EP3857031B1 - Ringvorrichtung für turbomaschine und verfahren zum einbau einer solchen vorrichtung - Google Patents

Ringvorrichtung für turbomaschine und verfahren zum einbau einer solchen vorrichtung Download PDF

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Publication number
EP3857031B1
EP3857031B1 EP19797323.3A EP19797323A EP3857031B1 EP 3857031 B1 EP3857031 B1 EP 3857031B1 EP 19797323 A EP19797323 A EP 19797323A EP 3857031 B1 EP3857031 B1 EP 3857031B1
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EP
European Patent Office
Prior art keywords
plate
rail
tangential
assembly according
annular
Prior art date
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Active
Application number
EP19797323.3A
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English (en)
French (fr)
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EP3857031A1 (de
Inventor
Lancelot GUILLOU
Stéphane Louis Lucien AUBERGER
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
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Safran Aircraft Engines SAS
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Publication of EP3857031A1 publication Critical patent/EP3857031A1/de
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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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • 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
    • 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
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/213—Heat transfer, e.g. cooling by the provision of a heat exchanger within the cooling circuit
    • 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
    • F05D2260/38—Retaining components in desired mutual position by a spring, i.e. spring loaded or biased towards a certain position
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/12—Light metals
    • F05D2300/121—Aluminium

Definitions

  • the present invention relates to the fixing of a heat exchanger carried by an annular part of a turbomachine.
  • FIG. 1 represents a turbomachine 10 with double flow which comprises moving parts which rub against other moving parts or against fixed parts, this connection is for example a bearing.
  • the parts are sprayed with oil which allows on the one hand to limit (or contain) their heating and, on the other hand, to lubricate them to facilitate the sliding of the parts on each other.
  • the oil circulates in a circuit provided with heat exchangers, in particular oil/air exchangers 12, as shown in figure 2 , having a matrix, in the form of a sinuous conduit shaped so as to achieve a heat exchange, into which the oil coming from said parts is introduced and then cooled before being re-injected onto said parts.
  • the heat exchanger 12 shown in figure 2 is an annular heat exchanger which is mounted on the radially internal or external face (relative to the longitudinal axis A of the turbomachine) of an annular shell 14 delimiting radially towards the outside or the inside an annular flow vein for a secondary air flow.
  • the hot oil can thus circulate in the heat exchanger 12 and is cooled with the cold air from the annular secondary air stream of the turbomachine.
  • the heat exchanger 12 is not made of the same material as the annular shell on which it is fixed, it is found that the differences in expansion between the shell 14 and the material constituting the exchanger 12 can weaken the connections of the exchanger thermal 12 to the shell.
  • These differential expansions are all the more significant as the heat exchanger 12 has a large dimension, which is generally the case when it is fixed on the external annular shell.
  • the differential expansions are also amplified by the temperature differences between the annular shell 14 and the heat exchanger 12.
  • These differential expansions lead to significant mechanical stresses in the heat exchanger 12. It is therefore essential to take these differences in expansions into account.
  • US4522559 shows the technical characteristics of the preamble of independent claim 1.
  • the invention aims in particular to provide a simple, effective and economical solution to the aforementioned problems.
  • the present invention relates first of all to an annular assembly for a dual-flow turbomachine having a longitudinal axis and comprising a casing comprising an annular shell, one face of which supports an annular piece of equipment, a plurality of means for fixing the equipment to the annular shell being distributed around the longitudinal axis and allowing a degree of freedom in the tangential direction of the equipment relative to the annular shell, characterized in that each fixing means comprises a rail secured to the annular piece of equipment and arranged radially between a first radially internal plate and a second radially external plate and capable of sliding in the tangential direction between said first plate and second plate, and in that a removable support element is fixedly connected to the annular shell and to the first plate and second plate, the annular shell being an external annular shell of an annular flow vein of a secondary air flow, the equipment being carried by a radially internal face of the external shell, the equipment being a heat exchanger made of a material having a thermal expansion coefficient greater than that of the material
  • each fastening means comprises two plates secured to a removable support element fixed to the annular shell of the casing, which makes it possible to pre-assemble the first plate and the second plate to the exchanger, thereby facilitating the subsequent addition of the support element.
  • mounting the heat exchanger on the internal face of the annular shell of the casing is easier and does not require, at the time of its assembly on the casing, taking into account the connection of the support element with the first and second plates, unlike the prior art where fixing the exchanger was complicated.
  • the heat exchanger is supported by the casing shell by means of connections allowing deformation in the circumferential direction, which ensures optimum support of the exchanger while allowing its expansion in the circumferential direction during operation.
  • the annular casing shell is made of a mechanically resistant material such as titanium, for example, which has a lower coefficient of thermal expansion (but it can also be equal to or higher) than that of the heat exchanger which is made of a material, such as structurally less resistant aluminum but whose coefficient of thermal expansion is generally higher, but not necessarily.
  • This situation is amplified by the difference in temperatures between the annular shell (rather cold because at the air temperature) and the heat exchanger (rather hot because at the oil temperature), which generates additional differential circumferential movements.
  • the rail may comprise a closed-contour opening delimited internally by at least two substantially tangential edges facing each other in the longitudinal direction of two first tangential faces of the first plate or of the second plate and ensuring guidance of the rail in the tangential direction.
  • Said first tangential faces provide sliding guidance of the two circumferential edges of the rail.
  • each fixing means can slide in the tangential direction, thereby ensuring circumferential sliding of the exchanger.
  • Said two tangential faces are each formed on the first plate and are connected to two second tangential retaining faces radially towards the inside of the rail, the first tangential faces forming with the second tangential faces an L-shaped section.
  • This L-shape of two opposite edges of the first plate simultaneously provides guidance and retention radially inwards.
  • the first plate includes a central tubular portion tightly engaged in an orifice of the second plate.
  • the removable support element may comprise at least one rod secured to the first plate.
  • the rod is fixed directly to the first plate, which makes it possible to maintain the radial retention of the rail in all circumstances, unlike a fixing to the second plate.
  • Said rod may be a threaded rod screwed into the first plate and comprising a flat support on a face of the annular ferrule opposite that carrying the equipment.
  • Elastic means may be elastically constrained in the radial direction between the first plate and the rail.
  • the elastic means thus make it possible to limit the sliding movement of the rail relative to the ferrule.
  • the first plate and second plate are blocked in tangential direction on the rail, avoiding blows or impacts which could damage the different parts.
  • the first plate may comprise a housing for receiving elastic means, such as for example a wave washer.
  • the contour includes a convex edge delimiting a part of the rail used for radial support of the elastic means.
  • the invention is particularly interesting when the equipment is made of a material, such as for example aluminum, the casing shell is made of titanium.
  • FIG 3 represents an annular equipment for a turbomachine.
  • This equipment 16 is here a heat exchanger and the invention will be described below in relation to this specific equipment but is also applicable to other equipment.
  • the body of the heat exchanger 16 is generally made by extrusion of a material that is a good heat conductor, such as aluminum. With such a method, it is thus possible to make the conduits in the thickness of the exchanger 16. Only a portion of the angular sector of the exchanger 16 is shown in figure 3 .
  • This heat exchanger 16 comprises internal conduits for the circulation of oil to be cooled.
  • the circumferential ends of the exchanger 16 comprise added parts which allow the recirculation of oil.
  • the exchanger 16 comprises a plurality of means 18 for fixing the exchanger 16 to the external annular shell 14 which is shown in figure 5 . It will be immediately noted that the exchanger 16 can be fixed to an internal annular shell of a casing without it being necessary to make a new description so that it will be understood that what applies to the external annular shell 14 also applies to an internal annular shell.
  • the fixing means 18 of the exchanger 16 are distributed around the circumference of the heat exchanger 16, that is to say around the longitudinal axis A of the turbomachine.
  • figure 3 illustrates two annular rows of fixing means 18.
  • each fixing means 18 allows a connection with a degree of freedom in the tangential direction of the heat exchanger 16 with the external annular shell 14.
  • each fixing 18 comprises a rail 20 secured to the heat exchanger 16 and interposed radially between a first plate 22 and a second plate 24.
  • the rail 20 has a substantially rectangular shape with an internal opening 26 which is of closed contour.
  • This rail 20 thus comprises two rectilinear uprights 28 which are oriented in a tangential direction and which are connected to each other by a first end portion 30 and a second end portion 32.
  • the first end portion 30 and the second end portion 32 each comprise an orifice 34 for the passage of a screw 36 for fixing the rail 20 on radially external bosses 38 of the heat exchanger 16 ( figure 5 ).
  • the first end portion 32 of the rail 20 further comprises a portion 40 forming a tongue extending towards the inside of the opening 26.
  • the outline of the opening 26 is delimited by two parallel tangential edges 26a, 26b of which a first edge 26a is formed on a first rectilinear upright 28 and a second edge 26b is formed on a second rectilinear upright 28, by a longitudinal edge 26c and by a convex curved edge 26d tangentially opposite the longitudinal edge 26c.
  • This convex edge 26d is connected to the ends of the edges longitudinal 26a, 26b and delimit with these two slots 42 with the external contour of the tongue 40.
  • the first plate 22 also has a substantially rectangular shape. It comprises a central tubular portion 44 passing through the opening 26 of the rail 20. This tubular portion 44 is tightly engaged in an orifice 46 of the second plate 24.
  • the first plate 22 comprises two parts extending tangentially with an L-shaped section formed on either side of the tubular portion 44 and each formed by a first tangential face 48a and a second tangential face 48b.
  • the first tangential faces 48a come into longitudinal contact with the first 26a and second 26b edges of the contour of the opening 26 of the rail 20 so as to allow tangential guidance of the rail 20.
  • the second tangential faces 48b ensure radially inward retention of the rail 20 on the first plate 22.
  • the first plate 22 comprises an end portion having a concave curved edge 50 facing the convex curved edge of the tongue 40 of the rail 20.
  • the end portions of the concave curved edge 50 are intended to be housed in the aforementioned slots 42 of the rail 20, which makes it possible to improve the compactness of each fixing means 18.
  • a tangential end of the first plate 22 comprises a housing 52 in which are mounted elastic means 54 capable of elastically deforming in the radial direction.
  • These elastic means 54 are for example a wave washer as shown in figure 6 . They can be elastically prestressed when mounted between the first plate 22 and rail 20, here more specifically the tab 40 of the rail 20.
  • first plate 22 has a longitudinal dimension greater than the longitudinal dimension of the opening of the rail 20 ( Figures 4A and 4B ). More specifically, the rectilinear uprights 28 of the rail 20 are able to slide on the second plate 24 on either side of its orifice 46 for mounting the tubular portion 44 of the first plate 22.
  • first 48a tangential sliding guide faces of the first 26a and second 26b edges of the rail 20 could be formed on the second plate 24.
  • a removable support element 56 is mounted on the annular ferrule 14 and comprises a flat 56a for bearing on the radially external face of the external annular ferrule 14 and a rod 56b screwed into the tubular portion 44 of the first plate 22. With such an assembly, the first plate 22 and the second plate 24 are fixed integrally to the external annular ferrule 14.
  • each fastener is preassembled to the heat exchanger 16, which simplifies the assembly of the heat exchanger 16 on the external annular shell 14. Furthermore, the elastic means 54 make it possible to avoid untimely movements of the first 22 and second 24 plates since the first plate 22 secured to the second plate 24 is blocked on the rail 20.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
  • Details Of Heat-Exchange And Heat-Transfer (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (12)

  1. Ringförmige Anordnung für ein Mantelstrom-Triebwerk mit einer Längsachse (A) und mit einem Gehäuse (12), das einen Mantelring (14) aufweist, dessen eine Seite eine ringförmige Einrichtung trägt, wobei mehrere Befestigungsmittel (18) zum Befestigen der Einrichtung an dem Mantelring (14) um die Längsachse (A) herum verteilt angeordnet sind und in tangentialer Richtung einen Freiheitsgrad der Einrichtung (16) relativ zu dem Mantelring (14) zulassen,
    dadurch gekennzeichnet, dass jedes Befestigungsmittel (18) eine Schiene (20) umfasst, die fest mit der ringförmigen Einrichtung (16) verbunden ist und radial zwischen einer ersten, radial inneren Platte (22) und einer zweiten, radial äußeren Platte (24) angeordnet ist und in tangentialer Richtung zwischen der ersten Platte (22) und der zweiten Platte (24) verschiebbar ist, und
    dass ein abnehmbares Stützelement (56) ortsfest mit dem Mantelring und der ersten Platte (22) und der zweiten Platte (24) verbunden ist, wobei der Mantelring ein äußerer Mantelring eines ringförmigen Strömungskanals für einen Sekundärluftstrom ist, wobei die Einrichtung von einer radial inneren Fläche des äußeren Mantelrings getragen wird, wobei es sich bei der Einrichtung um einen Wärmetauscher (16) handelt, der aus einem Material hergestellt ist, das einen größeren Wärmeausdehnungskoeffizienten als das Material des Mantelrings des Gehäuses hat.
  2. Anordnung nach Anspruch 1,
    wobei die Schiene (20) eine Öffnung (26) mit geschlossenem Umriss umfasst, die innen von zumindest zwei im Wesentlichen tangential verlaufenden Randkanten (26a, 26b) begrenzt ist, die in Längsrichtung zwei ersten tangential verlaufenden Flächen (48a) der ersten Platte (22) bzw. der zweiten Platte (24) gegenüberliegen und eine Führung für die Schiene (20) in tangentialer Richtung sicherstellen.
  3. Anordnung nach Anspruch 2,
    wobei die beiden ersten tangential verlaufenden Flächen (48a) jeweils an der ersten Platte (22) ausgebildet sind und mit zwei zweiten tangential verlaufenden Flächen verbunden sind, um die Schiene (20) radial nach innen festzuhalten, wobei die beiden ersten tangential verlaufenden Flächen (48a) mit den beiden zweiten tangential verlaufenden Flächen (48b) einen L-förmigen Querschnitt bilden.
  4. Anordnung nach Anspruch 2 oder 3,
    wobei die beiden ersten tangential verlaufenden Flächen (48a) und/oder die beiden zweiten tangential verlaufenden Flächen (48b) an der ersten Platte (22) ausgebildet sind.
  5. Anordnung nach einem der Ansprüche 1 bis 4,
    wobei die erste Platte (22) einen zentralen rohrförmigen Abschnitt (44) aufweist, der in eine Öffnung der zweiten Platte (24) klemmend eingreift.
  6. Anordnung nach einem der Ansprüche 1 bis 5,
    wobei das abnehmbare Stützelement (56) zumindest eine Stange (56b) umfasst, die fest mit der ersten Platte (22) verbunden ist.
  7. Anordnung nach Anspruch 6,
    wobei die Stange (56b) eine Gewindestange ist, die in die erste Platte eingeschraubt ist und eine Abflachung (56a) zur Auflage auf einer Seite des Mantelrings (14) umfasst, die derjenigen gegenüberliegt, die die Einrichtung (16) trägt.
  8. Anordnung nach einem der Ansprüche 1 bis 7,
    wobei zwischen der ersten Platte (22) und der Schiene (20) Federmittel (54) in radialer Richtung federnd vorgespannt sind.
  9. Anordnung nach Anspruch 8,
    wobei die erste Platte (22) eine Aufnahme (52) zum Aufnehmen der Federmittel (54), wie beispielsweise einer Wellenscheibe, umfasst.
  10. Anordnung nach Anspruch 2 und einem der Ansprüche 7 oder 8, wobei die Kontur eine konvex ausgebildete Randkante (50) umfasst, der einen Teil der Schiene (20) begrenzt, der zur radialen Abstützung der Federmittel dient.
  11. Anordnung nach einem der Ansprüche 1 bis 10,
    wobei die Einrichtung aus Aluminium und der Mantelring des Gehäuses aus Titan hergestellt ist.
  12. Verfahren zur Montage der Anordnung nach einem der Ansprüche 1 bis 11, wobei:
    - für jede der ersten Befestigungen (18) die Schiene zwischen der ersten Platte (22) und der zweiten Platte (24), die aneinander befestigt sind, angeordnet wird, wobei die Schiene mit einer radial äußeren Fläche des Wärmetauschers (16) fest verbunden wird, und dann
    - die im vorherigen Schritt hergestellte Verbindung gegenüber der radial inneren Fläche des Mantelrings (14) vorgehalten wird und die Stützelemente fest mit einer der ersten Platte (22) und der zweiten Platte (24) verbunden werden.
EP19797323.3A 2018-09-28 2019-09-25 Ringvorrichtung für turbomaschine und verfahren zum einbau einer solchen vorrichtung Active EP3857031B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1859038A FR3086691B1 (fr) 2018-09-28 2018-09-28 Ensemble annulaire pour turbomachine
PCT/FR2019/052265 WO2020065220A1 (fr) 2018-09-28 2019-09-25 Ensemble annulaire pour turbomachine

Publications (2)

Publication Number Publication Date
EP3857031A1 EP3857031A1 (de) 2021-08-04
EP3857031B1 true EP3857031B1 (de) 2024-08-21

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EP19797323.3A Active EP3857031B1 (de) 2018-09-28 2019-09-25 Ringvorrichtung für turbomaschine und verfahren zum einbau einer solchen vorrichtung

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US (1) US11591930B2 (de)
EP (1) EP3857031B1 (de)
JP (1) JP7483697B2 (de)
CN (1) CN112912594B (de)
FR (1) FR3086691B1 (de)
WO (1) WO2020065220A1 (de)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3086691B1 (fr) * 2018-09-28 2020-12-11 Safran Aircraft Engines Ensemble annulaire pour turbomachine

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2115487B (en) 1982-02-19 1986-02-05 Gen Electric Double wall compressor casing
US4522559A (en) * 1982-02-19 1985-06-11 General Electric Company Compressor casing
GB0909470D0 (en) * 2009-06-03 2009-07-15 Rolls Royce Plc A guide vane assembly
US8510945B2 (en) 2009-12-22 2013-08-20 Unison Industries, Llc Method of mounting a heat exchanger in a gas turbine engine assembly
US9726043B2 (en) 2011-12-15 2017-08-08 General Electric Company Mounting apparatus for low-ductility turbine shroud
US9896971B2 (en) * 2012-09-28 2018-02-20 United Technologies Corporation Lug for preventing rotation of a stator vane arrangement relative to a turbine engine case
US9453429B2 (en) * 2013-03-11 2016-09-27 General Electric Company Flow sleeve for thermal control of a double-wall turbine shell and related method
US10393147B2 (en) * 2015-07-23 2019-08-27 Unison Industries, Llc Fan casing assemblies and method of mounting a cooler to a fan casing
FR3086691B1 (fr) * 2018-09-28 2020-12-11 Safran Aircraft Engines Ensemble annulaire pour turbomachine
US11248495B2 (en) * 2019-06-11 2022-02-15 General Electric Company Systems and methods for sensors on circumferential interior surface of turbomachine casing

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Publication number Publication date
JP7483697B2 (ja) 2024-05-15
CN112912594A (zh) 2021-06-04
FR3086691B1 (fr) 2020-12-11
FR3086691A1 (fr) 2020-04-03
US20210404347A1 (en) 2021-12-30
EP3857031A1 (de) 2021-08-04
US11591930B2 (en) 2023-02-28
WO2020065220A1 (fr) 2020-04-02
JP2022502599A (ja) 2022-01-11
CN112912594B (zh) 2024-01-09

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