EP0657624A1 - Turbinegehäuse mit Dichtungskörper - Google Patents

Turbinegehäuse mit Dichtungskörper Download PDF

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Publication number
EP0657624A1
EP0657624A1 EP94402807A EP94402807A EP0657624A1 EP 0657624 A1 EP0657624 A1 EP 0657624A1 EP 94402807 A EP94402807 A EP 94402807A EP 94402807 A EP94402807 A EP 94402807A EP 0657624 A1 EP0657624 A1 EP 0657624A1
Authority
EP
European Patent Office
Prior art keywords
casing
sealing body
flanges
flexible envelope
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
EP94402807A
Other languages
English (en)
French (fr)
Other versions
EP0657624B1 (de
Inventor
Jean Christian Henri Cattaneo
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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0657624A1 publication Critical patent/EP0657624A1/de
Application granted granted Critical
Publication of EP0657624B1 publication Critical patent/EP0657624B1/de
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
    • 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
    • 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

Definitions

  • the invention relates to a turbomachine wall comprising a sealing body.
  • the turbomachine walls used for aircraft engines include in particular an outer casing which ensures by its rigidity the cohesion of the assembly and an internal ferrule, concentric with the casing and formed of annular segments assembled to it and between them, which serve to delimit the gas flow stream.
  • the casing, the ferrule and the transverse flanges for assembling the segments to the casing then delimit empty partitioned volumes which are the seat of gas leaks which affect the good performance of the machine.
  • these often very hot gases produce radial and longitudinal thermal expansions on the casing, which are reflected on the shell and therefore increase the radial clearances between the shell and the free ends of the rotor blades.
  • a larger part of the gas flow escapes compression by the blades, then the rotor drive by expanding. We are therefore faced with a second cause of lower yield.
  • the object of the invention which is to completely or almost fill these empty volumes of form often tormented, is achieved by housing sealing bodies formed of a flexible envelope and not very permeable to air and of a thermally insulating fluff material and contained in the flexible envelope.
  • the turbomachine is shown at the location of a high pressure compressor, where the invention should find the most utility. It comprises an outer casing 1, the outer surface of which bears a number of circular bosses 2 in which oblique bolt holes 3 have been drilled. The internal surface of the casing 1 is smooth opposite the bosses 2, so that the flanges 4 of the shell segments 5 can rest thereon.
  • the flanges 4 are also provided with bolt holes 6, which are an extension of those 3 of the bosses 2, and bolts 7 are inserted therein to retain the flanges 4 in place, with a component radial force which applies them to the surface of the casing 1 and an axial component which allows them to block the seals 8 against the shoulders 9 of the casing 1.
  • the essential element of the seals 8 is however not the rigid ring which is thus compressed and serves as their reinforcement, but a thin and oblique web 10 of which one end is embedded in the ring and the other end, free, is supported on the corresponding segmented flange 4 to cover the bolt holes 6 and recesses 11 formed over a large part of their extension so that the flanges 4 are effectively supported on the casing 1 only by a small part of their circumference, which avoids excessive heat transmissions and decreases risk of jamming during assembly. Additional bolts 12 are then provided to complete the tightening of the seals 8 by applying nuts 13 of particular shape to them and to the wall of the casing 1.
  • the shell segments 5 delimit from the outside an annular gas flow stream 14. They must form a surface which is as continuous and regular as possible to avoid leaks and pressure drops and they are juxtaposed by different kinds of seals, but some of them can be assembled by interlocking 15 of a lip of one in a groove of the other.
  • Certain ferrule segments 5 carry vanes 16 for straightening the gas flow, which are arranged in stages alternating with stages of movable vanes 17 fixed to the rotor 18. Clearances 19 extend between the ferrule segments 5 and the movable blades 17, and it is desired that they be as small as possible in order to avoid an appreciable portion gases do not flow there. This is why many devices have been designed, not shown here but which are abundantly described and are the subject of numerous patents, for controlling the value of the clearances 19 at all speeds of the machine: these are blowing devices. of gas taken from another part of the machine in order to regulate the thermal expansions of the shell segments 5.
  • This harmful flow is prohibited (FIG. 2) by means of a sealing body 25 consisting essentially of a flock 26 contained in a flexible envelope 27 and which occupies all or almost all of these empty volumes 20 thanks to the flexibility of the body 25 and the compressibility of the wad 26, which deform under the action of the surrounding pressure differences and conform to the shapes of the cavity 20.
  • the materials used and in particular those of the wad 26 are poor conductors of heat and not very permeable to air, while being sufficiently porous so that the compressibility of the wad 26 is not compromised.
  • the wad 26 may have a fibrous structure, and the envelope 27 may be formed of a fabric.
  • the fiber can be quartz wool or metallic felts, and the fabric can be an intertwining of quartz, glass, carbon or metal wires.
  • FIG. 3 represents a slightly different design where the sealing body, then referenced 125 and still consisting of a wad 26 contained in a flexible envelope 27, is completed by a spring 28 of circular extension and whose cross section and linear and forms an acute angle, or an open pin: it consists of two substantially rigid sheets 29 which an elastic hinge 30 connects, and the volume 31 enclosed by the sheets 29 is empty.
  • the spring 28 is compressed, so that the sheets 29 tend to move apart, opening the spring 28, and the flock 26 is driven outwards and pushed back against the surfaces of the casing 1 and of the ferrule segments 5, including in their crevices.
  • FIG. 4 shows the sealing body 125 in the isolated state. It is made in the form of a rod, the desired length of which is cut and rolled up to form a ring, the ends of which can be closed, or even joined together by sewing, welding or any other suitable means. to the casing 27. If the sheets 29 are elastic and therefore have a certain stiffness, they must however be flexible enough to be curved.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gasket Seals (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP19940402807 1993-12-08 1994-12-07 Turbinegehäuse mit Dichtungskörper Expired - Lifetime EP0657624B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9314699 1993-12-08
FR9314699A FR2713709B1 (fr) 1993-12-08 1993-12-08 Paroi de turbomachine comprenant un corps d'étanchéité.

Publications (2)

Publication Number Publication Date
EP0657624A1 true EP0657624A1 (de) 1995-06-14
EP0657624B1 EP0657624B1 (de) 1998-02-04

Family

ID=9453679

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19940402807 Expired - Lifetime EP0657624B1 (de) 1993-12-08 1994-12-07 Turbinegehäuse mit Dichtungskörper

Country Status (3)

Country Link
EP (1) EP0657624B1 (de)
DE (1) DE69408423T2 (de)
FR (1) FR2713709B1 (de)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1067274A1 (de) * 1999-07-06 2001-01-10 Rolls-Royce Plc Rotordichtung
JP2003013705A (ja) * 2001-04-04 2003-01-15 Siemens Ag ギャップシール用のシール要素と該要素を持つ燃焼タービン
FR2957115A1 (fr) * 2010-03-05 2011-09-09 Snecma Etage de turbine dans une turbomachine
GB2488629A (en) * 2011-03-04 2012-09-05 Rolls Royce Plc Turbomachine casing with energy absorbing pocket
EP2620653A1 (de) * 2012-01-25 2013-07-31 Rolls-Royce plc Turbomaschinengehäuseanordnung mit Hohlraum zum Schaufelberstschutz
JP2016125485A (ja) * 2014-12-31 2016-07-11 ゼネラル・エレクトリック・カンパニイ 流路伝導カット部を有するケーシングリング組立体
US11566538B2 (en) * 2018-09-24 2023-01-31 Safran Aircraft Engines Internal turbomachine casing having improved thermal insulation

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013213834A1 (de) * 2013-07-15 2015-02-19 MTU Aero Engines AG Verfahren zum Herstellen eines Isolationselements und Isolationselement für ein Gehäuse eines Flugtriebwerks
EP2829689B1 (de) * 2013-07-23 2019-03-13 MTU Aero Engines GmbH Dämmeinrichtung für eine thermischen Gastrubine und hiermit ausgerüstete thermische Gasturbine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1235694A (fr) * 1958-07-28 1960-07-08 Connecticut Hard Rubber Co Structure de joint résistant aux températures élevées et aux carburants pour moteurs à réaction et applications analogues
GB1533515A (en) * 1975-11-10 1978-11-29 Caterpillar Tractor Co Support for concentric turbine blade shroud
JPS61164003A (ja) * 1985-01-11 1986-07-24 Hitachi Ltd 流体機械における熱伸びのある静翼部のシ−ル装置
US5104286A (en) * 1991-02-08 1992-04-14 Westinghouse Electric Corp. Recirculation seal for a gas turbine exhaust diffuser

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2051912A5 (de) * 1969-07-01 1971-04-09 Rabouyt Denis
DE2620762C2 (de) * 1976-05-11 1977-11-17 Motoren- und Turbinen-Union München GmbH, 8000 München Spaltdichtung für Strömungsmaschinen, insbesondere Gasturbinenstrahltriebwerke

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1235694A (fr) * 1958-07-28 1960-07-08 Connecticut Hard Rubber Co Structure de joint résistant aux températures élevées et aux carburants pour moteurs à réaction et applications analogues
GB1533515A (en) * 1975-11-10 1978-11-29 Caterpillar Tractor Co Support for concentric turbine blade shroud
JPS61164003A (ja) * 1985-01-11 1986-07-24 Hitachi Ltd 流体機械における熱伸びのある静翼部のシ−ル装置
US5104286A (en) * 1991-02-08 1992-04-14 Westinghouse Electric Corp. Recirculation seal for a gas turbine exhaust diffuser

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 10, no. 368 (M - 543)<2425> 9 December 1986 (1986-12-09) *

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1067274A1 (de) * 1999-07-06 2001-01-10 Rolls-Royce Plc Rotordichtung
JP2003013705A (ja) * 2001-04-04 2003-01-15 Siemens Ag ギャップシール用のシール要素と該要素を持つ燃焼タービン
FR2957115A1 (fr) * 2010-03-05 2011-09-09 Snecma Etage de turbine dans une turbomachine
GB2488629A (en) * 2011-03-04 2012-09-05 Rolls Royce Plc Turbomachine casing with energy absorbing pocket
EP2495401A3 (de) * 2011-03-04 2015-03-11 Rolls-Royce plc Turbomaschinengehäuseanordnung
EP2620653A1 (de) * 2012-01-25 2013-07-31 Rolls-Royce plc Turbomaschinengehäuseanordnung mit Hohlraum zum Schaufelberstschutz
JP2016125485A (ja) * 2014-12-31 2016-07-11 ゼネラル・エレクトリック・カンパニイ 流路伝導カット部を有するケーシングリング組立体
EP3059400A1 (de) * 2014-12-31 2016-08-24 General Electric Company Gehäuseringanordnung mit fliesspfadleitungsschnitt
US10337353B2 (en) 2014-12-31 2019-07-02 General Electric Company Casing ring assembly with flowpath conduction cut
US11566538B2 (en) * 2018-09-24 2023-01-31 Safran Aircraft Engines Internal turbomachine casing having improved thermal insulation

Also Published As

Publication number Publication date
FR2713709A1 (fr) 1995-06-16
FR2713709B1 (fr) 1996-01-12
DE69408423T2 (de) 1998-07-30
EP0657624B1 (de) 1998-02-04
DE69408423D1 (de) 1998-03-12

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