US3129921A - Blade damping device - Google Patents

Blade damping device Download PDF

Info

Publication number
US3129921A
US3129921A US207929A US20792962A US3129921A US 3129921 A US3129921 A US 3129921A US 207929 A US207929 A US 207929A US 20792962 A US20792962 A US 20792962A US 3129921 A US3129921 A US 3129921A
Authority
US
United States
Prior art keywords
blade
blades
disc
platform
damper
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.)
Expired - Lifetime
Application number
US207929A
Other languages
English (en)
Inventor
Thornton G Woodwell
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.)
RTX Corp
Original Assignee
United Aircraft Corp
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 United Aircraft Corp filed Critical United Aircraft Corp
Priority to US207929A priority Critical patent/US3129921A/en
Priority to SE7374/63A priority patent/SE305278B/xx
Priority to CH837063A priority patent/CH415691A/de
Priority to DE19631426869 priority patent/DE1426869B2/de
Priority to GB26666/63A priority patent/GB995514A/en
Application granted granted Critical
Publication of US3129921A publication Critical patent/US3129921A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • 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

  • One feature of the invention is a damping device adapted for attachment to one side of a row of compressor or turbine blades. Another feature is a device of this character which becomes increasingly effective with an increase in the speed of the disc carrying the blades.
  • Another feature is a damper which is readily attached to an existing rotor construction without substantial modification of the blades.
  • Another feature is a damper particularly adapted for use with the so-called extended roottype of blade.
  • FIG. 1 is a fragmentary view in elevation of a portion of a rotor incorporating the invention.
  • FIG. 2 is a sectional view substantially along the line 2-2 of FIG. 1.
  • FIG. 3 is a perspective view of a damper element and the adjacent structures.
  • FIG. 4 is a fragmentary sectional view along the line 44 of FIG. 2.
  • FIG. 5 is a sectional view substantially along the line 55 of FIG. 2.
  • the invention is shown in connection with a rotor con struction in which a disc 2 has axial grooves 4 in the periphery to receive the blade root or fastening 6 shown in the shape of a dovetail and located at the inner end of the blade element 8.
  • the blade element includes the dovetail portion 6, a radially projecting root extension 10 extending outwardly from the dovetail portion, an operative blade portion 12 at the outer end of the element, and a blade platform 14 positioned between the root extension and the operative blade portion.
  • the periphery 16 of the disc is spaced radially inward from the platform 14, as best shown in FIG. 1.
  • the plurality of blade elements are thus arranged in a circumferential row in spaced relation to one another and form with the disc a rotor which may be utilized in either a compressor or turbine.
  • the platforms 14 of adjacent blades are in closely spaced relation to one another, as best shown in FIGS. 4 and 5, such that each blade may vibrate circumferentially to some extent, independently of each other blade.
  • the purpose of the present invention is to control the vibratory movement of the individual blades.
  • the blades are retained in position on the periphery of the disc by end plates 18 and 20 attached as by rivets 22 to opposite sides of the disc adjacent the periphery.
  • the disc 18 extends far enough to reach the blade platform and form a closure for the spaces between the root extensions.
  • the plate 249 is especially designed to form a part of the damper structure embodying the present invention, as will appear hereinafter.
  • Each blade is damped by an individual blade damping element 24 which has a base portion 26 having a circumferentially extending surface 28 thereon to engage with the inner surface of a lug 30 on the inside of the plate 20.
  • the surfaces 28 of the several damping elements are all located at the same distance from the center of the disc so that the several lugs 30 form an interrupted cylindrical flange on the inside of the plate 20.
  • the lugs are carried by integral fingers 31 forming a part of the coverplate. Projecting from the base 26 of the damping element is an arm 32 which extends radially outward beyond the lug 30 and also obliquely with respect to the radius for engagement with the platform 14 of one of the blades.
  • the arm 32 terminates in a circumferentially extending surface 34 which engages the underside of the platform 14 and by frictional engagement therewith will reduce the vibratory motion of the blade.
  • the circumferential dimension of the surface 34 is preferably slightly less than the circumferential dimension of the blade platform and the circumferential dimension of the arm 32 is so selected that the arms 32 on adjacent blade dampers Will not be in contact.
  • the integral radially extending fingers 31 on the plate 20 are spaced apart circumferentially and terminate at a point radially outward beyond the lug 39, thus these fingers serve to hold the damping elements in position against the end surfaces of the root extensions and in the proper position to engage effectively with the lug 3t) and blade platform 14.
  • the lugs 39 serve to locate the damper elements circumferentially as best shown in FIG. 5 thus making sure that each damper is in engagement with the respective lug and blade platform. It will be noted that the circumferential dimension of the bases 26 of the blade damping elements is such that adjacent elements are spaced apart to some extent so that each damper is free to move circumferentially to a limited degree so that frictional damping can occur between the surface 28 and the lug 30.
  • the radial load on the end plate 24 resulting from the action of the blade dampers is carried in part by a circumferentially extending flange 38 on the inner end of the plate 20 engaging with a notch 4% on the disc.
  • the plate 20 may also have another circumferential flange 42 which carries sealing fins 44.
  • the blade dampers are free to move to a limited extent in a radial direction. As the rotor is spun, centrifugal force will urge the dampers radially outward bringing the surfaces 23 and 34 into contact with the lug 30 and platform 14, respectively.
  • the damper can be so arranged that a greater force is exerted by the surface 28 than by the surface 34, such that, with equal friction coefiicients, damping will occur by relative motion between the damper and the blade platform.
  • the blade dampers may have obliquely positioned surfaces 46 at their inner edges to engage with a similarly inclined surface 48 on the plate 20 to limit the free radial movement of the blade dampers with respect to the coverplate.
  • a rotor construction for compressors or turbines including a disc, a row of blades mounted on and extending substantially radially from the periphery of the disc, each blade presenting a circumferentially extending surface and having a platform thereon, said blades having end surfaces in a radial plane, a coverplate for attachment to one side of the disc in overlying relation to a part of each of the blades, and damping means including a plurality of circumferentially spaced lugs on the inside of the coverplate, and damping elements, one for each blade, positioned in part between the coverplate and the end surfaces of the blades and guided by said coverplate and said end surfaces of the blades for substantially radial movement under centrifugal force, each element having a surface frictionally engaging with one of said lugs and another surface frictionally engageable with the surface on the platform on one of the blades.
  • damping elements are limited in radially outward movement only by contact of said two surfaces therein with the associated lug and platform.
  • a device as in claim 1 in which the lug engaging surface on each element is offset circumferentially of the coverplate from the platform engaging surface.
  • a damper device for the blades including a coverplate attached to and overlying one side of the disc adjacent the periphery, said coverplate having a plurality of circumferentially spaced lugs thereon corresponding in spacing to the blades, and a plurality of damper elements, one for each blade, positioned between the row of blades and the coverplate, each damper element having a circumferentially extending surface engaging with one of the lugs and another radially and circumferentially spaced surface extending in a circumferential direction and engaging with a circumferential surface on one of the blades, each damper element being supported in a radially outward direction solely by the lug and circumferential surface on the blade such that, when the disc is rotated, the
  • damper is urged by centrifugal force against the lug and surface.
  • each blade has a circumferentially extending platform located radially between the inner and outer ends of the blade and providing the circumferential surface engaged by the damper element.
  • each blade has a root fitting in a slot in the blade periphery and a radially projecting root extension between the root and the platform and the coverplate overlies these root extensions.
  • root extensions for the blades have radially extending end surfaces all substantially in a radial plane and the damper elements are positioned between the radially extending end surfaces of the root extensions and the coverplate.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US207929A 1962-07-06 1962-07-06 Blade damping device Expired - Lifetime US3129921A (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US207929A US3129921A (en) 1962-07-06 1962-07-06 Blade damping device
SE7374/63A SE305278B (de) 1962-07-06 1963-07-03
CH837063A CH415691A (de) 1962-07-06 1963-07-05 Schaufel Schwingungs-Dämpfungsvorrichtung
DE19631426869 DE1426869B2 (de) 1962-07-06 1963-07-05 Vorrichtung zur Schwingungsdämpfung von Verdichter- oder Turbinenschaufeln
GB26666/63A GB995514A (en) 1962-07-06 1963-07-05 Turbine or compressor blade damping device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US207929A US3129921A (en) 1962-07-06 1962-07-06 Blade damping device

Publications (1)

Publication Number Publication Date
US3129921A true US3129921A (en) 1964-04-21

Family

ID=22772541

Family Applications (1)

Application Number Title Priority Date Filing Date
US207929A Expired - Lifetime US3129921A (en) 1962-07-06 1962-07-06 Blade damping device

Country Status (5)

Country Link
US (1) US3129921A (de)
CH (1) CH415691A (de)
DE (1) DE1426869B2 (de)
GB (1) GB995514A (de)
SE (1) SE305278B (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3888601A (en) * 1974-05-23 1975-06-10 Gen Electric Turbomachine with balancing means

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4192633A (en) * 1977-12-28 1980-03-11 General Electric Company Counterweighted blade damper
GB2043796B (en) * 1979-03-10 1983-04-20 Rolls Royce Bladed rotor for gas turbine engine
USRE32339E (en) * 1980-10-02 1987-01-27 United Technologies Corporation Blade to blade vibration damper
US4568247A (en) * 1984-03-29 1986-02-04 United Technologies Corporation Balanced blade vibration damper

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB667979A (en) * 1949-07-28 1952-03-12 Rolls Royce Improvements in or relating to axial flow compressors and turbines
US2660400A (en) * 1948-11-25 1953-11-24 Rolls Royce Blade for turbines or compressors
US2935297A (en) * 1954-06-09 1960-05-03 Stalker Corp Vibration dampers for rotor blades
US2999668A (en) * 1958-08-28 1961-09-12 Curtiss Wright Corp Self-balanced rotor blade

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2660400A (en) * 1948-11-25 1953-11-24 Rolls Royce Blade for turbines or compressors
GB667979A (en) * 1949-07-28 1952-03-12 Rolls Royce Improvements in or relating to axial flow compressors and turbines
US2935297A (en) * 1954-06-09 1960-05-03 Stalker Corp Vibration dampers for rotor blades
US2999668A (en) * 1958-08-28 1961-09-12 Curtiss Wright Corp Self-balanced rotor blade

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3888601A (en) * 1974-05-23 1975-06-10 Gen Electric Turbomachine with balancing means

Also Published As

Publication number Publication date
DE1426869A1 (de) 1968-12-05
DE1426869B2 (de) 1970-02-19
CH415691A (de) 1966-06-30
SE305278B (de) 1968-10-21
GB995514A (en) 1965-06-16

Similar Documents

Publication Publication Date Title
US2689107A (en) Vibration damper for blades and vanes
US4182598A (en) Turbine blade damper
US2942843A (en) Blade vibration damping structure
US3104093A (en) Blade damping device
US2310412A (en) Vibration dampener
US3751183A (en) Interblade baffle and damper
US4936749A (en) Blade-to-blade vibration damper
US2916257A (en) Damping turbine buckets
US3045968A (en) Fir tree blade mount
US3266771A (en) Turbines and compressors
US2610823A (en) Turbine bucket damping arrangement
US3752599A (en) Bucket vibration damping device
US2936155A (en) Resiliently mounted turbine blades
US2999669A (en) Damping apparatus
US4743166A (en) Blade root seal
US3653781A (en) Turbomachinery blade retainer
US2812159A (en) Securing means for turbo-machine blading
US3181835A (en) Blade vibration damping device
US2801074A (en) Blade retaining means
US2994507A (en) Blade locking structure
JPS5813759B2 (ja) ガスタ−ビンエンジンのロ−タ−段
GB786475A (en) Improved turbine bucket vibration damping means
US3598503A (en) Blade lock
JPH024761B2 (de)
US4473337A (en) Blade damper seal