US3689177A - Blade constraining structure - Google Patents

Blade constraining structure Download PDF

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Publication number
US3689177A
US3689177A US135310A US3689177DA US3689177A US 3689177 A US3689177 A US 3689177A US 135310 A US135310 A US 135310A US 3689177D A US3689177D A US 3689177DA US 3689177 A US3689177 A US 3689177A
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United States
Prior art keywords
rotor
axially
ring
blades
wedge ring
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Expired - Lifetime
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US135310A
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English (en)
Inventor
David Dubble Klassen
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General Electric Co
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General Electric Co
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Publication date
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    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • 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
    • 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
    • F01D5/24—Blade-to-blade connections, e.g. for damping vibrations using wire or the like
    • 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

Definitions

  • the constraining means include a ring which is circumferentially expandable under centrifugal loading. Part of the outward radial force causing the expansion of the ring is directed axially against the blade members to provide an axially constraining force which is proportional to the centrifugal loading on the rotor.
  • This invention generally relates to a blade constraining structure for use in an axial flow apparatus of the type having stator and rotor elements and more particularly to structure for constraining axial movement of blades under high centrifugal loading in axial flow compressors.
  • blades are commonly retained by inserting rootportions into either circumferentially or axially extending dovetail slots around the periphery of rotor elements. It is well known to retain the blades in the forward stages of a compressor by means of axially extending dovetail slots while the smaller blades in the aft stages are retained by means of circumferentially extending dovetail slots. The reason is simply that circumferential dovetail slots, due to inherent strength limitations, are not as well suited for retaining the larger and heavier forward stage blades under high centrifugal loading as are the axially extending dovetail slots.
  • the blade constraining structure of an axial flow compressor includes rotor and stator elements.
  • a first rotor element has axially opposed faces together with a plurality of open ended generally radial slots extending from one face to the other. Each slot has a pair of side walls which are undercut to provide inwardly directed abutment faces.
  • a second rotor member is axially spaced from the first rotor and includes an axially extending, circumferential flange. The tip of the flange is closely spaced opposite the slots of the first rotor and is axially undercut to provide an inwardly directed surface.
  • a wedge ring has an outer annular surface which is axially overcut to provide an outwardly directed surface which abuts the inwardly directed surface of the flange. Under centrifugal loading the wedge ring circumferentially expands, and the overcut surface slides over the undercut surface in both an outward radial direction and an axial direction, effecting both a radial and axial translation of the wedge ring.
  • FIG. 1 is a partial cross-sectional view of an axial flow compressor embodying the invention
  • FIG. 2 is a section view taken along the line 22 of FIG. 1;
  • FIG. 3 is a section view taken along the line 3-3 of FIG. 1.
  • FIG. 1 shows a partial cross-sectional view of two intermediate stages of an axial flow compressor of the type that is suitable for use in a gas turbine engine.
  • the axial flow compressor includes an annular outer casing 20.
  • a rotor assembly is shown generally at 11 and includes first and second disc like rotor elements l2 and 14 which are rotatably disposed around a central axis 15.
  • Rotor disc 12 has opposed faces 13 and 17 and includes a plurality of open-ended, uniform dovetail cross-sectional slots 16 in its periphery for retaining blades 24.
  • the slots 16 extend from the face 13 to the face 17 of the rotor disc 12 and each has side walls 21 as shown in FIG. 2 which are undercut to provide inwardly directed abutment faces 18 on the side walls 21.
  • Each of the blades 24 has a platform 29 and a root portion 26 which is thickened at the inner radial end to provide outwardly extending shoulders 19 which abut the inwardly directed faces 18 of the dovetail slot,
  • an adjacent rotor disc 14 which includes a first axially extending flange member 31, the end of which mates with rotor disc 12 to prevent circumferential slippage between the rotor elements.
  • the mating structure may include a series of interlocking male splines 51 and female splines 52 as shown in the limited cross-sectional view of FIG. 3.
  • An air seal may be provided between the interlocking male and female splines by an annular resilient plastic ring 53 inserted into abutting relation with the inside surfaces of the interlocking splines.
  • the plastic ring 53 is maintained in fixed relation to the splines during rotation by the centrifugal forces which urge outward circumferential expansion of the ring.
  • Rotor disc 14 includes a plurality of circumferentially spaced blades 25 disposed about its periphery.
  • the blades 25' may be radially and axially retained by means of a circumferential dovetail groove 37 extending around the outer periphery of the rotor disc 14.
  • Each blade 25 includes a dovetail root section 27 for engagement with the opposing surfaces of the dovetail groove 37 and must be inserted through a notch (not shown) in the dovetail groove 37 and circumferentially slid around the slot into abutting relation with an adjoining blade.
  • notch may then be locked in a manner well known to the art.
  • stator vanes 22 An intervening row of stator vanes 22 is shown disposed between blades 24 and 25 and is fixedly attached to compressor casing 20.
  • the vanes may also be rotatably attached to casing 20 in a manner well known to the art which is described in US. Pat. No. 3,216,700 filed by R. 'H. Bostock Jr., and assigned to General Electric Company.
  • Rotor disc 14 includes a second axially extending, circumferential flange member 32, the annular tip portion 35 of which is in close proximity to the trailing edge 'of the blade platform 29 in order to establish a smooth flow path and minimize flow losses.
  • the outer tip portion of the flange member 32 is axially undercut to provide an inwardly directed surface 34.
  • Blades 24 are individually inserted into their respective dovetail slots 16 from a forward axial direction and retained from outward radial travel under centrifugal loading by the interaction of the blade roots 26 and the dovetail slots 16 in the manner previously described. Axial movement of the blades, however, is also critical and any shift of the axial blade position would alter the rotor balance, causing vibrational damage. Accurate axial blade retention even under high centrifugal loading is accomplished in the following manner.
  • a wedge ring 30 is stationed in abutting relation to the inwardly directed surface 34 which axially undercuts the outer tip 35 of theflange member 32.
  • An outside surface 36 of the wedge ring is axially overcut to provide an outwardly directed surface for sliding contact with the inwardly directed surface 34.
  • the undercut and overcut surfaces of the flange 32 and wedge ring 30 are preferably nominally planar, although curvilinear surfaces could also be utilized.
  • the wedge ring may be formed of any resilient, plastic-like material which allows the circumference of the ring to be expanded slightly without fracture. Although the wedge ring must exhibit resiliency, it must also be of sufficient stiffness to resist axial cross-sectional compression without substantial deformation.
  • a highly suitable plastic for use in the wedge ring of this invention is polyimide sold under the trade name of Vespel.
  • the rotor disc 12 is provided with a plurality of circumferentially spaced apart projections 40, axially extending from the face 13 thereof. Each projection 40 has a downward extending lip 42 for receiving and retaining the locking ring 44. The projections 40 are spaced radially outward to coincide with the spaced apart dovetail slots 16 so that locking ring 44 abuts the root portions 26 of the individual blades, thereby constraining axial movement.
  • centrifugal force operates on the wedge ring 30, causing it to circumferentially expand.
  • Circumferential expansion of the wedge ring causes the overcut surface 36 of the wedge ring to slide outward along the abutting undercut'surface 34 of the flange 32.
  • the abutting undercut surface of the flange 32 restrains the outward radial movement of the wedge ring 30, imparting an axial component thereto, so as to increase the axial constraining force operating on the individual blades 24.
  • a portion of the centrifugal force operat-- ing on the wedge ring is directed to the forward inserted faces of the blade roots and cooperates with the locking ring to further restrict axial movement of the blades upon rotation of the rotor.
  • the wedge ring also serves as an effective air seal between rotor elements preventing high pressure compressor air from leaking out of the main flow path into the cavities between the rotor elements.
  • a blade constraining structure comprising:
  • first rotor element having axially opposed faces and a plurality of open-ended generally radial slots extending from one face to the other, with each slot having side walls which are undercut to provide inwardly directed abutment faces;
  • a second rotor member axially spaced from said first member and including an axially extending circumferential flange, the tip of which is in closely spaced opposing relation to said slots and is axially undercut to provide an inwardly directed surface;
  • a wedge ring whose outer radial annular surface is axially overcut to provide an outwardly directed surface abutting said inwardly directed surface of said flange, such that under the influence of centrifugal loading said wedge ring circumferentially expands and said overcut surface slides over said undercut surface in both an outward radial direction and an axial direction, effecting an axial translation of said wedge ring;
  • each root is thickened to provide outwardly extending shoulders which abut the inwardly extending shoulders of said slots so as to radially retain said blades under centrifugal loading;
  • locking means constraining the other face of each root to inhibit axial movement of said roots such that under centrifugal loading the axial translation of said wedge ring is directed against the abutting root faces and cooperates with said locking means to further restrict axial movement of said blades.
  • said second rotor member includes a plurality of circumfercntially spaced blades disposed about its periphery wherein said blades are radially and axially retained by means of a circumferential dovetail groove around the outer periphery of said second rotor member.
  • wedge ring is a plastic-like resilient material which allows the circumference of the ring to be expanded slightly without fracture, yet is of suflicient stiffness to resist axial crosssectional compression without substantial deformation.
  • said locking means includes a locking ringabutting the other faces of said blade roots and maintained in abutting relation by a plurality of projections axially extending from said first rotor with each projection including an inward extending radial lip overlapping said locking ring.
  • first and second rotor members are mated by a series of axially extending interlocking male and female splines so as to prevent circumferential slippage between the rotor elements.
US135310A 1971-04-19 1971-04-19 Blade constraining structure Expired - Lifetime US3689177A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13531071A 1971-04-19 1971-04-19

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US (1) US3689177A (de)
BE (1) BE778125A (de)
CA (1) CA941746A (de)
DE (1) DE2201383A1 (de)
FR (1) FR2135943A5 (de)
GB (1) GB1369513A (de)
IT (1) IT946577B (de)

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4021138A (en) * 1975-11-03 1977-05-03 Westinghouse Electric Corporation Rotor disk, blade, and seal plate assembly for cooled turbine rotor blades
US4047840A (en) * 1975-05-29 1977-09-13 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Impact absorbing blade mounts for variable pitch blades
US4127359A (en) * 1976-05-11 1978-11-28 Motoren-Und Turbinen-Union Munchen Gmbh Turbomachine rotor having a sealing ring
FR2413544A1 (fr) * 1977-12-27 1979-07-27 Gen Electric Dispositif perfectionne de retenue d'aubes
US4344740A (en) * 1979-09-28 1982-08-17 United Technologies Corporation Rotor assembly
FR2523208A1 (fr) * 1982-03-12 1983-09-16 Snecma Dispositif d'amortissement des vibrations d'aubes mobiles de turbine
US4480957A (en) * 1983-04-14 1984-11-06 General Electric Company Dynamic response modification and stress reduction in dovetail and blade assembly
US4523890A (en) * 1983-10-19 1985-06-18 General Motors Corporation End seal for turbine blade base
US4737076A (en) * 1986-10-20 1988-04-12 United Technologies Corporation Means for maintaining concentricity of rotating components
US4743166A (en) * 1984-12-20 1988-05-10 General Electric Company Blade root seal
US4836750A (en) * 1988-06-15 1989-06-06 Pratt & Whitney Canada Inc. Rotor assembly
US5478207A (en) * 1994-09-19 1995-12-26 General Electric Company Stable blade vibration damper for gas turbine engine
US6406263B1 (en) 1999-04-13 2002-06-18 Honeywell International, Inc. Gas turbine shaft pilot system with separate pilot rings
US20050254952A1 (en) * 2004-05-14 2005-11-17 Paul Stone Bladed disk fixing undercut
JP2006138255A (ja) * 2004-11-12 2006-06-01 Hitachi Ltd タービンロータ及びガスタービン
GB2422176A (en) * 2005-01-18 2006-07-19 Rolls Royce Plc Retaining components/blades on a rotor
US20070009360A1 (en) * 2004-07-13 2007-01-11 Honeywell International, Inc. Non-parallel spacer for improved rotor group balance
US20110052371A1 (en) * 2008-02-13 2011-03-03 Emil Aschenbruck Multi-Component Bladed Rotor for a Turbomachine
CN102105655A (zh) * 2008-05-29 2011-06-22 斯奈克玛 涡轮机风扇转子
FR2960021A1 (fr) * 2010-05-12 2011-11-18 Snecma Roue mobile de turbomachine munie d'un jonc d'amortissement des vibrations
US20140112793A1 (en) * 2012-10-18 2014-04-24 General Electric Company Systems and Methods to Axially Retain Blades
US20160186592A1 (en) * 2014-12-31 2016-06-30 General Electric Company Flowpath boundary and rotor assemblies in gas turbines
US20170067354A1 (en) * 2015-09-09 2017-03-09 United Technologies Corporation Seal assembly for turbine engine component
US20180016920A1 (en) * 2016-07-15 2018-01-18 Rolls-Royce Plc Rotor assembly for a turbomachine and a method of manufacturing the same
US10975714B2 (en) * 2018-11-22 2021-04-13 Pratt & Whitney Canada Corp. Rotor assembly with blade sealing tab
US20210246789A1 (en) * 2020-02-07 2021-08-12 Rolls-Royce Plc Rotor assembly

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4872812A (en) * 1987-08-05 1989-10-10 General Electric Company Turbine blade plateform sealing and vibration damping apparatus
US10718220B2 (en) * 2015-10-26 2020-07-21 Rolls-Royce Corporation System and method to retain a turbine cover plate with a spanner nut

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2356605A (en) * 1940-01-08 1944-08-22 Meininghaus Ulrich Turbine rotor
CH284188A (de) * 1948-10-01 1952-07-15 Maschf Augsburg Nuernberg Ag Stahlläufer mit keramischen Schaufeln für Turbinen.
US2656147A (en) * 1946-10-09 1953-10-20 English Electric Co Ltd Cooling of gas turbine rotors
FR1145755A (fr) * 1955-04-10 1957-10-29 Maschf Augsburg Nuernberg Ag Rotor composé pour machines tournantes, notamment pour turbines à gaz à circulation axiale
US3356339A (en) * 1966-12-12 1967-12-05 Gen Motors Corp Turbine rotor

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2356605A (en) * 1940-01-08 1944-08-22 Meininghaus Ulrich Turbine rotor
US2656147A (en) * 1946-10-09 1953-10-20 English Electric Co Ltd Cooling of gas turbine rotors
CH284188A (de) * 1948-10-01 1952-07-15 Maschf Augsburg Nuernberg Ag Stahlläufer mit keramischen Schaufeln für Turbinen.
FR1145755A (fr) * 1955-04-10 1957-10-29 Maschf Augsburg Nuernberg Ag Rotor composé pour machines tournantes, notamment pour turbines à gaz à circulation axiale
US3356339A (en) * 1966-12-12 1967-12-05 Gen Motors Corp Turbine rotor

Cited By (39)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4047840A (en) * 1975-05-29 1977-09-13 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Impact absorbing blade mounts for variable pitch blades
US4021138A (en) * 1975-11-03 1977-05-03 Westinghouse Electric Corporation Rotor disk, blade, and seal plate assembly for cooled turbine rotor blades
US4127359A (en) * 1976-05-11 1978-11-28 Motoren-Und Turbinen-Union Munchen Gmbh Turbomachine rotor having a sealing ring
FR2413544A1 (fr) * 1977-12-27 1979-07-27 Gen Electric Dispositif perfectionne de retenue d'aubes
US4344740A (en) * 1979-09-28 1982-08-17 United Technologies Corporation Rotor assembly
EP0089272A1 (de) * 1982-03-12 1983-09-21 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Turbinenrotor mit Schwingungsdämpfer für die Turbinenschaufeln
FR2523208A1 (fr) * 1982-03-12 1983-09-16 Snecma Dispositif d'amortissement des vibrations d'aubes mobiles de turbine
US4480959A (en) * 1982-03-12 1984-11-06 S.N.E.C.M.A. Device for damping vibrations of mobile turbine blades
US4480957A (en) * 1983-04-14 1984-11-06 General Electric Company Dynamic response modification and stress reduction in dovetail and blade assembly
US4523890A (en) * 1983-10-19 1985-06-18 General Motors Corporation End seal for turbine blade base
US4743166A (en) * 1984-12-20 1988-05-10 General Electric Company Blade root seal
US4737076A (en) * 1986-10-20 1988-04-12 United Technologies Corporation Means for maintaining concentricity of rotating components
US4836750A (en) * 1988-06-15 1989-06-06 Pratt & Whitney Canada Inc. Rotor assembly
US5478207A (en) * 1994-09-19 1995-12-26 General Electric Company Stable blade vibration damper for gas turbine engine
US6406263B1 (en) 1999-04-13 2002-06-18 Honeywell International, Inc. Gas turbine shaft pilot system with separate pilot rings
US7153102B2 (en) * 2004-05-14 2006-12-26 Pratt & Whitney Canada Corp. Bladed disk fixing undercut
US20050254952A1 (en) * 2004-05-14 2005-11-17 Paul Stone Bladed disk fixing undercut
US20070009360A1 (en) * 2004-07-13 2007-01-11 Honeywell International, Inc. Non-parallel spacer for improved rotor group balance
US7510380B2 (en) 2004-07-13 2009-03-31 Honeywell International Inc. Non-parallel spacer for improved rotor group balance
JP4591047B2 (ja) * 2004-11-12 2010-12-01 株式会社日立製作所 タービンロータ及びガスタービン
JP2006138255A (ja) * 2004-11-12 2006-06-01 Hitachi Ltd タービンロータ及びガスタービン
GB2422176A (en) * 2005-01-18 2006-07-19 Rolls Royce Plc Retaining components/blades on a rotor
US8784064B2 (en) * 2008-02-13 2014-07-22 Man Diesel & Turbo Se Multi-component bladed rotor for a turbomachine
US20110052371A1 (en) * 2008-02-13 2011-03-03 Emil Aschenbruck Multi-Component Bladed Rotor for a Turbomachine
CN102105655A (zh) * 2008-05-29 2011-06-22 斯奈克玛 涡轮机风扇转子
US20110150657A1 (en) * 2008-05-29 2011-06-23 Snecma Turbomachine fan rotor
US8740568B2 (en) * 2008-05-29 2014-06-03 Snecma Turbomachine fan rotor
FR2960021A1 (fr) * 2010-05-12 2011-11-18 Snecma Roue mobile de turbomachine munie d'un jonc d'amortissement des vibrations
US20140112793A1 (en) * 2012-10-18 2014-04-24 General Electric Company Systems and Methods to Axially Retain Blades
US9476310B2 (en) * 2012-10-18 2016-10-25 General Electric Company Systems and methods to axially retain blades
US20160186592A1 (en) * 2014-12-31 2016-06-30 General Electric Company Flowpath boundary and rotor assemblies in gas turbines
CN105863742A (zh) * 2014-12-31 2016-08-17 通用电气公司 燃气涡轮中的流路边界和转子组件
US20170067354A1 (en) * 2015-09-09 2017-03-09 United Technologies Corporation Seal assembly for turbine engine component
US10233763B2 (en) * 2015-09-09 2019-03-19 United Technologies Corporation Seal assembly for turbine engine component
US10808562B2 (en) 2015-09-09 2020-10-20 Raytheon Technologies Corporation Seal assembly for turbine engine component
US20180016920A1 (en) * 2016-07-15 2018-01-18 Rolls-Royce Plc Rotor assembly for a turbomachine and a method of manufacturing the same
US10975714B2 (en) * 2018-11-22 2021-04-13 Pratt & Whitney Canada Corp. Rotor assembly with blade sealing tab
US20210246789A1 (en) * 2020-02-07 2021-08-12 Rolls-Royce Plc Rotor assembly
US11834958B2 (en) * 2020-02-07 2023-12-05 Rolls-Royce Plc Rotor assembly

Also Published As

Publication number Publication date
IT946577B (it) 1973-05-21
CA941746A (en) 1974-02-12
FR2135943A5 (de) 1972-12-22
GB1369513A (en) 1974-10-09
BE778125A (fr) 1972-05-16
DE2201383A1 (de) 1972-10-26

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