EP3517737A1 - Damper for damping vibrations of a tube in a hollow strut of a gas turbine engine and hub strut case with such a damper - Google Patents

Damper for damping vibrations of a tube in a hollow strut of a gas turbine engine and hub strut case with such a damper Download PDF

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Publication number
EP3517737A1
EP3517737A1 EP18153738.2A EP18153738A EP3517737A1 EP 3517737 A1 EP3517737 A1 EP 3517737A1 EP 18153738 A EP18153738 A EP 18153738A EP 3517737 A1 EP3517737 A1 EP 3517737A1
Authority
EP
European Patent Office
Prior art keywords
damper
tube
strut
hollow
contact part
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.)
Withdrawn
Application number
EP18153738.2A
Other languages
German (de)
French (fr)
Inventor
Patrick Lang
Benedikt Heidenreich
René Grahnert
Monika Bajda
Marcin Rozak
Lukasz Dudzik
Marcin Pomianek
Szczepan Sowa
Krzysztof Miller
Artur Kaleta
Michal Borla
Rafal Bator
Axel Mitzscherlich
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP18153738.2A priority Critical patent/EP3517737A1/en
Publication of EP3517737A1 publication Critical patent/EP3517737A1/en
Withdrawn legal-status Critical Current

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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04Antivibration arrangements
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162Bearing supports
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00Stators
    • F01D9/06Fluid supply conduits to nozzles or the like
    • F01D9/065Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00Manufacture
    • F05D2230/50Building or constructing in particular ways
    • F05D2230/54Building or constructing in particular ways by sheet metal manufacturing
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00Function
    • F05D2260/96Preventing, counteracting or reducing vibration or noise

Definitions

  • the present invention relates to a damper for damping vibrations of a tube, especially an oil tube, in a hollow strut of a gas turbine engine and the use thereof.
  • the turbine center frame (TCF) for large aircraft engines plays a key role in every turbofan.
  • the TCF is situated between the high-pressure turbine and the low-pressure turbine, where it performs two important functions. It connects the high-pressure shaft's rear bearing with the housing and forms an aerodynamic transition duct between the high-pressure and low-pressure turbine. This area is subject to very high stresses, because bearing loads are conducted to the outer casing through the TCF structure.
  • the turbine center frame In the event of faults, such as a broken fan blade, the turbine center frame must be able to withstand the resulting loads in terms of mechanical integrity.
  • the component has to permanently withstand temperatures in excess of 1,000 degrees Celsius.
  • TCFs essentially consist of two main component groups.
  • the first group includes a hub strut case (HCS), which is a load-bearing structure and takes form of a casing with several struts assembled around the hub with an integrated bearing.
  • the second group includes the struts' panels and fairings - also known as flowpath hardware - which form a channel for hot gas flowing from the high-pressure turbine.
  • flowpath hardware also known as flowpath hardware
  • an object of the present invention is to provide a new damper design with improved contact conditions between the damper and the hollow strut.
  • a damper for damping vibrations of a tube in a hollow strut of a gas turbine engine comprises:
  • the contact part is in the form of a portion of a hollow sphere or of a hollow torus.
  • the contact part is curved towards the axis of the cylinder defined by fixing part.
  • the damper comprises a longitudinal crevice extending through the contact part and at least partially through the middle part, which enables pre-tensioning of a damper during tube assembly into the strut.
  • the crevice is ended with a substantially circular orifice in the middle part.
  • the damper according to the invention is formed from a sheet of metal.
  • the present invention also relates to a hub strut case (HCS) comprising a damper arrangement comprising at least two dampers described above, fixed to an oil tube passing through the hollow strut on the opposite sides of the oil tube surface, such that contact parts of the dampers bear against the inner surface of the hollow strut walls.
  • HCS hub strut case
  • the present invention also relates to the use of the damper defined above for damping vibrations of a tube in the hollow strut of a gas turbine engine.
  • the dampers according to the present invention when fixed to an oil tube, form a tulip-shape damper assembly.
  • Providing two dampers on the opposite sides of the tube enables to achieve at least the two-point contact per side resulting in a kind of a self-locking assembly. Resulting friction between the contact parts of the damper and the hollow strut side walls has been found to be sufficient to keep the tube in place.
  • a damper (1) for damping vibrations of a tube (2) in a hollow strut (3) in a gas turbine engine as shown in fig. 3 and 4 comprises a fixing part (4), a contact part (5) and a middle part (6).
  • the fixing (4) part is in the form of a portion of a cylinder surface to adjoin the cylindrical exterior surface of an oil tube (2).
  • the contact part (6) is in the form of a portion of a hollow torus, curved towards the axis of the cylinder defined by fixing part (4). Between the fixing (4) part and a contact part (5) extends a middle part (6) in form of a cone surface portion.
  • the damper (1) comprises a longitudinal crevice (7) extending through the contact part (5) and through the middle part (6), which is ended with a circular orifice (8) in the middle part (6).
  • Longitudinal crevice (7) is parallel to the axis of a cylinder defined by a fixing part (4) and a tube (2), when the damper (1) is fixed on said tube (2).
  • Figure 5 shows the dampers (1) fixed to an oil tube (2).
  • the dampers (1) are placed on the opposite sides of the tube (2) surface and form a tulip-like shape.
  • Figure 7 is a cross section of a hollow strut (3) comprising an oil tube (2) with two dampers (1) fixed on the opposite sides of the tube (2).
  • the hollow strut (3) is hollow through the center, with an axially (with regard to HCS shape) elongated cross-section.
  • the fixing parts of a dampers (1) are brazed to the oil tube (2).
  • the contact parts (5) bear against the inner surface of the hollow strut (3) walls providing 4-point contact.
  • the middle part (6) extends between the surface of the oil tube and the contact part.
  • damper (1) is pre-tensioned as damper (1) arrangement width (diameter) is greater than inner hollow strut (3) cross-section.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Fluid-Damping Devices (AREA)

Abstract

The present invention relates to a damper (1) for damping vibrations of a tube (2) in a strut (3) of a gas turbine engine, characterised in that it comprises:
a fixing part (4) for fixing the damper (1) to the tube (2), the fixing part being shaped substantially in a form of a portion of a cylinder surface,
a contact part (5) for contacting the strut inner wall, the contact part (5) being in a form of a curved surface, and
a middle part (6) connecting the fixing part (4) and the contact part (5), the middle part (6) being substantially in a form of a cone surface portion.

Description

    Field of the invention
  • The present invention relates to a damper for damping vibrations of a tube, especially an oil tube, in a hollow strut of a gas turbine engine and the use thereof.
  • Technical background
  • The turbine center frame (TCF) for large aircraft engines plays a key role in every turbofan. The TCF is situated between the high-pressure turbine and the low-pressure turbine, where it performs two important functions. It connects the high-pressure shaft's rear bearing with the housing and forms an aerodynamic transition duct between the high-pressure and low-pressure turbine. This area is subject to very high stresses, because bearing loads are conducted to the outer casing through the TCF structure. In the event of faults, such as a broken fan blade, the turbine center frame must be able to withstand the resulting loads in terms of mechanical integrity. In addition, the component has to permanently withstand temperatures in excess of 1,000 degrees Celsius.
  • TCFs essentially consist of two main component groups. The first group includes a hub strut case (HCS), which is a load-bearing structure and takes form of a casing with several struts assembled around the hub with an integrated bearing. The second group includes the struts' panels and fairings - also known as flowpath hardware - which form a channel for hot gas flowing from the high-pressure turbine. In addition, there are various seals, and finally, oil lines and cooling air channels, through which oil and air are conveyed through the TCF to the turbines and the bearing.
  • During engine operation, its parts may be excited to vibrate at their natural frequencies. For example an oil tube passing through a hollow strut may start to vibrate causing the strut or tube damage. It is therefore desirable to eliminate or reduce such vibrations.
  • Currently, so called "hurricane" damper design is used, which comprises two dampers spirally formed and fixed to the tube (fig. 1). These dampers have to be manually bent to a conical shape (fig. 2) to enable installation of the tubes through a limited cross section of the HSC. Due to this pre-bending necessity and their geometry per design, contact conditions of current dampers to adjacent strut are almost undefined. In the best case, line contact can be achieved, which is effective in one direction only (circumferential, see fig. 2). For the other direction (axial) such a damper design is inappropriate.
  • Therefore an object of the present invention is to provide a new damper design with improved contact conditions between the damper and the hollow strut.
  • Summary of the invention
  • According to the present invention a damper for damping vibrations of a tube in a hollow strut of a gas turbine engine, comprises:
    • a fixing part for fixing the damper to the tube, the fixing part being shaped substantially in a form of a portion of a cylinder surface,
    • a contact part for contacting the strut inner wall, the contact part being in a form of a curved surface, and
    • a middle part connecting the fixing part and the contact part, the middle part being substantially in a form of a portion of a cone surface.
  • Preferably the contact part is in the form of a portion of a hollow sphere or of a hollow torus.
  • Preferably the contact part is curved towards the axis of the cylinder defined by fixing part.
  • Preferably the damper comprises a longitudinal crevice extending through the contact part and at least partially through the middle part, which enables pre-tensioning of a damper during tube assembly into the strut. Preferably the crevice is ended with a substantially circular orifice in the middle part. In a preferred embodiment the damper according to the invention is formed from a sheet of metal.
  • The present invention also relates to a hub strut case (HCS) comprising a damper arrangement comprising at least two dampers described above, fixed to an oil tube passing through the hollow strut on the opposite sides of the oil tube surface, such that contact parts of the dampers bear against the inner surface of the hollow strut walls.
  • The present invention also relates to the use of the damper defined above for damping vibrations of a tube in the hollow strut of a gas turbine engine.
  • The dampers according to the present invention, when fixed to an oil tube, form a tulip-shape damper assembly. Providing two dampers on the opposite sides of the tube, enables to achieve at least the two-point contact per side resulting in a kind of a self-locking assembly. Resulting friction between the contact parts of the damper and the hollow strut side walls has been found to be sufficient to keep the tube in place.
  • Pre-bending during installation no longer affects the damper shape itself, but its diameter only. Thus, the conditions of contacting the hollow strut remain unchanged and defined per design, which provides simplified requirements for those who install the tubes inside the hollow struts.
  • Brief description of drawings
  • Exemplary embodiments of the invention are described with reference to the following figures, which are provided for the purpose of illustration only, the full scope of the invention being set forth in the claims that follow:
    • Figure 1 shows "hurricane" damper prior art design;
    • Figure 2 shows a top view of two "hurricane" prior art dampers installed in the hollow strut;
    • Figure 3 is a perspective view of the exemplary damper according to the invention;
    • Figure 4 is another perspective view of the exemplary damper according to the invention;
    • Figure 5 shows two exemplary dampers according to the invention fixed to an oil tube;
    • Figure 6 shows a simplified image of a hollow strut;
    • Figure 7 is a cross section of a hollow strut comprising an oil tube with two exemplary dampers according to the invention.
    Detailed description of preferred embodiment
  • A damper (1) for damping vibrations of a tube (2) in a hollow strut (3) in a gas turbine engine as shown in fig. 3 and 4 comprises a fixing part (4), a contact part (5) and a middle part (6). The fixing (4) part is in the form of a portion of a cylinder surface to adjoin the cylindrical exterior surface of an oil tube (2). The contact part (6) is in the form of a portion of a hollow torus, curved towards the axis of the cylinder defined by fixing part (4). Between the fixing (4) part and a contact part (5) extends a middle part (6) in form of a cone surface portion.
  • The damper (1) comprises a longitudinal crevice (7) extending through the contact part (5) and through the middle part (6), which is ended with a circular orifice (8) in the middle part (6). Longitudinal crevice (7) is parallel to the axis of a cylinder defined by a fixing part (4) and a tube (2), when the damper (1) is fixed on said tube (2).
  • Figure 5 shows the dampers (1) fixed to an oil tube (2). The dampers (1) are placed on the opposite sides of the tube (2) surface and form a tulip-like shape.
  • Figure 7 is a cross section of a hollow strut (3) comprising an oil tube (2) with two dampers (1) fixed on the opposite sides of the tube (2). The hollow strut (3) is hollow through the center, with an axially (with regard to HCS shape) elongated cross-section. The fixing parts of a dampers (1), not visible on the figure, are brazed to the oil tube (2). The contact parts (5) bear against the inner surface of the hollow strut (3) walls providing 4-point contact. The middle part (6) extends between the surface of the oil tube and the contact part.
  • During tube assembly into the hollow strut (3), the damper (1) is pre-tensioned as damper (1) arrangement width (diameter) is greater than inner hollow strut (3) cross-section.

Claims (8)

  1. A damper (1) for damping vibrations of a tube (2) in a hollow strut (3) of a gas turbine engine, characterised in that it comprises:
    a fixing part (4) for fixing the damper (1) to the tube (2), the fixing part being shaped substantially in a form of a portion of a cylinder surface,
    a contact part (5) for contacting the hollow strut inner wall, the contact part (5) being in a form of a curved surface, and
    a middle part (6) connecting the fixing part (4) and the contact part (5), the middle part (6) being substantially in a form of a cone surface portion.
  2. The damper (1) according to claim 1, characterised in that the contact part (5) is in the form of a portion of a hollow sphere or of a hollow torus.
  3. The damper (1) according to claim 1 or 2, characterised in that the contact part (5) is curved towards the axis of the cylinder defined by the fixing part (4).
  4. The damper (1) according to claim 1 or 2 or 3, characterised in that it comprises a longitudinal crevice (7) extending through the contact part (5) and at least partially through the middle part (6).
  5. The damper (1) according to claim 3, characterized in that the crevice (7) is ended with a substantially circular orifice (8) in the middle part (6).
  6. The damper (1) according to one of the preceding claims, characterized in that the damper (1) is formed from a sheet of metal.
  7. A hub strut case (HCS) comprising a damper arrangement comprising at least two dampers (1) according to any of the preceding claims, fixed to an oil tube (2) passing through a hollow strut (3) on the opposite sides of the oil tube (2) surface, such that a contact parts (5) of the dampers (1) bear against the inner surface of the hollow strut (3) walls.
  8. Use of the damper (1) according to any of claims 1-6 for damping vibrations of a tube (2) in a hollow strut (3) of a gas turbine engine.
EP18153738.2A 2018-01-26 2018-01-26 Damper for damping vibrations of a tube in a hollow strut of a gas turbine engine and hub strut case with such a damper Withdrawn EP3517737A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP18153738.2A EP3517737A1 (en) 2018-01-26 2018-01-26 Damper for damping vibrations of a tube in a hollow strut of a gas turbine engine and hub strut case with such a damper

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP18153738.2A EP3517737A1 (en) 2018-01-26 2018-01-26 Damper for damping vibrations of a tube in a hollow strut of a gas turbine engine and hub strut case with such a damper

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EP3517737A1 true EP3517737A1 (en) 2019-07-31

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2574107A (en) * 2018-03-30 2019-11-27 Safran Aircraft Engines Assembly for a turbine engine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4972671A (en) * 1988-05-11 1990-11-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Turbo-engine air intake grill
US5284011A (en) * 1992-12-14 1994-02-08 General Electric Company Damped turbine engine frame
FR3050229A1 (en) * 2016-04-18 2017-10-20 Snecma TURBOMACHINE EXHAUST CASE
FR3051854A1 (en) * 2016-05-30 2017-12-01 Snecma TURBOMACHINE EXHAUST CASE

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4972671A (en) * 1988-05-11 1990-11-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Turbo-engine air intake grill
US5284011A (en) * 1992-12-14 1994-02-08 General Electric Company Damped turbine engine frame
FR3050229A1 (en) * 2016-04-18 2017-10-20 Snecma TURBOMACHINE EXHAUST CASE
FR3051854A1 (en) * 2016-05-30 2017-12-01 Snecma TURBOMACHINE EXHAUST CASE

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2574107A (en) * 2018-03-30 2019-11-27 Safran Aircraft Engines Assembly for a turbine engine
US10934884B2 (en) 2018-03-30 2021-03-02 Safran Aircraft Engines Assembly for a turbine engine
GB2574107B (en) * 2018-03-30 2022-09-21 Safran Aircraft Engines Assembly for a turbine engine

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