US1890581A - Blades for turbine rotors - Google Patents

Blades for turbine rotors Download PDF

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Publication number
US1890581A
US1890581A US421721A US42172130A US1890581A US 1890581 A US1890581 A US 1890581A US 421721 A US421721 A US 421721A US 42172130 A US42172130 A US 42172130A US 1890581 A US1890581 A US 1890581A
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US
United States
Prior art keywords
blade
disk
blades
base
periphery
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 - Lifetime
Application number
US421721A
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English (en)
Inventor
Kohler Gustav
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.)
Siemens Schuckertwerke AG
Siemens AG
Original Assignee
Siemens 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
Priority claimed from DES89180D external-priority patent/DE544623C/de
Priority claimed from DES89128D external-priority patent/DE542423C/de
Priority claimed from DES91524D external-priority patent/DE564790C/de
Application filed by Siemens AG filed Critical Siemens AG
Application granted granted Critical
Publication of US1890581A publication Critical patent/US1890581A/en
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type

Definitions

  • Myinvention relates to improvements in blades for turbine rotors and the method of their manufacture.
  • the blade has a considareas is uite unsuitable for the reat stresses b developing in modern turbines.
  • the blades have a Wedge-shaped base, the load supporting crosssectional area of which progressively decreases from the extreme end portion of the base toward the beginning of the blade proper, where it emerges from the disk periphery.
  • a form of blade is thus obtained which has a cross-section conforming with the shape requirements for withstanding the great stresses developing in modern turbines, and being free from any sudden clianges in cross-sectional area, undercuts, notches, thickened portions or beads, such as are present in the prior art suggestions of axially insertedbladebases,with their incident internal stresses and the stresses upon the material at the disk periphery.
  • FIG. 1 represents the face view of a portion of the disk periphery with the blade bases inserted into the slots, the blades being indicated in transverse section taken at a distance from the base,
  • Figs. 2 and 3 represent transverse sections of the disk rim with a portion of a blade, these figures showing different modes of locking the blade bases to the rim,
  • Fig. 4 shows in a developed face view of the disk periphery a further modification of securing the blades on the disk.
  • Fig. 5 represents a sectionof a multi-disk rotor portion, showing the relative position between the rotor and stator blades, and
  • Fig. 6 represents in side elevation a portion of the disk rim with the blades in place.
  • FIG. 1 of the drawings shows a portionof the wheel periphery face with.:
  • the slot for the blade is designed as a portion of a conical ring more clearly shown at C in Fig. 6, with the common axis m for,
  • the wheel disks 1 may, for instance as shown in Fig. 2, be slightly undercut at a distance from the periphery, so that the bases of the blades 2 project by a small amount into this undercut position. These projectingbase portions may be conveniently upset or peened over the slot edges.
  • Another way of locking the blades in position is to provide the bases with a bore close to the wheel periphery, through which is threaded a wire 3, which rests in a central peripheral groove provided in the wheel as shown in Fig. 3 of the drawings.
  • the slot for the blade base may also be made so that it enters at one side of the rim,
  • Fig. 4 which represents a face view of a portion of the wheel rim developed into a straight plane. 4 is the outer wheel periphery, 5 are the milled slots which do not extend across the entire width of the wheel.
  • the blades may be held in position similar to the manner shown in Fig. 3.
  • the novel kind of blading is not only of special advantage for turbines composed of individual wheel disks but also for turbine constructions in which a plurality of disks are combined into a unit.
  • Very broad stationary guide blades are then required, however. If, on the other hand, my improved blading is made use of in which enlarged rims, or the like are omitted, the disks lot) iiu
  • a turbine rotor disk having rigid blades extending radially from the disk periphery and having at least one curved medium guide surface, each blade having a solid base integral with the blade and being insertable into the disk rim in the direction of the disk axis, said base having a thickness, measured in the circumferential direction of the disk, which gradually increases from the blade thickness measured at the disk periphery, toward the extreme base end, whereby the transverse sectional area of the base is gradually increased toward the base end in amounts to form together with the blade a structure of substantially uniform strength.
  • a turbine rotor disk having radially extending axially inserted blades, each blade having a base forming on one side a continuation of one blade surface, said base, measured in the circumferential direction of the disk, having a thickness gradually increasing from the blade thickness at the disk periphery toward the extreme base end, the longitudinal sides of said base forming parts of the inner and outer surface of an annular rotary body.
  • a turbine rotor disk having radially extending axially inserted blades, each blade having a base forming on the blade side facing against the direction of rotation a continuation of the blade surface, said base, measured in the circumferential direction of the disk, having a thickness gradually increasingfrom the blade thickness at the disk periphery toward the extreme base end in amounts to form a blade body of substantially constant strength, the longitudinal sides of said base forming parts of the inner and outer surface of a cone-shaped ring.
  • a turbine rotor disk having radially extending axially inserted blades, each blade having a base forming on the blade side facing against the direction of rotation a continuation of the blade surface, said base, measured in the circumferential direction of the disk, having a-thickness gradually increasing from the blade thickness at the disk periphery toward the extreme base end in amounts to form a blade body of substantially constant strength, the longitudinal sides of said base forming parts of the inner and outer surfaces of a cone-shaped ring, whose center of rotation is located outside of the rotor disk periphery.
  • a turbine rotor disk having rigid blades extending radially from the disk periphery and having at least one curved medium guide surface, each blade having a solid base integral with the blade and being insertable into the disk rim in the direction of the disk axis, said base having a thickness, measured in the circumferential direction of the disk, which gradually increases from the blade thickness, measured at the disk periphery, toward the extreme base end, whereby the transverse-sectional area of the base is gradually increased toward the base end in amounts to form together with the blade a structure of substantially uniform strength, said disk having substantially axially di rected slots in its periphery conforming with

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US421721A 1928-12-29 1930-01-18 Blades for turbine rotors Expired - Lifetime US1890581A (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DES89180D DE544623C (de) 1928-12-29 1928-12-29 Von der Seite in das Rad eingesetzte Turbinenschaufel
DES89128D DE542423C (de) 1928-12-29 1928-12-29 In axialer Richtung eingesetzte Turbinenlaufschaufel mit verstaerktem Fuss
DES91524D DE564790C (de) 1929-05-04 1929-05-04 Verfahren zur Herstellung von Schaufelnuten fuer in Achsrichtung einzusetzende Turbinenschaufeln

Publications (1)

Publication Number Publication Date
US1890581A true US1890581A (en) 1932-12-13

Family

ID=27212865

Family Applications (1)

Application Number Title Priority Date Filing Date
US421721A Expired - Lifetime US1890581A (en) 1928-12-29 1930-01-18 Blades for turbine rotors

Country Status (5)

Country Link
US (1) US1890581A (ru)
BE (1) BE366550A (ru)
FR (2) FR687114A (ru)
GB (3) GB335841A (ru)
NL (1) NL27859C (ru)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2415847A (en) * 1943-05-08 1947-02-18 Westinghouse Electric Corp Compressor apparatus
US2421890A (en) * 1944-11-27 1947-06-10 Goetaverken Ab Turbine blade
US2660413A (en) * 1950-02-03 1953-11-24 Rolls Royce Locking arrangement for blading of axial-flow turbines and compressors
US2781998A (en) * 1950-03-07 1957-02-19 Centrax Power Units Ltd Bladed rotors
US2781962A (en) * 1951-07-26 1957-02-19 Gen Motors Corp Blade fastening means
US2807436A (en) * 1952-03-25 1957-09-24 Gen Motors Corp Turbine wheel and bucket assembly
US3986793A (en) * 1974-10-29 1976-10-19 Westinghouse Electric Corporation Turbine rotating blade
US4050134A (en) * 1974-10-29 1977-09-27 Westinghouse Electric Corporation Method for removing rotatable blades without removing the casting of a turbine
US4767275A (en) * 1986-07-11 1988-08-30 Westinghouse Electric Corp. Locking pin system for turbine curved root side entry closing blades
US4895490A (en) * 1988-11-28 1990-01-23 The United States Of America As Represented By The Secretary Of The Air Force Internal blade retention system for rotary engines
US4915587A (en) * 1988-10-24 1990-04-10 Westinghouse Electric Corp. Apparatus for locking side entry blades into a rotor
US5720596A (en) * 1997-01-03 1998-02-24 Westinghouse Electric Corporation Apparatus and method for locking blades into a rotor
EP2282010A1 (de) * 2009-06-23 2011-02-09 Siemens Aktiengesellschaft Laufschaufel für eine axial durchströmbare Turbomaschine

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1053420A (ru) * 1964-08-11
US4053257A (en) * 1976-02-20 1977-10-11 Westinghouse Electric Corporation Stator vane assembly for gas turbines
DE3507274A1 (de) * 1985-03-01 1986-09-04 Arthur Pfeiffer Vakuumtechnik Wetzlar Gmbh, 6334 Asslar Scheiben mit schaufeln hoher stabilitaet fuer turbomolekularpumpen

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2415847A (en) * 1943-05-08 1947-02-18 Westinghouse Electric Corp Compressor apparatus
US2421890A (en) * 1944-11-27 1947-06-10 Goetaverken Ab Turbine blade
US2660413A (en) * 1950-02-03 1953-11-24 Rolls Royce Locking arrangement for blading of axial-flow turbines and compressors
US2781998A (en) * 1950-03-07 1957-02-19 Centrax Power Units Ltd Bladed rotors
US2781962A (en) * 1951-07-26 1957-02-19 Gen Motors Corp Blade fastening means
US2807436A (en) * 1952-03-25 1957-09-24 Gen Motors Corp Turbine wheel and bucket assembly
US3986793A (en) * 1974-10-29 1976-10-19 Westinghouse Electric Corporation Turbine rotating blade
US4050134A (en) * 1974-10-29 1977-09-27 Westinghouse Electric Corporation Method for removing rotatable blades without removing the casting of a turbine
US4767275A (en) * 1986-07-11 1988-08-30 Westinghouse Electric Corp. Locking pin system for turbine curved root side entry closing blades
US4915587A (en) * 1988-10-24 1990-04-10 Westinghouse Electric Corp. Apparatus for locking side entry blades into a rotor
US4895490A (en) * 1988-11-28 1990-01-23 The United States Of America As Represented By The Secretary Of The Air Force Internal blade retention system for rotary engines
US5720596A (en) * 1997-01-03 1998-02-24 Westinghouse Electric Corporation Apparatus and method for locking blades into a rotor
EP2282010A1 (de) * 2009-06-23 2011-02-09 Siemens Aktiengesellschaft Laufschaufel für eine axial durchströmbare Turbomaschine
CN102459819A (zh) * 2009-06-23 2012-05-16 西门子公司 用于轴流式涡轮机的动叶片和用于动叶片的装配装置
CN102459819B (zh) * 2009-06-23 2014-10-22 西门子公司 用于轴流式涡轮机的动叶片和用于动叶片的装配装置
US8951016B2 (en) 2009-06-23 2015-02-10 Siemens Aktiengesellschaft Rotor blade for an axial flow turbomachine and mounting for such a rotor blade

Also Published As

Publication number Publication date
GB345359A (en) 1931-03-26
GB346480A (en) 1931-04-16
FR687114A (fr) 1930-08-05
BE366550A (ru)
NL27859C (ru)
FR687343A (fr) 1930-08-07
GB335841A (ru) 1930-10-02

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