EP1970541A1 - Dränrohr des Austrittsgehäuses einer Strömungsmaschine - Google Patents

Dränrohr des Austrittsgehäuses einer Strömungsmaschine Download PDF

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Publication number
EP1970541A1
EP1970541A1 EP08151545A EP08151545A EP1970541A1 EP 1970541 A1 EP1970541 A1 EP 1970541A1 EP 08151545 A EP08151545 A EP 08151545A EP 08151545 A EP08151545 A EP 08151545A EP 1970541 A1 EP1970541 A1 EP 1970541A1
Authority
EP
European Patent Office
Prior art keywords
drain
turbomachine
skirt
orifice
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
EP08151545A
Other languages
English (en)
French (fr)
Other versions
EP1970541B1 (de
Inventor
Nicolas Auguste Marcel Pommier
Christian René Schnell
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 EP1970541A1 publication Critical patent/EP1970541A1/de
Application granted granted Critical
Publication of EP1970541B1 publication Critical patent/EP1970541B1/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
    • F01D25/30—Exhaust heads, chambers, or the like
    • 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
    • F01D25/32—Collecting of condensation water; Drainage ; Removing solid particles
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/231—Three-dimensional prismatic cylindrical
    • 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
    • F05D2260/60—Fluid transfer
    • F05D2260/602—Drainage

Definitions

  • the present invention relates to a drain for draining liquids, in an exhaust casing of a turbomachine such as a turbojet engine.
  • the exhaust casing of a turbomachine generally comprises a groove which is formed downstream and close to the upstream fastening flange of this casing and which constitutes a dead zone, that is to say, protected from the flow primary. It is common for liquids, such as water, fuel and oil, to be held in an area “at 6 o'clock", i.e., downward, in this groove.
  • the exhaust casings generally comprise an orifice with a drain at this zone. in order to evacuate the liquids towards the outside of the turbomachine.
  • This drain is usually formed of a cylindrical body which is welded to the housing at the aforementioned discharge orifice.
  • the object of the present invention is to provide a simple, effective and economical solution to this problem, in particular by simplifying the mounting of the drain on the exhaust casing and considerably reducing the working time required for this assembly.
  • Another object of the invention is to guarantee a good solidity and a correct sealing of the fixing of the drain on the housing.
  • turbomachine exhaust casing comprising an annular groove pierced with an orifice in which is mounted a drain formed of a tubular cylindrical body, for discharging liquids retained in this groove, characterized in that that the drain comprises a skirt formed at one end of the cylindrical body and crimped in the hole of the groove of the housing for fixing the drain to the housing.
  • Fixing the drain by crimping makes it possible to avoid the use of an annular weld, the disadvantages of which have been mentioned above, and thus offers a significant time saving when mounting the drain on the exhaust casing of the turbomachine, the time complete assembly being approximately 30 minutes instead of several hours.
  • the drain is made of a metal alloy having a coefficient of thermal expansion greater than the coefficient of thermal expansion of the housing around the mounting hole of the drain.
  • the expansion of the drain under the effect of the increase in temperature in operation, induces a drain blocking effect in the housing orifice, and thus improves the fixing of the drain to the housing.
  • the drain mounting orifice comprises, at one end, a cylindrical portion connected by an internal flange to a frustoconical portion at the other end of the orifice, this frustoconical portion having a center angle of about 60 degrees.
  • the skirt of the drain which has a thickness less than that of the cylindrical body and extends in the extension of the inner surface of this cylindrical body, is applied to the inner flange and the frustoconical portion after crimping.
  • This configuration makes it possible to obtain optimal crimping and to limit at best the risks of loss of the drain during operation or during the maintenance phase of the turbomachine.
  • the cylindrical portion of the orifice has a diameter greater than the maximum diameter of the frustoconical portion.
  • the cylindrical part thus forms a chamber in which the end of the cylindrical body of the drain carrying the skirt is inserted, so that an annular rim of the cylindrical body, formed at the base of this skirt, is applied to a bottom of this chamber.
  • the free end of the skirt after crimping is substantially at the inner surface of the groove of the housing.
  • the drain is connected to the casing by at least one weld point to reinforce its attachment to the housing.
  • the invention also relates to a turbomachine, such as an aircraft turbojet, characterized in that it comprises an exhaust casing of the type described above.
  • the invention also relates to an exhaust casing drain in a turbomachine, characterized in that it comprises a tubular cylindrical body extended at one end by a cylindrical crimping skirt having a thickness less than that of the body and extending the inner surface of the cylindrical body.
  • FIG 1 showing a turbomachine exhaust casing 10 of a known type, seen from upstream, comprising two coaxial cylindrical shells respectively inner 12 and outer 14, connected by oblique arms 16.
  • the outer shell 14 has at its upstream end an annular groove 18, which is located downstream and close to the upstream flange 20 fixing the exhaust casing, and a region located "at 6 o'clock", that is to say at the bottom, is pierced d an evacuation orifice 22 provided with a drain intended to evacuate outwards liquids capable of being collected in this groove.
  • the figure 2 is a view on a larger scale of the discharge orifice 22 and its drain 24 which is formed of a tubular cylindrical body 26 fixed to the rim of the orifice 22 by an annular weld 28 formed on the periphery of this orifice .
  • the surface 30 of the weld 28 connecting the inner wall 32 of the drain to the inner wall 34 of the groove 18 of the housing is frustoconical.
  • the mounting of the drain 24 on the exhaust casing 10 consists in particular in producing the weld 28 and then manually retouching this weld in order to eliminate any surplus on the inner wall 32 of the drain and on the inner wall 34 of the groove 18, and to form the frustoconical surface of the weld 28.
  • Such an assembly requires about 4 hours of work.
  • the present invention aims to change the way of fixing the drain to the exhaust casing to avoid the use of an annular welding as in the prior art.
  • FIG 3 schematically shows a drain 36 according to the invention before its mounting on the exhaust casing 10.
  • This drain comprises a tubular cylindrical body 38 and a skirt 40, which is formed at one end of the body 38, which has a thickness less than that of this body, and which extends in the extension of the inner surface 42 of the body, this skirt 40 being intended to allow the attachment of the drain 36 by crimping in the orifice 22 of the groove 18 of the housing.
  • the end of the cylindrical body 38 carrying the skirt 40 forms an annular flange 44 at the base of this skirt.
  • the figure 4 represents the drain 36 mounted in the orifice 22 of the exhaust casing 10 after crimping its skirt 40.
  • This orifice has been machined to allow this crimping to fix the drain to the casing, and comprises at one end outside the groove, a cylindrical portion 46, connected by an inner flange 48 to a frustoconical portion 50 at the other end of the orifice within the groove, the frustoconical portion 50 having a center angle of about 60 degrees.
  • the cylindrical portion 46 whose inner diameter is substantially equal to the outer diameter of the cylindrical body 38 of the drain 36, forms a recess having a bottom 52 bounded by the internal rim 48 of the orifice and on which the annular flange 44 of the drain 36.
  • the skirt 40 has an outer diameter substantially equal to the inner diameter of the flange 48 and is applied to the frustoconical portion 50 of the orifice 22, to ensure the retention of the drain to the housing.
  • the drain 36 is made of a metal alloy with a coefficient of thermal expansion greater than that of the exhaust casing 10.
  • the temperature rise inherent in the operation of the turbomachine induces a plating and a locking of the skirt 40 on the parts cylindrical 48 and frustoconical 50 of the orifice 22, which has the effect of reinforcing the attachment of the drain 36 to the casing 10.
  • the free end of the skirt 40 is substantially at the surface of the groove 18 of the housing, in order to optimize the crimping while preventing this free end of the skirt protruding into the groove.
  • the crimping of the skirt 40 is a simple and fast operation, which can for example be performed by means of a crimping gun, and requires about 30 minutes.
  • drain 36 is damaged, it is possible to replace it with a welded drain of known type after having pierced the orifice 22 of the groove 18 of the exhaust casing to obtain a smooth orifice compatible with this type of drain.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Exhaust Silencers (AREA)
  • Gasket Seals (AREA)
  • Supercharger (AREA)
EP08151545A 2007-03-16 2008-02-18 Dränrohr des Austrittsgehäuses einer Strömungsmaschine Active EP1970541B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0701905A FR2913725B1 (fr) 2007-03-16 2007-03-16 Drain de carter d'echappement de turbomachine

Publications (2)

Publication Number Publication Date
EP1970541A1 true EP1970541A1 (de) 2008-09-17
EP1970541B1 EP1970541B1 (de) 2010-04-07

Family

ID=38698781

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08151545A Active EP1970541B1 (de) 2007-03-16 2008-02-18 Dränrohr des Austrittsgehäuses einer Strömungsmaschine

Country Status (6)

Country Link
US (1) US8277176B2 (de)
EP (1) EP1970541B1 (de)
CA (1) CA2625314C (de)
DE (1) DE602008000925D1 (de)
FR (1) FR2913725B1 (de)
RU (1) RU2472004C2 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015004059A1 (fr) * 2013-07-09 2015-01-15 Snecma Carter de turbomachine a bride decoupee
US20150082769A1 (en) * 2013-09-25 2015-03-26 Snecma Exhaust casing comprising a fluid discharge device and turbine engine
FR3037614A1 (fr) * 2015-06-22 2016-12-23 Snecma Drain pour carter d'echappement de turbomachine

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3019210B1 (fr) * 2014-04-01 2016-05-13 Snecma Partie de turbomachine comportant une bride avec un dispositif de drainage
DE102015016030A1 (de) 2015-12-11 2017-06-14 Man Truck & Bus Ag Abgasturbolader für ein Kraftfahrzeug
FR3098243B1 (fr) 2019-07-04 2021-06-04 Safran Aircraft Engines Ensemble récupérateur de fluide pour turbomachine à gaz
FR3098242B1 (fr) 2019-07-04 2021-06-25 Safran Aircraft Engines Ensemble récupérateur de fluide pour turbomachine à gaz
FR3152534B1 (fr) 2023-09-06 2025-07-18 Safran Aircraft Engines Carter comprenant un drain d'echappement de turbomachine
US20250367771A1 (en) * 2024-06-04 2025-12-04 Pratt & Whitney Canada Corp. Drain shield

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2643678A1 (fr) 1989-02-28 1990-08-31 United Technologies Corp Ensemble de purge d'un fluide, notamment pour turbomoteur, et son procede de fabrication
EP1304514A1 (de) 2001-10-22 2003-04-23 General Electric Company Ölluftseparatorplug
EP1621741A1 (de) 2004-07-28 2006-02-01 Hitachi, Ltd. Gasturbine

Family Cites Families (9)

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US5133727A (en) * 1990-05-10 1992-07-28 Symbiosis Corporation Radial jaw biopsy forceps
US4538834A (en) * 1982-09-09 1985-09-03 General Electric Co. Tubular assembly for transferring fluids
RU2053373C1 (ru) * 1989-02-13 1996-01-27 Научно-производственное объединение "Турбоатом" Выхлопная часть паровой турбины
RU1783124C (ru) * 1990-06-22 1992-12-23 Московский энергетический институт Выхлопной патрубок турбомашины
US5338153A (en) * 1993-06-30 1994-08-16 Caterpillar Inc. Non-drip fluid circulating pump
RU2210675C2 (ru) * 2001-05-07 2003-08-20 Открытое акционерное общество "Ленинградский Металлический завод" Часть низкого давления паровой турбины с аксиальным выходом
FR2869875B1 (fr) * 2004-05-05 2006-06-16 Snecma Moteurs Sa Dispositif de fixation d'un conduit de fluide sur un carter d'un turboreacteur
US7921646B2 (en) * 2007-12-20 2011-04-12 General Electric Company Fluidic valve water drain
US8441361B2 (en) * 2010-02-13 2013-05-14 Mcallister Technologies, Llc Methods and apparatuses for detection of properties of fluid conveyance systems

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2643678A1 (fr) 1989-02-28 1990-08-31 United Technologies Corp Ensemble de purge d'un fluide, notamment pour turbomoteur, et son procede de fabrication
EP1304514A1 (de) 2001-10-22 2003-04-23 General Electric Company Ölluftseparatorplug
EP1621741A1 (de) 2004-07-28 2006-02-01 Hitachi, Ltd. Gasturbine

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015004059A1 (fr) * 2013-07-09 2015-01-15 Snecma Carter de turbomachine a bride decoupee
FR3008450A1 (fr) * 2013-07-09 2015-01-16 Snecma Carter de turbomachine a bride decoupee
US10006307B2 (en) 2013-07-09 2018-06-26 Snecma Turbine engine casing having a cut-out flange
US20150082769A1 (en) * 2013-09-25 2015-03-26 Snecma Exhaust casing comprising a fluid discharge device and turbine engine
FR3011035A1 (fr) * 2013-09-25 2015-03-27 Snecma Carter d'echappement comprenant un dispositif d'evacuation de fluide, et turbomachine
US9771831B2 (en) * 2013-09-25 2017-09-26 Snecma Exhaust casing comprising a fluid discharge device and turbine engine
FR3037614A1 (fr) * 2015-06-22 2016-12-23 Snecma Drain pour carter d'echappement de turbomachine

Also Published As

Publication number Publication date
US8277176B2 (en) 2012-10-02
US20080226445A1 (en) 2008-09-18
CA2625314C (fr) 2015-08-11
FR2913725A1 (fr) 2008-09-19
FR2913725B1 (fr) 2011-10-28
DE602008000925D1 (de) 2010-05-20
RU2008110028A (ru) 2009-09-20
CA2625314A1 (fr) 2008-09-16
EP1970541B1 (de) 2010-04-07
RU2472004C2 (ru) 2013-01-10

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