US3857650A - Vaned rotor for gas turbines - Google Patents

Vaned rotor for gas turbines Download PDF

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US3857650A
US3857650A US00408335A US40833573A US3857650A US 3857650 A US3857650 A US 3857650A US 00408335 A US00408335 A US 00408335A US 40833573 A US40833573 A US 40833573A US 3857650 A US3857650 A US 3857650A
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rotor
vanes
coil
vaned
support surface
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US00408335A
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R Cerrato
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Fiat SpA
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Fiat SpA
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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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of 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
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding

Definitions

  • ABSTRACT A vaned rotor of the type comprising a central metal hub or rotor body carrying a plurality of rotor blades made of a ceramic material, in which the blades are simply located on the rotor body and held in place by a coil of carbon fibres or ceramic fibres which surrounds the blades.
  • each blade has a transverse part at the radially outer end thereof, which is partly cylindrical and which together with the transverse parts of the other blades, forms a substantially cylindrical support surface for the coil.
  • This invention relates to vaned rotors for gas turbines, and particularly to rotors of the type having a metal body and a number of ceramic vanes attached at the root thereof to the rotor body. Such rotors are particularly suited to operate in gases at a very high temperature.
  • ceramic materials used for such vanes have much better physical properties at high temperatures (i.e., over l,lC than any metal alloy, especially if undergoing compression loads, they are nevertheless very difficult to couple to metal parts because of their relative fragility, lack of ductility, and their low coefficient of expansion.
  • the present invention seeks to provide a vaned rotor for a gas turbine, of the type having a metal rotor body and ceramic vanes, in which the above mentioned inconveniences are overcome.
  • a vaned rotor for a gas turbine of the type comprising a rotor having a metal rotor body and a plurality of ceramic vanes attached to the periphery of the metal body, in which each vane has a transverse part at the radially outer end thereof, the said transverse parts of the vanes together forming a support surface around which is wound a coil of substantially inextensible filaments, the coil acting to absorb the radial forces exerted on the vanes of the rotor during use.
  • FIG. 1 is a view in axial section of part ofa rotor for a gas turbine, formed as an embodiment of this invention; and 1 FIG. 2 is a partial face view of the rotor illustrated in FIG. 1.
  • the periphery 12 of the disc 10 has a number of grooves which extend parallel to the axis of the disc, in which the roots 16 of a number of vanes 18 are located.
  • the shape of the grooves 20 is not important as far as this invention is concerned and can be any suitable shape instead of that shown; for example they could have a which are orthogonal to the grooves 20.
  • the vanes 18 are made of a ceramic material and at the radially outer end each has a transverse portion 22, formed as a part-cylindrical surface coaxial with the disc 10.
  • Each transverse portion 22 is integral with the vane 18 on which it is formed, and is provided with axially spaced, circumferentially extending lateral shoulders or borders 24 and 26.
  • the combined transverse portions 22 of all the vanes 18 forms an effectively continuous cylindrical surface around which is wound a coil 28 formed by filaments of ceramic fibres or carbon fibres having-a high modulus of elasticity.
  • the coil of filaments acts to hold the vanes 18 on the disc 10 and to maintain them in position during operation of the turbine without relying on any form of coupling at the roots of the vanes.
  • the fibres used are sensitive to oxidation they can be protected, during winding of the coil onto the cylindrical surface formed by the transverse parts of the vanes, with a thin layer of liquid ceramic, which after baking will encapsulate the fibres isolating them from the oxidising agents; alternatively metallization before or after the winding operation may be effected.
  • a vaned rotor for a gas turbine of the type comprising:
  • each vane has a transverse part at the radially outer end thereof, said transverse parts of said vanes together forming a support surface
  • each said vane is a partly cylindrical surface, said partly cylindrical surfaces together forming a substantially continuous cylindrical support surface, two lateral shoulders on said radially outer surface of each said transverse part, said shoulders being axially spaced and extending sub stantially circumferentially of said cylindrical surface,

Abstract

A vaned rotor of the type comprising a central metal hub or rotor body carrying a plurality of rotor blades made of a ceramic material, in which the blades are simply located on the rotor body and held in place by a coil of carbon fibres or ceramic fibres which surrounds the blades. To form a support surface for the coil each blade has a transverse part at the radially outer end thereof, which is partly cylindrical and which together with the transverse parts of the other blades, forms a substantially cylindrical support surface for the coil.

Description

United States Patent '[191 Cerrato [30] Foreign Application Priority Data Oct. 23, 1972 Italy 70323/72 [52] U.S. Cl 416/218, 416/189, 416/195 [51] Int. Cl. .L. Fld 5/24 [58] Field of Search 416/191, 192, 190, 195, 416/196, 218, 189, 194; 415/214 [56] References Cited UNITED STATES PATENTS 3,042,366 7/1962 Holmquist 416/241 X 3,095,138 6/1963 Wamken 416/190 3,403,844 /1968 Stoffer 415/214 UX 3,556,675 1/1971 Howald et a1 416/190 3,601,500 8/1971 Palfreyman et al.'.... 416/190 3,754,839 8/1973 Bodman..;. 416/l [451 Dec. 31, 1974 FOREIGN PATENTS OR APPLICATIONS 223,227 12/1958 Australia 416/ 997,219 9/1951 France..... 415/214 55,020 12/1950 France 415/214 Primary Examiner-Everette A. Powell, Jr. Attorney, Agent, or Firm-Sughrue, Rothwell, Mion, Zinn & MacPeak [5 7] ABSTRACT A vaned rotor of the type comprising a central metal hub or rotor body carrying a plurality of rotor blades made of a ceramic material, in which the blades are simply located on the rotor body and held in place by a coil of carbon fibres or ceramic fibres which surrounds the blades. To form a support surface for the coil each blade has a transverse part at the radially outer end thereof, which is partly cylindrical and which together with the transverse parts of the other blades, forms a substantially cylindrical support surface for the coil.
6 Claims, 2 Drawing Figures VANED ROTOR FOR GAS TURBINES This invention relates to vaned rotors for gas turbines, and particularly to rotors of the type having a metal body and a number of ceramic vanes attached at the root thereof to the rotor body. Such rotors are particularly suited to operate in gases at a very high temperature.
Although ceramic materials used for such vanes (silicon nitride, silicon carbide, alumina, etc.) have much better physical properties at high temperatures (i.e., over l,lC than any metal alloy, especially if undergoing compression loads, they are nevertheless very difficult to couple to metal parts because of their relative fragility, lack of ductility, and their low coefficient of expansion.
Because of the lack of ductility of ceramic materials, the driving forces exerted during operation of the rotor give rise to a concentration of the load in parts of the coupling areas between the ceramic vanes and the metal body of the rotor. This frequently causes breakages in these parts. The various systems presently in use for attaching a ceramic blade by the root to a metal rotor body for a gas turbine are generally inadequate because these systems, including dovetail fixings having both straight and curved sides, do not take sufficient account of the rigidity and relative fragility of the ceramic vanes.
This problem is exacerbated by the fact that present manufacturing techniques for ceramic materials are still not able to provide a complete homogeneity of composition and structure of the material, so that adjacent areas of ceramic material can vary by up to 200% in tensile strength. For this reason the known types of coupling between a support disc forming a rotor body and rotor vanes of ceramic material, which rely on a wedging action, are not satisfactory.
The present invention seeks to provide a vaned rotor for a gas turbine, of the type having a metal rotor body and ceramic vanes, in which the above mentioned inconveniences are overcome.
According to the present invention, there is provided a vaned rotor for a gas turbine, of the type comprising a rotor having a metal rotor body and a plurality of ceramic vanes attached to the periphery of the metal body, in which each vane has a transverse part at the radially outer end thereof, the said transverse parts of the vanes together forming a support surface around which is wound a coil of substantially inextensible filaments, the coil acting to absorb the radial forces exerted on the vanes of the rotor during use.
One embodiment of the invention will now be more particularly described, by way of example only, with reference to the accompanying drawings, in which:
FIG. 1 is a view in axial section of part ofa rotor for a gas turbine, formed as an embodiment of this invention; and 1 FIG. 2 is a partial face view of the rotor illustrated in FIG. 1.
Referring now to the drawings there is shown a metal body in the shape of a disc having a central hub. The periphery 12 of the disc 10 has a number of grooves which extend parallel to the axis of the disc, in which the roots 16 of a number of vanes 18 are located. The shape of the grooves 20 is not important as far as this invention is concerned and can be any suitable shape instead of that shown; for example they could have a which are orthogonal to the grooves 20.
The vanes 18 are made of a ceramic material and at the radially outer end each has a transverse portion 22, formed as a part-cylindrical surface coaxial with the disc 10. Each transverse portion 22 is integral with the vane 18 on which it is formed, and is provided with axially spaced, circumferentially extending lateral shoulders or borders 24 and 26. The combined transverse portions 22 of all the vanes 18 forms an effectively continuous cylindrical surface around which is wound a coil 28 formed by filaments of ceramic fibres or carbon fibres having-a high modulus of elasticity. The coil of filaments acts to hold the vanes 18 on the disc 10 and to maintain them in position during operation of the turbine without relying on any form of coupling at the roots of the vanes. The particular feature of ceramic or carbon fibres with a high modulus of elasticity is their very high tensile strength and this is exploited in the construction of the present invention. The forces applied to the vanes are therefore, for the most part, compression forces, and only minimum flexure of the vanes can take place as the tangential forces derived from the action of the gas are very small.
If the fibres used are sensitive to oxidation they can be protected, during winding of the coil onto the cylindrical surface formed by the transverse parts of the vanes, with a thin layer of liquid ceramic, which after baking will encapsulate the fibres isolating them from the oxidising agents; alternatively metallization before or after the winding operation may be effected.
I claim:
1. In a vaned rotor for a gas turbine, of the type comprising:
a rotor. having a metal rotor body,
a plurality of ceramic vanes, and
means for locating the vanes on the periphery of the metal body,
the improvement wherein,
- each vane has a transverse part at the radially outer end thereof, said transverse parts of said vanes together forming a support surface, and
a coil of substantially inextensible filaments, wound around said support surface, said coil acting to absorb all the radial forces exerted on said vanes of said rotor during use.
2. The vaned rotor of claim 1, wherein said coil wound on said support surface formed by said transverse parts of said vanes, comprises a plurality of filaments of a material with a high modulus of elasticity.
3. The vaned rotor of claim 2, wherein said filaments are fibres of a ceramic material.
4. The vaned rotor of claim 2, wherein said filaments are carbon fibres.
5. The vaned rotor of claim 1, wherein the radially outer surface of said transverse parts of each said vane is a partly cylindrical surface, said partly cylindrical surfaces together forming a substantially continuous cylindrical support surface, two lateral shoulders on said radially outer surface of each said transverse part, said shoulders being axially spaced and extending sub stantially circumferentially of said cylindrical surface,
to define therebetween a circumferential channel for said fibres.
6. The vaned rotor of claim 1 wherein said means for locating the vanes on the periphery of the metal body comprise a plurality of grooves in the circumference of said plurality of grooves and intercepting said grooves.

Claims (6)

1. In a vaned rotor for a gas turbine, of the type comprising: a rotor having a metal rotor body, a plurality of ceramic vanes, and means for locating the vanes on the periphery of the metal body, the improvement wherein, - each vane has a transverse part at the radially outer end thereof, said transverse parts of said vanes together forming a support surface, and a coil of substantially inextensible filaments, wound around said support surface, said coil acting to absorb all the radial forces exerted on said vanes of said rotor during use.
2. The vaned rotor of claim 1, wherein said coil wound on said support surface formed by said transverse parts of said vanes, comprises a plurality of filaments of a material with a high modulus of elasticity.
3. The vaned rotor of claim 2, wherein said filaments are fibres of a ceramic material.
4. The vaned rotor of claim 2, wherein said filaments are carbon fibres.
5. The vaned rotor of claim 1, wherein the radially outer surface of said transverse parts of each said vane is a partly cylindrical surface, said partly cylindrical surfaces together forming a substantially continuous cylindrical support surface, two lateral shoulders on said radially outer surface of each said transverse part, said shoulders being axially spaced and extending substantially circumferentially of said cylindrical surface, to define therebetween a circumFerential channel for said fibres.
6. The vaned rotor of claim 1 wherein said means for locating the vanes on the periphery of the metal body comprise a plurality of grooves in the circumference of said rotor body extending parallel to the axis of rotation of said body and a circumferential groove deeper than said plurality of grooves and intercepting said grooves.
US00408335A 1972-10-23 1973-10-23 Vaned rotor for gas turbines Expired - Lifetime US3857650A (en)

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Application Number Priority Date Filing Date Title
IT70323/72A IT975329B (en) 1972-10-23 1972-10-23 STRUCTURE OF STATIC OR ROTATING METALLIC AND NOM METALLIC PARTS FOR HIGH TEMPERATURE ENVIRONMENTS ESPECIALLY FOR ROTORS AND STATE OF GAS TURBINES

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Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4011295A (en) * 1974-10-07 1977-03-08 The Garrett Corporation Ceramic rotor for gas turbine engine
US4017209A (en) * 1975-12-15 1977-04-12 United Technologies Corporation Turbine rotor construction
US4580943A (en) * 1980-12-29 1986-04-08 The United States Of America As Represented By The Secretary Of The Army Turbine wheel for hot gas turbine engine
US4767273A (en) * 1987-02-24 1988-08-30 Westinghouse Electric Corp. Apparatus and method for reducing blade flop in steam turbine
WO1999037888A1 (en) * 1998-01-23 1999-07-29 Diversitech, Inc. Shrouds for gas turbine engines and methods for making the same
US6439844B1 (en) * 2000-12-11 2002-08-27 General Electric Company Turbine bucket cover and brush seal
US20100158675A1 (en) * 2008-12-23 2010-06-24 Snecma Turbomachine rotor having blades of composite material provided with metal labyrinth teeth
GB2483495A (en) * 2010-09-10 2012-03-14 Magna Parva Ltd Rotor blade disc, eg for a turbofan engine, having blades supported by an outer ring
US20140301858A1 (en) * 2011-08-15 2014-10-09 Tsinghua University Rotor device, turbine rotor device, and gas turbine and turbine engine having same
GB2521588A (en) * 2013-10-11 2015-07-01 Reaction Engines Ltd Turbine blades

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2475113A1 (en) * 1980-02-04 1981-08-07 Rockwell International Corp CERAMIC ROTOR FOR TURBINE
DE3842710C1 (en) * 1988-12-19 1989-08-03 Mtu Muenchen Gmbh

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR55020E (en) * 1946-09-20 1951-06-05 High temperature gas turbine
FR997219A (en) * 1945-06-16 1952-01-03 Turbine
US3042366A (en) * 1958-05-05 1962-07-03 Holmquist Ernst Rudolf Magnus Axial flow gas turbine
US3095138A (en) * 1957-05-28 1963-06-25 Studebaker Corp Rotating shroud
US3403844A (en) * 1967-10-02 1968-10-01 Gen Electric Bladed member and method for making
US3556675A (en) * 1969-01-29 1971-01-19 Gen Electric Turbomachinery rotor with integral shroud
US3601500A (en) * 1968-08-28 1971-08-24 Rolls Royce Rotor assembly for a fluid flow machine
US3754839A (en) * 1972-05-01 1973-08-28 United Aircraft Corp Filament reinforced rotor assembly

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR997219A (en) * 1945-06-16 1952-01-03 Turbine
FR55020E (en) * 1946-09-20 1951-06-05 High temperature gas turbine
US3095138A (en) * 1957-05-28 1963-06-25 Studebaker Corp Rotating shroud
US3042366A (en) * 1958-05-05 1962-07-03 Holmquist Ernst Rudolf Magnus Axial flow gas turbine
US3403844A (en) * 1967-10-02 1968-10-01 Gen Electric Bladed member and method for making
US3601500A (en) * 1968-08-28 1971-08-24 Rolls Royce Rotor assembly for a fluid flow machine
US3556675A (en) * 1969-01-29 1971-01-19 Gen Electric Turbomachinery rotor with integral shroud
US3754839A (en) * 1972-05-01 1973-08-28 United Aircraft Corp Filament reinforced rotor assembly

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4011295A (en) * 1974-10-07 1977-03-08 The Garrett Corporation Ceramic rotor for gas turbine engine
US4076456A (en) * 1974-10-07 1978-02-28 The Garrett Corporation Ceramic rotor for gas turbine engine
US4017209A (en) * 1975-12-15 1977-04-12 United Technologies Corporation Turbine rotor construction
US4580943A (en) * 1980-12-29 1986-04-08 The United States Of America As Represented By The Secretary Of The Army Turbine wheel for hot gas turbine engine
US4767273A (en) * 1987-02-24 1988-08-30 Westinghouse Electric Corp. Apparatus and method for reducing blade flop in steam turbine
US6223524B1 (en) 1998-01-23 2001-05-01 Diversitech, Inc. Shrouds for gas turbine engines and methods for making the same
WO1999037888A1 (en) * 1998-01-23 1999-07-29 Diversitech, Inc. Shrouds for gas turbine engines and methods for making the same
US6439844B1 (en) * 2000-12-11 2002-08-27 General Electric Company Turbine bucket cover and brush seal
US20100158675A1 (en) * 2008-12-23 2010-06-24 Snecma Turbomachine rotor having blades of composite material provided with metal labyrinth teeth
US8870531B2 (en) * 2008-12-23 2014-10-28 Snecma Turbomachine rotor having blades of composite material provided with metal labyrinth teeth
GB2483495A (en) * 2010-09-10 2012-03-14 Magna Parva Ltd Rotor blade disc, eg for a turbofan engine, having blades supported by an outer ring
GB2483495B (en) * 2010-09-10 2013-02-13 Magnaparva Space Ltd Mounting of rotor blades
US20140301858A1 (en) * 2011-08-15 2014-10-09 Tsinghua University Rotor device, turbine rotor device, and gas turbine and turbine engine having same
US10378365B2 (en) * 2011-08-15 2019-08-13 Tsinghua University Rotor device, turbine rotor device, and gas turbine and turbine engine having same
GB2521588A (en) * 2013-10-11 2015-07-01 Reaction Engines Ltd Turbine blades

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GB1411316A (en) 1975-10-22
FR2204216A5 (en) 1974-05-17
IT975329B (en) 1974-07-20

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