EP1318276B1 - Raccord à baionnette pour des sections d'un carter de compresseur à haute pression d'une turbine à gaz - Google Patents

Raccord à baionnette pour des sections d'un carter de compresseur à haute pression d'une turbine à gaz Download PDF

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Publication number
EP1318276B1
EP1318276B1 EP02026024A EP02026024A EP1318276B1 EP 1318276 B1 EP1318276 B1 EP 1318276B1 EP 02026024 A EP02026024 A EP 02026024A EP 02026024 A EP02026024 A EP 02026024A EP 1318276 B1 EP1318276 B1 EP 1318276B1
Authority
EP
European Patent Office
Prior art keywords
housing
ring
type coupling
pressure compressor
casing
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.)
Expired - Fee Related
Application number
EP02026024A
Other languages
German (de)
English (en)
Other versions
EP1318276A2 (fr
EP1318276A3 (fr
Inventor
Christian Seydel
Uwe Buchholzer
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP1318276A2 publication Critical patent/EP1318276A2/fr
Publication of EP1318276A3 publication Critical patent/EP1318276A3/fr
Application granted granted Critical
Publication of EP1318276B1 publication Critical patent/EP1318276B1/fr
Anticipated expiration legal-status Critical
Expired - Fee Related 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
    • 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
    • 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
    • F01D25/243—Flange connections; Bolting arrangements
    • 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
    • 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
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/33—Retaining components in desired mutual position with a bayonet coupling

Definitions

  • the invention relates to a bayonet connection for a ring housing for a high-pressure compressor of a gas turbine according to the preamble of the main claim.
  • the invention relates to a ring housing, which comprises a plurality of axially spaced housing rings.
  • US-A-4 630 994 which forms the closest prior art, discloses two housing rings arranged axially to each other which are suitable for a high-pressure compressor and which are connected to one another by means of a bayonet connection. Similar constructions are also shown in US-A-4,552,509 and US-A-3,939,651.
  • the invention has for its object to provide a ring housing of the type mentioned, which avoids the disadvantages of the prior art with a simple structure and simple, cost-effective mountability.
  • At least two adjacent housing rings are connected to one another by means of a bayonet connection.
  • the ring housing according to the invention is characterized by a number of significant advantages.
  • the housing ring is composed of individual ring segments.
  • a rotational fixation of the bayonet connection and thus a safeguard against unintentional release takes place in a preferred embodiment of the invention by means of releasable radial connecting elements. These may be formed as bolts, screws or in a similar manner.
  • At least one marking is attached to at least one housing ring. Consequently Accurate positioning of the housing parts (and the stator blade segments attachable thereto) is ensured prior to assembly.
  • the bayonet connection comprises mutually facing, mutually braceable sealing surfaces.
  • These sealing surfaces may have a trapezoidal or bevelled cross-section in a preferred embodiment of the invention. It is thus realized by the rotational fixation and tension of the individual parts of the ring housing at the same time a reliable seal, without the need for additional, additional components would be required.
  • sealing surfaces are arranged radially on the outside of the annular housing.
  • the ring housing inner housing of the high-pressure compressor
  • the figures show a front housing ring 1 and a rear housing ring 2. These are connected to each other by means of a bayonet connection 3.
  • the bayonet joint 3 comprises, as can be seen in particular from FIG. 1, against each other engagable trapezoidal elements 10, 11, each having beveled contact surfaces.
  • the two housing rings are inserted into each other by means of the bayonet joints and rotated by a predetermined angle to each other.
  • An anti-rotation and fixation by means of a plurality of connecting elements 12, which at the same time apply a radial force and lead to a correspondingly tight clamping of the trapezoidal elements 10, 11.
  • the outer contour (see Fig. 4) has a relatively smooth outer surface which facilitates the supply of cooling air and the introduction of cooling air openings or the like.
  • stator blade segments 8 are fastened by means of connecting elements 12 in the interior region of the rear housing ring 2.
  • the Statorschaufelsegmente threaded inserts 13 in which, as shown in Fig. 1, bolts or screws can be screwed.
  • plug-in elements 4 are formed on the front housing ring 1 and on the stator blade segments 8 (lugs or grooves) that prevent pre-fixing and unintentional twisting.

Landscapes

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

Claims (2)

  1. Carter annulaire pour un compresseur à haute pression d'une turbine à gaz avec plusieurs anneaux de carter (1, 2) disposés axialement les uns par rapport aux autres, sachant qu'au moins deux anneaux de carter (1, 2) adjacents et formés comme segments annulaires sont reliés entre eux par un raccord à baïonnette (3), caractérisé en ce qu'une fixation par rotation est effectuée au moyen d'éléments de jonction radiaux (12) amovibles, et que le raccord à baïonnette (3) comprend des surfaces d'étanchéité (10, 11) orientées les unes vers les autres, situées à l'extérieur dans le sens radial sur le carter annulaire, qui présentent une section transversale trapézoïdale et peuvent être serrées les unes contre les autres.
  2. Carter annulaire selon la revendication nº 1, caractérisé par au moins un repère sur l'anneau de carter.
EP02026024A 2001-12-05 2002-11-21 Raccord à baionnette pour des sections d'un carter de compresseur à haute pression d'une turbine à gaz Expired - Fee Related EP1318276B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10159669A DE10159669A1 (de) 2001-12-05 2001-12-05 Bajonettverbindung für ein Ringgehäuse eines Hochdruckkompressors einer Gasturbine
DE10159669 2001-12-05

Publications (3)

Publication Number Publication Date
EP1318276A2 EP1318276A2 (fr) 2003-06-11
EP1318276A3 EP1318276A3 (fr) 2005-02-09
EP1318276B1 true EP1318276B1 (fr) 2006-06-14

Family

ID=7708086

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02026024A Expired - Fee Related EP1318276B1 (fr) 2001-12-05 2002-11-21 Raccord à baionnette pour des sections d'un carter de compresseur à haute pression d'une turbine à gaz

Country Status (3)

Country Link
US (1) US20030102670A1 (fr)
EP (1) EP1318276B1 (fr)
DE (2) DE10159669A1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2984428B1 (fr) * 2011-12-19 2018-12-07 Safran Aircraft Engines Redresseur de compresseur pour turbomachine.
US9546571B2 (en) * 2012-08-22 2017-01-17 United Technologies Corporation Mounting lug for connecting a vane to a turbine engine case
US9598981B2 (en) * 2013-11-22 2017-03-21 Siemens Energy, Inc. Industrial gas turbine exhaust system diffuser inlet lip
JP6311118B2 (ja) * 2014-06-05 2018-04-18 パナソニックＩｐマネジメント株式会社 送風装置用筐体及びこれを備えた送風装置
WO2022232365A1 (fr) * 2021-04-30 2022-11-03 Zipline International Inc. Coiffe de réduction de bruit pour aéronef

Family Cites Families (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2377740A (en) * 1944-03-31 1945-06-05 Gen Electric Centrifugal compressor
GB1438195A (en) * 1973-08-08 1976-06-03 Penny Turbines Ltd Noel Mounting for attaching a tubular member in co-axial registration with an aperture in a wall
US4066129A (en) * 1976-09-17 1978-01-03 Central Sprinkler Corporation Sprinkler head assembly
US4344740A (en) * 1979-09-28 1982-08-17 United Technologies Corporation Rotor assembly
DE3003469A1 (de) * 1980-01-31 1981-08-06 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Einrichtung zur verbindung einander rotationssymmetrisch zugeordneter bauteile fuer stroemungsmaschinen, insbesondere gasturbinentriebwerke
US4411399A (en) * 1981-09-29 1983-10-25 The Boeing Company Retractable nozzle fairing system for aeroplane center boost engine
DE3333436C1 (de) * 1983-09-16 1985-02-14 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Einrichtung zur Axial- und Umfangssicherung von statischen Gehaeusebauteilen fuer Stroemungsmaschinen
FR2621554B1 (fr) * 1987-10-07 1990-01-05 Snecma Capot d'entree non tournant de turboreacteur a fixation centrale et turboreacteur ainsi equipe
US4911573A (en) * 1987-12-24 1990-03-27 Nuova Omec S.R.L. Rigid axial retainer
US5049770A (en) * 1990-03-26 1991-09-17 General Motors Corporation Electric motor-driven impeller-type air pump
US5288210A (en) * 1991-10-30 1994-02-22 General Electric Company Turbine disk attachment system
US5232340A (en) * 1992-09-28 1993-08-03 General Electric Company Gas turbine engine stator assembly
US5584577A (en) * 1993-03-25 1996-12-17 Whirlpool Corporation Seal for a food blender
US5537814A (en) * 1994-09-28 1996-07-23 General Electric Company High pressure gas generator rotor tie rod system for gas turbine engine
DE19515537A1 (de) * 1995-04-27 1996-10-31 Bmw Rolls Royce Gmbh Kopfteil einer Gasturbinen-Ringbrennkammer
US6318728B1 (en) * 1997-07-11 2001-11-20 Demag Delaval Turbomachinery Corporation Brush-seal designs for elastic fluid turbines
US6139264A (en) * 1998-12-07 2000-10-31 General Electric Company Compressor interstage seal
US6250878B1 (en) * 1999-09-24 2001-06-26 General Electric Company Method and assembly for connecting air ducts in gas turbine engines
US6375421B1 (en) * 2000-01-31 2002-04-23 General Electric Company Piggyback rotor blisk
US6575703B2 (en) * 2001-07-20 2003-06-10 General Electric Company Turbine disk side plate
US20040136873A1 (en) * 2003-01-09 2004-07-15 Argonaut Technologies, Inc. Modular reactor system

Also Published As

Publication number Publication date
EP1318276A2 (fr) 2003-06-11
US20030102670A1 (en) 2003-06-05
DE10159669A1 (de) 2003-07-03
DE50207188D1 (de) 2006-07-27
EP1318276A3 (fr) 2005-02-09

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