US2573621A - Elastic fluid turbine - Google Patents

Elastic fluid turbine Download PDF

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Publication number
US2573621A
US2573621A US733663A US73366347A US2573621A US 2573621 A US2573621 A US 2573621A US 733663 A US733663 A US 733663A US 73366347 A US73366347 A US 73366347A US 2573621 A US2573621 A US 2573621A
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US
United States
Prior art keywords
blades
discs
rotor
turbine
stages
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
US733663A
Other languages
English (en)
Inventor
Sterland Ernest George
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.)
English Electric Co Ltd
Original Assignee
English Electric Co Ltd
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 English Electric Co Ltd filed Critical English Electric Co Ltd
Application granted granted Critical
Publication of US2573621A publication Critical patent/US2573621A/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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections

Definitions

  • Circular grooves are machined in the opposing surfaces of at least some of the discs near their circumferences, and additional rows of blades, with their roots profiled complementarily to said grooves in order to secure fixing, are inserted into the said grooves between such adjacent discs, th rotor blades on the individual discs being arranged substantially on the centre planes of discs engaged by rotor blades inserted in the profiles between adjacent discs on both sides, and being arranged off-set from the centre planes of discs engaged on one side only by rotor blades inserted into the circumferential grooves of adjacent discs, the off-set being away from the inserted blades.
  • Fig. 1 is a part of an elevation in section of a turbine according to the invention.
  • Fig. 2 is a detail on a larger scale.
  • the solid rotor I has a bore 2 for internal inspection of the forging and is sub-divided into discs 3, 4, 5, 6, by deep annular recesses I, 8, 9, machined into the rotor body. Thus these discs are integral with the solid centre portion adjacent the bore 2 of the rotor I.
  • the blades of four stages ll, I2, I4 and I6 of the turbine are arranged in the usual Way on the discs 3, 4, 5 and 6 respectively, and additional rows of blades I3 and I 5 are inserted into the gaps between discs 4, 5 and 5, 6 respectively.
  • the turbine stator 20 and the guide vanes 2I to 26 for the turbine stages II to I6 are indicated diagrammatically for completeness but do not in themselves differ from the usual design of such components.
  • serrations Il are arranged in the roots of the blades, such as 15, and complementary serrations I8 in the opposite surfaces of adjacent discs, such as 5 and 6, near their circumference.
  • the serrations I1 and I8 are interlocked and transmit forces from the turbine blades to the respective discs.
  • the roots of the blades I5 or I3 may be for example T-shaped as shown for the roots of blades I6, and engage appropriately shaped grooves on the adjacent discs instead of the serrations shown.
  • th turbine blades I2 and I6 are offset from the centre planes of their respective discs 4 and 6 towards the sides away from the adjacent row of additional inserted blades I3, I5 respectively. This is done in order to balance the forces transmitted from the blades I3 and E5 to one side of each of the respective discs 4, 6.
  • the blades such as I4 are arranged substantially on the centre line.
  • the number of inserted stages is shown to be two in Fig. 1 but obviously as many such stages can be arranged as required by the overall number of stages and the particular design of the turbine.
  • no such additional blades have been inserted between the stages marked H and I2 in order that the stresses in the disc 3 which carries the blades II and whicla fis expose dag higl temperatures, be kept as ,lQw as. possible.)
  • a row of additional blades could be arranged between stages H and [2 as well. n.i,-. .M.
  • the rotor blades on the individual discs being 2 a'rrang'd substantially on the centre planes of g I dl scs engaged by rotor blades inserted in the profil consisting of a central body andudisc s integral with the said central body, said disc sloeing fgir; cumferentially grooved on opposing sides near the circumference thereof, rows of rotor -blades blades "between adjacent discs on both sides, and

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US733663A 1946-03-21 1947-03-10 Elastic fluid turbine Expired - Lifetime US2573621A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB265292X 1946-03-21

Publications (1)

Publication Number Publication Date
US2573621A true US2573621A (en) 1951-10-30

Family

ID=10245054

Family Applications (1)

Application Number Title Priority Date Filing Date
US733663A Expired - Lifetime US2573621A (en) 1946-03-21 1947-03-10 Elastic fluid turbine

Country Status (2)

Country Link
US (1) US2573621A (fr)
CH (1) CH265292A (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110052371A1 (en) * 2008-02-13 2011-03-03 Emil Aschenbruck Multi-Component Bladed Rotor for a Turbomachine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB751740A (en) * 1953-10-02 1956-07-04 English Electric Co Ltd Improvements in and relating to the fixing of rotor blades of axial flow turbines and compressors

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1118361A (en) * 1914-06-19 1914-11-24 Gen Electric Wheel for elastic-fluid turbines.
GB383252A (en) * 1932-01-25 1932-11-10 Bbc Brown Boveri & Cie Improvements in and relating to reaction turbines
US1967962A (en) * 1933-09-09 1934-07-24 John F Metten Steam turbine rotor

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1118361A (en) * 1914-06-19 1914-11-24 Gen Electric Wheel for elastic-fluid turbines.
GB383252A (en) * 1932-01-25 1932-11-10 Bbc Brown Boveri & Cie Improvements in and relating to reaction turbines
US1967962A (en) * 1933-09-09 1934-07-24 John F Metten Steam turbine rotor

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110052371A1 (en) * 2008-02-13 2011-03-03 Emil Aschenbruck Multi-Component Bladed Rotor for a Turbomachine
US8784064B2 (en) * 2008-02-13 2014-07-22 Man Diesel & Turbo Se Multi-component bladed rotor for a turbomachine

Also Published As

Publication number Publication date
CH265292A (fr) 1949-11-30

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