EP2971609B1 - Anneau de turbine pour turbomachine - Google Patents

Anneau de turbine pour turbomachine Download PDF

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Publication number
EP2971609B1
EP2971609B1 EP14720173.5A EP14720173A EP2971609B1 EP 2971609 B1 EP2971609 B1 EP 2971609B1 EP 14720173 A EP14720173 A EP 14720173A EP 2971609 B1 EP2971609 B1 EP 2971609B1
Authority
EP
European Patent Office
Prior art keywords
sector
support
ring
damper device
hook
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.)
Active
Application number
EP14720173.5A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2971609A1 (fr
Inventor
Carole Jaureguiberry
Manuel Silva
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 Helicopter Engines SAS
Original Assignee
Safran Helicopter Engines 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 Safran Helicopter Engines SAS filed Critical Safran Helicopter Engines SAS
Priority to PL14720173T priority Critical patent/PL2971609T3/pl
Publication of EP2971609A1 publication Critical patent/EP2971609A1/fr
Application granted granted Critical
Publication of EP2971609B1 publication Critical patent/EP2971609B1/fr
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
    • F01D25/24—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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • 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
    • 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
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2240/00—Components
    • F05D2240/40—Use of a multiplicity of similar components

Definitions

  • the present disclosure relates to a turbomachine turbine ring, in particular for a helicopter.
  • Such a ring can be used for any type of turbomachine to reduce vibratory behaviors that may appear within such rings.
  • the high pressure turbine rings generally comprise a ring of sectors fixed on a ring support. As is visible on the FIG 2 , the sectors have for this purpose hooks capable of cooperating with hooks of the support.
  • the ring sectors In contact with the air stream, the ring sectors are subjected to the stresses of the aerodynamic flow, caused in particular by the wake of the upstream and downstream stages, and can thus experience a vibratory behavior. In particular, in the operating range of the motor, the sectors are likely to come into resonance, which can lead to cracking due to vibration fatigue or premature wear phenomena.
  • the present disclosure relates to a turbine ring according to claim 1, comprising a support, substantially cylindrical, and one or more sectors forming a ring configured to materialize a section of air stream, each sector being fixed on the support by a device of in which the hooking device comprises a hook portion belonging to the support and projecting towards the sector, and a hook portion belonging to the sector and projecting towards the support, the hook parts of the support and the sector being configured to cooperate in order to secure the sector on the medium; the ring further comprises a damping device provided within the coupling device and radially constrained between a portion of the sector and a portion of the support so as to damp the relative movements of the sector relative to the support; the damping device is in alternating contact, in the circumferential direction, with the inner surface of the support and the outer surface of the hook portion of the sector.
  • This damping device also frees the sector of its secondary objective of limiting vibrations. From then on, his geometry can be chosen more freely: it can be simplified, resulting in cost savings, or optimized more effectively with respect to other functions in the sector.
  • this damping device allows easy assembly of the sector on the support by acting as a guide whose radial dimension substantially corresponds to the clearance to separate the sector of the support: the sector can be pressed against the damping device for ensure its precise positioning. This provides increased accuracy and repeatability of positioning, resulting in particular better control of the game at the top of the blade and reducing machining nonconformities.
  • the damping device is further configured to press a portion of the sector against a portion of the support. Therefore, the relative movements of the sector and the support can also be damped by friction of the sector against the support.
  • the support is also fixed via a second hooking device similar to the first attachment device; it is also equipped with a second damping device, provided in the second attachment device, similar to the first damping device.
  • the damping device comprises a flexible blade.
  • this flexible blade is a sheet metal element.
  • Such a flexible sheet is inexpensive, easy to form, and has a stiffness adapted to such damping.
  • the damping device is constrained radially between said portion of the sector and said portion of the support over its entire length. Therefore, the constraints on the sector and support are spread over the entire length of the sector. In addition, depreciation is homogeneous across the sector.
  • the damping device is substantially smooth over its entire length with the exception of localized recesses distributed along its length. It may especially be spherical impressions made by stamping, for example.
  • the device comprises a corrugated sheet element.
  • the damping device is provided between an outer surface of the sector hook portion and an inner surface of the carrier. Such a configuration is easy to assemble. In addition, in this configuration, the two hook parts are pressed against each other which reinforces the attachment of the sector and its damping.
  • the damping device is provided between an inner surface of the hook portion of the carrier and an outer surface of the sector.
  • the damping device is housed at least in part in a groove made in a portion of the sector. With this groove, it is possible to mount the damping device on the sector before assembly on the support, which facilitates the assembly procedure. In addition, this reduces the radial clearance between the sector and the support.
  • the damping device is housed at least partly in a groove made in a portion of the support.
  • the cushioning device envelopes at least the distal portion of the hook portion of the carrier. The damping device is thus easily put in place and remains in position even in the absence of the sector.
  • the damping device is configured to continuously maintain at least one pressure zone on the outer surface of the hook portion of the support and a pressure zone on its inner surface, on the one hand , and at least one pressure zone on the inner surface of the sector hook portion and / or a pressure zone on an outer surface of the sector, other share.
  • the damping device is thus clipped around the end of the hook, which ensures its positioning and its immobilization.
  • the damping device envelopes at least the distal portion of the sector hook portion.
  • the damping device is integral and continuous along the circumference of the ring formed by the sector or sectors. It can, however, be interrupted by a break in an azimuthal plane of the device.
  • the damping device is divided into a plurality of sections succeeding each other along the circumference of the ring formed by the sector or sectors.
  • a section of the damping device is associated with each sector.
  • each section of the damping device is associated with a plurality of sectors.
  • the damping device is configured to further provide a seal between the support and the sector. It may be for example a braided seal.
  • the damping device is secured to either the sector or the support. This joining is preferably performed by welding.
  • the present disclosure also relates to a turbomachine comprising at least one ring according to any one of the aforementioned embodiments.
  • the turbomachine is a helicopter turbine engine. Said ring equips the linked turbine and / or the free turbine.
  • the turbomachine is an airplane turbojet engine.
  • FIG 1 illustrates a turbomachine 10, in this case a helicopter turbine engine.
  • this turbine engine 10 comprises a compressor 11, a gas generator 12 and linked turbines 13 and free 14, also called high pressure turbine and low pressure turbine, driven in rotation by the flue gas flow exiting the combustion chamber 12.
  • the free turbine 14 comprises a turbine wheel 14a which is fixed at one end of the combustion chamber. a shaft 15. At the other end of the shaft 15 is a primary gear 16 which meshes with an intermediate gear 17. This intermediate gear 17 meshes with an output gear 18.
  • the intermediate gear 17 and the pinion output 18 are gear wheels which form part of the speed reducer of the turbomachine 10.
  • the output gear 18 is connected to an output shaft 19 intended to be coupled to the main gearbox of the helicopter (not shown right here).
  • the linked turbine 13, comprising a turbine wheel 13a, is in turn connected to the compressor 11 via a drive shaft 20.
  • the linked turbine 13 is further equipped with a turbine ring 30 which materializes the vein of air vis-à-vis the blades of the turbine wheel 13a.
  • FIG 2 illustrates a first example of such a turbine ring 30.
  • This comprises a generally cylindrical ring support 31, forming an integral part of the turbine casing 13, and a ring sector ring 32 fixed on the support of ring 31 so as to materialize the air stream of the turbine 13.
  • each ring sector 32 is fixed on the ring support 31 by means of attachment devices 33a and 33b: in each attachment device 33a, 33b, a hook 34 of the sector 32 extends towards the support 31 to cooperate with a hook 35 of the support 31 extending towards the ring sector 32.
  • These hooks 34 of the sector 32 thus have a radial portion 34a and a tangential portion 34b and extend continuously along each sector 32.
  • the hooks 35 of the support 31 also have a radial portion 35a and a tangential portion 35b and extend circumferentially continuously along the circumference of the support 31.
  • the hooks 34 of the sector 32 are provided with a rib 41 projecting on the outer surface 34e of the hook 34 in the extension, at least partially, of the radial portion 34a of the hook 34.
  • This rib 41 allows to play a game radial between the outer surface 34e of the hook 34 and the inner surface 31i of the support 31 to set up a damper 50.
  • This damper 50 is a flexible blade, preferably a metal sheet, taking substantially the shape of a V in this axial section plane: this sectional shape is substantially constant over the entire length of the damper 50.
  • the damper 50 is thus constrained between the outer surface 34e of the hook 34 of the sector 32 and the inner surface 31i of the support 31 in such a way that it exerts, on the one hand, a pressure on the hook 34 by its central zone and, on the other hand, part, a pressure on the support 31 by its 2 ends.
  • this damper 50 can be adjusted by adjusting the thickness, the length and more generally the shape of the damper.
  • the damper is made using a sheet of thickness about 0.2mm. Its material can also be chosen according to the desired stiffness. In this case, this sheet is a plate Inconel 718.
  • the damper 50 of each attachment device 33a, 33b is integral and continuous all along the ring support 31 with the exception of a break in an azimuthal plane of the damper 50 of however, in other examples, the damper could be continuous all along the ring support without hyphenation.
  • a groove 42 is hollowed in the outer surface 34e of the hook 34 of the ring sector 32.
  • Such a groove 42 can accommodate the damper 52.
  • the depth of the groove 42 is nevertheless smaller than the height of the damper 52 so that the damper 52 protrudes above the outer surface 34e of the hook 34: the damper 52 is constrained between the support 31 and the hook 34 of the sector 32.
  • FIG 4 illustrates that it is also possible to mount the damper 52 in a head-to-tail position relative to that of the damper 50 of the FIG 3 : then, the damper 52 exerts a pressure on the inner surface 31i of the support 31 by its central zone while it exerts a pressure on the hook 34 of the sector 32 by its two ends.
  • FIG 5 illustrates another variant of the first embodiment of the ring 30.
  • the damper 54 is not monobloc but divided: in this case, the divisions of the damper 54 are provided to correspond to the divisions of the ring sectors 32 such that a damper section 54 is associated with each sector 32.
  • the damper 54 could be divided otherwise.
  • FIG 6A and 6B illustrate yet another variant of the first example of a turbine ring 30.
  • the damper 56 is not here shaped along its length.
  • the damper 56 is a flexible blade, preferably a metal sheet, substantially smooth over its entire length with the exception of recesses 57 made regularly in its smooth surface.
  • the damper 56 is configured so that its outer surface bears against the inner surface 31i of the ring support 31 while the inner end of these recesses 57 bears against the outer surface 33e of the hook 33 the ring sector 32 so that the damping device 56 is in alternating contact, in the circumferential direction, with the inner surface 31i of the support 31 and the outer surface 33e of the hook 33 of the ring sector 32.
  • FIG 7A and 7B illustrate a last variant of the first example of a turbine ring 30.
  • the damper 58 is a corrugated sheet whose oscillations allow the damper 58 to be in contact alternately, in the circumferential direction, with the surface internal 31i of the support 31 and the outer surface 34e of the hook 33 of the ring sector 32.
  • the FIG 8A illustrates a second example of turbine ring 130.
  • the damper 160 is a flexible blade, preferably a metal sheet, substantially in the shape of a U in this axial torque plane, engaged around the distal portion of the hook 135 of the support 131, that is to say at the end of the tangential portion 135b of the hook 135.
  • the damper 160 thus comprises a flat portion 161, pressed against the distal surface of the hook 135, which extend the two branches of the damper 160.
  • the two branches are tightened so as to grip the distal portion of the hook 135 and then, in a second portion 163, the two branches depart to come rely on the inner surface 134i of the tangential portion 134b of the hook 134 on the one hand, and on the outer surface 132e of the ring sector 132 on the other.
  • the two branches of the damper 160 are symmetrical.
  • FIG 8B illustrates a variant of the second example of a turbine ring 130.
  • the internal branch of the damper 160 is longer than its external branch.
  • the second portion 163 of the inner branch rests on the outer surface 132e of the ring sector 132 further downstream than in the example of FIG. FIG 8A .
  • FIG 8C illustrates another variant of the second example of a turbine ring 130.
  • the internal branch of the damper 160 comprises a first constricted portion 162 which bears against the inner surface 135i of the hook 135 but does not have a second portion bearing against the outer surface 132e of the ring sector 132.
  • the FIG 9 illustrates a third example of turbine ring 230.
  • the damper 260 is a flexible blade, preferably a metal sheet, taking substantially the shape of an L in this axial section plane, engaged around the distal portion of the hook 234 of the ring sector 232.
  • the damper 260 comprises a flat portion 261, pressed against the radial portion 235a of the hook 235 of the ring support 231, which extends a generally tangential branch.
  • this branch tapers inwards so as to abut against the outer surface 234e of the hook 234 of the sector 232, then in a second portion 263, this branch deviates towards the outside of so as to come to rest on the inner surface 231i of the support 231.
  • this branch folds radially inward so as to bear at right angles against the outer surface 234e of the hook 234.
  • the hook portion 234 of the sector 232 is thus pressed against the hook portion 235 of the support 231.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Aviation & Aerospace Engineering (AREA)
EP14720173.5A 2013-03-14 2014-03-13 Anneau de turbine pour turbomachine Active EP2971609B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL14720173T PL2971609T3 (pl) 2013-03-14 2014-03-13 Pierścień turbiny do maszyny wirowej

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1352257A FR3003301B1 (fr) 2013-03-14 2013-03-14 Anneau de turbine pour turbomachine
PCT/FR2014/050579 WO2014140493A1 (fr) 2013-03-14 2014-03-13 Anneau de turbine pour turbomachine

Publications (2)

Publication Number Publication Date
EP2971609A1 EP2971609A1 (fr) 2016-01-20
EP2971609B1 true EP2971609B1 (fr) 2019-08-07

Family

ID=48289407

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14720173.5A Active EP2971609B1 (fr) 2013-03-14 2014-03-13 Anneau de turbine pour turbomachine

Country Status (10)

Country Link
US (1) US10138734B2 (ja)
EP (1) EP2971609B1 (ja)
JP (1) JP6453252B2 (ja)
KR (1) KR102199586B1 (ja)
CN (1) CN105189937B (ja)
CA (1) CA2904951C (ja)
FR (1) FR3003301B1 (ja)
PL (1) PL2971609T3 (ja)
RU (1) RU2653710C2 (ja)
WO (1) WO2014140493A1 (ja)

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US10400896B2 (en) * 2014-08-28 2019-09-03 United Technologies Corporation Dual-ended brush seal assembly and method of manufacture
FR3036436B1 (fr) * 2015-05-22 2020-01-24 Safran Ceramics Ensemble d'anneau de turbine avec maintien par brides
CN105386797B (zh) * 2015-12-29 2017-06-16 中国航空工业集团公司沈阳发动机设计研究所 一种涡轮静子结构
US11466700B2 (en) * 2017-02-28 2022-10-11 Unison Industries, Llc Fan casing and mount bracket for oil cooler
FR3064022B1 (fr) * 2017-03-16 2019-09-13 Safran Aircraft Engines Ensemble d'anneau de turbine
FR3064023B1 (fr) * 2017-03-16 2019-09-13 Safran Aircraft Engines Ensemble d'anneau de turbine
US10533446B2 (en) 2017-05-15 2020-01-14 United Technologies Corporation Alternative W-seal groove arrangement
US10753222B2 (en) * 2017-09-11 2020-08-25 Raytheon Technologies Corporation Gas turbine engine blade outer air seal
FR3076852B1 (fr) * 2018-01-16 2020-01-31 Safran Aircraft Engines Anneau de turbomachine
US10920600B2 (en) * 2018-09-05 2021-02-16 Raytheon Technologies Corporation Integrated seal and wear liner
FR3086327B1 (fr) * 2018-09-25 2020-12-04 Safran Aircraft Engines Ensemble pour une turbine de turbomachine
RU199280U1 (ru) * 2019-03-07 2020-08-25 Публичное акционерное общество "МОТОР СИЧ" Корпус подвески турбовинтового двигателя
FR3093536B1 (fr) * 2019-03-08 2021-02-19 Safran Aircraft Engines Rotor pour une turbine contrarotative de turbomachine
FR3096731B1 (fr) * 2019-05-29 2021-05-07 Safran Aircraft Engines Ensemble pour turbomachine
FR3096725B1 (fr) * 2019-05-29 2021-05-14 Safran Helicopter Engines Module de turbomachine d’aeronef
FR3100838B1 (fr) * 2019-09-13 2021-10-01 Safran Aircraft Engines Anneau d’etancheite de turbomachine
US11466588B2 (en) * 2019-10-30 2022-10-11 Raytheon Technologies Corporation Axially rigid curved beam with squeeze damper
CN113803115B (zh) * 2020-06-16 2024-04-05 中国航发商用航空发动机有限责任公司 涡轮叶片缘板阻尼器、涡轮叶片和航空发动机
KR20230035614A (ko) 2020-08-13 2023-03-14 미츠비시 파워 가부시키가이샤 정익 세그먼트, 및 이것을 구비하는 증기 터빈
FR3140115B1 (fr) * 2022-09-22 2024-10-04 Safran Aircraft Engines Pièce d'amortissement des déformations d'un carter de récupération d'huile, ensemble qui le comporte et turbomachine ainsi équipée
CN117869016B (zh) * 2024-03-12 2024-05-17 中国航发四川燃气涡轮研究院 一种降低涡轮外环导热的冷却单元及其分析方法

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Also Published As

Publication number Publication date
US20160024926A1 (en) 2016-01-28
PL2971609T3 (pl) 2019-12-31
RU2015143679A (ru) 2017-04-26
US10138734B2 (en) 2018-11-27
RU2015143679A3 (ja) 2018-03-01
FR3003301B1 (fr) 2018-01-05
KR20150128882A (ko) 2015-11-18
RU2653710C2 (ru) 2018-05-14
CA2904951A1 (fr) 2014-09-18
CN105189937A (zh) 2015-12-23
CN105189937B (zh) 2018-03-30
JP2016511362A (ja) 2016-04-14
FR3003301A1 (fr) 2014-09-19
JP6453252B2 (ja) 2019-01-16
CA2904951C (fr) 2021-01-26
WO2014140493A1 (fr) 2014-09-18
KR102199586B1 (ko) 2021-01-07
EP2971609A1 (fr) 2016-01-20

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