US2689107A - Vibration damper for blades and vanes - Google Patents

Vibration damper for blades and vanes Download PDF

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Publication number
US2689107A
US2689107A US110065A US11006549A US2689107A US 2689107 A US2689107 A US 2689107A US 110065 A US110065 A US 110065A US 11006549 A US11006549 A US 11006549A US 2689107 A US2689107 A US 2689107A
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US
United States
Prior art keywords
vane
opening
blade
strip
blades
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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.)
Expired - Lifetime
Application number
US110065A
Inventor
Eugene A Odegaard
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Raytheon Technologies Corp
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United Aircraft Corp
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Priority to US110065A priority Critical patent/US2689107A/en
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Publication of US2689107A publication Critical patent/US2689107A/en
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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
    • 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
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/182—Two-dimensional patterned crenellated, notched
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Definitions

  • This invention relates to dempers for blades or vanes as used in compressors or turbines or other aerodynamic devices such as fans and propellers.
  • a feature of this invention is a damper of the frictlonal type and particularly one which is effective without changing the external contours of the blade or vane.
  • a feature of this invention is a damper adapted for use with many types of hollow blades or vanes without the necessity for modification of the vane structure.
  • Another feature is a damper which will fit within a hollow blade or vane and in engagement with the side walls thereof for frictional damping.
  • One feature is a frictional damper means for rotary devices so arranged that the damping effect is increased as the speed of the rotor carrying the vane increases.
  • Fig. l is a transverse sectional view through a blade showing one form of the invention.
  • Fig. 2 is a sectional view at right angles to Fig. l.
  • Fig. 3 is a sectional view similar to Fig. 2 showing a modification.
  • Fig. 4 is a sectional view substantially on the line 4-4 of Fig. 2.
  • the blade 2 has a root section 4 adapted to t in a similarly shaped axial slot in a disc 6.
  • the effective blade section 8 of the turbine blade extends radially outward from the root and is hollow having a centrally located opening I extending from the outer end of the blade inwardly toward the root section.
  • the blade section 8, as shown in Fig. 4, is approximately airfoil in shape and the opening I0 may be approximately the same shape being defined between spaced substantially parallel walls I2 and I4 making up the inner and outer blade surfaces. In the arrangement shown, the opposite walls of the opening I0 are substantially parallel and the walls I2 and I4 may become thinner toward the tip of the turbine blade.
  • the strip I 6 is supported adjacent to or at itstip end within the opening IIJ, the arrangement shown for supporting this strip being a, cap or shroud piece 20 for the tip of the turbine blade ⁇ which is attached as by brazing or welding 22 tov close the tip end of the opening I0 within the blade.
  • the blade When the rotor is in operation, the blade may begin to vibrate in the plane of the disc B andi such'vibration is effectively damped by the frictional contact between the lands I8 of the resilient strip I B and the cooperating surfaces of the opening I 0.
  • thel centrifugal force acting on the strip I6 tends to move the strip radially outward thereby increasing the contact pressure between the lands I 8 andthe associated blade'structure so that the damper? becomes more effective at higher speeds.
  • no revision of the hollow blade structure is necessary for use of the blade damper since it can be inserted without modification of the blade and requires only the Welding of the cap 20 to the tip of the blade to hold the damper in position.
  • the damper may be a single flexible strip as in Figs. 1 and 2 in which case the width of the strip is selected to give the required amount of damping.
  • the damping device may be made up of a series of relatively narrow strips 24, as shown in Fig. 3, in which event the strips may all be integral at the tip end where they are attached to the cap 20A. In either event, for most effective damping, it will be noted that the damper is preferably arranged to fill as nearly as possible the available space within the hollow blade. It will be understood that the particular blade configuration shown is merely by way of example and that many other types of hollow blades may have a damper of the type above described applied thereto.
  • a hollow metallic vane of airfoil cross section having interior walls defining a longitudinally extending opening therein, the chordal dimension of the opening being less than the chordal dimension of the vane, at least one resilient metallic strip mounted within said opening and extending longitudinally of the vane, said strip being of sinuous form and having longitudinally spaced lands extending in a chordal direction, said lands engaging opposite walls of said opening and being free of connection withsaid walls so as to be capable of longitudinal motion with respect to said vane, said strip providing friction damping when the vane vibrates.
  • a hollow metallic vane of airfoil cross section said vane having a root and a tip and interior walls defining a longitudinally extending opening therein, the chordal dimension of the opening being less than the chordal dimension of the vane, at least one resilient metallic strip mounted Within said opening and extending longitudinally of the vane, said strip being of sinuous form and having longitudinally spaced lands extending in a chordal direction, said lands engaging opposite walls of said opening and being free of connection with said walls so as to be capable of longitudinal motion with respect to said vane, the root end of said strip being unrestrained against longitudinal movement,- and means limiting longitudinal movement of the tip end of said strip away from said vane root, said strip providing friction damping when the vane vibrates.
  • a hollow metallic vane of airfoil cross section having interior Walls defining a longitudinally extending opening therein, the chordal dimension of the opening being less than the chordal dimension of the vane, a plurality-of resilient metallic strips mounted in side-by-side relation within said opening and extending longitudinally of the vane, said strips being of sinuous form and having longitudinally spaced lands extending in a chordal direction, said lands engaging opposite walls of said opening and being free of connection with said walls so as to be capable of longitudinal motion with respect to said vane, and means joining the tip end of said strips to position said strips Within said opening, said strips providing friction damping when the vane vibrates.
  • a hollow metallic vane of aix-toil cross section said vane having a root and a tip and interior Walls defining a longitudinally extending opening therein, the chordal dimension of the opening being less than the chordal dimension of the vane, a plurality of resilient metallic strips mounted Within said opening and extending longitudinally of the vane, said strips being of sinuous form and having longitudinally spaced lands extending in a chordal direction, said lands engaging opposite Walls of said opening and being free of connection with said walls so as to be capable of longitudinal motion with respect to said vane, the tip end of said strips being connected together, and means limiting longitudinal movement of the connected ends away from said vvane root, said strips providing friction damping when the vane vibrates.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Sept 14, 1954 E. A. ODEGAARD VIBRATION DAMPER FOR BLADES AND VNES Filed Aug. l5, 1949 INVENTOR. Eagezye a7. delgazi cH aweg www Patented Sept, 14, 1954 UNITED STATES PATENT OFFICE Eugene A. Odegaard, East Hartford, Conn., as-
sgnor to United Aircraft Corporation, East Hartford, Conn., a corporation of Delaware Application August 13, 1949, Serial No. 110,065
4 Claims.
l This invention relates to dempers for blades or vanes as used in compressors or turbines or other aerodynamic devices such as fans and propellers.
The damping of vibrations in blades or vanes, particularly in the moving vanes in high speed rotors in compressors" and turbines, is frequently necessary to prevent excessive strains resulting from such vibrations. Inertia type dampers have been proposed for this purpose but the increase in weight is detrimental in many installations. A feature of this invention is a damper of the frictlonal type and particularly one which is effective without changing the external contours of the blade or vane.
Particularly in gas turbine power plants there is a trend toward hollow blades or vanes because of cooling problems as well as stress and weight problems. A feature of this invention is a damper adapted for use with many types of hollow blades or vanes without the necessity for modification of the vane structure. Another feature is a damper which will fit within a hollow blade or vane and in engagement with the side walls thereof for frictional damping. One feature is a frictional damper means for rotary devices so arranged that the damping effect is increased as the speed of the rotor carrying the vane increases.
Other objects and advantages will be apparent from the specification and claims, and from the accompanying drawing which illustrates an embodiment of the invention.
Fig. l is a transverse sectional view through a blade showing one form of the invention.
Fig. 2 is a sectional view at right angles to Fig. l.
Fig. 3 is a sectional view similar to Fig. 2 showing a modification.
Fig. 4 is a sectional view substantially on the line 4-4 of Fig. 2.
With reference to the drawing, in which the invention is shown as applied to the blade of a rotor, the blade 2 has a root section 4 adapted to t in a similarly shaped axial slot in a disc 6. The effective blade section 8 of the turbine blade extends radially outward from the root and is hollow having a centrally located opening I extending from the outer end of the blade inwardly toward the root section. The blade section 8, as shown in Fig. 4, is approximately airfoil in shape and the opening I0 may be approximately the same shape being defined between spaced substantially parallel walls I2 and I4 making up the inner and outer blade surfaces. In the arrangement shown, the opposite walls of the opening I0 are substantially parallel and the walls I2 and I4 may become thinner toward the tip of the turbine blade.
I0. f The strip I 6 is supported adjacent to or at itstip end within the opening IIJ, the arrangement shown for supporting this strip being a, cap or shroud piece 20 for the tip of the turbine blade` which is attached as by brazing or welding 22 tov close the tip end of the opening I0 within the blade.
When the rotor is in operation, the blade may begin to vibrate in the plane of the disc B andi such'vibration is effectively damped by the frictional contact between the lands I8 of the resilient strip I B and the cooperating surfaces of the opening I 0. As the rotor speed increases, thel centrifugal force acting on the strip I6 tends to move the strip radially outward thereby increasing the contact pressure between the lands I 8 andthe associated blade'structure so that the damper? becomes more effective at higher speeds. It will be noted that no revision of the hollow blade structure is necessary for use of the blade damper since it can be inserted without modification of the blade and requires only the Welding of the cap 20 to the tip of the blade to hold the damper in position.
The damper may be a single flexible strip as in Figs. 1 and 2 in which case the width of the strip is selected to give the required amount of damping. Instead of a single strip, the damping device may be made up of a series of relatively narrow strips 24, as shown in Fig. 3, in which event the strips may all be integral at the tip end where they are attached to the cap 20A. In either event, for most effective damping, it will be noted that the damper is preferably arranged to fill as nearly as possible the available space within the hollow blade. It will be understood that the particular blade configuration shown is merely by way of example and that many other types of hollow blades may have a damper of the type above described applied thereto.
It is to be understood that the invention is not limited to the specific embodiment herein illustrated and described, but may be used in other ways without departure from its spirit as defined by the following claims.
I claim:
1. In a vane construction, a hollow metallic vane of airfoil cross section having interior walls defining a longitudinally extending opening therein, the chordal dimension of the opening being less than the chordal dimension of the vane, at least one resilient metallic strip mounted within said opening and extending longitudinally of the vane, said strip being of sinuous form and having longitudinally spaced lands extending in a chordal direction, said lands engaging opposite walls of said opening and being free of connection withsaid walls so as to be capable of longitudinal motion with respect to said vane, said strip providing friction damping when the vane vibrates.
2. In a vane construction, a hollow metallic vane of airfoil cross section, said vane having a root and a tip and interior walls defining a longitudinally extending opening therein, the chordal dimension of the opening being less than the chordal dimension of the vane, at least one resilient metallic strip mounted Within said opening and extending longitudinally of the vane, said strip being of sinuous form and having longitudinally spaced lands extending in a chordal direction, said lands engaging opposite walls of said opening and being free of connection with said walls so as to be capable of longitudinal motion with respect to said vane, the root end of said strip being unrestrained against longitudinal movement,- and means limiting longitudinal movement of the tip end of said strip away from said vane root, said strip providing friction damping when the vane vibrates.
1 3. In a ,vane construction, a hollow metallic vane of airfoil cross section having interior Walls defining a longitudinally extending opening therein, the chordal dimension of the opening being less than the chordal dimension of the vane, a plurality-of resilient metallic strips mounted in side-by-side relation within said opening and extending longitudinally of the vane, said strips being of sinuous form and having longitudinally spaced lands extending in a chordal direction, said lands engaging opposite walls of said opening and being free of connection with said walls so as to be capable of longitudinal motion with respect to said vane, and means joining the tip end of said strips to position said strips Within said opening, said strips providing friction damping when the vane vibrates.
4. In a vane construction, a hollow metallic vane of aix-toil cross section, said vane having a root and a tip and interior Walls defining a longitudinally extending opening therein, the chordal dimension of the opening being less than the chordal dimension of the vane, a plurality of resilient metallic strips mounted Within said opening and extending longitudinally of the vane, said strips being of sinuous form and having longitudinally spaced lands extending in a chordal direction, said lands engaging opposite Walls of said opening and being free of connection with said walls so as to be capable of longitudinal motion with respect to said vane, the tip end of said strips being connected together, and means limiting longitudinal movement of the connected ends away from said vvane root, said strips providing friction damping when the vane vibrates.
References Cited in the file of this patent UNITED STATES PATENTS Number Name Date 925,031 Russel June 15, 1909 y1,363,692 Summers Dec. 28, 1920 1,434,414 Stoney Nov. 7, 1922 1,765,079 Landis June 17, 1930 1,833,754 Paget Nov. 24, 1931 FOREIGN PATENTS Number Country Date 438,036 Great Britain Nov. 11. 1935 602,530 Great Britain May 28, 1948 891,635 France Dec. 11, 1943
US110065A 1949-08-13 1949-08-13 Vibration damper for blades and vanes Expired - Lifetime US2689107A (en)

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Cited By (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2828941A (en) * 1952-12-24 1958-04-01 United Aircraft Corp Blade damping means
US2862686A (en) * 1954-08-19 1958-12-02 Thompson Prod Inc Hollow vane with internal vibration dampener
US2920868A (en) * 1955-10-05 1960-01-12 Westinghouse Electric Corp Dampened blade structure
US4460314A (en) * 1980-12-29 1984-07-17 Rolls-Royce Limited Vibration damped rotor blades for turbomachines
US5056738A (en) * 1989-09-07 1991-10-15 General Electric Company Damper assembly for a strut in a jet propulsion engine
US5165860A (en) * 1991-05-20 1992-11-24 United Technologies Corporation Damped airfoil blade
US5232344A (en) * 1992-01-17 1993-08-03 United Technologies Corporation Internally damped blades
WO1994017303A1 (en) * 1992-11-05 1994-08-04 Bonus Energy A/S Windmill blade
US5407321A (en) * 1993-11-29 1995-04-18 United Technologies Corporation Damping means for hollow stator vane airfoils
US5498137A (en) * 1995-02-17 1996-03-12 United Technologies Corporation Turbine engine rotor blade vibration damping device
WO1999043955A1 (en) * 1998-02-24 1999-09-02 Lm Glasfiber A/S Wind turbine blade
US6283707B1 (en) * 1999-03-19 2001-09-04 Rolls-Royce Plc Aerofoil blade damper
US20050265843A1 (en) * 2004-05-27 2005-12-01 United Technologies Corporation Rotor blade with a stick damper
US7413405B2 (en) 2005-06-14 2008-08-19 General Electric Company Bipedal damper turbine blade
US20080253898A1 (en) * 2007-04-10 2008-10-16 Randall Charles Bauer Damper configured turbine blade
US20080313899A1 (en) * 2007-06-25 2008-12-25 Randall Charles Bauer Bimaterial turbine blade damper
US20100014980A1 (en) * 2006-05-31 2010-01-21 Katharina Bergander Turbine blade
US20110070085A1 (en) * 2009-09-21 2011-03-24 El-Aini Yehia M Internally damped blade
US8262363B2 (en) 2008-03-17 2012-09-11 General Electric Company Blade having a damping element and method of fabricating same
US20130243587A1 (en) * 2010-12-22 2013-09-19 Hiroyuki Yamashita Turbine vane of steam turbine and steam turbine
US20130280045A1 (en) * 2012-04-24 2013-10-24 Gregory M. Dolansky Airfoil including damper member
JP2015148287A (en) * 2014-02-06 2015-08-20 三菱日立パワーシステムズ株式会社 Liquid damper and rotary machine blade including the same
US9121288B2 (en) 2012-05-04 2015-09-01 Siemens Energy, Inc. Turbine blade with tuned damping structure
EP2966262A1 (en) * 2014-07-11 2016-01-13 MTU Aero Engines GmbH Turbomachine blade
US20160024940A1 (en) * 2013-03-14 2016-01-28 United Technologies Corporation Fan Blade Damping Device
US20160341221A1 (en) * 2014-01-24 2016-11-24 United Technologies Corporation Additive manufacturing process grown integrated torsional damper mechanism in gas turbine engine blade
EP2466072A3 (en) * 2010-12-16 2016-12-21 Howden Axial Fans AB Axial air movement fans
RU2629309C2 (en) * 2016-02-01 2017-08-28 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Ульяновский государственный технический университет" Gas turbine engine
RU2695513C2 (en) * 2017-06-06 2019-07-24 ФЕДЕРАЛЬНОЕ ГОСУДАРСТВЕННОЕ БЮДЖЕТНОЕ ОБРАЗОВАТЕЛЬНОЕ УЧРЕЖДЕНИЕ ВЫСШЕГО ОБРАЗОВАНИЯ "Брянский государственный технический университет" Device for damping vibrations of cooled blades of gas turbine engines
US10724376B2 (en) * 2018-02-08 2020-07-28 General Electric Company Airfoil having integral fins
US11143036B1 (en) * 2020-08-20 2021-10-12 General Electric Company Turbine blade with friction and impact vibration damping elements
US20220213794A1 (en) * 2021-01-07 2022-07-07 General Electric Company Inner shroud damper for vibration reduction
US11536144B2 (en) 2020-09-30 2022-12-27 General Electric Company Rotor blade damping structures
US11739645B2 (en) 2020-09-30 2023-08-29 General Electric Company Vibrational dampening elements
US11808166B1 (en) * 2021-08-19 2023-11-07 United States Of America As Represented By The Administrator Of Nasa Additively manufactured bladed-disk having blades with integral tuned mass absorbers
RU225855U1 (en) * 2024-02-29 2024-05-13 федеральное государственное бюджетное образовательное учреждение высшего образования "Ульяновский государственный технический университет" Nozzle blade of a gas turbine engine with vibration damping system

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US925031A (en) * 1908-04-27 1909-06-15 Joseph Russel Fan.
US1363692A (en) * 1917-10-23 1920-12-28 Edgar W Summers Aeroplane-propeller
US1434414A (en) * 1921-05-14 1922-11-07 Stoney George Gerald Prevention or reduction of vibration in rotating bodies
US1765079A (en) * 1929-12-13 1930-06-17 Harry G Landis Metal aeroplane wing
US1833754A (en) * 1930-08-22 1931-11-24 Gen Electric Vibration damping by impact
GB438036A (en) * 1934-05-09 1935-11-11 Federated Engineers Ltd Improvements in blowers and the like
FR891635A (en) * 1942-02-04 1944-03-13 Bmw Flugmotorenbau Gmbh Internally cooled turbine blade
GB602530A (en) * 1945-10-16 1948-05-28 Bristol Aeroplane Co Ltd Improvements in or relating to gas turbines

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US925031A (en) * 1908-04-27 1909-06-15 Joseph Russel Fan.
US1363692A (en) * 1917-10-23 1920-12-28 Edgar W Summers Aeroplane-propeller
US1434414A (en) * 1921-05-14 1922-11-07 Stoney George Gerald Prevention or reduction of vibration in rotating bodies
US1765079A (en) * 1929-12-13 1930-06-17 Harry G Landis Metal aeroplane wing
US1833754A (en) * 1930-08-22 1931-11-24 Gen Electric Vibration damping by impact
GB438036A (en) * 1934-05-09 1935-11-11 Federated Engineers Ltd Improvements in blowers and the like
FR891635A (en) * 1942-02-04 1944-03-13 Bmw Flugmotorenbau Gmbh Internally cooled turbine blade
GB602530A (en) * 1945-10-16 1948-05-28 Bristol Aeroplane Co Ltd Improvements in or relating to gas turbines

Cited By (52)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2828941A (en) * 1952-12-24 1958-04-01 United Aircraft Corp Blade damping means
US2862686A (en) * 1954-08-19 1958-12-02 Thompson Prod Inc Hollow vane with internal vibration dampener
US2920868A (en) * 1955-10-05 1960-01-12 Westinghouse Electric Corp Dampened blade structure
US4460314A (en) * 1980-12-29 1984-07-17 Rolls-Royce Limited Vibration damped rotor blades for turbomachines
US5056738A (en) * 1989-09-07 1991-10-15 General Electric Company Damper assembly for a strut in a jet propulsion engine
US5165860A (en) * 1991-05-20 1992-11-24 United Technologies Corporation Damped airfoil blade
US5232344A (en) * 1992-01-17 1993-08-03 United Technologies Corporation Internally damped blades
WO1994017303A1 (en) * 1992-11-05 1994-08-04 Bonus Energy A/S Windmill blade
US5407321A (en) * 1993-11-29 1995-04-18 United Technologies Corporation Damping means for hollow stator vane airfoils
US5498137A (en) * 1995-02-17 1996-03-12 United Technologies Corporation Turbine engine rotor blade vibration damping device
EP0727563A2 (en) * 1995-02-17 1996-08-21 United Technologies Corporation Turbine engine rotor blade vibration damping device
EP0727563A3 (en) * 1995-02-17 1998-11-04 United Technologies Corporation Turbine engine rotor blade vibration damping device
WO1999043955A1 (en) * 1998-02-24 1999-09-02 Lm Glasfiber A/S Wind turbine blade
US6283707B1 (en) * 1999-03-19 2001-09-04 Rolls-Royce Plc Aerofoil blade damper
US20050265843A1 (en) * 2004-05-27 2005-12-01 United Technologies Corporation Rotor blade with a stick damper
US7217093B2 (en) * 2004-05-27 2007-05-15 United Technologies Corporation Rotor blade with a stick damper
US7413405B2 (en) 2005-06-14 2008-08-19 General Electric Company Bipedal damper turbine blade
US7832988B2 (en) * 2006-05-31 2010-11-16 Siemens Aktiengesellschaft Turbine blade
US20100014980A1 (en) * 2006-05-31 2010-01-21 Katharina Bergander Turbine blade
US20080253898A1 (en) * 2007-04-10 2008-10-16 Randall Charles Bauer Damper configured turbine blade
US7736124B2 (en) 2007-04-10 2010-06-15 General Electric Company Damper configured turbine blade
US7824158B2 (en) 2007-06-25 2010-11-02 General Electric Company Bimaterial turbine blade damper
US20080313899A1 (en) * 2007-06-25 2008-12-25 Randall Charles Bauer Bimaterial turbine blade damper
US8262363B2 (en) 2008-03-17 2012-09-11 General Electric Company Blade having a damping element and method of fabricating same
US20110070085A1 (en) * 2009-09-21 2011-03-24 El-Aini Yehia M Internally damped blade
US7955054B2 (en) * 2009-09-21 2011-06-07 Pratt & Whitney Rocketdyne, Inc. Internally damped blade
EP2305954A3 (en) * 2009-09-21 2014-06-18 Pratt & Whitney Rocketdyne Inc. Internally damped blade
EP2466072A3 (en) * 2010-12-16 2016-12-21 Howden Axial Fans AB Axial air movement fans
US20130243587A1 (en) * 2010-12-22 2013-09-19 Hiroyuki Yamashita Turbine vane of steam turbine and steam turbine
US9488066B2 (en) * 2010-12-22 2016-11-08 Mitsubishi Hitachi Power Systems, Ltd. Turbine vane of steam turbine and steam turbine
EP2841699A1 (en) * 2012-04-24 2015-03-04 United Technologies Corporation Airfoil including damper member
EP2841699A4 (en) * 2012-04-24 2015-04-29 United Technologies Corp Airfoil including damper member
US8915718B2 (en) * 2012-04-24 2014-12-23 United Technologies Corporation Airfoil including damper member
US20130280045A1 (en) * 2012-04-24 2013-10-24 Gregory M. Dolansky Airfoil including damper member
US9121288B2 (en) 2012-05-04 2015-09-01 Siemens Energy, Inc. Turbine blade with tuned damping structure
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RU225855U1 (en) * 2024-02-29 2024-05-13 федеральное государственное бюджетное образовательное учреждение высшего образования "Ульяновский государственный технический университет" Nozzle blade of a gas turbine engine with vibration damping system

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