US20130330198A1 - Turbine Rotor and Blade Assembly with Blind Holes - Google Patents

Turbine Rotor and Blade Assembly with Blind Holes Download PDF

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Publication number
US20130330198A1
US20130330198A1 US13/489,495 US201213489495A US2013330198A1 US 20130330198 A1 US20130330198 A1 US 20130330198A1 US 201213489495 A US201213489495 A US 201213489495A US 2013330198 A1 US2013330198 A1 US 2013330198A1
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US
United States
Prior art keywords
rotor
blade
locking
turbine rotor
turbine
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.)
Abandoned
Application number
US13/489,495
Inventor
Thomas Joseph Farineau
Nicholas Andrew Tisencheck
Mehmet M. Dede
James Royce Howes
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Priority to US13/489,495 priority Critical patent/US20130330198A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: DEDE, MEHMET M., HOWES, JAMES ROYCE, FARINEAU, THOMAS JOSEPH, TISENCHEK, NICHOLAS ANDREW
Priority to EP13170089.0A priority patent/EP2672067A1/en
Priority to JP2013116554A priority patent/JP2013253597A/en
Priority to RU2013125740/06A priority patent/RU2013125740A/en
Priority to CN2013102228997A priority patent/CN103470307A/en
Publication of US20130330198A1 publication Critical patent/US20130330198A1/en
Abandoned 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
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • 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
    • 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
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • 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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/11—Purpose of the control system to prolong engine life
    • F05D2270/114—Purpose of the control system to prolong engine life by limiting mechanical stresses

Definitions

  • the present application and the resultant patent relate generally to turbo-machinery and more particularly relate to a turbine rotor and blade assembly for use with a steam turbine having redundant locking blade retention screw holes for reduced tangential stress.
  • Steam turbine airfoils or buckets generally are positioned about a rotor at regular intervals in a bucket assembly.
  • the bucket assembly may be created by inserting the buckets one at a time tangentially into an opening on the rotor and then sliding the buckets circumferentially about the rotor.
  • the buckets may be attached to the rotor by complementary male and female dovetails and other configurations. In order to close the bucket assembly, however, the last bucket must be restrained by a feature other than a dovetail.
  • This last bucket generally called the locking blade or the closure bucket, may be affixed to the rotor via one or more blade retention screws and the like tapped or screwed into the rotor. Other types of connection means and other types of bucket assemblies also may be used.
  • centrifugal loads may be placed on the buckets and the rotor during operation.
  • Such centrifugal loads and coincident thermally induced loads associated with loading transients may induce stresses in the dovetails and adjacent areas that attach the buckets to the rotor. These stresses may be of sufficient magnitude to impact adversely rotor cycle fatigue life.
  • rotor stress concentrations associated with blade retention screws may be tapped or otherwise inserted directly into the rotor.
  • an improved turbine rotor and blade assembly for a steam turbine and the like.
  • an improved turbine rotor and blade assembly may reduce tangential thermal stresses therein for an improved overall rotor fatigue life.
  • the present application and the resultant patent thus provide a turbine rotor and blade assembly for a steam turbine.
  • the turbine rotor and blade assembly may include a rotor, a number of buckets positioned about the rotor, a locking blade positioned about the rotor, and a blind hole positioned about the rotor adjacent to the locking blade.
  • the present application and the resultant patent further provide a turbine rotor and blade assembly for a steam turbine.
  • the turbine rotor and blade assembly described herein may include a rotor, a number of buckets positioned about the rotor, a locking blade positioned about the rotor, a locking blade retention screw securing the locking blade to the rotor, and a blind hole positioned about the rotor adjacent to the locking blade.
  • the present application and the resultant patent further provide a steam turbine.
  • the steam turbine described herein may include a rotor, a number of buckets positioned about the rotor, a locking blade positioned about the rotor, a locking blade retention hole positioned about the locking blade, a locking blade retention screw positioned in the locking blade retention hole so as to secure the locking blade to the rotor, and one or more blind holes positioned about the rotor adjacent to the locking blade.
  • FIG. 1 is a schematic diagram of an example of a steam turbine with a number of sections.
  • FIG. 2 is a partial perspective view of a turbine rotor and blade assembly as may be described herein.
  • FIG. 1 is a schematic diagram of an example of a steam turbine 10 as may be used herein.
  • the steam turbine 10 may include a first section 15 and a second section 20 .
  • the sections 15 , 20 may be high pressure sections, intermediate pressure sections, and/or low pressure sections. Each of the sections 15 , 20 may have a number of stages therein.
  • An outer shell or casing 25 may be divided axially into upper and lower half sections 30 , 35 , respectively.
  • a rotor shaft 40 may extend through the casing 25 and may be supported by a number of journal bearings 45 .
  • a number of seals 50 also may surround the rotor shaft 40 about the ends and elsewhere.
  • a central section 55 may include one or more steam inlets 60 .
  • a flow splitter 65 may extend between the sections 15 , 20 .
  • a flow of steam 70 passes through the steam inlets 60 and into the sections 15 , 20 such that mechanical work may be extracted from the steam by the stages therein so as to rotate the rotor shaft 40 .
  • the flow of steam 70 then may exit the sections 15 , 20 for further processing and the like.
  • the steam turbine 10 described herein is for the purpose of example only. Steam turbines and/or other types of turbo-machinery in many other configurations and with many other or different components also may be used herein.
  • FIG. 2 shows a portion of a steam turbine 100 as may be described herein.
  • the steam turbine 100 may include a turbine rotor and blade assembly 110 .
  • the turbine rotor and blade assembly 110 includes a turbine rotor 120 .
  • the turbine rotor 120 includes a dovetail slot 130 formed therein.
  • a number of buckets 140 may be mounted on the rotor 120 via tangential entry and the like.
  • Each of the buckets 140 may include a blade 150 and a dovetail 160 .
  • the dovetail 160 may be configured to mate with the conforming dovetail slot 130 (or vice versa) of the rotor 120 .
  • the rotor 120 and the buckets 140 may have any size, shape, or configuration. Other components and other configurations may be used herein.
  • the turbine rotor and blade assembly 110 also may include a locking blade 170 .
  • the locking blade 170 lacks the dovetail 160 . Rather, a base 180 of the locking blade 170 may be retained within the rotor 120 via a number of blade retention screws 190 and the like.
  • the blade retention screws 190 may be grub screws or other types of set screws and the like with or without a head on one end. Each blade retention screw 190 may be positioned in a blade retention hole 200 .
  • the blade retention hole 200 may extend into the rotor 120 adjacent to the locking blade 170 as well as into the base 180 of the locking blade 170 so as to retain the locking blade 170 therein. Any number of the blade retention screws 190 may be used.
  • the respective components described herein may have any size, shape, or configuration. Other components and other configurations also may be used herein.
  • the turbine rotor and blade assembly 110 therefore may have a number of blind holes 210 formed therein.
  • the blind holes 210 may be positioned in the rotor 120 on either or both sides of the blade retention hole 200 .
  • the blind holes 210 may be placed about the locking blade 170 on both axial and radial sides thereof.
  • the blind holes 210 may have a similar size, shape, and configuration as compared to the blade retention holes 200 .
  • the blind holes 210 also may have any size, shape, or configuration. Blind holes 210 of differing sizes, shapes, or configurations also may be used herein together. Any number of the blind holes 210 may be used herein.
  • the blind holes 210 thus may improve the fatigue life of the turbine rotor and blade assembly 110 by “shielding” the blade retention holes 200 from local stress fields and the like.
  • the blind holes 210 may straddle the blade retention holes 200 tangentially so as to protect the blade retention holes 200 from potentially damaging tangential stresses.
  • the blind holes 200 thus may improve the fatigue life of the rotor 120 and related components for an extended component lifetime.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The present application provides a turbine rotor and blade assembly for a steam turbine. The turbine rotor and blade assembly may include a rotor, a number of buckets positioned about the rotor, a locking blade positioned about the rotor, and a blind hole positioned about the rotor adjacent to the locking blade.

Description

    TECHNICAL FIELD
  • The present application and the resultant patent relate generally to turbo-machinery and more particularly relate to a turbine rotor and blade assembly for use with a steam turbine having redundant locking blade retention screw holes for reduced tangential stress.
    • BACKGROUND OF THE INVENTION
  • Steam turbine airfoils or buckets generally are positioned about a rotor at regular intervals in a bucket assembly. The bucket assembly may be created by inserting the buckets one at a time tangentially into an opening on the rotor and then sliding the buckets circumferentially about the rotor. The buckets may be attached to the rotor by complementary male and female dovetails and other configurations. In order to close the bucket assembly, however, the last bucket must be restrained by a feature other than a dovetail. This last bucket, generally called the locking blade or the closure bucket, may be affixed to the rotor via one or more blade retention screws and the like tapped or screwed into the rotor. Other types of connection means and other types of bucket assemblies also may be used.
  • Large centrifugal loads may be placed on the buckets and the rotor during operation. Such centrifugal loads and coincident thermally induced loads associated with loading transients may induce stresses in the dovetails and adjacent areas that attach the buckets to the rotor. These stresses may be of sufficient magnitude to impact adversely rotor cycle fatigue life. Of particular concern may be rotor stress concentrations associated with blade retention screws that may be tapped or otherwise inserted directly into the rotor.
  • There is thus a desire for an improved turbine rotor and blade assembly for a steam turbine and the like. Preferably such an improved turbine rotor and blade assembly may reduce tangential thermal stresses therein for an improved overall rotor fatigue life.
    • SUMMARY OF THE INVENTION
  • The present application and the resultant patent thus provide a turbine rotor and blade assembly for a steam turbine. The turbine rotor and blade assembly may include a rotor, a number of buckets positioned about the rotor, a locking blade positioned about the rotor, and a blind hole positioned about the rotor adjacent to the locking blade.
  • The present application and the resultant patent further provide a turbine rotor and blade assembly for a steam turbine. The turbine rotor and blade assembly described herein may include a rotor, a number of buckets positioned about the rotor, a locking blade positioned about the rotor, a locking blade retention screw securing the locking blade to the rotor, and a blind hole positioned about the rotor adjacent to the locking blade.
  • The present application and the resultant patent further provide a steam turbine. The steam turbine described herein may include a rotor, a number of buckets positioned about the rotor, a locking blade positioned about the rotor, a locking blade retention hole positioned about the locking blade, a locking blade retention screw positioned in the locking blade retention hole so as to secure the locking blade to the rotor, and one or more blind holes positioned about the rotor adjacent to the locking blade.
  • These and other features and improvements of the present application and the resultant patent will become apparent to one of ordinary skill in the art upon review of the following detailed description when taken in conjunction with the several drawings and the appended claims.
    • BRIEF DESCRIPTION OF THE DRAWINGS
  • FIG. 1 is a schematic diagram of an example of a steam turbine with a number of sections.
  • FIG. 2 is a partial perspective view of a turbine rotor and blade assembly as may be described herein.
    •  DETAILED DESCRIPTION
  • Referring now to the drawings, in which like numerals refer to like elements throughout the several views, FIG. 1 is a schematic diagram of an example of a steam turbine 10 as may be used herein. The steam turbine 10 may include a first section 15 and a second section 20. The sections 15, 20 may be high pressure sections, intermediate pressure sections, and/or low pressure sections. Each of the sections 15, 20 may have a number of stages therein. An outer shell or casing 25 may be divided axially into upper and lower half sections 30, 35, respectively. A rotor shaft 40 may extend through the casing 25 and may be supported by a number of journal bearings 45. A number of seals 50 also may surround the rotor shaft 40 about the ends and elsewhere. A central section 55 may include one or more steam inlets 60. A flow splitter 65 may extend between the sections 15, 20.
  • In use, a flow of steam 70 passes through the steam inlets 60 and into the sections 15, 20 such that mechanical work may be extracted from the steam by the stages therein so as to rotate the rotor shaft 40. The flow of steam 70 then may exit the sections 15, 20 for further processing and the like. The steam turbine 10 described herein is for the purpose of example only. Steam turbines and/or other types of turbo-machinery in many other configurations and with many other or different components also may be used herein.
  • FIG. 2 shows a portion of a steam turbine 100 as may be described herein. Specifically, the steam turbine 100 may include a turbine rotor and blade assembly 110. The turbine rotor and blade assembly 110 includes a turbine rotor 120. The turbine rotor 120 includes a dovetail slot 130 formed therein. A number of buckets 140 may be mounted on the rotor 120 via tangential entry and the like. Each of the buckets 140 may include a blade 150 and a dovetail 160. The dovetail 160 may be configured to mate with the conforming dovetail slot 130 (or vice versa) of the rotor 120. The rotor 120 and the buckets 140 may have any size, shape, or configuration. Other components and other configurations may be used herein.
  • The turbine rotor and blade assembly 110 also may include a locking blade 170. As described above, the locking blade 170 lacks the dovetail 160. Rather, a base 180 of the locking blade 170 may be retained within the rotor 120 via a number of blade retention screws 190 and the like. The blade retention screws 190 may be grub screws or other types of set screws and the like with or without a head on one end. Each blade retention screw 190 may be positioned in a blade retention hole 200. The blade retention hole 200 may extend into the rotor 120 adjacent to the locking blade 170 as well as into the base 180 of the locking blade 170 so as to retain the locking blade 170 therein. Any number of the blade retention screws 190 may be used. The respective components described herein may have any size, shape, or configuration. Other components and other configurations also may be used herein.
  • As was described above, tangential thermal stresses may tend to develop about the blade retention holes 200 during operation. The turbine rotor and blade assembly 110 therefore may have a number of blind holes 210 formed therein. The blind holes 210 may be positioned in the rotor 120 on either or both sides of the blade retention hole 200. The blind holes 210 may be placed about the locking blade 170 on both axial and radial sides thereof. The blind holes 210 may have a similar size, shape, and configuration as compared to the blade retention holes 200. The blind holes 210, however, also may have any size, shape, or configuration. Blind holes 210 of differing sizes, shapes, or configurations also may be used herein together. Any number of the blind holes 210 may be used herein.
  • The blind holes 210 thus may improve the fatigue life of the turbine rotor and blade assembly 110 by “shielding” the blade retention holes 200 from local stress fields and the like. The blind holes 210 may straddle the blade retention holes 200 tangentially so as to protect the blade retention holes 200 from potentially damaging tangential stresses. The blind holes 200 thus may improve the fatigue life of the rotor 120 and related components for an extended component lifetime.
  • It should be apparent that the foregoing relates only to certain embodiments of the present application and the resultant patent. Numerous changes and modifications may be made herein by one of ordinary skill in the art without departing from the general spirit and scope of the invention as defined by the following claims and the equivalents thereof.

Claims (20)

We claim:
1. A turbine rotor and blade assembly for a steam turbine, comprising:
a rotor;
a plurality of buckets positioned about the rotor;
a locking blade positioned about the rotor; and
a blind hole positioned about the rotor adjacent to the locking blade.
2. The turbine rotor and blade assembly of claim 1, wherein the locking blade comprises a base.
3. The turbine rotor and blade assembly of claim 2, further comprising one or more blade retention holes extending into the rotor and the base of the locking blade.
4. The turbine rotor and blade assembly of claim 3, further comprising a blade retention screw extending into each blade retention hole so as to secure the locking blade to the rotor.
5. The turbine rotor and blade assembly of claim 3, wherein the blind hole and the one or more blade retention holes comprise a similar depth.
6. The turbine rotor and blade assembly of claim 1, wherein the rotor comprises a dovetail slot and wherein the plurality of buckets is positioned therein.
7. The turbine rotor and blade assembly of claim 6, wherein each of the plurality of buckets comprises a dovetail for mating with the dovetail slot.
8. The turbine rotor and blade assembly of claim 7, wherein each of the plurality of buckets comprises a blade extending from the dovetail.
9. The turbine rotor and blade assembly of claim 1, further comprising a plurality of blind holes.
10. The turbine rotor and blade assembly of claim 1, further comprising a first blind hole on a first axial side of the locking blade and a second blind hole on a second axial side of the locking blade.
11. The turbine rotor and blade assembly of claim 1, further comprising a first blind hole on a first radial side of the locking blade and a second blind hole on a second radial side of the locking blade.
12. A turbine rotor and blade assembly for a steam turbine, comprising:
a rotor;
a plurality of buckets positioned about the rotor;
a locking blade positioned about the rotor;
a locking blade retention screw securing the locking blade to the rotor; and
a blind hole positioned about the rotor adjacent to the locking blade.
13. The turbine rotor and blade assembly of claim 12, wherein the locking blade comprises a base and wherein the locking blade retention screw extends into the base.
14. The turbine rotor and blade assembly of claim 12, further comprising one or more blade retention holes extending into the rotor and the base of the locking blade for the blade retention screw.
15. The turbine rotor and blade assembly of claim 14, wherein the blind hole and the one or more blade retention holes comprise a similar depth.
16. The turbine rotor and blade assembly of claim 12, wherein the rotor comprises a dovetail slot and wherein the plurality of buckets is positioned therein.
17. The turbine rotor and blade assembly of claim 12, further comprising a plurality of blind holes.
18. The turbine rotor and blade assembly of claim 12, further comprising a first blind hole on a first axial side of the locking blade and a second blind hole on a second axial side of the locking blade.
19. The turbine rotor and blade assembly of claim 12, further comprising a first blind hole on a first radial side of the locking blade and a second blind hole on a second radial side of the locking blade.
20. A steam turbine, comprising:
a rotor;
a plurality of buckets positioned about the rotor;
a locking blade positioned about the rotor;
a locking blade retention hole positioned about the locking blade;
a locking blade retention screw positioned in the locking blade retention hole to secure the locking blade to the rotor; and
one or more blind holes positioned about the rotor adjacent to the locking blade.
US13/489,495 2012-06-06 2012-06-06 Turbine Rotor and Blade Assembly with Blind Holes Abandoned US20130330198A1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US13/489,495 US20130330198A1 (en) 2012-06-06 2012-06-06 Turbine Rotor and Blade Assembly with Blind Holes
EP13170089.0A EP2672067A1 (en) 2012-06-06 2013-05-31 Turbine rotor and blade assembly with blind holes and corresponding steam turbine
JP2013116554A JP2013253597A (en) 2012-06-06 2013-06-03 Turbine rotor and blade assembly with blind hole
RU2013125740/06A RU2013125740A (en) 2012-06-06 2013-06-05 TURBINE SHOVEL UNIT FOR STEAM TURBINE (OPTIONS) AND STEAM TURBINE
CN2013102228997A CN103470307A (en) 2012-06-06 2013-06-06 Turbine rotor and blade assembly with blind holes

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/489,495 US20130330198A1 (en) 2012-06-06 2012-06-06 Turbine Rotor and Blade Assembly with Blind Holes

Publications (1)

Publication Number Publication Date
US20130330198A1 true US20130330198A1 (en) 2013-12-12

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US13/489,495 Abandoned US20130330198A1 (en) 2012-06-06 2012-06-06 Turbine Rotor and Blade Assembly with Blind Holes

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US (1) US20130330198A1 (en)
EP (1) EP2672067A1 (en)
JP (1) JP2013253597A (en)
CN (1) CN103470307A (en)
RU (1) RU2013125740A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140363300A1 (en) * 2013-06-11 2014-12-11 General Electric Company Closure bucket for turbo-machine
US9988918B2 (en) 2015-05-01 2018-06-05 General Electric Company Compressor system and airfoil assembly
US10465537B2 (en) 2016-05-27 2019-11-05 General Electric Company Margin bucket dovetail radial support feature for axial entry buckets
US11433535B2 (en) * 2020-09-01 2022-09-06 Daegu Gyeongbuk Institute Of Science And Technology Series elastic actuator
US11555407B2 (en) 2020-05-19 2023-01-17 General Electric Company Turbomachine rotor assembly

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US1829881A (en) * 1930-04-05 1931-11-03 Allis Chalmers Mfg Co Turbine blade mounting
DE1197095B (en) * 1959-07-10 1965-07-22 Siemens Ag Shovel lock
US20070048130A1 (en) * 2005-08-24 2007-03-01 General Electric Company Stacked steampath and grooved bucket wheels for steam turbines
US7874806B2 (en) * 2006-10-20 2011-01-25 Rolls-Royce Plc Turbomachine rotor blade and a turbomachine rotor
US7901187B2 (en) * 2006-06-23 2011-03-08 Siemens Energy, Inc. Turbine rotor blade groove entry slot lock structure

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NL5896C (en) * 1918-01-21 1900-01-01
NL64087C (en) * 1946-05-04 1900-01-01
GB854548A (en) * 1958-07-25 1960-11-23 Westinghouse Electric Corp Improvements in or relating to bladed rotors, for example of turbines
DE102012200057A1 (en) * 2012-01-03 2013-07-04 Siemens Aktiengesellschaft Attaching a lock blade to a rotor unit

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1829881A (en) * 1930-04-05 1931-11-03 Allis Chalmers Mfg Co Turbine blade mounting
DE1197095B (en) * 1959-07-10 1965-07-22 Siemens Ag Shovel lock
US20070048130A1 (en) * 2005-08-24 2007-03-01 General Electric Company Stacked steampath and grooved bucket wheels for steam turbines
US7901187B2 (en) * 2006-06-23 2011-03-08 Siemens Energy, Inc. Turbine rotor blade groove entry slot lock structure
US7874806B2 (en) * 2006-10-20 2011-01-25 Rolls-Royce Plc Turbomachine rotor blade and a turbomachine rotor

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140363300A1 (en) * 2013-06-11 2014-12-11 General Electric Company Closure bucket for turbo-machine
US9366146B2 (en) * 2013-06-11 2016-06-14 General Electric Company Closure bucket for turbo-machine
US9988918B2 (en) 2015-05-01 2018-06-05 General Electric Company Compressor system and airfoil assembly
US10465537B2 (en) 2016-05-27 2019-11-05 General Electric Company Margin bucket dovetail radial support feature for axial entry buckets
US11555407B2 (en) 2020-05-19 2023-01-17 General Electric Company Turbomachine rotor assembly
US11433535B2 (en) * 2020-09-01 2022-09-06 Daegu Gyeongbuk Institute Of Science And Technology Series elastic actuator

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RU2013125740A (en) 2014-12-10
EP2672067A1 (en) 2013-12-11
CN103470307A (en) 2013-12-25
JP2013253597A (en) 2013-12-19

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