US3610778A - Support for rotor blades in a rotor - Google Patents

Support for rotor blades in a rotor Download PDF

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Publication number
US3610778A
US3610778A US813235A US3610778DA US3610778A US 3610778 A US3610778 A US 3610778A US 813235 A US813235 A US 813235A US 3610778D A US3610778D A US 3610778DA US 3610778 A US3610778 A US 3610778A
Authority
US
United States
Prior art keywords
blades
combination
rotor
set forth
crosspiece
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
US813235A
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English (en)
Inventor
Peter Suter
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.)
Sulzer AG
Original Assignee
Sulzer 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 Sulzer AG filed Critical Sulzer AG
Application granted granted Critical
Publication of US3610778A publication Critical patent/US3610778A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • 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 a support for rotor blades in a rotor. More particularly, this invention relates to a support for rotor blades of a turboengine rotor.
  • Turboengine rotors have been known wherein a plurality of turbine blades have been mounted in slots within the rotor with wedgelike baffle elements therebetween.
  • blades have been constructed with a baseplate, a necklike extension below the baseplate and a base below the extension which has been shaped to mate within an axial or oblique slot in the rotor.
  • the baffle elements have been sized to fit within the space between the necklike extension of two adjacent blades. Further, such baffle elements have been sized and fitted so as to obtain as smooth as possible a transition between the baseplates and rotor.
  • the invention provides a baffle element for turbine blades in a rotor which is situated between a pair of blades and contacts each blade at a point in an elastic yieldable manner opposite the contact point of the other blade.
  • This allows the blades to vibrate more or less freely with respect to the baffle element.
  • an elastic yieldable section is provided in the baffle element between the contact points with the respective turbine blades.
  • the blades are able to oscillate more or less freely with respect to the baffle element while their natural frequency is reduced.
  • the natural vibration frequency of the blades can be adjusted to a desired value within certain limits.
  • various configurations of the baffle elements can likewise be elastically effective.
  • FIG. 1 illustrates a fragmentary side view of a rotor having blades mounted in place by baffle elements according to the invention
  • FIG. 2 illustrates a view taken on line A-B of FIG. 1;
  • FIG. 3 illustrates a perspective view of the baffle element of FIG. 1
  • FIGS. 4 to 6 respectively illustrate perspective views of modified baffle elements according to the invention.
  • FIG. 7 illustrates a view similar to FIG. 1 of another modified baffle element according to the invention.
  • the rotor I is provided with a plurality of circumferentially spaced axial or oblique slots 2 each of which receives a complementary shaped base 3 of a turbine blade 4.
  • each blade 4 has a baseplate 5 and a necklike extension 6 between the base 3 and baseplate 5.
  • the necklike extensions 6 of each pair of adjacent blades 4 are spaced apart to provide an interspace for a baffle element 7.
  • Each baffle element 7 serves to fill up the interspace between the blade extensions 6.
  • each baffle element 7 has a pair of plates 8, which are joined together in spaced relation by a crosspiece 9 of substantially T-shaped cross section.
  • elevations 11, I6 are provided at either end of the crosspiece 9 to extend over a part of the length of the crosspiece 9, for example, one-quarter of the crosspiece length.
  • the elevations ll, 16 are further disposed diagonally opposite each other on the top of the crosspiece 9.
  • each baffle element 7 has a lug 18 extending therefrom in the same plane which abuts the side of a blade 4 so as to prevent axial displacement of the baffle element 7. Since each of the baffle elements 7 contacts the baseplates 5 of adjacent blades 4 at separated points and is of a shape to elastically yield under stress, the baseplates 5 can move with respect to one another, for example, under a torsional vibration.
  • the baffle element 7 is provided with a slot 14 substantially in the center of the crosspiece 9 which passes upwardly through the upper part of the cross section of the crosspiece 9.
  • a plurality of slots can be distributed uniformly or nonuniformly over the length of the crosspiece 9.
  • the elastic yieldability of the baffle element 7 can also be increased by reducing the cross-sectional area of the center of the crosspiece 9 in the upper part.
  • the flat horizontal upper part of the crosspiece can be centrally interrupted.
  • the elastic yieldability of the baffle element can be increased by positioning the two elevations 12 on the same side of the crosspiece 9. This allows the baffle element 7 to bear against only one of the two adjacent blades 4 during operation while the contact point of the baffle element 7 with the other blade 4 lies between the plates 8 and the necklike extension 6 substantially in the area 13, as shown, opposite the lug I8.
  • a baffle element 7' having an axial slot 20 can also be fitted between the necklike extensions 6 of a pair of blades 4. This allows an elastic yieldable connection to be formed at the contact points I9 between the upper surfaces of the element 7' on opposite sides of the slot 20 and the baseplates 5 of the blades 4.
  • a rotor having a plurality of circumferentially spaced slots; a plurality of turbine blades mounted in respective slots of said rotor, each blade having a base received in a respective slot, a baseplate and a necklike extension between said base and baseplate; and a plurality of elements, each said element being of approximately the same axial length as said necklike extensions and positioned between a pair of adjacent blades between said necklike extensions, each said element having a pair of spaced-apart elevations projecting therefrom, one of said elevations contacting one blade at a first contact point and the other of said elevations contacting the other blade of said pair of blades at a second contact point, and each said element being elastically yieldable between said points of contact and said elevations.
  • said element includes a pair of spaced plates between said pair of blades and a crosspiece joining said plates.
  • each baseplate is disposed radially over said elements and wherein said crosspiece mounts said elevations on an upper surface thereof with each said elevation extending along not more than one-quarter of the length of said crosspiece.
  • said crosspiece includes at least one slot therein between said contact points.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Nozzles For Electric Vacuum Cleaners (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US813235A 1968-08-09 1969-04-03 Support for rotor blades in a rotor Expired - Lifetime US3610778A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1201168A CH494896A (de) 1968-08-09 1968-08-09 Halterung von Laufschaufeln im Rotor einer Turbomaschine

Publications (1)

Publication Number Publication Date
US3610778A true US3610778A (en) 1971-10-05

Family

ID=4379003

Family Applications (1)

Application Number Title Priority Date Filing Date
US813235A Expired - Lifetime US3610778A (en) 1968-08-09 1969-04-03 Support for rotor blades in a rotor

Country Status (7)

Country Link
US (1) US3610778A (ko)
BE (1) BE737251A (ko)
CH (1) CH494896A (ko)
DE (1) DE1800817B1 (ko)
FR (1) FR1579923A (ko)
GB (1) GB1280701A (ko)
NL (1) NL6812195A (ko)

Cited By (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3751183A (en) * 1971-12-02 1973-08-07 Gen Electric Interblade baffle and damper
US3887298A (en) * 1974-05-30 1975-06-03 United Aircraft Corp Apparatus for sealing turbine blade damper cavities
US4088421A (en) * 1976-09-30 1978-05-09 General Electric Company Coverplate damping arrangement
US4101245A (en) * 1976-12-27 1978-07-18 United Technologies Corporation Interblade damper and seal for turbomachinery rotor
US4182598A (en) * 1977-08-29 1980-01-08 United Technologies Corporation Turbine blade damper
US4473337A (en) * 1982-03-12 1984-09-25 United Technologies Corporation Blade damper seal
US4626169A (en) * 1983-12-13 1986-12-02 United Technologies Corporation Seal means for a blade attachment slot of a rotor assembly
US4645425A (en) * 1984-12-19 1987-02-24 United Technologies Corporation Turbine or compressor blade mounting
US5201849A (en) * 1990-12-10 1993-04-13 General Electric Company Turbine rotor seal body
US5313786A (en) * 1992-11-24 1994-05-24 United Technologies Corporation Gas turbine blade damper
US5513955A (en) * 1994-12-14 1996-05-07 United Technologies Corporation Turbine engine rotor blade platform seal
US5573375A (en) * 1994-12-14 1996-11-12 United Technologies Corporation Turbine engine rotor blade platform sealing and vibration damping device
US5785499A (en) * 1996-12-24 1998-07-28 United Technologies Corporation Turbine blade damper and seal
US5827047A (en) * 1996-06-27 1998-10-27 United Technologies Corporation Turbine blade damper and seal
US5924699A (en) * 1996-12-24 1999-07-20 United Technologies Corporation Turbine blade platform seal
US20050129522A1 (en) * 2003-12-11 2005-06-16 Siemens Westinghouse Power Corporation Locking spacer assembly for slotted turbine component
US20050169754A1 (en) * 2004-02-04 2005-08-04 United Technologies Corporation Cooled rotor blade with vibration damping device
JP2010038165A (ja) * 2008-08-01 2010-02-18 Rolls Royce Plc 振動ダンパー
US20100040479A1 (en) * 2008-08-15 2010-02-18 United Technologies Corp. Gas Turbine Engine Systems Involving Baffle Assemblies
US20100111700A1 (en) * 2008-10-31 2010-05-06 Hyun Dong Kim Turbine blade including a seal pocket
DE102009011879A1 (de) * 2009-03-05 2010-09-16 Mtu Aero Engines Gmbh Integral beschaufelter Rotor und Verfahren zur Herstellung eines integral beschaufelten Rotors
US8393869B2 (en) 2008-12-19 2013-03-12 Solar Turbines Inc. Turbine blade assembly including a damper
GB2506225A (en) * 2012-06-04 2014-03-26 Snecma Turbine wheel and associated turbine engine
US20140119917A1 (en) * 2012-10-31 2014-05-01 Solar Turbines Incorporated Turbine blade for a gas turbine engine
CN104334857A (zh) * 2012-05-31 2015-02-04 索拉透平公司 涡轮风挡
US20150118055A1 (en) * 2013-10-31 2015-04-30 General Electric Company Gas turbine engine rotor assembly and method of assembling the same
CN104334857B (zh) * 2012-05-31 2016-11-30 索拉透平公司 涡轮风挡
US9650901B2 (en) 2012-05-31 2017-05-16 Solar Turbines Incorporated Turbine damper
US20210246790A1 (en) * 2020-02-10 2021-08-12 United Technologies Corporation Disk supported damper for a gas turbine engine

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1549152A (en) * 1977-01-11 1979-08-01 Rolls Royce Rotor stage for a gas trubine engine
GB2043797A (en) * 1979-03-10 1980-10-08 Rolls Royce Bladed Rotor for Gas Turbine Engine
FR2669686B1 (fr) * 1990-11-28 1994-09-02 Snecma Rotor de soufflante avec aubes sans plates-formes et sabots reconstituant le profil de veine.
FR3126446A1 (fr) * 2021-09-01 2023-03-03 Safran Aircraft Engines Amortisseur déformable pour roue mobile de turbomachine

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2669383A (en) * 1951-02-06 1954-02-16 A V Roe Canada Ltd Rotor blade
US2942842A (en) * 1956-06-13 1960-06-28 Gen Motors Corp Turbine blade lock
US3001760A (en) * 1959-08-07 1961-09-26 Gen Motors Corp Turbine blade lock
US3008689A (en) * 1954-08-12 1961-11-14 Rolls Royce Axial-flow compressors and turbines
US3037741A (en) * 1958-12-29 1962-06-05 Gen Electric Damping turbine buckets
US3112915A (en) * 1961-12-22 1963-12-03 Gen Electric Rotor assembly air baffle
US3119595A (en) * 1961-02-23 1964-01-28 Gen Electric Bladed rotor and baffle assembly
US3266771A (en) * 1963-12-16 1966-08-16 Rolls Royce Turbines and compressors
US3294364A (en) * 1962-01-02 1966-12-27 Gen Electric Rotor assembly

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2669383A (en) * 1951-02-06 1954-02-16 A V Roe Canada Ltd Rotor blade
US3008689A (en) * 1954-08-12 1961-11-14 Rolls Royce Axial-flow compressors and turbines
US2942842A (en) * 1956-06-13 1960-06-28 Gen Motors Corp Turbine blade lock
US3037741A (en) * 1958-12-29 1962-06-05 Gen Electric Damping turbine buckets
US3001760A (en) * 1959-08-07 1961-09-26 Gen Motors Corp Turbine blade lock
US3119595A (en) * 1961-02-23 1964-01-28 Gen Electric Bladed rotor and baffle assembly
US3112915A (en) * 1961-12-22 1963-12-03 Gen Electric Rotor assembly air baffle
US3294364A (en) * 1962-01-02 1966-12-27 Gen Electric Rotor assembly
US3266771A (en) * 1963-12-16 1966-08-16 Rolls Royce Turbines and compressors

Cited By (40)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3751183A (en) * 1971-12-02 1973-08-07 Gen Electric Interblade baffle and damper
US3887298A (en) * 1974-05-30 1975-06-03 United Aircraft Corp Apparatus for sealing turbine blade damper cavities
US4088421A (en) * 1976-09-30 1978-05-09 General Electric Company Coverplate damping arrangement
US4101245A (en) * 1976-12-27 1978-07-18 United Technologies Corporation Interblade damper and seal for turbomachinery rotor
US4182598A (en) * 1977-08-29 1980-01-08 United Technologies Corporation Turbine blade damper
US4473337A (en) * 1982-03-12 1984-09-25 United Technologies Corporation Blade damper seal
US4626169A (en) * 1983-12-13 1986-12-02 United Technologies Corporation Seal means for a blade attachment slot of a rotor assembly
US4645425A (en) * 1984-12-19 1987-02-24 United Technologies Corporation Turbine or compressor blade mounting
US5201849A (en) * 1990-12-10 1993-04-13 General Electric Company Turbine rotor seal body
US5313786A (en) * 1992-11-24 1994-05-24 United Technologies Corporation Gas turbine blade damper
US5513955A (en) * 1994-12-14 1996-05-07 United Technologies Corporation Turbine engine rotor blade platform seal
US5573375A (en) * 1994-12-14 1996-11-12 United Technologies Corporation Turbine engine rotor blade platform sealing and vibration damping device
US5827047A (en) * 1996-06-27 1998-10-27 United Technologies Corporation Turbine blade damper and seal
US5785499A (en) * 1996-12-24 1998-07-28 United Technologies Corporation Turbine blade damper and seal
US5924699A (en) * 1996-12-24 1999-07-20 United Technologies Corporation Turbine blade platform seal
US20050129522A1 (en) * 2003-12-11 2005-06-16 Siemens Westinghouse Power Corporation Locking spacer assembly for slotted turbine component
US6929453B2 (en) 2003-12-11 2005-08-16 Siemens Westinghouse Power Corporation Locking spacer assembly for slotted turbine component
US20050169754A1 (en) * 2004-02-04 2005-08-04 United Technologies Corporation Cooled rotor blade with vibration damping device
US7125225B2 (en) * 2004-02-04 2006-10-24 United Technologies Corporation Cooled rotor blade with vibration damping device
AU2004240224B2 (en) * 2004-02-04 2007-02-08 United Technologies Corporation Cooled rotor blade with vibration damping device
JP2010038165A (ja) * 2008-08-01 2010-02-18 Rolls Royce Plc 振動ダンパー
US8240987B2 (en) * 2008-08-15 2012-08-14 United Technologies Corp. Gas turbine engine systems involving baffle assemblies
US20100040479A1 (en) * 2008-08-15 2010-02-18 United Technologies Corp. Gas Turbine Engine Systems Involving Baffle Assemblies
US20100111700A1 (en) * 2008-10-31 2010-05-06 Hyun Dong Kim Turbine blade including a seal pocket
US8137072B2 (en) 2008-10-31 2012-03-20 Solar Turbines Inc. Turbine blade including a seal pocket
US8596983B2 (en) 2008-12-19 2013-12-03 Solar Turbines Inc. Turbine blade assembly including a damper
US8393869B2 (en) 2008-12-19 2013-03-12 Solar Turbines Inc. Turbine blade assembly including a damper
DE102009011879A1 (de) * 2009-03-05 2010-09-16 Mtu Aero Engines Gmbh Integral beschaufelter Rotor und Verfahren zur Herstellung eines integral beschaufelten Rotors
CN104334857B (zh) * 2012-05-31 2016-11-30 索拉透平公司 涡轮风挡
CN104334857A (zh) * 2012-05-31 2015-02-04 索拉透平公司 涡轮风挡
US9279332B2 (en) 2012-05-31 2016-03-08 Solar Turbines Incorporated Turbine damper
US9650901B2 (en) 2012-05-31 2017-05-16 Solar Turbines Incorporated Turbine damper
GB2506225A (en) * 2012-06-04 2014-03-26 Snecma Turbine wheel and associated turbine engine
GB2506225B (en) * 2012-06-04 2018-12-05 Snecma A turbine wheel in a turbine engine
US20140119917A1 (en) * 2012-10-31 2014-05-01 Solar Turbines Incorporated Turbine blade for a gas turbine engine
US9297263B2 (en) * 2012-10-31 2016-03-29 Solar Turbines Incorporated Turbine blade for a gas turbine engine
US9896946B2 (en) * 2013-10-31 2018-02-20 General Electric Company Gas turbine engine rotor assembly and method of assembling the same
US20150118055A1 (en) * 2013-10-31 2015-04-30 General Electric Company Gas turbine engine rotor assembly and method of assembling the same
US20210246790A1 (en) * 2020-02-10 2021-08-12 United Technologies Corporation Disk supported damper for a gas turbine engine
US11193376B2 (en) * 2020-02-10 2021-12-07 Raytheon Technologies Corporation Disk supported damper for a gas turbine engine

Also Published As

Publication number Publication date
BE737251A (ko) 1970-02-09
GB1280701A (en) 1972-07-05
FR1579923A (ko) 1969-08-29
CH494896A (de) 1970-08-15
NL6812195A (ko) 1970-02-11
DE1800817B1 (de) 1970-03-12

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