EP2058477A1 - Verbindung von radialen Streben mit einem kreisförmigen Gehäuse durch Stifte und Abstandshalter - Google Patents

Verbindung von radialen Streben mit einem kreisförmigen Gehäuse durch Stifte und Abstandshalter Download PDF

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Publication number
EP2058477A1
EP2058477A1 EP08168197A EP08168197A EP2058477A1 EP 2058477 A1 EP2058477 A1 EP 2058477A1 EP 08168197 A EP08168197 A EP 08168197A EP 08168197 A EP08168197 A EP 08168197A EP 2058477 A1 EP2058477 A1 EP 2058477A1
Authority
EP
European Patent Office
Prior art keywords
ferrule
arm
arms
spacers
bores
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
EP08168197A
Other languages
English (en)
French (fr)
Other versions
EP2058477B1 (de
Inventor
Godefroy Francis Frédéric Drelon
Sébastien Jean Laurent Prestel
Jean-Luc Soupizon
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 SAS
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Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP2058477A1 publication Critical patent/EP2058477A1/de
Application granted granted Critical
Publication of EP2058477B1 publication Critical patent/EP2058477B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins

Definitions

  • the subject of the invention is the connection of radial arms to a circular shell by axes and spacers, particularly in turbomachines used in aeronautics.
  • turbomachines comprise an outer shell concentric with a ferrule of an inner hub and joined to it by radial arms and delimiting an annular chamber or a portion of gas flow vein, also annular but open at its ends.
  • FIG 1 which partially and schematically represents a turbomachine conventionally comprising, between a stator 1 and a rotor 2, successively low pressure compressors 3 and high pressure 4, a combustion chamber 5, and high pressure turbines 6 and low pressure 7; the rotor 2 can be divided into two separate parts between the turbines 6 and 7, and an inner hub 8 extends between these two parts to maintain a smooth shape of a vein 9 of gas flow in the turbomachine.
  • the inner hub 8 is supported by substantially radial arms 10 which join its ferrule (inner circular) to a concentric outer shell 11 belonging to the stator 1 and which also delimits the gas flow vein 9 on the opposite outer side.
  • the arms 10 are profiles of simple section, generally rectangular. They are subjected to the high temperatures reached by the combustion gases, while influencing their flow. It is necessary to surround them fairing 12 separated from them by a sufficient clearance, to protect them somewhat from the heating and to provide a contour profile of good aerodynamic gas quality.
  • the figure 4 illustrates the assembly of the outer shell 11, the arms 10 and the inner hub in the isolated state, to give a clearer idea. The assembly flanges (not referenced) to stator 1 and rotor 2 appear therein.
  • the docking movement of the arms 10 to the assembly locations of the outer shell 11 is therefore difficult to achieve, as is the introduction of the tools required for assembly through the fairing fairing 12.
  • the connection between the arms 10 and the outer shell 11 must be designed to meet these constraints, but also to withstand the significant forces exerted on the arms in service and the significant warm-ups that they undergo despite fairings 12.
  • a classic montage illustrated at figure 2 , consists in making a hole at the end of each arm 10, to establish an ear 13 pierced on the outer shell 11, to place the arm 10 against the ear 13 so as to align its piercing with the piercing of the ear, and to pass a bolt 14 through the alignment of the holes and which serves as the axis of support; but the forces experienced by the arm 10 subject the parts of the assembly to greater efforts because of the cantilever assembly, and in particular the bolt is loaded flexion, which is disadvantageous and requires of course- dimensioning the connection parts, so as to withstand greater bending stresses than in the case of a symmetrical configuration with two ears.
  • the outer shell 11 is provided with two parallel lugs 15 and 16 between which the end of the arm 10 is placed and a bolt 17 is mounted through the bores of the arm 10 and the two lugs 15 and 16.
  • connection designs between the arms and the outer shell use intermediate parts, assembled both at the ferrule and the arms.
  • An example is in the document US 5,272,869 . They often have the drawbacks of having excessive dimensions to allow easy assembly and are usually bolted to the arms, with the risk of making disassembly of arms impossible if the bolts seize.
  • the mounting of the connection is easy, even with reduced access whose fairing is responsible; the parts of the connection are simple, of small volume and not heavy; additional efforts due to overhangs or deformations in the assembly are avoided; the bolts are disjoint from the arm, in contact with less hot parts, and therefore less subject to heating and seizure; and the precise positioning of the arms on the ferrule is guaranteed.
  • the invention in a general form, relates to an arrangement comprising a circular ferrule, essentially radial arms joining the ferrule to another concentric ferrule, and connections of the arms to the ferrule or to the inner means, the connections each comprising at least one piercing traversing the arm parallel to the ferrule, an axis passing through each of said bores, characterized in that the shaft is provided with a pair of bores on either side of the arm, and the connections further comprise a pair of spacers disposed on either side of the arm between the axis and the ferrule, bores passing through the ferrule and the spacers and forming alignments with the bores of the axis, and bolts passing through the alignments of the bores and tightening the shell, axis and spacers.
  • the ferrule connected to the arm as indicated may be the outer shell 11, as is usual, but also the circular shell of the inner means 8: the arrangement would be the same except a few dimensional changes.
  • the arrangement further comprises a pair of axes for each of the connections, the axes of the pair being parallel, and four alignments of the aforesaid holes and bolts.
  • the arrangement includes locating pins in other drill alignments that extend into the arm, and either into the ferrule or into the axis or axes.
  • Another aspect of the invention is a turbomachine comprising the connection arrangement detailed above.
  • the assembly is represented at figure 5 , and its elements to Figures 6, 7, 8 and 9 .
  • the end of the arm 10 carries two parallel holes 20, established at its end through the smallest dimension and on two opposite sides ( Figures 5 and 8 ).
  • Axes 21 ( Figures 5 and 6 ) are engaged through the holes 20 while exceeding. They comprise a central portion 22 having the same section - preferably circular - that the holes 20 and housed in them and two lateral portions 23 projecting from the arm 10 and each traversed by an axis bore 24. The lateral portions 23 are provided with 25.
  • the arrangement further comprises spacers 26 ( Figures 5 and 7 ), traversed by a pair of spacer holes 27 parallel to each other.
  • the outer shell 11 is provided with a boss 28 ( Figures 5 and 9 ) associated with each of the connections and whose surface is flat or cylindrical, the cylinder admitting the same axis as the turbomachine. It is pierced by holes, including four outer holes 29 and two inner holes 30, through each boss 28.
  • the assembly is carried out by mounting the shrouds 12 (which are not shown in the last figures) around the arms 10 and introducing the assembly consisting of the inner hub 8, arms 10 and shrouds 12 in the outer shell 11 axial movement.
  • the setting in position is made when the inner holes 30 come in extension of holes 31 established in the ends of the arm 10 ( figure 8 ).
  • Positioning pieces 32 can then be introduced into these drill alignments 30 and 31 to maintain the arms 10 at a precise and fixed position.
  • the pins 21 are then introduced into the holes 20.
  • the spacers 26 are then introduced between the bosses 28 and the flats 25 of the pins 21 on either side of the arm 10, each of the spacers 26 in one of the protruding portions 23 of each At the positional adjustment, four alignments each comprising an outer bore 29 of the ferrule 11, a spacer bore 27 and an axle bore 24 were made.
  • the bolts 33 are finally threaded through them. aligning holes and tightened so as to compress the spacers 26 between the pins 21 and the outer shell 11.
  • positioning pins similar to 32 could extend into another bore of the axis 21 to retain the latter in place.
  • the symmetrical nature of the assembly reduces the forces applied, and above all to the arms 10. All the parts of the connection are placed at a short distance from the outer shell 11, which allows them to be mounted or adjusted without difficulty by the present game. between the outer shell 11 and the fairing 12.
  • the bolts 32 are easily accessible and can be mounted at will with the nut inside or outside the outer shell 11, according to the constraints of space or other qu 'we can meet.
  • the bolts 32 are disjoined arms 10, so that the disassembly of the connections should remain possible even in case of complications, such as nut seizures.
  • the axes 21 can be reduced to one by accepting a distribution a little less good efforts.
  • the sections of the central portion 22 and the holes 20 may be non-circular, although a circular shape is preferred since it is easier to manufacture while allowing a distribution of more regular and better defined efforts.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Connection Of Plates (AREA)
  • Mutual Connection Of Rods And Tubes (AREA)
EP08168197.5A 2007-11-09 2008-11-03 Verbindung von radialen Streben mit einem kreisförmigen Gehäuse durch Stifte und Abstandshalter Active EP2058477B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0758941A FR2923530B1 (fr) 2007-11-09 2007-11-09 Raccordement de bras radiaux a une virole circulaire par des axes et des entretoises

Publications (2)

Publication Number Publication Date
EP2058477A1 true EP2058477A1 (de) 2009-05-13
EP2058477B1 EP2058477B1 (de) 2013-08-07

Family

ID=39539735

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08168197.5A Active EP2058477B1 (de) 2007-11-09 2008-11-03 Verbindung von radialen Streben mit einem kreisförmigen Gehäuse durch Stifte und Abstandshalter

Country Status (7)

Country Link
US (1) US8142152B2 (de)
EP (1) EP2058477B1 (de)
JP (1) JP5058125B2 (de)
CN (1) CN101429876B (de)
CA (1) CA2643536C (de)
FR (1) FR2923530B1 (de)
RU (1) RU2494265C2 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3068383A1 (fr) * 2017-06-28 2019-01-04 Safran Aircraft Engines Raccordement de bras radiaux a une virole circulaire par imbrication de pieces rapportees

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8662819B2 (en) * 2008-12-12 2014-03-04 United Technologies Corporation Apparatus and method for preventing cracking of turbine engine cases
FR2986040B1 (fr) * 2012-01-20 2016-03-25 Turbomeca Support de palier de turbomachine
US9816387B2 (en) 2014-09-09 2017-11-14 United Technologies Corporation Attachment faces for clamped turbine stator of a gas turbine engine
US10443447B2 (en) * 2016-03-14 2019-10-15 General Electric Company Doubler attachment system
AU2016277549B2 (en) * 2016-10-24 2018-10-18 Intex Holdings Pty Ltd A multi-stage axial flow turbine adapted to operate at low steam temperatures

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5180282A (en) * 1991-09-27 1993-01-19 General Electric Company Gas turbine engine structural frame with multi-yoke attachment of struts to outer casing
US5272869A (en) 1992-12-10 1993-12-28 General Electric Company Turbine frame
US5292227A (en) * 1992-12-10 1994-03-08 General Electric Company Turbine frame
GB2272027A (en) * 1992-10-28 1994-05-04 Snecma Interlocking the ends of blades
EP1149987A2 (de) * 2000-04-29 2001-10-31 General Electric Company Turbinengehäuse
US6439841B1 (en) 2000-04-29 2002-08-27 General Electric Company Turbine frame assembly
EP1482130A2 (de) * 2003-05-29 2004-12-01 General Electric Company Rahmenstruktur einer Turbomaschine

Family Cites Families (12)

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Publication number Priority date Publication date Assignee Title
US3271949A (en) * 1963-04-26 1966-09-13 Williams Res Corp Gas turbine
GB1387866A (en) * 1972-06-21 1975-03-19 Rolls Royce Aerofoil members for gas turbine engines
US4286921A (en) * 1979-12-13 1981-09-01 Westinghouse Electric Corp. Locking structure for an alignment bushing of a combustion turbine engine
SU1160066A1 (ru) * 1983-12-27 1985-06-07 Selikhov Vyacheslav L Охлаждаема опора подшипников консольной турбомашины
GB2168755B (en) * 1984-12-08 1988-05-05 Rolls Royce Improvements in or relating to gas turbine engines
JPH0451073Y2 (de) * 1987-06-12 1992-12-02
US4793770A (en) * 1987-08-06 1988-12-27 General Electric Company Gas turbine engine frame assembly
US4890978A (en) * 1988-10-19 1990-01-02 Westinghouse Electric Corp. Method and apparatus for vane segment support and alignment in combustion turbines
JPH0446209A (ja) * 1990-06-06 1992-02-17 Matsushita Electric Ind Co Ltd 締結具
US5141394A (en) * 1990-10-10 1992-08-25 Westinghouse Electric Corp. Apparatus and method for supporting a vane segment in a gas turbine
US5848874A (en) * 1997-05-13 1998-12-15 United Technologies Corporation Gas turbine stator vane assembly
US7581402B2 (en) * 2005-02-08 2009-09-01 Siemens Energy, Inc. Turbine engine combustor with bolted swirlers

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5180282A (en) * 1991-09-27 1993-01-19 General Electric Company Gas turbine engine structural frame with multi-yoke attachment of struts to outer casing
GB2272027A (en) * 1992-10-28 1994-05-04 Snecma Interlocking the ends of blades
US5272869A (en) 1992-12-10 1993-12-28 General Electric Company Turbine frame
US5292227A (en) * 1992-12-10 1994-03-08 General Electric Company Turbine frame
EP1149987A2 (de) * 2000-04-29 2001-10-31 General Electric Company Turbinengehäuse
US6439841B1 (en) 2000-04-29 2002-08-27 General Electric Company Turbine frame assembly
EP1482130A2 (de) * 2003-05-29 2004-12-01 General Electric Company Rahmenstruktur einer Turbomaschine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3068383A1 (fr) * 2017-06-28 2019-01-04 Safran Aircraft Engines Raccordement de bras radiaux a une virole circulaire par imbrication de pieces rapportees

Also Published As

Publication number Publication date
JP5058125B2 (ja) 2012-10-24
CA2643536A1 (en) 2009-05-09
EP2058477B1 (de) 2013-08-07
US8142152B2 (en) 2012-03-27
FR2923530A1 (fr) 2009-05-15
CN101429876B (zh) 2013-05-01
FR2923530B1 (fr) 2014-04-04
US20090123279A1 (en) 2009-05-14
RU2008144229A (ru) 2010-05-20
JP2009121459A (ja) 2009-06-04
CA2643536C (en) 2015-06-02
RU2494265C2 (ru) 2013-09-27
CN101429876A (zh) 2009-05-13

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