US3521974A - Turbine blade construction - Google Patents

Turbine blade construction Download PDF

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Publication number
US3521974A
US3521974A US759111A US3521974DA US3521974A US 3521974 A US3521974 A US 3521974A US 759111 A US759111 A US 759111A US 3521974D A US3521974D A US 3521974DA US 3521974 A US3521974 A US 3521974A
Authority
US
United States
Prior art keywords
blade
root
clamping ring
ring
blade construction
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
US759111A
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English (en)
Inventor
Ferdinand Zerlauth
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 US3521974A publication Critical patent/US3521974A/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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • 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

  • a turbine blade whose root includes a cylindrical portion and a plurality of spaced plane surfaces against one or another of which a suitably selected clamping ring can be brought to bear in order to detune the natural frequency of oscillation of the blade from oscillation frequencies to be encountered by the blade in service.
  • turbomachine e.g. a stator blade construction for turbo-compressors.
  • turbomachine is intended to denote a turbine-type machine whether for development of mechanical energy at a rotating shaft from a fluid flowing through the machine as in a turbine, or for the delivery of energy from a rotating shaft to the fluid, as in a pump or compressor.
  • the foot or root of the blade includes at least one circularly cylindrical surface and at least two plane surfaces perpendicular to the axis of that cylindrical surface.
  • It also includes a thread so that, in accordance with the vibrational conditions obtaining, the blade may be fastened into the cylindrical bore of a blade carrier with the help of a nut engaged on the thread, with the help of a clamping ring bearing against the cylindrical surface and against one of the plane surfaces, and with the help of a wedging ring having a conical bore which is drawn down over the first-named ring.
  • the blade can be detuned from the frequency of oscillations existing in the vicinity thereof, for example those in the fioW of the working substance, so that the blade will not be set into corresponding sympathetic vibrations. Consequently, no resonance builds up and there is no critical range of oscillations.
  • the blade can be easily set to the desired angle or pitch and if necessary can be easily corrected in that respect.
  • the root of the blade can be provided with an annular neck or constriction with the help of which large changes in the natural period of vibration of the blade can be achieved in the initial manufacture thereof.
  • the fine adjustment in this respect is made on assembly by suitable choice in the positioning of the clamping ring applied to one or another of the plane surfaces.
  • the clamping ring can then be split into two or more parts and the wedging ring can be similarly split.
  • FIG. 1 shows in simplified form a blade construction according to the invention having a clamping ring bearing against one of two plane surfaces
  • FIG. 2 is a similar view showing a clamping ring hearing against the other of those plane surfaces.
  • the blade 12 possesses a root portion 11 with the help of which the blade is to be fastened in a blade carrier 23.
  • the carrier 23 possesses a shape matching the groove in a rotor or stator blade ring so that in customary fashion it can be set thereinto. With additional necessary blades the result is one stage of rotor or stator blading of a turbomachine such as a steam turbine, gas turbine or axial compressor, for example.
  • the root 11 of the blade 12 may be shaped as a body of revolution, for example by a turning operation or operations.
  • the blade root possesses a circularly cylindrical surface 13 and two plane surfaces 16 and 17, perpendicular to the axis of the surface 13.
  • the root includes a thread 18, onto which a nut 24 can be run.
  • a clamping ring 19.1 can be brought, as in FIG. 1, to bear against the circularly cylindrical surface 13 and against the plane surface 16.
  • a clamping ring 19.2 can be brought to bear against the surface 13 and against the plane surface 17.
  • the clamping rings 19a and 19b possess a conical outer surface 20.
  • This conical surface mates with the conical bore of a covering or wedging ring 21.
  • the two rings will be wedged against each other and between the cylindrical surfaces 13 and 22, so that the root 11 and blade 12 will be locked both axially and angularly with respect to the blade carrier 23.
  • the blade and blade support can be held in the proper relative position by means of jigs, which canbe inserted for example into the groove 28 to bear against the root and against the profile of the blade. The result will be that after tightening of the nut has been completed, the blade will be correctly positioned.
  • the bores 26 in the blade carrier 23 serve to permit subsequent observation as to which of the clamping members 19a and 19b has been employed in the completely assembled blade.
  • the blade carrier 23 (of which there may be a plurality in any one blade ring) can have any desired profile to be set into circular closed blade grooves or in transverse grooves of plates or other blade-supporting elements.
  • a groove 25 or constriction can be provided in the root 11.
  • desired preliminary detuning can be achieved for the blade with respect to the vibration frequency expected to be encountered.
  • the frequency can be further brought to the desired value without mechanical attack upon the blade.
  • the invention thus provides a turbine blade construction which facilitates accurate and secure positioning of the blades, and which also permits, by choice among rings such as the rings 19a and 19b in the embodiment de scribed, change in the free unsupported length of the blades. This permits control of their natural frequency of vibration, so as to detune them from oscillations to which they may be exposed in service.
  • a turbine blade construction comprising:

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US759111A 1968-03-26 1968-09-11 Turbine blade construction Expired - Lifetime US3521974A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH446168A CH488939A (de) 1968-03-26 1968-03-26 Schaufel für Turbomaschinen

Publications (1)

Publication Number Publication Date
US3521974A true US3521974A (en) 1970-07-28

Family

ID=4276544

Family Applications (1)

Application Number Title Priority Date Filing Date
US759111A Expired - Lifetime US3521974A (en) 1968-03-26 1968-09-11 Turbine blade construction

Country Status (6)

Country Link
US (1) US3521974A (de)
BE (1) BE730456A (de)
CH (1) CH488939A (de)
FR (1) FR2004710A1 (de)
GB (1) GB1192159A (de)
NL (1) NL6805582A (de)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4012171A (en) * 1974-04-24 1977-03-15 Suvak Michael N Blade and mounting means
US4245954A (en) * 1978-12-01 1981-01-20 Westinghouse Electric Corp. Ceramic turbine stator vane and shroud support
US5078576A (en) * 1989-07-06 1992-01-07 Rolls-Royce Plc Mounting system for engine components having dissimilar coefficients of thermal expansion
US5236304A (en) * 1990-12-27 1993-08-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Stemmed blade for a flow-straightening stage of a gas turbine engine and method of fixing said blade
GB2278647A (en) * 1990-12-27 1994-12-07 Snecma Method of fixing flow-straightening blades in a turboshaft engine
EP1217173A3 (de) * 2000-12-20 2003-10-29 United Technologies Corporation Turbomaschinenleitschaufel
US20090185899A1 (en) * 2008-01-21 2009-07-23 Guy Bouchard Hp segment vanes
US20090252610A1 (en) * 2008-04-04 2009-10-08 General Electric Company Turbine blade retention system and method
ITTO20080578A1 (it) * 2008-07-28 2010-01-29 Ansaldo Energia Spa Gruppo di collegamento per collegare una paletta ad un anello di supporto, in particolare ad un anello interno di uno statore di compressore
US20110014053A1 (en) * 2009-07-14 2011-01-20 General Electric Company Turbine bucket lockwire rotation prevention
US20120301288A1 (en) * 2009-11-23 2012-11-29 Dieter Maier Charging device
US20170114795A1 (en) * 2015-07-22 2017-04-27 Safran Aero Boosters Sa Composite compressor vane of an axial turbine engine
FR3127533A1 (fr) * 2021-09-28 2023-03-31 Safran Aircraft Engines Système de calage pour aube articulée de turbomachine, aube de turbomachine équipée de ce système de calage et procédé de montage d’un tel système de calage sur une aube articulée

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE724793C (de) * 1940-04-16 1942-09-05 Sulzer Ag Foerdermaschine mit vornehmlich axial wirkenden Laufschaufeln
US2955799A (en) * 1957-02-11 1960-10-11 United Aircraft Corp Blade damping means

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE724793C (de) * 1940-04-16 1942-09-05 Sulzer Ag Foerdermaschine mit vornehmlich axial wirkenden Laufschaufeln
US2955799A (en) * 1957-02-11 1960-10-11 United Aircraft Corp Blade damping means

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4012171A (en) * 1974-04-24 1977-03-15 Suvak Michael N Blade and mounting means
US4245954A (en) * 1978-12-01 1981-01-20 Westinghouse Electric Corp. Ceramic turbine stator vane and shroud support
US5078576A (en) * 1989-07-06 1992-01-07 Rolls-Royce Plc Mounting system for engine components having dissimilar coefficients of thermal expansion
US5236304A (en) * 1990-12-27 1993-08-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Stemmed blade for a flow-straightening stage of a gas turbine engine and method of fixing said blade
US5319850A (en) * 1990-12-27 1994-06-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Method of fixing stemmed blade for a flow-straightening stage of a gas turbine engine
GB2278647A (en) * 1990-12-27 1994-12-07 Snecma Method of fixing flow-straightening blades in a turboshaft engine
GB2278647B (en) * 1990-12-27 1995-04-05 Snecma Method of fixing flow-straightening blades in a turboshaft engine
GB2253444B (en) * 1990-12-27 1995-04-05 Snecma Stemmed blade for a flow-straightening stage of a turboshaft engine and method of fixing said blade
EP1217173A3 (de) * 2000-12-20 2003-10-29 United Technologies Corporation Turbomaschinenleitschaufel
US8092165B2 (en) 2008-01-21 2012-01-10 Pratt & Whitney Canada Corp. HP segment vanes
US20090185899A1 (en) * 2008-01-21 2009-07-23 Guy Bouchard Hp segment vanes
US20090252610A1 (en) * 2008-04-04 2009-10-08 General Electric Company Turbine blade retention system and method
JP2009250237A (ja) * 2008-04-04 2009-10-29 General Electric Co <Ge> タービンブレード保持システム及び方法
US8894370B2 (en) 2008-04-04 2014-11-25 General Electric Company Turbine blade retention system and method
ITTO20080578A1 (it) * 2008-07-28 2010-01-29 Ansaldo Energia Spa Gruppo di collegamento per collegare una paletta ad un anello di supporto, in particolare ad un anello interno di uno statore di compressore
EP2149678A1 (de) * 2008-07-28 2010-02-03 Ansaldo Energia S.P.A. Verbindungsanordnung zur Verbindung einer Schaufel mit einem Trägerring
US20110014053A1 (en) * 2009-07-14 2011-01-20 General Electric Company Turbine bucket lockwire rotation prevention
US8485784B2 (en) 2009-07-14 2013-07-16 General Electric Company Turbine bucket lockwire rotation prevention
US20120301288A1 (en) * 2009-11-23 2012-11-29 Dieter Maier Charging device
US20170114795A1 (en) * 2015-07-22 2017-04-27 Safran Aero Boosters Sa Composite compressor vane of an axial turbine engine
FR3127533A1 (fr) * 2021-09-28 2023-03-31 Safran Aircraft Engines Système de calage pour aube articulée de turbomachine, aube de turbomachine équipée de ce système de calage et procédé de montage d’un tel système de calage sur une aube articulée

Also Published As

Publication number Publication date
BE730456A (de) 1969-09-26
CH488939A (de) 1970-04-15
FR2004710A1 (de) 1969-11-28
GB1192159A (en) 1970-05-20
NL6805582A (de) 1969-09-30

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