobei das Band aus abreibbarem Material 30 % bis 70 % der axialen Ausdehnung der genannten Schaufeln bedeckt.
  9. Turbomaschine, umfassend mindestens eine Einheit nach einem der Ansprüche 1 bis 8.
EP13779269.3A 2012-09-25 2013-09-19 Turbomaschinengehäuse und laufrad Active EP2901021B2 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1258959A FR2995949B1 (fr) 2012-09-25 2012-09-25 Carter de turbomachine
PCT/FR2013/052172 WO2014049239A1 (fr) 2012-09-25 2013-09-19 Carter et roue a aubes de turbomachine

Publications (3)

Publication Number Publication Date
EP2901021A1 EP2901021A1 (de) 2015-08-05
EP2901021B1 EP2901021B1 (de) 2020-05-20
EP2901021B2 true EP2901021B2 (de) 2023-07-19

Family

ID=47505053

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13779269.3A Active EP2901021B2 (de) 2012-09-25 2013-09-19 Turbomaschinengehäuse und laufrad

Country Status (9)

Country Link
US (1) US9982554B2 (de)
EP (1) EP2901021B2 (de)
JP (1) JP6382821B2 (de)
CN (1) CN104704244B (de)
BR (1) BR112015006386B1 (de)
CA (1) CA2885650C (de)
FR (1) FR2995949B1 (de)
RU (1) RU2727943C2 (de)
WO (1) WO2014049239A1 (de)

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US9598981B2 (en) * 2013-11-22 2017-03-21 Siemens Energy, Inc. Industrial gas turbine exhaust system diffuser inlet lip
JP6770594B2 (ja) * 2017-02-08 2020-10-14 三菱重工エンジン＆ターボチャージャ株式会社 遠心圧縮機及びターボチャージャ
US10648484B2 (en) 2017-02-14 2020-05-12 Honeywell International Inc. Grooved shroud casing treatment for high pressure compressor in a turbine engine
US10876423B2 (en) 2018-12-28 2020-12-29 Honeywell International Inc. Compressor section of gas turbine engine including hybrid shroud with casing treatment and abradable section
FR3091548B1 (fr) * 2019-01-09 2022-12-09 Safran Aircraft Engines Elément abradable de turbomachine pourvu de témoins d’usure visuels
US10914318B2 (en) * 2019-01-10 2021-02-09 General Electric Company Engine casing treatment for reducing circumferentially variable distortion
US11015465B2 (en) 2019-03-25 2021-05-25 Honeywell International Inc. Compressor section of gas turbine engine including shroud with serrated casing treatment
US11078805B2 (en) * 2019-04-15 2021-08-03 Raytheon Technologies Corporation Inclination of forward and aft groove walls of casing treatment for gas turbine engine
JP7234178B2 (ja) * 2020-03-19 2023-03-07 株式会社東芝 記憶装置
KR102519091B1 (ko) * 2021-05-28 2023-04-05 두산에너빌리티 주식회사 가스터빈의 축류 압축기 유로형상 설계방법

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Also Published As

Publication number Publication date
BR112015006386A2 (pt) 2017-07-04
US20150226078A1 (en) 2015-08-13
EP2901021A1 (de) 2015-08-05
WO2014049239A1 (fr) 2014-04-03
CA2885650C (fr) 2020-09-15
CN104704244A (zh) 2015-06-10
JP6382821B2 (ja) 2018-08-29
CN104704244B (zh) 2018-03-02
US9982554B2 (en) 2018-05-29
EP2901021B1 (de) 2020-05-20
FR2995949A1 (fr) 2014-03-28
RU2015115673A (ru) 2016-11-20
JP2015531447A (ja) 2015-11-02
CA2885650A1 (fr) 2014-04-03
RU2727943C2 (ru) 2020-07-27
BR112015006386B1 (pt) 2022-05-24
FR2995949B1 (fr) 2018-05-25

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