US3790303A - Gas turbine bucket - Google Patents

Gas turbine bucket Download PDF

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Publication number
US3790303A
US3790303A US00241165A US3790303DA US3790303A US 3790303 A US3790303 A US 3790303A US 00241165 A US00241165 A US 00241165A US 3790303D A US3790303D A US 3790303DA US 3790303 A US3790303 A US 3790303A
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United States
Prior art keywords
bucket
blade
gas turbine
root
turbine bucket
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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
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US00241165A
Inventor
W Endres
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BBC Brown Boveri AG Switzerland
BBC Brown Boveri France SA
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BBC Brown Boveri France SA
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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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion

Definitions

  • ABSTRACT In a gas turbine bucket, having a blade and a root,
  • the blade is reinforced by eutectic fibers disposed in grain-orientated form, whilst in the root of the bucket the structure is nonorientated and enjoys a desirably high impact strength and ductility.
  • the prior art discloses gas turbine buckets which are reinforced by eutectic fibers, solidified in grainorientated form. They suffer from the disadvantage of having only a low notch impact strength. While a low notch impact strength in the blade of the bucket does not result in any substantial disadvantages, the bucket root itself suffers from the serious disadvantage that it is unable to deform itself sufficiently in the zone at which it is joined to the rotor.
  • An object of the present invention is to provide a gas turbine bucket, the blade of which is reinforced in known manner by eutectic fibers but having sufficient impact strength in the bucket root.
  • the crystals embedded in the parent material are formed as fibers disposed longitudinally in parallel to the bucket blade and extending into the bucket root, the bucket root having a non-orientated structure.
  • FIG. 1 is a gas turbine bucket in section
  • FIG. 2 is an apparatus forproducing a gas turbine bucket of the-kind illustrated in FIG. 1.
  • FIG. 1 shows a gas turbine bucket 1 comprising a bucket blade 2 and a bucket root 3.
  • the gas turbine bucket l is composed 'of a eutectic alloy, the bucket blade having been subjected to grain-oriented solidification.
  • the crystals embedded in the parent material 4 take the form of longitudinally parallel fibers 5 extending from the outer end of the bucket blade 2 through the blade and into the bucket root 3.
  • a gas turbine bucket of this kind is constructed as follows.
  • a melt of a pseudo binary eutectic alloy Co1 ,,Cr Cr ,Co,C containing in weight percentages, 56.] percent cobalt, 40 percent chromium and 2.4 percent carbon, is cast into a precision mold of corundum.
  • the precision mold 6 is introduced into a graphite succeptor 7 which may be inductively heated by means of a heating spiral 8. To this endthe precision mold 6 is introduced into the graphite succeptor 7 so that the bucket blade 2 and the upper quarter of the bucket root 3 are disposed in the graphite succeptor 7 while the lower part of the bucket root 3 extends from the aforementioned succeptor, as shown in FIG. 2.
  • the graphite succeptor 7 is heated to a temperature between .1 ,400 and l,600 C. and is maintained at the aforementioned temperature. Since the melting temperature of the alloy is 1,310 C., the melt forming the bucket blade is retained in the superheated, fluid state while the bucket root 3 solidifies. After solidification of the bucket root 3, the graphite succeptor 7 is moved upwardly in the direction of the arrow and axially relative to the precision mold 6, the velocity of the said motion being between 5 and cm/h. Accordingly, the melt solidifies in the upper quarter of the bucket root 3 and then in the bucket blade 2, the solidification front moving from the bucket root 3 to the upper end of the bucket blade 2. The gas turbine blade may be stripped from the mold as soon as the precision mold 6 has been entirely withdrawn from the graphite succeptor 7 and the melt has solidified.
  • the blade structure is reinforced by eutectic fibers which are solidified in grain-oriented form, whilst in the root per se of the bucket the structure is non-oriented, as is illustrated in FIG. 1, and has an advantageous ductility at the operating temperature of the turbine bucket.
  • the method is also suitable for the following alloys:
  • Gas turbine bucket formed of a eutectic alloy and having a root and a bIade,-said blade having a crystalline structure oriented in parallel to the longitudinal orientation of the bucket blade whilst in the bucket root the structure is not grain-oriented and is ductile at the operating temperature of the turbine.
  • Gas turbine bucket according to claim 1 in the blade of which crystals embedded in matrix are present as fibers disposed longitudinally in parallel to the blade and extend through the blade and to the root per se.
  • the eutectic alloy is a member of the group of alloys consisting of CoCrC, NbNb C, Ta'Ta C,
  • Ni-Ni Nb Ni Ni Ti, NiAlvCr, CoTiC, Ni-TaC,
  • the alloy is a CoCrC alloy consisting essentially of 56.1 wt. percent cobalt, 40 wt. percent chromium and 2.4 wt. percent carbon.

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

Abstract

In a gas turbine bucket, having a blade and a root, composed of a eutectic alloy the blade is reinforced by eutectic fibers disposed in grain-orientated form, whilst in the root of the bucket the structure is non-orientated and enjoys a desirably high impact strength and ductility.

Description

United States Patent [1 1 Endres GAS TURBINE BUCKET [75] Inventor: Wilhelm Endres, Ennetbaden, Switzerland [73] Assignee: Aktiengesellschaft Brown, Boveri &
Cie, Baden, Switzerland [22] Filed: Apr. 5, 1972 [21] Appl. No.: 241,165
[30] Foreign Application Priority Data Apr. 8, 1971 Switzerland 5225/71 [52] US. Cl. 416/241 [51] Int. Cl. Fold 5/28 [58] Field of Search 416/241; 164/60, 122, 125, 164/127 [56] References Cited UNITED STATES PATENTS v 2,422,193 6/1947 Hague 416/241 UX Feb. 5, 1974 3,044,746 7/1962 Stargardter 416/241 3,260,505 7/1966 Ver Snyder... 416/214 X 3,342,455 9/1967 Fleck et al. 416/241 3,494,709 2/1970 Piearcey 416/241 X Primary Examiner-Everette A. Powell, Jr. Attorney, Agent, or Firm-Ralph B. Parker et al.
[5 7] ABSTRACT In a gas turbine bucket, having a blade and a root,
composed of a eutectic alloy the blade is reinforced by eutectic fibers disposed in grain-orientated form, whilst in the root of the bucket the structure is nonorientated and enjoys a desirably high impact strength and ductility.
4 Claims, 2 Drawing Figures 1 GAS TURBINE BUCKET This invention relates to turbine buckets, and is concerned with the development of quite different properties in different parts of the bucket, the chemical composition of the metal in the bucket being the same in both blade and root.
The prior art discloses gas turbine buckets which are reinforced by eutectic fibers, solidified in grainorientated form. They suffer from the disadvantage of having only a low notch impact strength. While a low notch impact strength in the blade of the bucket does not result in any substantial disadvantages, the bucket root itself suffers from the serious disadvantage that it is unable to deform itself sufficiently in the zone at which it is joined to the rotor.
An object of the present invention is to provide a gas turbine bucket, the blade of which is reinforced in known manner by eutectic fibers but having sufficient impact strength in the bucket root.
According to the invention this and other inventive objects are achieved in that in the gas turbine bucket, which is constructed of a eutectic alloy, the crystals embedded in the parent material are formed as fibers disposed longitudinally in parallel to the bucket blade and extending into the bucket root, the bucket root having a non-orientated structure.
The invention will now be explained in greater detail I hereinbelow, and with reference to the accompanying schematic drawing, in which:
FIG. 1 is a gas turbine bucket in section; and
FIG. 2 is an apparatus forproducing a gas turbine bucket of the-kind illustrated in FIG. 1. FIG. 1 shows a gas turbine bucket 1 comprising a bucket blade 2 and a bucket root 3. The gas turbine bucket l is composed 'of a eutectic alloy, the bucket blade having been subjected to grain-oriented solidification. The crystals embedded in the parent material 4 take the form of longitudinally parallel fibers 5 extending from the outer end of the bucket blade 2 through the blade and into the bucket root 3. A gas turbine bucket of this kind is constructed as follows.
A melt of a pseudo binary eutectic alloy Co1 ,,Cr Cr ,Co,C containing in weight percentages, 56.] percent cobalt, 40 percent chromium and 2.4 percent carbon, is cast into a precision mold of corundum. The precision mold 6 is introduced into a graphite succeptor 7 which may be inductively heated by means of a heating spiral 8. To this endthe precision mold 6 is introduced into the graphite succeptor 7 so that the bucket blade 2 and the upper quarter of the bucket root 3 are disposed in the graphite succeptor 7 while the lower part of the bucket root 3 extends from the aforementioned succeptor, as shown in FIG. 2.
The graphite succeptor 7 is heated to a temperature between .1 ,400 and l,600 C. and is maintained at the aforementioned temperature. Since the melting temperature of the alloy is 1,310 C., the melt forming the bucket blade is retained in the superheated, fluid state while the bucket root 3 solidifies. After solidification of the bucket root 3, the graphite succeptor 7 is moved upwardly in the direction of the arrow and axially relative to the precision mold 6, the velocity of the said motion being between 5 and cm/h. Accordingly, the melt solidifies in the upper quarter of the bucket root 3 and then in the bucket blade 2, the solidification front moving from the bucket root 3 to the upper end of the bucket blade 2. The gas turbine blade may be stripped from the mold as soon as the precision mold 6 has been entirely withdrawn from the graphite succeptor 7 and the melt has solidified.
By practicing this technique the blade structure is reinforced by eutectic fibers which are solidified in grain-oriented form, whilst in the root per se of the bucket the structure is non-oriented, as is illustrated in FIG. 1, and has an advantageous ductility at the operating temperature of the turbine bucket.
The method is also suitable for the following alloys:
' Co, ,,Cr TaC CoTaC Ni, ,,Cr -TaC. I claim: 1. Gas turbine bucket formed of a eutectic alloy and having a root and a bIade,-said blade having a crystalline structure oriented in parallel to the longitudinal orientation of the bucket blade whilst in the bucket root the structure is not grain-oriented and is ductile at the operating temperature of the turbine.
2. Gas turbine bucket according to claim 1, in the blade of which crystals embedded in matrix are present as fibers disposed longitudinally in parallel to the blade and extend through the blade and to the root per se.
3. Gas turbine bucket according to claim 1, in which the eutectic alloy is a member of the group of alloys consisting of CoCrC, NbNb C, Ta'Ta C,
Ni-Ni Nb, Ni Ni Ti, NiAlvCr, CoTiC, Ni-TaC,
' the alloy is a CoCrC alloy consisting essentially of 56.1 wt. percent cobalt, 40 wt. percent chromium and 2.4 wt. percent carbon.

Claims (3)

  1. 2. Gas turbine bucket according to claim 1, in the blade of which crystals embedded in matrix are present as fibers disposed longitudinally in parallel to the blade and extend through the blade and to the root per se.
  2. 3. Gas turbine bucket according to claim 1, in which the eutectic alloy is a member of the group of alloys consisting of Co-Cr-C, Nb-Nb2C, Ta-Ta2C, Ni-Ni3Nb, Ni-Ni3Ti, NiAl-Cr, Co-TiC, Ni-TaC, Co-VC, NiAl-Ni3Nb, Ni3-Al-Ni3Ta, Co1 x-Crx-TaC, Co-TaC, and Ni1 x-Crx-TaC.
  3. 4. Gas turbine bucket according to claim 3, wherein the alloy is a Co-Cr-C alloy consisting essentially of 56.1 wt. percent cobalt, 40 wt. percent chromium and 2.4 wt. percent carbon.
US00241165A 1971-04-08 1972-04-05 Gas turbine bucket Expired - Lifetime US3790303A (en)

Applications Claiming Priority (1)

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CH522571A CH544217A (en) 1971-04-08 1971-04-08 Gas turbine blade

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CH (1) CH544217A (en)
DE (1) DE2122353C3 (en)
FR (1) FR2136170A5 (en)
GB (1) GB1377137A (en)

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4103063A (en) * 1976-03-23 1978-07-25 United Technologies Corporation Ceramic-metallic eutectic structural material
US4190094A (en) * 1978-10-25 1980-02-26 United Technologies Corporation Rate controlled directional solidification method
US4540038A (en) * 1984-06-05 1985-09-10 Westinghouse Electric Corp. Method for production of combustion turbine blade having a hybrid structure
US4637448A (en) * 1984-08-27 1987-01-20 Westinghouse Electric Corp. Method for production of combustion turbine blade having a single crystal portion
US4659288A (en) * 1984-12-10 1987-04-21 The Garrett Corporation Dual alloy radial turbine rotor with hub material exposed in saddle regions of blade ring
US4712604A (en) * 1986-10-14 1987-12-15 The United States Of America As Represented By The Secretary Of The Air Force Apparatus for casting directionally solidified articles
US4850802A (en) * 1983-04-21 1989-07-25 Allied-Signal Inc. Composite compressor wheel for turbochargers
US5451142A (en) * 1994-03-29 1995-09-19 United Technologies Corporation Turbine engine blade having a zone of fine grains of a high strength composition at the blade root surface
US5468548A (en) * 1993-08-02 1995-11-21 United Technologies Corporation Directionally solidified eutectic reinforcing fibers and fiber reinforced composites containing the fibers
EP1818510A1 (en) * 2006-02-08 2007-08-15 Siemens Aktiengesellschaft Turbine blade, especially for a gas turbine or a steam turbine
US20110293431A1 (en) * 2009-01-21 2011-12-01 Harald Harders Component having varying structures and method for production
WO2015148994A3 (en) * 2014-03-27 2015-11-26 General Electric Company Article for use in high stress environments having multiple grain structures
WO2017168777A1 (en) * 2016-03-31 2017-10-05 三菱重工業株式会社 Turbine blade designing method, turbine blade manufacturing method, and turbine blade
US10287896B2 (en) * 2013-09-17 2019-05-14 United Technologies Corporation Turbine blades and manufacture methods

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4464094A (en) * 1979-05-04 1984-08-07 Trw Inc. Turbine engine component and method of making the same
US4921405A (en) * 1988-11-10 1990-05-01 Allied-Signal Inc. Dual structure turbine blade
US5106266A (en) * 1989-07-25 1992-04-21 Allied-Signal Inc. Dual alloy turbine blade
CA2060884A1 (en) * 1989-07-25 1991-01-26 Frederick G. Borns Dual alloy turbine blade
EP0513407B1 (en) * 1991-05-13 1995-07-19 Asea Brown Boveri Ag Method of manufacture of a turbine blade
DE4219469A1 (en) * 1992-06-13 1993-12-16 Asea Brown Boveri Component subject to high temperatures, in particular turbine blade, and method for producing this component
DE4219470A1 (en) * 1992-06-13 1993-12-16 Asea Brown Boveri Component for high temperatures, in particular turbine blade, and method for producing this component
DE4432999C2 (en) * 1994-09-16 1998-07-30 Mtu Muenchen Gmbh Impeller of a turbomachine, in particular an axially flow-through turbine of a gas turbine engine
EP2716386A1 (en) * 2012-10-08 2014-04-09 Siemens Aktiengesellschaft Gas turbine component, process for the production of same and casting mould for the use of this method

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2422193A (en) * 1944-06-12 1947-06-17 Westinghouse Electric Corp Method of making cast turbine blading
US3044746A (en) * 1960-05-18 1962-07-17 Gen Electric Fluid-flow machinery blading
US3260505A (en) * 1963-10-21 1966-07-12 United Aircraft Corp Gas turbine element
US3342455A (en) * 1964-11-24 1967-09-19 Trw Inc Article with controlled grain structure
US3494709A (en) * 1965-05-27 1970-02-10 United Aircraft Corp Single crystal metallic part

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2422193A (en) * 1944-06-12 1947-06-17 Westinghouse Electric Corp Method of making cast turbine blading
US3044746A (en) * 1960-05-18 1962-07-17 Gen Electric Fluid-flow machinery blading
US3260505A (en) * 1963-10-21 1966-07-12 United Aircraft Corp Gas turbine element
US3342455A (en) * 1964-11-24 1967-09-19 Trw Inc Article with controlled grain structure
US3494709A (en) * 1965-05-27 1970-02-10 United Aircraft Corp Single crystal metallic part

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4103063A (en) * 1976-03-23 1978-07-25 United Technologies Corporation Ceramic-metallic eutectic structural material
US4190094A (en) * 1978-10-25 1980-02-26 United Technologies Corporation Rate controlled directional solidification method
US4850802A (en) * 1983-04-21 1989-07-25 Allied-Signal Inc. Composite compressor wheel for turbochargers
US4540038A (en) * 1984-06-05 1985-09-10 Westinghouse Electric Corp. Method for production of combustion turbine blade having a hybrid structure
US4637448A (en) * 1984-08-27 1987-01-20 Westinghouse Electric Corp. Method for production of combustion turbine blade having a single crystal portion
US4659288A (en) * 1984-12-10 1987-04-21 The Garrett Corporation Dual alloy radial turbine rotor with hub material exposed in saddle regions of blade ring
US4712604A (en) * 1986-10-14 1987-12-15 The United States Of America As Represented By The Secretary Of The Air Force Apparatus for casting directionally solidified articles
US5468548A (en) * 1993-08-02 1995-11-21 United Technologies Corporation Directionally solidified eutectic reinforcing fibers and fiber reinforced composites containing the fibers
US5451142A (en) * 1994-03-29 1995-09-19 United Technologies Corporation Turbine engine blade having a zone of fine grains of a high strength composition at the blade root surface
EP1818510A1 (en) * 2006-02-08 2007-08-15 Siemens Aktiengesellschaft Turbine blade, especially for a gas turbine or a steam turbine
US20110293431A1 (en) * 2009-01-21 2011-12-01 Harald Harders Component having varying structures and method for production
US10287896B2 (en) * 2013-09-17 2019-05-14 United Technologies Corporation Turbine blades and manufacture methods
US11008875B2 (en) * 2013-09-17 2021-05-18 Raytheon Technologies Corporation Turbine blades and manufacture methods
WO2015148994A3 (en) * 2014-03-27 2015-11-26 General Electric Company Article for use in high stress environments having multiple grain structures
CN107073571A (en) * 2014-03-27 2017-08-18 通用电气公司 With multiple grainiesses for the product that is used in high stress environment
WO2017168777A1 (en) * 2016-03-31 2017-10-05 三菱重工業株式会社 Turbine blade designing method, turbine blade manufacturing method, and turbine blade
KR20180112047A (en) * 2016-03-31 2018-10-11 미츠비시 쥬고교 가부시키가이샤 Method of designing turbine blades, manufacturing method of turbine blades and turbine blades
CN108779680A (en) * 2016-03-31 2018-11-09 三菱重工业株式会社 The design method of turbo blade, the manufacturing method of turbo blade and turbo blade
CN108779680B (en) * 2016-03-31 2020-10-02 三菱重工业株式会社 Method for designing turbine blade, method for manufacturing turbine blade, and turbine blade
US10975700B2 (en) 2016-03-31 2021-04-13 Mitsubishi Heavy Industries, Ltd. Turbine blade designing method, turbine blade manufacturing method, and turbine blade

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Publication number Publication date
FR2136170A5 (en) 1972-12-22
DE2122353B2 (en) 1974-02-14
CH544217A (en) 1973-11-15
DE2122353A1 (en) 1973-06-14
GB1377137A (en) 1974-12-11
DE2122353C3 (en) 1977-07-28

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