US3765793A - Turbine rotors - Google Patents

Turbine rotors Download PDF

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Publication number
US3765793A
US3765793A US00166378A US3765793DA US3765793A US 3765793 A US3765793 A US 3765793A US 00166378 A US00166378 A US 00166378A US 3765793D A US3765793D A US 3765793DA US 3765793 A US3765793 A US 3765793A
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United States
Prior art keywords
core
central part
radially
root portions
rotor
Prior art date
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Expired - Lifetime
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US00166378A
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English (en)
Inventor
G Savonuzzi
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Fiat SpA
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Fiat SpA
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Publication date
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Publication of US3765793A publication Critical patent/US3765793A/en
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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
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means

Definitions

  • ABSTRACT A turbine rotor is described, particularly for motor vehicle gas turbines, in which a number of identical blade root portions, each formed integrally with a respective turbine blade, are secured, for example by welding, to a central rotor disc, the adjoining outer faces of the root portions forming two substantially continous annular faces, minimising drag on the rotor when in use.
  • this invention relates to a turbine rotor of the type comprising a central disc having a number of blades extending radially therefrom.
  • a solution hitherto adapted to solve this problem is to make turbine rotors for motor vehicles in one piece with blades formed integrally with a central disc, generally by casting.
  • Rotors of this type are satisfactory from the mechanical point of view because cast blades have in general better resistance to corrosion than machine blades.
  • the already high cost of the rotors described above is further increased by the high cost of the machining operations to which the cast rotors have to be subjected.
  • the thin radial slots in the central disc are formed by means of very thin diamond drills which are easily broken.
  • this invention provides a turbine rotor in which the central disc is formed by a monolithic central part having a cylindrical outer surface and a number of identical root portions arranged circumferentially adjacent each other so as to form an annular crown secured to the central part and having two substantially continuous annular faces adjoining the end faces of the central part, the root portions being each formed integrally with a respective turbine blade.
  • each of the root portions extends radially outwardly from the central part and has a thickness equal to that of the latter, the root portion having at its radially inner end facing the central part a cylindrical surface portion joined to the outer cylindrical surface of the central part by welding.
  • reference numeral 1 indicates generally a turbine rotor comprising a central disc 2 and a number of blades 3 extending radially from the central disc 2 and evenly distributed around the outer periphery of the latter.
  • the central disc 2 itself comprises a central part 4 formed in one piece and having a cylindrical outer surface and a central hub 5.
  • the hub 5 permits the mounting of the rotor l on a turbine shaft (not illustrated) adapted to be driven by the rotor.
  • the central disc 2 is formed with an outer annular crown 6 formed by a number of identical segmental root portions 7 arranged side-by-side circumferentially around the rotor disc 2.
  • the root portions 7 are equal in number to the number of blades 3 and each root portion 7 is formed in one piece, generally by casting, with the respective blade 3.
  • Each root portion 7 comprises (FIG. 4) two face plates 8 and 9 with flat external faces substantially parallel to each other, a core 10 interposed between the two plates 8 and 9 and connected thereto and a bridge piece 11 connected to the core 10 and spanning the radially outer ends of the plates 8 and 9.
  • the respective blade 3 is connected to the bridge piece 11 and projects rotor illustrated in FIG. I
  • Each of the plates 8 and 9 has a shape in plan which is substantially trapezoidal with the smaller base radially innermost and adjoining the outer cylindrical surface of the central part 4 of the rotor disc 2.
  • the bridge piece 11 is on the other hand arranged parallel to the outer cylindrical surface of the central part 4 and interconnects the larger bases of the trapezoidal face plates 8 and 9.
  • the bridge piece 11 has a cylindrical outer surface portion l2, which when the root portion 7 is assembled on the rotor disc 2, is coaxial with the cylindrical outer surface of the central part 4 of the disc.
  • the blade 3 extends radially from the central part of the cylindrical surface portion 12.
  • the thickness of the core increases radially in wardly from the bridge piece 11, while the width of the core 10 decreases radially inwardly from the bridge piece 1 l.
  • the core 10 is connected to the inside surface of the bridge piece 11 along a band which extends substantially parallel to the axis of the central part 4, along the middle part of the inside surface of the piece 11.
  • the core 10 has a substantially rectangular cross section at its radially inner end, being connected to the inside surfaces of the plates 8 and 9 along substantially the entire width of said plates.
  • the radially inner surfaces of the plates 8 and 9 and of the core 10 together form a cylindrical surface por-' tion 13 which is rectangular in plan and which is joined to the outer cylindrical surface of the monolithic central part 4 of the rotor disc 2 by deep welding, generally by means of electron beam welding.
  • each radial chamber 16 communicates with a central axial duct 17 in the central part 4 by way of a respective radial conduit 18 (FIG. 3).
  • Each radial chamber 16 also communicates with a cavity 3a (broken outline) formedwithin the respective blade 3, by way of a further conduit 3b, shown diagrammatically in broken outline.
  • each root portion 7 forming the outer crown 6 is joined in the central part 4 of the rotor disc 2 at its radially inner end, independently of the adjacent root portions 7. in consequence small radial clearances are formed between neighbouring root portions 7 guaranteeing sufficient elasticity to the outer crown 6 of the rotor disc 2. Furthermore, the root portions 7 can warp radially independently of each other without causing internal stresses leading to fracture of the central disc 2 of the rotor 1.
  • each root portion 7 and the respective blade 3 are formed in one piece by casting.
  • Each portion 7 is subsequently welded on the central part 4 of the rotor 1.
  • the outer crown 6 it is, however, possible to form the outer crown 6 from a number of groups of root portions 7 welded on the central part 4: the root portions 7 forming each group are firmly joined to each other for example the group may be cast in one piece and each group forms, together with its respective blades 3, a single piece separately welded to the central part 4.
  • a turbine rotor comprising a central disc having a monolithic central part provided with two end faces, a cylindrical outer surface and a plurality of identical turbine blades having root portions welded to the central part and arranged circumferentially adjacent each other to form an annular crown having two substantially continuous annular faces contiguous with the end faces of the central part, each of said root portions comprising two parallel face plates with flat outer surfaces, a core interposed between and connected to said face plate, and a bridge piece connected to said core and interconnecting the radially outer ends of said two faced plates, said bridge piece supporting the respective blades on its radially outer surface, said core and said two face plates having radially inner end surfaces defining a cylindrical radially inner surface portion of the root portion complementary in curvature to the cylindrical outer surface of the central part, said core and said two face plates of each root portion delimiting, together with the core and face plates of adjacent root portions, two circumferentially adjacent radially extending chambers closed at their radially outermost ends by adjacent ridge pieces

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US00166378A 1970-07-27 1971-07-26 Turbine rotors Expired - Lifetime US3765793A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
IT6958270 1970-07-27

Publications (1)

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US3765793A true US3765793A (en) 1973-10-16

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ID=11312429

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US00166378A Expired - Lifetime US3765793A (en) 1970-07-27 1971-07-26 Turbine rotors

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Country Link
US (1) US3765793A (ja)
DE (1) DE2137527A1 (ja)
GB (1) GB1302661A (ja)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3873234A (en) * 1971-11-10 1975-03-25 Robert Noel Penny Turbine rotor
US4538331A (en) * 1983-02-14 1985-09-03 Williams International Corporation Method of manufacturing an integral bladed turbine disk
US4573876A (en) * 1983-02-14 1986-03-04 Williams International Corporation Integral bladed disk
US5035579A (en) * 1988-11-22 1991-07-30 Hitachi, Ltd. Water-turbine runner and process for manufacturing the same
CN101403394A (zh) * 2007-10-04 2009-04-08 通用电气公司 盘形转子及其制造方法
US20130108445A1 (en) * 2011-10-28 2013-05-02 Gabriel L. Suciu Spoked rotor for a gas turbine engine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015001615B4 (de) 2015-02-07 2019-02-14 Ronny Ulrich Reese Vorrichtung zur Erzeugung kinetischer Energie, Einrichtung zur Komprimierung und Verfahren zur Gewinnung elektrischer Energie

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2384919A (en) * 1942-11-05 1945-09-18 Sulzer Ag Turbine blade attachment by welding
FR1029185A (fr) * 1950-12-07 1953-06-01 Perfectionnement au refroidissement des aubes dans les turbines à gaz
US3097824A (en) * 1958-11-26 1963-07-16 Bendix Corp Turbine, wheel containment
US3297301A (en) * 1964-08-11 1967-01-10 Rolls Royce Bladed rotor for use in a fluid flow machine
DE1808069A1 (de) * 1968-11-09 1970-08-06 Motoren Turbinen Union Laufrad mit gekuehlten oder ungekuehlten Laufschaufeln
US3556676A (en) * 1968-08-28 1971-01-19 Igor Konstantinovich Gorbunov Liquid-cooling system of gas turbine rotors

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2384919A (en) * 1942-11-05 1945-09-18 Sulzer Ag Turbine blade attachment by welding
FR1029185A (fr) * 1950-12-07 1953-06-01 Perfectionnement au refroidissement des aubes dans les turbines à gaz
US3097824A (en) * 1958-11-26 1963-07-16 Bendix Corp Turbine, wheel containment
US3297301A (en) * 1964-08-11 1967-01-10 Rolls Royce Bladed rotor for use in a fluid flow machine
US3556676A (en) * 1968-08-28 1971-01-19 Igor Konstantinovich Gorbunov Liquid-cooling system of gas turbine rotors
DE1808069A1 (de) * 1968-11-09 1970-08-06 Motoren Turbinen Union Laufrad mit gekuehlten oder ungekuehlten Laufschaufeln

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3873234A (en) * 1971-11-10 1975-03-25 Robert Noel Penny Turbine rotor
US4538331A (en) * 1983-02-14 1985-09-03 Williams International Corporation Method of manufacturing an integral bladed turbine disk
US4573876A (en) * 1983-02-14 1986-03-04 Williams International Corporation Integral bladed disk
US5035579A (en) * 1988-11-22 1991-07-30 Hitachi, Ltd. Water-turbine runner and process for manufacturing the same
CN101403394A (zh) * 2007-10-04 2009-04-08 通用电气公司 盘形转子及其制造方法
US20090092494A1 (en) * 2007-10-04 2009-04-09 General Electric Company Disk rotor and method of manufacture
US20130108445A1 (en) * 2011-10-28 2013-05-02 Gabriel L. Suciu Spoked rotor for a gas turbine engine
US9938831B2 (en) * 2011-10-28 2018-04-10 United Technologies Corporation Spoked rotor for a gas turbine engine
US10760423B2 (en) 2011-10-28 2020-09-01 Raytheon Technologies Corporation Spoked rotor for a gas turbine engine

Also Published As

Publication number Publication date
DE2137527A1 (de) 1972-03-16
GB1302661A (ja) 1973-01-10

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