EP2901021A1 - Turbomaschinengehäuse und laufrad - Google Patents

Turbomaschinengehäuse und laufrad

Info

Publication number
EP2901021A1
EP2901021A1 EP13779269.3A EP13779269A EP2901021A1 EP 2901021 A1 EP2901021 A1 EP 2901021A1 EP 13779269 A EP13779269 A EP 13779269A EP 2901021 A1 EP2901021 A1 EP 2901021A1
Authority
EP
European Patent Office
Prior art keywords
groove
downstream
abradable material
blades
housing
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
EP13779269.3A
Other languages
English (en)
French (fr)
Other versions
EP2901021B1 (de
EP2901021B2 (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
SNECMA Services SA
SNECMA 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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=47505053&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP2901021(A1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by SNECMA Services SA, SNECMA SAS filed Critical SNECMA Services SA
Publication of EP2901021A1 publication Critical patent/EP2901021A1/de
Publication of EP2901021B1 publication Critical patent/EP2901021B1/de
Application granted granted Critical
Publication of EP2901021B2 publication Critical patent/EP2901021B2/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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 paddle wheel disposed therein.
  • the housing can house one or more paddle wheels, mounted (s) rotation relative to the interior of the housing.
  • the vanes are arranged in such a way that their ends pass as close as possible to the internal wall of the casing.
  • turbomachine casings To prevent these contacts from damaging the wall of the casing, in a manner known per se, the internal surface of turbomachine casings is in some cases equipped with a strip of abradable material (that is to say, intended to undergo abrasion), arranged inside the casing at the end of the blades.
  • abradable material that is to say, intended to undergo abrasion
  • the length of the blades is then determined so that the blades, at full speed of the turbomachine, come into contact with the band of abradable material.
  • the band of abradable material wears until it reaches a shape that 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 housing.
  • the international application WO2012 / 025357 has presented a casing comprising a paddle wheel, and wherein the end of the blades is arranged to be substantially shorter on the blade. downstream side only on the upstream side.
  • the object of the invention is therefore to provide a housing arrangement and / or blades that allows to minimize the clearance between the blades and the housing, which limits as much as possible the contacts and friction between the blades and the housing, and keeps the blades at maximum efficiency.
  • an assembly comprising a turbomachine casing and a bladed wheel disposed in said casing, the casing having an inner wall comprising a circumferential band of abradable material; and wherein, opposite the ends of the blades, the casing has upstream, the strip of abradable material, and downstream, a circumferential groove; the strip of abradable material being delimited downstream by the circumferential groove, and a downstream limit of the circumferential groove being arranged axially at right angles or downstream of the trailing edge of the vanes.
  • the casing / impeller assembly defined above which comprises, at the ends of the blades, a strip of material abradable on the upstream side, and a circumferential groove on the downstream side, has the following advantages.
  • the band of abradable material is placed at the ends of the blades on an upstream part thereof. However, it is at the upstream portion of the end of the blades that the reduction of the clearance between the end of the blades and the housing is the most useful.
  • the casing comprises a groove arranged immediately downstream of the band of abradable material.
  • the bottom of the groove is thus hollow with respect to the band of abradable material.
  • the groove has a radius greater than the band of abradable material (more precisely, than the inner surface thereof).
  • This radius difference causes blades having a substantially constant radius from the leading edge to the trailing edge, may have ends having an upstream portion very close to the band of abradable material, so as to wear this band when setting implementation of the turbomachine, in a manner known per se, and a downstream portion not or very unlikely to come into contact with the surfaces of the groove and thus the housing.
  • downstream limit of the circumferential groove may be located at right, or substantially right, of the downstream limit of the blade tips.
  • downstream limit of the circumferential groove is disposed axially downstream of the trailing edge of the blades.
  • downstream limit of the circumferential groove is preferably at an axial distance, relative to the trailing edge of the blades, between 5 and 20% of the axial rope of the blade blade dawn. This distance allows the circumferential groove to have a sufficient clearance range of the top of the blade relative to its nominal position.
  • the housing has an optimized contact surface, and advantageously comprises a strip of abradable material of minimum axial extent, which allows to minimize contact and friction between the blades and the housing.
  • the groove except a groove surface formed by the band of abradable material, may have a concave axial section.
  • a bottom of the groove may comprise a cylindrical portion.
  • the groove except for a groove surface formed by the band of abradable material, may have a concave axial section at any point from upstream to downstream.
  • the groove can be connected on the downstream side to the inner wall of the housing by a concave fillet, in particular having a section arcuate.
  • the groove can be connected on the downstream side to the inner wall of the housing by a substantially frustoconical surface.
  • the bottom of the groove may have a radius less than the maximum radius of the band of abradable material.
  • a groove surface may be formed by the strip of abradable material and be frustoconical in shape, the angle of the truncated cone being at least 45 °, and preferably at least 60 °.
  • this surface of the groove formed by the band of abradable material may be formed in a plane transverse to the housing, and be perpendicular to the axis of the housing.
  • the groove can be waterproof, or have a sealed bottom.
  • the groove is not connected to gas or fluid circulation ducts. It does not allow the sampling or the supply of gas, but is only used to allow free rotation of the blade ends avoiding shocks between them and the housing.
  • the band of abradable material covers 30% to 70% of the axial extent of the blades.
  • the invention further relates to a turbomachine axial flow compressor, comprising a housing or the assembly (casing and impeller) defined above.
  • the invention finally relates to a turbomachine comprising at least one housing as defined above.
  • FIG. 1 is a schematic view of a compressor portion comprising a housing according to the invention
  • FIG. 2 is a schematic axial section of a compressor portion passing through a blade in a first embodiment of the invention
  • FIG. 3 is a section similar to that of Figure 2, showing a second embodiment of the invention
  • FIG. 4 is a section similar to that of Figure 2, showing a third embodiment of the invention.
  • FIG. 5 is a section similar to that of Figure 2, showing a fourth embodiment of the invention.
  • FIG. 6 is a section similar to that of Figure 2, showing a fifth embodiment of the invention.
  • FIG. 1 represents a turbomachine axial flow compressor
  • the latter comprises a casing 12, inside which is mounted a paddle wheel 14.
  • the paddle wheel 14 itself comprises a rotor disk 16, on which are fixed in known manner radial blades 18 , axisymmetrically.
  • the impeller is arranged to be rotatable about an axis of rotation A inside the housing 12.
  • the housing 12 has an inner wall 20 defining a gas passage vein.
  • This inner wall forms a surface of revolution, which has a generally conical general shape, and in the present case cylindrical, at (axially) level of the impeller 14.
  • each of the blades 18 has a leading edge 18A, a trailing edge 18B, and an end 19.
  • the radially inner portion of the casing 12 consists mainly of two parts: a substantially cylindrical sleeve 22 of metal or metal alloy (titanium alloy, aluminum, steel, etc.), and a strip 24 of abradable material, different from the material of the 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 thereof is slightly greater than the maximum radius of the impeller 14, measured at the end of the blades 18. The sleeve 22 has no channel or internal passage used to ensure a flow of gas to the right of the paddle wheel 14.
  • the sleeve 22 Facing or at the ends of the vanes 18, the sleeve 22 comprises a housing 26.
  • the latter has the shape of a circular circumferential groove, having a shape of revolution about the axis A, and formed recess in the sleeve 22.
  • This housing 26 has a bottom surface 27 which is generally of substantially cylindrical shape.
  • the band 24 which is also in the form of a sleeve, is disposed in the housing 26 and occupies the upstream portion thereof.
  • the casing has upstream, the band 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 such that when the sleeve 24 is disposed in the housing 26, the inner surfaces 23 of the sleeve 22 and 25 of the band 24 are in continuity with one another, 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 band 24, is thus equal to the thickness of the band 24.
  • the upstream limit of the surface 25 of the strip 24 is arranged axially substantially right of the leading edge 18A of the vanes 18, or slightly upstream of it.
  • the surface 25 of the strip 24 may have a discontinuity (position and / or tangency) relative to the surface 23.
  • the band 24 may have a slightly smaller inner radius or slightly greater than the radius R of the surface 23 of the sleeve 22.
  • the downstream limit of the band 24 is located approximately halfway (along the axis A) between the leading edge 18A and the trailing edge 18B of the blade 18.
  • the band 24 of abradable material covers at least 30% of the axial extent of the blades.
  • the groove 30 Immediately downstream of the band 24 is the groove 30. The latter is delimited upstream by the band 24, and at the bottom and 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 band 24, a bottom 34, and a downstream part 36.
  • the upstream portion is formed by the downstream surface of the strip 24. Inversely, the bottom 34 and the downstream portion 36 are not formed of abradable material.
  • this surface is disposed 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 a stair step 'outgoing', at which the fluid flow diameter increases abruptly.
  • the bottom surface 34 is a part of the bottom surface of the housing 26.
  • the housing 26 has a cylindrical bottom surface and therefore in these embodiments, the surfaces bottom 27 are cylindrical.
  • downstream surface 36 of the groove 30 may be, like the surface 32, disposed in a plane transverse to the axis A of the casing 12 (embodiment of FIG. 2).
  • the downstream surface 36 of the groove 30 forms at the downstream end of the groove 30 a 'reentrant' stair step, at which the fluid flow diameter decreases. brutally to become equal to that of the inner surface of the piece 22.
  • the downstream limit of the surface 36 of the groove 30 is disposed axially substantially to the right of the trailing edge 18B of the blades 18, or slightly downstream thereof.
  • the groove 30 thus has a concave axial section.
  • Figures 3 to 7 show different embodiments of the groove 30.
  • the downstream surface 36 is of frustoconical shape, of axis A.
  • the groove 30 is connected on the downstream side to the inner wall 20 of the housing by a substantially frustoconical surface, forming in axial section a constant slope connecting the bottom 34 to the wall 20 of the housing. This form advantageously limits the formation of turbulence at the downstream part of the end of the blades 18.
  • downstream surface 36 is a concave fillet, having an arcuate section.
  • the upstream limit of this connection fillet is in continuity of position and tangency with the bottom 34 of the groove 30.
  • 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 is completed upstream of the trailing edge of the blades 18, and not to the right thereof.
  • the downstream surface 36 of the groove 30 thus extends from the downstream limit of the bottom surface 34 upstream of the trailing edge of the vanes 18 to the level (axially) of this trailing edge or downstream thereof. this.
  • downstream limit of the circumferential groove is disposed not at the trailing edge 18B of the vanes, but downstream thereof.
  • the downstream limit of the circumferential groove is thus disposed at an axial distance along the axis A, counted from the trailing edge 18B of the blades, between 5 and 20% of the axial rope of the blades. taken at the top of dawn.
  • the value of the 'axial cord of the blades' corresponds to the distance along the axis A, such that shown in the figures, between the leading edge 18A and the trailing edge 18B of the blades.
  • FIG. 5 is similar to that of FIG. 4. The only difference is the shape of the bottom of the housing 26.
  • the bottom of the housing 26 is divided into two parts: an upstream portion which receives the band 24, and a downstream part which forms groove 30. These two parts are both cylindrical in shape; the upstream portion has a larger inner diameter than the downstream portion, and therefore these two portions are separated by a shoulder 38.
  • This shoulder 38 serves to maintain the position in position of the band 34, in particular in the axial direction.
  • Figure 6 shows an embodiment in which the bottom 34 and downstream 36 surfaces are continuous; no limit between them is perceptible.
  • This surface 40 has a strictly concave axial section
  • this surface section does not include a line segment.
  • Its shape is any shape, which ideally is determined in use or by calculation so as to ensure that in all modes of operation of the turbomachine, the surfaces 34 and 36 (and therefore the surface 40) remain without contact with the blades 18.
  • FIG. 7 shows an embodiment which differs from that shown in FIG. 3 by the shape of the upstream surface 32 of the groove 30.
  • the upstream surface 32 is frustoconical, of axis A. It forms with the latter an angle at the apex of 45 °.
  • the angle a is preferably at least 45 °.
  • the end 19 of the blades 18 is located radially strictly inside the wall 20.
  • the blade length (measured in the radial direction) is constant.
  • the blades may have a length
  • the blades may thus have a total radius (overall radius of vanes mounted on the impeller) axially variable.
  • the blades may also have a total radius possibly greater or at least locally higher (that is to say only over a certain axial interval along the axis of the impeller) to the radius 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 housing.
  • the blades may also have a non-uniform radial clearance with the housing, as shown in the embodiments presented above.
  • the total blade radius may be smaller than or greater than the inner radius (R) of the crankcase surface immediately upstream or downstream of the blades.
  • the total radius of the blades may also vary between one of these configurations depending on the position on the axis of the impeller.

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)
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 true EP2901021A1 (de) 2015-08-05
EP2901021B1 EP2901021B1 (de) 2020-05-20
EP2901021B2 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)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9598981B2 (en) * 2013-11-22 2017-03-21 Siemens Energy, Inc. Industrial gas turbine exhaust system diffuser inlet lip
US11092163B2 (en) 2017-02-08 2021-08-17 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Compressor and turbocharger
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

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4534698A (en) * 1983-04-25 1985-08-13 General Electric Company Blade containment structure
GB2245312B (en) * 1984-06-19 1992-03-25 Rolls Royce Plc Axial flow compressor surge margin improvement
JPH0835402A (ja) 1994-07-26 1996-02-06 Ishikawajima Harima Heavy Ind Co Ltd タービンケーシング構造
US5474417A (en) * 1994-12-29 1995-12-12 United Technologies Corporation Cast casing treatment for compressor blades
US5607284A (en) * 1994-12-29 1997-03-04 United Technologies Corporation Baffled passage casing treatment for compressor blades
US6227794B1 (en) † 1999-12-16 2001-05-08 Pratt & Whitney Canada Corp. Fan case with flexible conical ring
US6382905B1 (en) * 2000-04-28 2002-05-07 General Electric Company Fan casing liner support
WO2002036950A2 (en) * 2000-11-06 2002-05-10 Advanced Components And Materials, Inc. Compliant brush shroud assembly for gas turbine engine compressors
US6585479B2 (en) * 2001-08-14 2003-07-01 United Technologies Corporation Casing treatment for compressors
FR2832180B1 (fr) * 2001-11-14 2005-02-18 Snecma Moteurs Revetement abradable pour parois de turbines a gaz
GB0206136D0 (en) * 2002-03-15 2002-04-24 Rolls Royce Plc Improvements in or relating to cellular materials
US20080041842A1 (en) 2005-09-07 2008-02-21 United Technologies Corporation Connector for heater
GB0526011D0 (en) * 2005-12-22 2006-02-01 Rolls Royce Plc Fan or compressor casing
FR2899274B1 (fr) * 2006-03-30 2012-08-17 Snecma Dispositif de fixation de secteurs d'anneau autour d'une roue de turbine d'une turbomachine
JP4942206B2 (ja) 2008-01-24 2012-05-30 株式会社日立製作所 回転機械
US8177494B2 (en) * 2009-03-15 2012-05-15 United Technologies Corporation Buried casing treatment strip for a gas turbine engine
FR2947016B1 (fr) * 2009-06-17 2013-07-12 Snecma Compresseur centrifuge.
GB2483059A (en) 2010-08-23 2012-02-29 Rolls Royce Plc An aerofoil blade with a set-back portion
US9115594B2 (en) * 2010-12-28 2015-08-25 Rolls-Royce Corporation Compressor casing treatment for gas turbine engine
GB201103682D0 (en) * 2011-03-04 2011-04-20 Rolls Royce Plc A turbomachine casing assembly

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2014049239A1 *

Also Published As

Publication number Publication date
EP2901021B1 (de) 2020-05-20
JP2015531447A (ja) 2015-11-02
BR112015006386A2 (pt) 2017-07-04
CN104704244B (zh) 2018-03-02
RU2727943C2 (ru) 2020-07-27
EP2901021B2 (de) 2023-07-19
CA2885650C (fr) 2020-09-15
BR112015006386B1 (pt) 2022-05-24
JP6382821B2 (ja) 2018-08-29
US20150226078A1 (en) 2015-08-13
US9982554B2 (en) 2018-05-29
FR2995949A1 (fr) 2014-03-28
WO2014049239A1 (fr) 2014-04-03
CA2885650A1 (fr) 2014-04-03
RU2015115673A (ru) 2016-11-20
FR2995949B1 (fr) 2018-05-25
CN104704244A (zh) 2015-06-10

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