GB836030A - Improvements in or relating to a turbine blade and rotor assembly - Google Patents

Improvements in or relating to a turbine blade and rotor assembly

Info

Publication number
GB836030A
GB836030A GB2613756A GB2613756A GB836030A GB 836030 A GB836030 A GB 836030A GB 2613756 A GB2613756 A GB 2613756A GB 2613756 A GB2613756 A GB 2613756A GB 836030 A GB836030 A GB 836030A
Authority
GB
United Kingdom
Prior art keywords
layer
blade root
rotor
shim
steel
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
Application number
GB2613756A
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.)
MAN AG
Original Assignee
MAN Maschinenfabrik Augsburg Nuernberg 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 MAN Maschinenfabrik Augsburg Nuernberg AG filed Critical MAN Maschinenfabrik Augsburg Nuernberg AG
Publication of GB836030A publication Critical patent/GB836030A/en
Expired legal-status Critical Current

Links

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
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/284—Selection of ceramic materials
    • 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
    • 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
    • F01D5/3084—Fixing blades to rotors; Blade roots ; Blade spacers the blades being made of ceramics

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Ceramic Engineering (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

836,030. Mounting turbine rotor blades. MASCHINENFABRIK AUGSBURG-NURNBERG A.G. Aug. 27, 1956 [Oct. 31, 1955], No. 26137/56. Class 110 (3). [Also in Group XXV] In a bladed turbine rotor assembly in which a blade formed of brittle material such as ceramic is mounted in a metallic turbine rotor, a multi-layer shim is disposed between the bearing-surfaces of the rotor and blade root, the shim having one layer which is adapted to deform plastically under the action of centrifugal force when the rotor is first set in operation so as to conform with irregularities on the bearing- surface of the blade root, and at least one other layer which is adapted to deform elastically. In Fig. 2, the irregular surface of the unmachined blade root is shown at 1 and the machined surface of the rotor blade-mounting slot is shown at 2, a multi-layer shim 3 being disposed therebetween. The shim comprises a layer 5 of soft metal, such as a copper or aluminium alloy, which is partly covered by a steel jacket 4 disposed between the layer 5 and the blade root surface, and a layer 6 of, for example, chromiumnickel steel which lies against and is secured to the layer 5 by welding or brazing. The layer 5 is deformable plastically and completely fills the jacket 4 as a result of plastic deformation while the layer 6 is deformable elastically. In Fig. 3 the surface 2<1> of the rotor blade-mounting slot is also unmachined and the elastic layer 6<1> is partly covered by a steel strip 7 which has secured on its outer surface, a layer 8 of soft metal such as copper which deforms under operating conditions so as to conform with the irregular surface of the rotor blade-mounting slot. In this embodiment sliding can take place between the steel layer 6<1> and the steel strip 7. The layer 5 is deformable plastically as in Fig. 2 so as to conform to the irregularities on the surface 1 of the blade root. In Fig. 4 the shim 3<11> is formed by enclosing a brass mesh 11 within a steel envelope 10, the brass mesh constituting the plastic layer which is deformed under operating conditions so as to conform with irregularities on the surface 1 of the blade root. The thickness of the walls of the steel jackets 4 and 11 which bear against the blade root surfaces may be reduced either by grinding or by metal erosion. The two shims 3, 3<1> disposed one at either side of a blade root are connected by a steel strip bent to U-shape, a loop formed at the bottom of the U engaging a recess in the rotor. The shim shown in Fig. 4 may be bent to a U-shape so as to extend on both sides of the blade root.
GB2613756A 1955-10-31 1956-08-27 Improvements in or relating to a turbine blade and rotor assembly Expired GB836030A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DEM28639A DE1025421B (en) 1955-10-31 1955-10-31 Fastening of blades made of sproated material in a metallic blade carrier

Publications (1)

Publication Number Publication Date
GB836030A true GB836030A (en) 1960-06-01

Family

ID=7300459

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2613756A Expired GB836030A (en) 1955-10-31 1956-08-27 Improvements in or relating to a turbine blade and rotor assembly

Country Status (3)

Country Link
DE (1) DE1025421B (en)
FR (1) FR1163439A (en)
GB (1) GB836030A (en)

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3752600A (en) * 1971-12-09 1973-08-14 United Aircraft Corp Root pads for composite blades
US3809495A (en) * 1973-03-27 1974-05-07 Westinghouse Electric Corp Turbine rotor having cushioned support surfaces for ceramic blades mounted thereon
US3966353A (en) * 1975-02-21 1976-06-29 Westinghouse Electric Corporation Ceramic-to-metal (or ceramic) cushion/seal for use with three piece ceramic stationary vane assembly
US4207029A (en) * 1978-06-12 1980-06-10 Avco Corporation Turbine rotor assembly of ceramic blades to metallic disc
US4335998A (en) * 1978-05-24 1982-06-22 Volkswagenwerk Aktiengesellschaft Ceramic-metal assembly
JPS59113206A (en) * 1982-12-20 1984-06-29 Hitachi Ltd Blade fixing structure for turbo machine
US5087174A (en) * 1990-01-22 1992-02-11 Westinghouse Electric Corp. Temperature activated expanding mineral shim
US5160243A (en) * 1991-01-15 1992-11-03 General Electric Company Turbine blade wear protection system with multilayer shim
US5240375A (en) * 1992-01-10 1993-08-31 General Electric Company Wear protection system for turbine engine rotor and blade
WO1999064726A3 (en) * 1998-05-22 2000-03-09 Allied Signal Inc Compliant sleeve for ceramic turbine blades
US6832896B1 (en) * 2001-10-24 2004-12-21 Snecma Moteurs Blade platforms for a rotor assembly
GB2408295A (en) * 2003-11-14 2005-05-25 Rolls Royce Plc An assembly with a plastic insert between two metal components
EP1561905A1 (en) * 2004-02-09 2005-08-10 Siemens Aktiengesellschaft Plastically deformable layer in the mounting area of a turbine blade and method of turbine blade attachment
FR2951494A1 (en) * 2009-10-15 2011-04-22 Snecma Tinsel for e.g. ceramic matrix composites vane of rotor assembly in turbo engine of airplane, has proximal deformable portion projecting toward outside of tinsel, where portion is extended by distal portion that stops against end face
FR2959527A1 (en) * 2010-04-28 2011-11-04 Snecma Fan for turbojet engine of aircraft, has anti-wear part mounted on blades to form protection warps on corresponding surfaces of rear portion of stilt to avoid contact between surfaces and fixation flanges arranged opposite surfaces
RU2469193C2 (en) * 2007-09-25 2012-12-10 Снекма Gas turbine engine blade liner
CN103790640A (en) * 2014-02-19 2014-05-14 中国航空动力机械研究所 Blade capable of preventing wheel dish from being cracked
WO2014158276A3 (en) * 2013-03-05 2014-12-04 Rolls-Royce Corporation Structure and method for providing compliance and sealing between ceramic and metallic structures
WO2014163701A3 (en) * 2013-03-11 2014-12-11 Uskert Richard C Compliant intermediate component of a gas turbine engine and method of assembling this component
US9039379B2 (en) 2011-04-11 2015-05-26 Rolls-Royce Plc Retention device for a composite blade of a gas turbine engine
EP3139004A1 (en) * 2015-09-02 2017-03-08 General Electric Technology GmbH Turbine blade with ultrasonic wave scattering feature
EP2511480A3 (en) * 2011-04-14 2017-04-19 Rolls-Royce plc Annulus filler system
US10309257B2 (en) 2015-03-02 2019-06-04 Rolls-Royce North American Technologies Inc. Turbine assembly with load pads
CN111075511A (en) * 2013-05-29 2020-04-28 通用电气公司 Composite airfoil metal patch

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2108176A1 (en) * 1971-02-20 1972-08-31 Motoren Turbinen Union Fastening of ceramic turbine blades
US3836282A (en) * 1973-03-28 1974-09-17 United Aircraft Corp Stator vane support and construction thereof
USRE33954E (en) * 1982-02-22 1992-06-09 United Technologies Corporation Rotor blade assembly
GB2171151B (en) * 1985-02-20 1988-05-18 Rolls Royce Rotors for gas turbine engines
US5123813A (en) * 1991-03-01 1992-06-23 General Electric Company Apparatus for preloading an airfoil blade in a gas turbine engine
US5275536A (en) * 1992-04-24 1994-01-04 General Electric Company Positioning system and impact indicator for gas turbine engine fan blades
FR2934873B1 (en) * 2008-08-06 2011-07-08 Snecma VIBRATION DAMPER DEVICE FOR BLADE FASTENERS.
US9932831B2 (en) 2014-05-09 2018-04-03 United Technologies Corporation High temperature compliant metallic elements for low contact stress ceramic support
FR3124218A1 (en) * 2021-06-21 2022-12-23 Safran Aircraft Engines LONG TONGUE SNAP SHEET FOR TURBOMACHINE ROTOR BLADE FOOT
FR3139159A1 (en) * 2022-08-31 2024-03-01 Safran Aircraft Engines TURBINE WHEEL INCLUDING A RADIAL DEVICE FOR HOLDING BLADE FOOT IN THE CELLS OF A ROTOR DISC

Cited By (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3752600A (en) * 1971-12-09 1973-08-14 United Aircraft Corp Root pads for composite blades
US3809495A (en) * 1973-03-27 1974-05-07 Westinghouse Electric Corp Turbine rotor having cushioned support surfaces for ceramic blades mounted thereon
US3966353A (en) * 1975-02-21 1976-06-29 Westinghouse Electric Corporation Ceramic-to-metal (or ceramic) cushion/seal for use with three piece ceramic stationary vane assembly
US4335998A (en) * 1978-05-24 1982-06-22 Volkswagenwerk Aktiengesellschaft Ceramic-metal assembly
US4207029A (en) * 1978-06-12 1980-06-10 Avco Corporation Turbine rotor assembly of ceramic blades to metallic disc
JPS59113206A (en) * 1982-12-20 1984-06-29 Hitachi Ltd Blade fixing structure for turbo machine
JPS6261761B2 (en) * 1982-12-20 1987-12-23 Hitachi Ltd
US5087174A (en) * 1990-01-22 1992-02-11 Westinghouse Electric Corp. Temperature activated expanding mineral shim
US5160243A (en) * 1991-01-15 1992-11-03 General Electric Company Turbine blade wear protection system with multilayer shim
US5240375A (en) * 1992-01-10 1993-08-31 General Electric Company Wear protection system for turbine engine rotor and blade
WO1999064726A3 (en) * 1998-05-22 2000-03-09 Allied Signal Inc Compliant sleeve for ceramic turbine blades
US6832896B1 (en) * 2001-10-24 2004-12-21 Snecma Moteurs Blade platforms for a rotor assembly
GB2408295A (en) * 2003-11-14 2005-05-25 Rolls Royce Plc An assembly with a plastic insert between two metal components
EP1561905A1 (en) * 2004-02-09 2005-08-10 Siemens Aktiengesellschaft Plastically deformable layer in the mounting area of a turbine blade and method of turbine blade attachment
RU2469193C2 (en) * 2007-09-25 2012-12-10 Снекма Gas turbine engine blade liner
FR2951494A1 (en) * 2009-10-15 2011-04-22 Snecma Tinsel for e.g. ceramic matrix composites vane of rotor assembly in turbo engine of airplane, has proximal deformable portion projecting toward outside of tinsel, where portion is extended by distal portion that stops against end face
FR2959527A1 (en) * 2010-04-28 2011-11-04 Snecma Fan for turbojet engine of aircraft, has anti-wear part mounted on blades to form protection warps on corresponding surfaces of rear portion of stilt to avoid contact between surfaces and fixation flanges arranged opposite surfaces
WO2012072903A1 (en) * 2010-04-28 2012-06-07 Snecma Wear-resistant part for the support of a blade of a turbojet engine fan
US9500091B2 (en) 2010-04-28 2016-11-22 Snecma Wear-resistant part for the support of a blade of a turbojet fan
RU2582845C2 (en) * 2010-04-28 2016-04-27 Снекма Wear-resistant part for support of blade of turbojet fan
US9039379B2 (en) 2011-04-11 2015-05-26 Rolls-Royce Plc Retention device for a composite blade of a gas turbine engine
EP2511480A3 (en) * 2011-04-14 2017-04-19 Rolls-Royce plc Annulus filler system
US9951640B2 (en) 2013-03-05 2018-04-24 Rolls-Royce Corporation Structure and method for providing compliance and sealing between ceramic and metallic structures
WO2014158276A3 (en) * 2013-03-05 2014-12-04 Rolls-Royce Corporation Structure and method for providing compliance and sealing between ceramic and metallic structures
US9593596B2 (en) 2013-03-11 2017-03-14 Rolls-Royce Corporation Compliant intermediate component of a gas turbine engine
WO2014163701A3 (en) * 2013-03-11 2014-12-11 Uskert Richard C Compliant intermediate component of a gas turbine engine and method of assembling this component
CN111075511A (en) * 2013-05-29 2020-04-28 通用电气公司 Composite airfoil metal patch
CN111075511B (en) * 2013-05-29 2023-11-17 通用电气公司 Composite airfoil metal patch
CN103790640B (en) * 2014-02-19 2015-10-28 中国航空动力机械研究所 Anti-wheel disc explosion blade
CN103790640A (en) * 2014-02-19 2014-05-14 中国航空动力机械研究所 Blade capable of preventing wheel dish from being cracked
US10309257B2 (en) 2015-03-02 2019-06-04 Rolls-Royce North American Technologies Inc. Turbine assembly with load pads
EP3139004A1 (en) * 2015-09-02 2017-03-08 General Electric Technology GmbH Turbine blade with ultrasonic wave scattering feature
WO2017036797A1 (en) * 2015-09-02 2017-03-09 General Electric Technology Gmbh Turbine blade with ultrasonic wave scattering feature
CN107923252A (en) * 2015-09-02 2018-04-17 通用电器技术有限公司 Turbo blade with ultrasonic scatterer feature
US10648950B2 (en) 2015-09-02 2020-05-12 General Electric Company Turbine blade with ultrasonic wave scattering feature
CN107923252B (en) * 2015-09-02 2020-10-27 通用电器技术有限公司 Turbine blade with ultrasonic scattering features

Also Published As

Publication number Publication date
FR1163439A (en) 1958-09-25
DE1025421B (en) 1958-03-06

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