EP0591565A1 - Fixation d'aube statorique pour turbomachine à écoulement axial - Google Patents

Fixation d'aube statorique pour turbomachine à écoulement axial Download PDF

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Publication number
EP0591565A1
EP0591565A1 EP92116970A EP92116970A EP0591565A1 EP 0591565 A1 EP0591565 A1 EP 0591565A1 EP 92116970 A EP92116970 A EP 92116970A EP 92116970 A EP92116970 A EP 92116970A EP 0591565 A1 EP0591565 A1 EP 0591565A1
Authority
EP
European Patent Office
Prior art keywords
blade
blade carrier
guide
carrier segments
segments
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
EP92116970A
Other languages
German (de)
English (en)
Other versions
EP0591565B1 (fr
Inventor
Kamil Matyscak
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.)
ABB Asea Brown Boveri Ltd
ABB AB
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Priority to EP92116970A priority Critical patent/EP0591565B1/fr
Priority to DE59205187T priority patent/DE59205187D1/de
Priority to US08/121,317 priority patent/US5387082A/en
Priority to JP5247687A priority patent/JPH06193403A/ja
Publication of EP0591565A1 publication Critical patent/EP0591565A1/fr
Application granted granted Critical
Publication of EP0591565B1 publication Critical patent/EP0591565B1/fr
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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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

Definitions

  • the invention relates to an axially flow-through turbomachine, in particular a gas turbine with a plurality of vane carrier segments suspended coaxially in a machine housing, in which the guide blades are held with their feet, the foot of each vane engaging in two axially adjacent vane carrier segments.
  • Turbomachines with axial flow are generally equipped with a blade carrier for the guide vanes, which is coaxially suspended in a housing, both the housing and the blade carrier being provided with a horizontal parting plane in which the upper and lower halves are screwed together.
  • Another measure consists in dispensing with the blade carrier designed as a screwed-together half-shell and in hanging the guide blades in blade carrier segments of the type mentioned above. These blade carrier segments are in turn suspended in radial ribs of the housing. With this solution, it is assumed that the thermal deformation of the outer housing is less than that of a half-shell blade carrier.
  • the guide blades are held with their feet in the blade support segments, the foot of each guide blade engaging in two blade support segments that are adjacent in the axial direction.
  • the disadvantage here is that the end faces of the blade carrier segments form the flow-limiting walls of the turbomachine and as such are exposed to the high temperatures prevailing in the flow channel.
  • the segments must therefore be made of a high quality material.
  • the invention tries to avoid this disadvantage.
  • the feet of the guide vanes are provided with a collar which extends in the axial direction up to at least the inlet plane of the upstream or the outlet plane of the rotor blade arranged downstream, and there against the The foot of another guide vane seals.
  • This collar thus forms the flow-limiting wall in the plane of the rotor blade and protects the segments against inadmissible heating.
  • the annular space delimited by the blade carrier segments and the collar of the blade roots is expediently connected to a cooling air space via a bore arranged in the blade carrier segments. Since the other free surfaces of the segments also project into axially adjacent cooling air spaces, in which the air for cooling the guide vanes is also provided, the segments are thus cooled relatively evenly all round.
  • the blade carrier segments are provided with interlocking teeth in the circumferential direction.
  • a blade carrier segment receives at least three blade roots of the same guide row and is positioned in the turbine housing in a stationary manner by means of a screw. If the screw is arranged in the middle of the segment, this ensures that each segment is stretched on both sides in the circumferential direction, the segment ends growing into the toothings, which are equipped with the appropriate play for this purpose.
  • the gas turbine of which the exhaust side and the last four axially flowed stages are shown in FIG. 1 only above the machine axis 13, essentially consists of the rotor 1 bladed with rotor blades and the blade carrier segments 2 equipped with guide blades. These segments 2 are via hammer head grooves (Fig.2) in corresponding receptacles in the machine housing 3, here a turbine housing 3. The suspension takes place in radial ribs 22 which are cast integrally with the housing.
  • the exhaust housing 5 is flanged to the turbine housing, which essentially consists of a hub-side, annular inner part 6 and an annular outer part 7, which delimit the diffuser 9.
  • Both elements 6 and 7 can Half shells with an axial parting plane or one-piece pot housing. They are connected to one another by a plurality of welded-on radial flow ribs 8, which are arranged evenly distributed over the circumference.
  • the annular outer part 7 is provided on the turbine side with an annular sealing strip 10 which is flush with the contour of the turbine channel on the cylinder side.
  • the outlet-side mounting of the turbomachine is arranged in the cavity within the inner part 6, the rotor 1 being located in a support bearing 4.
  • the turbine housing 3 with the radial ribs 22 is provided with a horizontal parting plane (not shown) lying in the machine axis 13.
  • the upper and lower halves of the turbine housing, which are generally provided with flanges, are screwed together.
  • each guide vane 11 is guided with their feet 14 in the segments 2.
  • the foot 14 of each guide vane is provided on its side facing away from the flow channel with brackets which engage in corresponding grooves in the segments 2.
  • Each foot is guided over such a bracket in two axially adjacent blade carrier segments 2, 2 '.
  • the feet 14 of the guide blades 11 are provided with a collar 15 which is flush with the flow-limiting surface of the blade root.
  • the collar extends in the axial direction up to the entry plane 16 of the upstream rotor blade 12. In this plane the collar seals against the foot 14 'of the preceding guide blade 11'.
  • the annular space 19 delimited by a segment 2, the opposite collar 15, and the lateral brackets of two adjacent feet 14, 14 ' is connected to a cooling air space 21 via a bore 20 arranged in the blade carrier segment.
  • FIG. 5 shows an example of such a seal.
  • These are two spring plates 23 stapled together in their center, which rest in the grooves of the foot 14 'and the collar 15 and thus ensure the free movement of heat of the elements involved with a good seal.
  • Such a sealing element is expediently provided in the circumferential direction per blade root. The abovementioned cooling air can escape into the flow channel at its abutment points in the circumferential direction
  • a blade carrier segment 2 comprises three blade feet 11 of the same guide row after blading.
  • Each segment is in the turbine housing, i.e. screwed to its corresponding radial rib 22 with a stud 18. These screws are advantageously arranged in the middle of the segment, as seen in the circumferential direction.
  • the blade carrier segments 2 are provided with interlocking teeth 17 at their ends on both sides, as can be seen in FIG. 4.
  • This toothing 17 has the play S in the circumferential direction in order to allow free expansion of the segments.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP92116970A 1992-10-05 1992-10-05 Fixation d'aube statorique pour turbomachine à écoulement axial Expired - Lifetime EP0591565B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP92116970A EP0591565B1 (fr) 1992-10-05 1992-10-05 Fixation d'aube statorique pour turbomachine à écoulement axial
DE59205187T DE59205187D1 (de) 1992-10-05 1992-10-05 Leitschaufeleinhängung für axialdurchströmte Turbomaschine
US08/121,317 US5387082A (en) 1992-10-05 1993-09-15 Guide wave suspension for an axial-flow turbomachine
JP5247687A JPH06193403A (ja) 1992-10-05 1993-10-04 軸流式のターボ機械

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP92116970A EP0591565B1 (fr) 1992-10-05 1992-10-05 Fixation d'aube statorique pour turbomachine à écoulement axial

Publications (2)

Publication Number Publication Date
EP0591565A1 true EP0591565A1 (fr) 1994-04-13
EP0591565B1 EP0591565B1 (fr) 1996-01-24

Family

ID=8210100

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92116970A Expired - Lifetime EP0591565B1 (fr) 1992-10-05 1992-10-05 Fixation d'aube statorique pour turbomachine à écoulement axial

Country Status (4)

Country Link
US (1) US5387082A (fr)
EP (1) EP0591565B1 (fr)
JP (1) JPH06193403A (fr)
DE (1) DE59205187D1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9086152B2 (en) 2010-04-23 2015-07-21 Carl Freudenberg Kg Mechanical face seal
WO2015120997A1 (fr) * 2014-02-14 2015-08-20 Siemens Aktiengesellschaft Protection contre l'érosion et la corrosion par érosion de nervures de carter moulés

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4436731A1 (de) * 1994-10-14 1996-04-18 Abb Management Ag Verdichter
EP1118806A1 (fr) * 2000-01-20 2001-07-25 Siemens Aktiengesellschaft Structure de paroi sous charge thermique et méthode pour fermer des fentes dans une tel structure
US6893214B2 (en) * 2002-12-20 2005-05-17 General Electric Company Shroud segment and assembly with surface recessed seal bridging adjacent members
US6808363B2 (en) * 2002-12-20 2004-10-26 General Electric Company Shroud segment and assembly with circumferential seal at a planar segment surface
EP1443275B1 (fr) * 2003-01-29 2008-08-13 Siemens Aktiengesellschaft Chambre de combustion
US7255929B2 (en) * 2003-12-12 2007-08-14 General Electric Company Use of spray coatings to achieve non-uniform seal clearances in turbomachinery
FR2902843A1 (fr) * 2006-06-23 2007-12-28 Snecma Sa Secteur de redresseur de compresseur ou secteur de distributeur de turbomachine
US7762766B2 (en) * 2006-07-06 2010-07-27 Siemens Energy, Inc. Cantilevered framework support for turbine vane
US8240045B2 (en) * 2007-05-22 2012-08-14 Siemens Energy, Inc. Gas turbine transition duct coupling apparatus
FR2918444B1 (fr) * 2007-07-05 2013-06-28 Snecma Deflecteur de fond de chambre, chambre de combustion le comportant et moteur a turbine a gaz en etant equipe
US8616007B2 (en) * 2009-01-22 2013-12-31 Siemens Energy, Inc. Structural attachment system for transition duct outlet
US8231338B2 (en) * 2009-05-05 2012-07-31 General Electric Company Turbine shell with pin support
US8651809B2 (en) 2010-10-13 2014-02-18 General Electric Company Apparatus and method for aligning a turbine casing
EP2700798A1 (fr) * 2012-08-21 2014-02-26 Siemens Aktiengesellschaft Turbomachine comprenant un rotor et un boîtier
US9631507B2 (en) * 2014-07-14 2017-04-25 Siemens Energy, Inc. Gas turbine sealing band arrangement having a locking pin
US10030541B2 (en) 2015-07-01 2018-07-24 Rolls-Royce North American Technologies Inc. Turbine shroud with clamped flange attachment
US11466700B2 (en) * 2017-02-28 2022-10-11 Unison Industries, Llc Fan casing and mount bracket for oil cooler
DE102018210601A1 (de) * 2018-06-28 2020-01-02 MTU Aero Engines AG Segmentring zur montage in einer strömungsmaschine
DE102018210600A1 (de) * 2018-06-28 2020-01-02 MTU Aero Engines AG Mantelringanordnung für eine strömungsmaschine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB647384A (en) * 1948-10-05 1950-12-13 English Electric Co Ltd Improvements in and relating to gas turbine blading
GB689270A (en) * 1949-12-13 1953-03-25 Rateau Soc Improvements in axial flow turbines or compressors
US3004700A (en) * 1959-08-18 1961-10-17 Gen Electric Turbine engine casing
US3427000A (en) * 1966-11-14 1969-02-11 Westinghouse Electric Corp Axial flow turbine structure
US3981609A (en) * 1975-06-02 1976-09-21 United Technologies Corporation Coolable blade tip shroud

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB786689A (en) * 1955-11-09 1957-11-20 Gen Motors Corp Improvements relating to elastic-fluid turbines
GB904138A (en) * 1959-01-23 1962-08-22 Bristol Siddeley Engines Ltd Improvements in or relating to stator structures, for example for axial flow gas turbine engines
US3542483A (en) * 1968-07-17 1970-11-24 Westinghouse Electric Corp Turbine stator structure
US3892497A (en) * 1974-05-14 1975-07-01 Westinghouse Electric Corp Axial flow turbine stationary blade and blade ring locking arrangement
CS174516B1 (fr) * 1974-09-26 1977-04-29
US5224824A (en) * 1990-09-12 1993-07-06 United Technologies Corporation Compressor case construction

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB647384A (en) * 1948-10-05 1950-12-13 English Electric Co Ltd Improvements in and relating to gas turbine blading
GB689270A (en) * 1949-12-13 1953-03-25 Rateau Soc Improvements in axial flow turbines or compressors
US3004700A (en) * 1959-08-18 1961-10-17 Gen Electric Turbine engine casing
US3427000A (en) * 1966-11-14 1969-02-11 Westinghouse Electric Corp Axial flow turbine structure
US3981609A (en) * 1975-06-02 1976-09-21 United Technologies Corporation Coolable blade tip shroud

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9086152B2 (en) 2010-04-23 2015-07-21 Carl Freudenberg Kg Mechanical face seal
WO2015120997A1 (fr) * 2014-02-14 2015-08-20 Siemens Aktiengesellschaft Protection contre l'érosion et la corrosion par érosion de nervures de carter moulés

Also Published As

Publication number Publication date
EP0591565B1 (fr) 1996-01-24
DE59205187D1 (de) 1996-03-07
JPH06193403A (ja) 1994-07-12
US5387082A (en) 1995-02-07

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