GB2407523A - A vibration damping coating - Google Patents

A vibration damping coating Download PDF

Info

Publication number
GB2407523A
GB2407523A GB0325069A GB0325069A GB2407523A GB 2407523 A GB2407523 A GB 2407523A GB 0325069 A GB0325069 A GB 0325069A GB 0325069 A GB0325069 A GB 0325069A GB 2407523 A GB2407523 A GB 2407523A
Authority
GB
United Kingdom
Prior art keywords
component
vibration damping
particles
matrix material
vane
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Withdrawn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
GB0325069A
Other versions
GB0325069D0 (en
Inventor
John Travis Gent
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB0325069A priority Critical patent/GB2407523A/en
Publication of GB0325069D0 publication Critical patent/GB0325069D0/en
Publication of GB2407523A publication Critical patent/GB2407523A/en
Withdrawn legal-status Critical Current

Links

Classifications

    • G—PHYSICS
    • G10—MUSICAL INSTRUMENTS; ACOUSTICS
    • G10K—SOUND-PRODUCING DEVICES; METHODS OR DEVICES FOR PROTECTING AGAINST, OR FOR DAMPING, NOISE OR OTHER ACOUSTIC WAVES IN GENERAL; ACOUSTICS NOT OTHERWISE PROVIDED FOR
    • G10K11/00—Methods or devices for transmitting, conducting or directing sound in general; Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
    • G10K11/16—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
    • G10K11/162—Selection of materials
    • G10K11/165—Particles in a matrix
    • C—CHEMISTRY; METALLURGY
    • C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
    • C09D—COATING COMPOSITIONS, e.g. PAINTS, VARNISHES OR LACQUERS; FILLING PASTES; CHEMICAL PAINT OR INK REMOVERS; INKS; CORRECTING FLUIDS; WOODSTAINS; PASTES OR SOLIDS FOR COLOURING OR PRINTING; USE OF MATERIALS THEREFOR
    • C09D7/00—Features of coating compositions, not provided for in group C09D5/00; Processes for incorporating ingredients in coating compositions
    • C09D7/40—Additives
    • C09D7/60—Additives non-macromolecular
    • C09D7/61—Additives non-macromolecular inorganic
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/18—After-treatment
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
    • C08K3/00—Use of inorganic substances as compounding ingredients
    • C08K3/18—Oxygen-containing compounds, e.g. metal carbonyls
    • C08K3/20—Oxides; Hydroxides
    • C08K3/22—Oxides; Hydroxides of metals
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
    • C08K3/00—Use of inorganic substances as compounding ingredients
    • C08K3/18—Oxygen-containing compounds, e.g. metal carbonyls
    • C08K3/24—Acids; Salts thereof
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • 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
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity

Abstract

A component (36) has a vibration damping coating (54). The vibration damping coating (54) comprises a matrix material (56) containing a plurality of voids (58), each void containing a plurality of un-bonded particles (60), each particle comprising vibration damping material. The matrix material may be ceramic such as yttria stabilised zirconia or magnesium aluminate spinel, metal such as aluminium, aluminium alloy, titanium, or titanium alloy or polymer such as polyurethane or polyester. The vibration damping material may be magnesium aluminate spinel. The component may comprise a metal substrate such as titanium alloy, nickel alloy, steel or cobalt alloy. The vibration damping coating may be applied by spraying e.g. thermal or plasma spraying or HVOF a matrix material containing composite particles comprising a plurality of particles bound together by organic binder and heating to remove the binder. The composite particles may comprise a cladding such as metal surrounding the plurality of particles. The vibration coating is suitable for use on static components of gas turbine engines such as vanes.

Description

A VIBRATION DAMPING COATING
The present invention relates to a vibration damping coating, in particular to a vibration damping coating for a component of a gas turbine engine more particularly for a rotor blade, or a stator vane, of a turbofan gas turbine engine.
The rotor blades and stator vanes of a gas turbine engine are subject to vibrations which reduce the fatigue ]0 life of the rotor blade, or stator vane, and which may lead to premature cracking of the rotor blade, or stator vane, if the amplitude of vibration is sufficiently large.
It is known to use a variety of means to damp vibrations in gas turbine engine components, rotor blades, ]5 stator vanes, combustion chambers, ducts etc. to reduce any adverse effects of the vibrations.
It is known from UK patent GB1369558 to provide a vibration damping coating for a rotor blade comprising an outer layer comprising magnesium aluminate or zirconium dioxide and an inner layer comprising a mixture of magnesium aluminate or zirconium dioxide and the metal of the substrate of the rotor blade.
It is also known from our published European patent application EP1098069A2 to provide a vibration damper for a combustion chamber comprising a body having a chamber filled with particles and the body is secured to the combustion chamber. It is not always practical to provide the particle filled body on a component.
Improved vibration damping of the components is required.
Accordingly the present invention seeks to provide a novel vibration damping coating.
Accordingly the present invention provides a component, a vibration damping coating on the component, the vibration damping coating comprising a matrix material containing a plurality of voids, each void containing a plurality of un-bonded particles, each particle comprising a vibration damping material.
Preferably the matrix material comprises a ceramic, a metal or a polymer.
The ceramic may comprise yttria-stabilised zirconia or magnesium aluminate.
Preferably the vibration damping material comprises magnesium aluminate.
Preferably the component comprises a metal substrate.
Preferably the metal substrate comprises a titanium alloy, a nickel alloy, steel or a cobalt alloy.
Preferably the component comprises a stator vane.
Preferably the stator vane comprises a fan outlet guide vane, a compressor vane or a turbine vane.
The present invention also provides a method of applying a vibration damping coating to a component, the method comprising applying a matrix material containing a plurality of composite particles to the component, each composite particle comprising a plurality of particles, each particle comprising a vibration damping material.
The composite particles may comprise a plurality of particles bonded together by an organic binder, the method comprising heating the vibration damping coating to remove the binder to form a plurality of voids in the matrix material and each void is filled with a plurality of un bonded particles.
Preferably each composite particle comprises a cladding surrounding the plurality of particles.
Preferably the cladding comprises a metal.
Preferably the matrix material and composite particles are applied to the component by spraying.
Preferably the spraying comprises thermal spraying, plasma spraying, vacuum plasma spraying, air plasma spraying or HVOF.
Preferably the matrix material comprises a ceramic, a metal or a polymer.
The ceramic may comprise yttria-stabilised zirconia or magnesium aluminate.
Preferably the vibration damping material comprises magnesium aluminate.
Preferably the component comprises a metal substrate.
Preferably the metal substrate comprises a titanium alloy, a nickel alloy, steel or a cobalt alloy.
Preferably the component comprises a stator vane.
Preferably the stator vane comprises a fan outlet guide vane, a compressor vane or a turbine vane.
The present invention will be more fully described by way of example with reference to the accompanying drawings in which: Figure 1 is a partially cut away view of a turbofan l5 gas turbine engine including a fan outlet guide vane having a vibration damping coating according to the present invention.
Figure 2 is an enlarged view of the fan outlet guide vane shown in figure 1.
Figure 3 is an enlarged cross-sectional view through a portion of the fan outlet guide and the vibration damping shown in figure 2.
Figure 4 is a further enlarged view of a composite particle shown in figure 3.
Figure 5 is a further enlarged view of an alternative composite particle shown in figure 3.
Figure 6 is a further enlarged view of an alternative composite particle shown in figure 3.
A turbofan gas turbine engine 10, as shown in figure 1, comprises in axial flow series an intake 12, a fan section 14, a compressor section 16, a combustion section 18, a turbine section 20 and an exhaust 22. The turbine section 20 comprises one or more turbines (not shown) arranged to drive one or more compressors (not shown) in the compressor section 16 via one or more shafts (not shown). The turbine section 20 also comprises one or more turbine (not shown) to drive a fan rotor 24 via a shaft (not shown). The fan section 14 comprises a fan rotor 24 carrying a plurality of circumferentially spaced radially outwardly extending fan blades 26. The fan rotor 24 and fan blades 26 are surrounded by a fan casing 28 and the fan casing 28 partially defines a fan duct 30, which has an exhaust 32 at its axially downstream end. The fan casing 28 is secured to a core engine casing 34 by a plurality of circumferentially spaced fan outlet guide vanes 36, which extend between and are secured to the fan casing 28 and the core engine casing 34.
The fan outlet guide vanes 36 suffer from vibration in operation of the turbofan gas turbine engine 10. The fan outlet guide vanes 36 comprise an aerofoil portion 40, a radially inner end 42 and a radially outer end 44. The radially inner end 42 of the fan outlet guide vane 36 is secured to the core engine casing 34 and the radially outer end 44 of the fan outlet guide vane 36 is secured to the fan casing 28. The aerofoil portion 40 of the fan outlet guide vane 36 has a leading edge 46, a trailing edge 48, a concave pressure surface 50 extending from the leading edge 46 to the trailing edge 48 and a convex suction surface 52 extending from the leading edge 46 to the trailing edge 48, as shown in figure 2. The fan outlet guide vane 36 generally comprises a titanium alloy.
The aerofoil portion 40 of the fan outlet guide vane 36 is provided with a vibration damping coating 54.
Preferably the vibration damping coating 54 is provided on all of the concave pressure surface 50 and on all the convex suction surface 52 of the fan outlet guide vane 36.
However, it may be possible to provide the vibration damping coating 54 on any suitable portion of the surfaces and 52. The vibration damping coating 54, as shown in figure 3 and 4, comprises a matrix material 56 and a plurality of voids 58 in the matrix material 56. Each void 58 contains a plurality of un-bonded particles 60 and each particle 60 consists of a vibration damping material. The matrix material 56 comprises a metal, a ceramic or a polymer. The vibration damping material consists of magnesium aluminate spinet or other suitable vibration damping materials. The metal matrix material may for example comprise aluminium, an aluminium alloy, titanium or a titanium alloy, the ceramic matrix material may comprise yttria stabilized zirconia or magnesium aluminate spinel and the polymer matrix material may comprise polyurethane or polyster.
In operation vibrations of the fan outlet guide vane 36 are damped by the movement of the particle 60 within the voids 58 in the matrix material 56 of the vibration damping coating 54.
The vibration damping coating 54 is applied to the surfaces 50 and 52 of the fan outlet guide vane 36 by spraying, for example thermal spraying, plasma spraying, vacuum plasma spraying, air plasma spraying or HVOF.
The matrix material 56 together with composite particles 62 comprising a plurality of particles 60 bonded together by an organic binder 64, as shown in figure 4, or composite particles 66 comprising a cladding 68 surrounding a plurality of particles 60, as shown in figure 5, or composite particles 70 comprising a plurality of particles bonded together by an organic binder 64 and a cladding 68 surrounding the plurality of particles 60 bonded together by the organic binder 64, as shown in figure 6, are sprayed onto the appropriate surfaces of the fan outlet guide vane 36. The cladding 68 may be a metal or a ceramic and the cladding 68 is used to protect the organic binder 64 during the spraying process. In the case of the organic matrix material a different process of application may be used for example brushing etc. In the case of the composite particles 62, 70 with organic binder 64 the vibration damping coating 54 is subsequently heated at an appropriate temperature to remove, burn out, the organic binder 64 to form the voids 58 and to de-bond the particles 60.
The vibration damping coating 54 may have a thickness in the range of 200pm to 500pm. The particles 60 have dimensions of 2m to lOpm and the composite particles 62 have dimensions of 50pm to lOOpm.
Preferably the matrix 56 comprises a vibration damping material. Preferably the vibration damping coating is a combination of a magnesium aluminate matrix 56 and magnesium aluminate particles 60.
The present invention is particularly applicable to damping of vibrations of stationary components, it is believed that the present invention may not be as beneficial for damping of vibrations in rotary component because the particles may be centrifuged outwardly and provide less vibration damping. However the present invention may be used on compressor vanes, turbine vanes, compressor casings, turbine casings, combustor casings etc. If the matrix material is a ceramic material it may be used on turbine vanes, turbine casings and combustion casings to additionally provide a thermal barrier.
The turbine vanes and combustion casings generally comprise nickel alloys or cobalt alloys.
The compressor vanes and compressor casings generally comprise nickel alloys, steel alloys or titanium alloys.

Claims (24)

  1. Claims: 1. A component, a vibration damping coating on the component, the
    vibration damping coating comprising a matrix material containing a plurality of voids, each void containing a plurality of un-bonded particles, each particle comprising a vibration damping material.
  2. 2. A component as claimed in claim 1 wherein the matrix material comprises a ceramic, a metal or a polymer.
  3. 3. A component as claimed in claim 1 or claim 2 wherein the ceramic comprises yttria-stabilised zirconia or magnesium aluminate.
  4. 4. A component as claimed in any of claims 1 to 3 wherein the vibration damping material comprises magnesium aluminate.
  5. 5. A component as claimed in any of claims 1 to 4 wherein the component comprises a metal substrate.
  6. 6. A component as claimed in claim 5 wherein the metal substrate comprises a titanium alloy, a nickel alloy, steel or a cobalt alloy.
  7. 7. A component as claimed in any of claims 1 to 6 wherein the component comprises a stator vane.
  8. 8. A component as claimed in claim 7 wherein the stator vane comprises a fan outlet guide vane, a compressor vane or a turbine vane.
  9. 9. A method of applying a vibration damping coating to a component, the method comprising applying a matrix material containing a plurality of composite particles to the component, each composite particle comprising a plurality of particles, each particle comprising a vibration damping material.
  10. 10. A method as claimed in claim 9 wherein the composite particles may comprise a plurality of particles bonded together by an organic binder, the method comprising heating the vibration damping coating to remove the binder to form a plurality of voids in the matrix material and each void is filled with a plurality of un-bonded particles.
  11. 11. A method as claimed in claim 10 or claim 11 wherein each composite particle comprises a cladding surrounding the plurality of particles.
  12. 12. A method as claimed in claim 11 wherein the cladding comprises a metal.
  13. 13. A method as claimed in any of claims 9 to 12 wherein the matrix material and composite particles are applied to l0 the component by spraying.
  14. 14. A method as claimed in claim 13 wherein the spraying comprises thermal spraying, plasma spraying, vacuum plasma spraying, air plasma spraying or HVOF.
  15. 15. A method as claimed in any of claims 9 to 14 wherein Is the matrix material comprises a ceramic, a metal or a polymer.
  16. 16. A method as claimed in claim 15 wherein the ceramic comprises yttriastabilised zirconia.
  17. 17. A method as claimed in any of claims 9 to 16 wherein the vibration damping material comprises magnesium aluminate.
  18. 18. A method as claimed in any of claims 9 to 17 wherein the component comprises a metal substrate.
  19. 19. A method as claimed in claim 18 wherein the metal substrate comprises a titanium alloy, a nickel alloy, steel or a cobalt alloy.
  20. 20. A method as claimed in any of claims 9 to 19 wherein the component comprises a stator vane.
  21. 21. A method as claimed in claim 20 wherein the stator vane comprises a fan outlet guide vane, a compressor vane or a turbine vane.
  22. 22. A component having a vibration damping coating substantially as hereinbefore described with reference to and as shown in figures 2 to 3 of the accompanying drawings.
  23. 23. A gas turbine engine having a component as claimed in any of claims 1 to 8 and 22.
  24. 24. A method of applying a vibration damping coating substantially as hereinbefore described with reference to figures 3 to 6.
GB0325069A 2003-10-28 2003-10-28 A vibration damping coating Withdrawn GB2407523A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB0325069A GB2407523A (en) 2003-10-28 2003-10-28 A vibration damping coating

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB0325069A GB2407523A (en) 2003-10-28 2003-10-28 A vibration damping coating

Publications (2)

Publication Number Publication Date
GB0325069D0 GB0325069D0 (en) 2003-12-03
GB2407523A true GB2407523A (en) 2005-05-04

Family

ID=29725459

Family Applications (1)

Application Number Title Priority Date Filing Date
GB0325069A Withdrawn GB2407523A (en) 2003-10-28 2003-10-28 A vibration damping coating

Country Status (1)

Country Link
GB (1) GB2407523A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2430985A (en) * 2005-10-06 2007-04-11 Gen Electric Vibration damper coating for a fan blade
US7445685B2 (en) * 2004-03-23 2008-11-04 Rolls-Royce Plc Article having a vibration damping coating and a method of applying a vibration damping coating to an article
WO2013034583A1 (en) 2011-09-06 2013-03-14 Vita Zahnfabrik H. Rauter Gmbh & Co. Kg Process for preparing ceramic implants for medical purposes
WO2014143266A1 (en) 2013-03-15 2014-09-18 United Technologies Corporation Turbine engine component with vibration damping

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB893787A (en) * 1959-07-03 1962-04-11 United Aircraft Corp Improvements relating to damped bodies and methods of manufacturing them
FR2501749A1 (en) * 1981-03-13 1982-09-17 Gadde V Sound absorbing mat or sheet - includes layer of cellular polymer filled with heavy metal or mineral powder and bonded to flexible substrate
JPH0839596A (en) * 1994-07-28 1996-02-13 Matsushita Electric Works Ltd Sound absorbing material and manufacture thereof
JPH09226035A (en) * 1996-02-27 1997-09-02 Agency Of Ind Science & Technol Sound insulating board and its manufacture
JPH10121598A (en) * 1996-10-16 1998-05-12 Matsushita Electric Works Ltd Sound absorption material and its manufacture

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB893787A (en) * 1959-07-03 1962-04-11 United Aircraft Corp Improvements relating to damped bodies and methods of manufacturing them
FR2501749A1 (en) * 1981-03-13 1982-09-17 Gadde V Sound absorbing mat or sheet - includes layer of cellular polymer filled with heavy metal or mineral powder and bonded to flexible substrate
JPH0839596A (en) * 1994-07-28 1996-02-13 Matsushita Electric Works Ltd Sound absorbing material and manufacture thereof
JPH09226035A (en) * 1996-02-27 1997-09-02 Agency Of Ind Science & Technol Sound insulating board and its manufacture
JPH10121598A (en) * 1996-10-16 1998-05-12 Matsushita Electric Works Ltd Sound absorption material and its manufacture

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7445685B2 (en) * 2004-03-23 2008-11-04 Rolls-Royce Plc Article having a vibration damping coating and a method of applying a vibration damping coating to an article
US8007244B2 (en) 2004-03-23 2011-08-30 Rolls-Royce Plc Article having a vibration damping coating and a method of applying a vibration damping coating to an article
GB2430985A (en) * 2005-10-06 2007-04-11 Gen Electric Vibration damper coating for a fan blade
US7360997B2 (en) 2005-10-06 2008-04-22 General Electric Company Vibration damper coating
GB2430985B (en) * 2005-10-06 2011-05-18 Gen Electric Vibration damper coating
WO2013034583A1 (en) 2011-09-06 2013-03-14 Vita Zahnfabrik H. Rauter Gmbh & Co. Kg Process for preparing ceramic implants for medical purposes
US9241795B2 (en) 2011-09-06 2016-01-26 Vita Zahnfabrik H. Rauter Gmbh & Co. Process for preparing ceramic implants for medical purposes
WO2014143266A1 (en) 2013-03-15 2014-09-18 United Technologies Corporation Turbine engine component with vibration damping
EP2971536A4 (en) * 2013-03-15 2016-11-02 United Technologies Corp Turbine engine component with vibration damping
US10167733B2 (en) 2013-03-15 2019-01-01 United Technologies Corporation Turbine engine component with vibration damping
US20190383164A1 (en) * 2013-03-15 2019-12-19 United Technologies Corporation Turbine engine component with vibration damping
US10711638B2 (en) 2013-03-15 2020-07-14 Raytheon Technologies Corporation Turbine engine component with vibration damping

Also Published As

Publication number Publication date
GB0325069D0 (en) 2003-12-03

Similar Documents

Publication Publication Date Title
US10392958B2 (en) Hybrid blade outer air seal for gas turbine engine
CA2899395C (en) Abradable composition and seal of an axial-flow turbomachine compressor casing
EP2196632A2 (en) A seal in a gas turbine and a method of manufacturing a seal
EP2573326A1 (en) Airfoil tip air seal assembly
EP2904216B1 (en) Aluminum based abradable material with reduced metal transfer to blades
MX2015006730A (en) Seal systems for use in turbomachines and methods of fabricating the same.
EP3081764A1 (en) Variable coating porosity to influence shroud and rotor durability
EP2481890A2 (en) Seal in a gas turbine engine component having a coating with abradability proportional to interaction rate
EP2196631A2 (en) A component having an abrasive layer and a method of applying an abrasive layer on a component
US20200191005A1 (en) Seal segment for shroud ring of a gas turbine engine
EP2540868B1 (en) Spall resistant abradable turbine air seal
JP7349778B2 (en) Abradable seal composition for turbomachinery compressors
CA3050170A1 (en) Coating and method of applying a coating for an aerofoil of a gas turbine engine
CN107091124B (en) System and method for simultaneously depositing multiple coatings on a turbine blade
US10458254B2 (en) Abradable coating composition for compressor blade and methods for forming the same
GB2407523A (en) A vibration damping coating
Mohammad et al. Criteria for abradable coatings to enhance the performance of gas turbine engines
US10544699B2 (en) System and method for minimizing the turbine blade to vane platform overlap gap
EP3626850B1 (en) Bond coat for spallation resistant ceramic coating
US20210087936A1 (en) Detuned turbine blade tip shrouds
US20230235680A1 (en) Non-uniform turbomachinery blade tips for frequency tuning
US11428105B2 (en) Airfoil with integral platform for gas turbine engines
CN116892422A (en) Yttria-stabilized zirconia slurry and method of applying same
EP3604738A1 (en) Laser tip cladding to net-shape with backing elements
US20180135638A1 (en) Ceramic coating composition for compressor casing and methods for forming the same

Legal Events

Date Code Title Description
WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)