EP0342087A1 - Statorgitter mit eingebauten Ölleitungen für eine Turbomaschine - Google Patents

Statorgitter mit eingebauten Ölleitungen für eine Turbomaschine Download PDF

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Publication number
EP0342087A1
EP0342087A1 EP89401184A EP89401184A EP0342087A1 EP 0342087 A1 EP0342087 A1 EP 0342087A1 EP 89401184 A EP89401184 A EP 89401184A EP 89401184 A EP89401184 A EP 89401184A EP 0342087 A1 EP0342087 A1 EP 0342087A1
Authority
EP
European Patent Office
Prior art keywords
arm
oil
oil passage
downstream
tube
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
EP89401184A
Other languages
English (en)
French (fr)
Other versions
EP0342087B1 (de
Inventor
Jean-Claude Asselin
Pierre Antoine Glowacki
Daniel Jean-Marie Martin
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 EP0342087A1 publication Critical patent/EP0342087A1/de
Application granted granted Critical
Publication of EP0342087B1 publication Critical patent/EP0342087B1/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
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids

Definitions

  • the thickness of the arms is itself very reduced, of the order of 8.5 mm at point where it is impossible to accommodate the oil circuit piping of the upstream bearing.
  • a conventional technology consists in making some of the radiating arms with a thicker section than the others.
  • the object of the present invention is to produce an inlet gate structure in which all the arms have the same section and therefore the same thickness, but in which certain arms are still suitable for receiving an oil piping intended for the servitudes of the engine and in particular for the lubrication of the upstream bearing.
  • the invention therefore relates to an aviation turbomachine having an inlet grid formed of radiating arms, support of the inlet casing, arranged between an internal ferrule and an external ferrule, some of them comprising a passage pipe of oil, the grid further comprising variable setting input guidelines, turbomachine in which all the arms of the input grid are of the same section including those comprising an oil passage pipe and of which said radiating arms are in two parts, a first fixed upstream structural part and a second part forming a downstream shutter with variable setting articulated on the upstream structural part and constituting the inlet director.
  • those of the radiating arms which comprise an oil passage pipe have in section their structural part divided into three enclosures separated by two radial partitions, the two upstream enclosures being traversed by hot air flow rates, while the 'downstream enclosure, open over its entire length along the trailing edge is capable of receiving the oil passage manifold.
  • the input guide wheel located upstream of the first stage 2 of the low pressure compressor rotor is made up of 1,1 ′ radial arms arranged between the outer ring 3 of the vein 4 and the internal ferrule 5 secured to the upstream central cone 6 of the engine.
  • the arms 1,1 ′ have an aerodynamic profile comprising a leading edge, a lower surface and an upper surface and comprise an adjustable downstream part formed by a flap 7 mounted rotating on an external pivot 8 and an internal pivot 9 arranged at the inside of bearings 10, the flaps 7 of all the radial arms being controlled in rotation by means of a control ring 11 to which they are connected by connecting rods 12.
  • the blades 1,1 ′ are hollow to allow a circulation of hot air, taken in an air collector 14, intended to prevent icing of the leading edge of the blade and of the central cone 6.
  • the blades 1,1 ′ have an upstream part, located between the leading edge 15 and a downstream partition 15a, which also forms an enclosure 16 reinforced by a rib 17 for the circulation of hot air taken from the manifold 14.
  • the part of the arm 1 located downstream of the partition 15a forms an enclosure 21 open over its entire length downstream to receive the tube 13 for the passage of oil.
  • FIG. 2 shows the example of an oil return organized according to the invention.
  • the internal ferrule of the inlet grille comprises an oil collector 18 which receives the recovery oil from the bearing P, said collector opening radially at the level of an arm 1 having an oil tube 13, in a cylindrical housing 19 receiving an end piece 20 of the tube 13 of the arm.
  • the downstream enclosure 21 of the structural arm is integral with the housing 22 of the external pivot of the downstream flap and said housing 22 comprises (see FIG. 3) a radial cutout 23 making the bore 22 receiving the pivot 8 communicate and the downstream enclosure 21 of the structural arm to allow the insertion by sliding of the tube 13 for the passage of oil into the downstream enclosure of the arm.
  • the tube 13 has a thinned central part of oblong section, internally matching the spindle shape of the structural arm which contains it and bent in three places 24 so as to correspond to the bent shape of the enclosure 21.
  • the thinned central part is connected to welded cylindrical end pieces 20 which each have a seal 25.
  • the external ferrule 3 of the grid receives, to the right of each oil passage pipe, a removable connection 26 comprising a bore coming to be positioned on the external nozzle 20 of the oil pipe, said connection being screwed onto a boss 27 of the outer shell and being hydraulically connected to a pump for recovering the oil circuit (not shown) of the turbomachine.
  • the arm 1 has a groove, or constricted, 28 (see FIGS. 6 to 8) about half of its length, intended to receive a shaped clip 29 of plastic stirrup which is mounted on the rear flanks of the arm at the level of the constriction and provides a double function of fixing the tube 13 in its enclosure 21 and of damping vibrations including sides of the arm, cantilevered, could be the object.
  • the tube 13 is slid into the bore 22 of the pivot of the flap 7, then (FIGS. 10 and 11), it is pushed upstream, parallel to itself, and the end 20 is radially external. of the tube 13 is slid towards its housing through the lumen 21, while the central part of the tube is received in the clip 29. Then, the tube is pushed radially inward until the internal end piece 20 is in place in its housing 19. Finally, the removable connector 26 is positioned, which is screwed onto the boss 27 of the outer shell 3.
  • the arm structure according to the invention allows the inlet grille to have externally identical arms, which constitutes a notable advantage for manufacturing and maintenance and also ensures the elimination of aerodynamic singularities which could exist in the past.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Lubrication Of Internal Combustion Engines (AREA)
  • Lubrication Details And Ventilation Of Internal Combustion Engines (AREA)
EP89401184A 1988-05-11 1989-04-26 Statorgitter mit eingebauten Ölleitungen für eine Turbomaschine Expired - Lifetime EP0342087B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8806340 1988-05-11
FR8806340A FR2631386A1 (fr) 1988-05-11 1988-05-11 Turbomachine comportant une grille d'entree incorporant des tubes de passage d'huile

Publications (2)

Publication Number Publication Date
EP0342087A1 true EP0342087A1 (de) 1989-11-15
EP0342087B1 EP0342087B1 (de) 1991-09-04

Family

ID=9366213

Family Applications (1)

Application Number Title Priority Date Filing Date
EP89401184A Expired - Lifetime EP0342087B1 (de) 1988-05-11 1989-04-26 Statorgitter mit eingebauten Ölleitungen für eine Turbomaschine

Country Status (5)

Country Link
US (1) US4972671A (de)
EP (1) EP0342087B1 (de)
JP (1) JPH0211833A (de)
DE (1) DE68900238D1 (de)
FR (1) FR2631386A1 (de)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4212878A1 (de) * 1992-04-17 1993-03-18 Daimler Benz Ag Verstellbarer leitschaufelkranz
EP1149986A3 (de) * 2000-04-29 2003-11-19 General Electric Company Turbinengehäuse
FR3051854A1 (fr) * 2016-05-30 2017-12-01 Snecma Carter d'echappement de turbomachine
WO2018172715A1 (fr) * 2017-03-23 2018-09-27 Safran Aircraft Engines Appuis centraux de tubes servitude a retour élastique
FR3083260A1 (fr) * 2018-06-28 2020-01-03 Safran Aircraft Engines Module d’un moteur d’aeronef a double flux dont un bras integre une aube de stator
FR3093128A1 (fr) 2019-02-25 2020-08-28 Safran Aircraft Engines Carter de turbomachine
EP3911860A1 (de) * 2019-01-14 2021-11-24 Safran Aircraft Engines Aerodynamischer arm für ein gehäuse einer flugzeugturbine
EP3967855A1 (de) * 2020-09-11 2022-03-16 Pratt & Whitney Canada Corp. Nabe für gasturbinentriebwerk

Families Citing this family (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5564903A (en) * 1993-11-23 1996-10-15 Alliedsignal Inc. In-line ram air turbine power system
FR2746141B1 (fr) * 1996-03-14 1998-04-17 Dispositif de commande pour pivot integre dans un collecteur
US5746574A (en) * 1997-05-27 1998-05-05 General Electric Company Low profile fluid joint
US6735954B2 (en) 2001-12-21 2004-05-18 Pratt & Whitney Canada Corp. Offset drive for gas turbine engine
US6619916B1 (en) * 2002-02-28 2003-09-16 General Electric Company Methods and apparatus for varying gas turbine engine inlet air flow
FR2857699B1 (fr) * 2003-07-17 2007-06-29 Snecma Moteurs Dispositif de degivrage pour aube de roue directrice d'entree de turbomachine, aube dotee d'un tel dispositif de degivrage, et moteur d'aeronef equipe de telles aubes
EP1505263A1 (de) * 2003-08-08 2005-02-09 Siemens Aktiengesellschaft Abströmleiteinrichtung im Diffusor einer Strömungsmaschine und Verfahren zur Strömungsablenkung
US7278516B2 (en) * 2004-03-09 2007-10-09 Honeywell International, Inc. Apparatus and method for bearing lubrication in turbine engines
FR2875855B1 (fr) 2004-09-27 2006-12-22 Snecma Moteurs Sa Turboreacteur avec un bras monobloc de raccord de servitudes et le bras monobloc de raccord de servitudes
FR2899272B1 (fr) * 2006-03-30 2010-08-13 Snecma Bras de passage des servitudes dans un carter intermediaire de turboreacteur
US7594794B2 (en) * 2006-08-24 2009-09-29 United Technologies Corporation Leaned high pressure compressor inlet guide vane
DE102008008886A1 (de) * 2008-02-13 2009-08-20 Man Turbo Ag Eintrittsstutzen für einen Axialverdichter
US8348600B2 (en) * 2008-05-27 2013-01-08 United Technologies Corporation Gas turbine engine having controllable inlet guide vanes
US9249731B2 (en) * 2012-06-05 2016-02-02 United Technologies Corporation Nacelle bifurcation for gas turbine engine
US20140314542A1 (en) * 2012-12-21 2014-10-23 United Technologies Corporation Gas turbine engine exhaust diffuser with movable struts
US9982600B2 (en) * 2015-05-19 2018-05-29 United Technologies Corporation Pre-skewed capture plate
FR3036437B1 (fr) * 2015-05-22 2017-05-05 Snecma Ensemble de turbomachine pour lubrifier un support de palier
FR3046811B1 (fr) * 2016-01-15 2018-02-16 Snecma Aube directrice de sortie pour turbomachine d'aeronef, presentant une fonction amelioree de refroidissement de lubrifiant
GB2551777B (en) * 2016-06-30 2018-09-12 Rolls Royce Plc A stator vane arrangement and a method of casting a stator vane arrangement
US10385710B2 (en) 2017-02-06 2019-08-20 United Technologies Corporation Multiwall tube and fitting for bearing oil supply
US10465828B2 (en) 2017-02-06 2019-11-05 United Technologies Corporation Tube fitting
US10393303B2 (en) 2017-02-06 2019-08-27 United Technologies Corporation Threaded fitting for tube
US10830139B2 (en) 2017-02-06 2020-11-10 Raytheon Technologies Corporation Fitting for multiwall tube
US10605119B2 (en) 2017-09-25 2020-03-31 United Technologies Corporation Turbine frame assembly for gas turbine engines
US10557572B2 (en) * 2017-09-29 2020-02-11 United Technologies Corporation Conduit with damping fingers
EP3517737A1 (de) * 2018-01-26 2019-07-31 MTU Aero Engines GmbH Dämpfer zur dämpfung von schwingungen eines rohres in einer hohlen strebe eines gasturbinentriebwerks und stützrahmen mit einem solchen dämpfer
US10781710B2 (en) * 2018-07-17 2020-09-22 Raytheon Technologies Corporation Sealing configuration to reduce air leakage
US11028728B2 (en) * 2019-03-22 2021-06-08 Raytheon Technologies Corporation Strut dampening assembly and method of making same
US11655762B2 (en) * 2019-04-08 2023-05-23 Pratt & Whitney Canada Corp. Gas turbine engine with trailing edge heat exchanger
GB201907074D0 (en) 2019-05-20 2019-07-03 Rolls Royce Plc Gas turbine engine
US11555418B2 (en) 2019-06-12 2023-01-17 General Electric Company Oil supply system for a gas turbine engine
CN119145956B (zh) * 2024-11-18 2025-02-14 中国航发湖南动力机械研究所 涡轴发动机集成机匣

Citations (8)

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US2919888A (en) * 1957-04-17 1960-01-05 United Aircraft Corp Turbine bearing support
US2930579A (en) * 1955-09-19 1960-03-29 Dominion Eng Works Ltd Turbine guide vane locking and vibration preventing arrangement
FR2219312A1 (de) * 1973-02-26 1974-09-20 Gen Electric
US4034558A (en) * 1975-10-14 1977-07-12 Westinghouse Canada Limited Cooling apparatus for split shaft gas turbine
US4076452A (en) * 1974-04-09 1978-02-28 Brown, Boveri-Sulzer Turbomaschinen Ag Gas turbine plant
US4183207A (en) * 1978-03-07 1980-01-15 Avco Corporation Oil-conducting strut for turbine engines
FR2526485A1 (fr) * 1982-05-07 1983-11-10 Snecma Roue directrice d'entree de soufflante de turboreacteur permettant le demontage unitaire des aubes mobiles, et procede pour la mise en oeuvre
FR2599086A1 (fr) * 1986-05-23 1987-11-27 Snecma Dispositif de commande d'aubes directrices d'entree d'air a calage variable pour turboreacteur

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US2487842A (en) * 1948-03-09 1949-11-15 Westinghouse Electric Corp Aircraft power plant apparatus
GB702931A (en) * 1951-04-18 1954-01-27 Bristol Aeroplane Co Ltd Improvements in or relating to rotary machines comprising fluid compressing means
US3312448A (en) * 1965-03-01 1967-04-04 Gen Electric Seal arrangement for preventing leakage of lubricant in gas turbine engines

Patent Citations (8)

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Publication number Priority date Publication date Assignee Title
US2930579A (en) * 1955-09-19 1960-03-29 Dominion Eng Works Ltd Turbine guide vane locking and vibration preventing arrangement
US2919888A (en) * 1957-04-17 1960-01-05 United Aircraft Corp Turbine bearing support
FR2219312A1 (de) * 1973-02-26 1974-09-20 Gen Electric
US4076452A (en) * 1974-04-09 1978-02-28 Brown, Boveri-Sulzer Turbomaschinen Ag Gas turbine plant
US4034558A (en) * 1975-10-14 1977-07-12 Westinghouse Canada Limited Cooling apparatus for split shaft gas turbine
US4183207A (en) * 1978-03-07 1980-01-15 Avco Corporation Oil-conducting strut for turbine engines
FR2526485A1 (fr) * 1982-05-07 1983-11-10 Snecma Roue directrice d'entree de soufflante de turboreacteur permettant le demontage unitaire des aubes mobiles, et procede pour la mise en oeuvre
FR2599086A1 (fr) * 1986-05-23 1987-11-27 Snecma Dispositif de commande d'aubes directrices d'entree d'air a calage variable pour turboreacteur

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4212878A1 (de) * 1992-04-17 1993-03-18 Daimler Benz Ag Verstellbarer leitschaufelkranz
EP1149986A3 (de) * 2000-04-29 2003-11-19 General Electric Company Turbinengehäuse
FR3051854A1 (fr) * 2016-05-30 2017-12-01 Snecma Carter d'echappement de turbomachine
US11136894B2 (en) 2017-03-23 2021-10-05 Safran Aircraft Engines Central support for auxiliary tubes with elastic return
WO2018172715A1 (fr) * 2017-03-23 2018-09-27 Safran Aircraft Engines Appuis centraux de tubes servitude a retour élastique
FR3064302A1 (fr) * 2017-03-23 2018-09-28 Safran Aircraft Engines Appuis centraux de tubes servitude a retour elastique
CN110546350A (zh) * 2017-03-23 2019-12-06 赛峰飞机发动机公司 用于辅助导管的具有弹性返回量的中心支撑件
CN110546350B (zh) * 2017-03-23 2022-06-17 赛峰飞机发动机公司 用于辅助导管的具有弹性返回量的中心支撑件
FR3083260A1 (fr) * 2018-06-28 2020-01-03 Safran Aircraft Engines Module d’un moteur d’aeronef a double flux dont un bras integre une aube de stator
US11319899B2 (en) 2018-06-28 2022-05-03 Safran Aircraft Engines Module of an aircraft bypass engine of which one arm integrates a stator blade
EP3911860A1 (de) * 2019-01-14 2021-11-24 Safran Aircraft Engines Aerodynamischer arm für ein gehäuse einer flugzeugturbine
US12180856B2 (en) 2019-01-14 2024-12-31 Safran Aircraft Engines Aerodynamic arm for an aircraft turbine engine casing
US11156129B2 (en) 2019-02-25 2021-10-26 Safran Aircraft Engines Turbine engine casing
EP3705686A1 (de) 2019-02-25 2020-09-09 Safran Aircraft Engines Gehäuse eines turbotriebwerks
CN111608750A (zh) * 2019-02-25 2020-09-01 赛峰航空器发动机 涡轮发动机壳体
FR3093128A1 (fr) 2019-02-25 2020-08-28 Safran Aircraft Engines Carter de turbomachine
CN111608750B (zh) * 2019-02-25 2024-04-19 赛峰航空器发动机 涡轮发动机壳体
EP3967855A1 (de) * 2020-09-11 2022-03-16 Pratt & Whitney Canada Corp. Nabe für gasturbinentriebwerk
US11384659B2 (en) 2020-09-11 2022-07-12 Pratt & Whitney Canada Corp. Boss for gas turbine engine

Also Published As

Publication number Publication date
EP0342087B1 (de) 1991-09-04
US4972671A (en) 1990-11-27
DE68900238D1 (de) 1991-10-10
FR2631386A1 (fr) 1989-11-17
JPH0211833A (ja) 1990-01-16
JPH0587650B2 (de) 1993-12-17

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