US2492833A - Rotor for multistage turbines and compressors - Google Patents

Rotor for multistage turbines and compressors Download PDF

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Publication number
US2492833A
US2492833A US710762A US71076246A US2492833A US 2492833 A US2492833 A US 2492833A US 710762 A US710762 A US 710762A US 71076246 A US71076246 A US 71076246A US 2492833 A US2492833 A US 2492833A
Authority
US
United States
Prior art keywords
disc
discs
projection
projections
annular
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
US710762A
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English (en)
Inventor
Baumann Karl
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.)
Metropolitan Vickers Electrical Co Ltd
Original Assignee
Metropolitan Vickers Electrical 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 Metropolitan Vickers Electrical Co Ltd filed Critical Metropolitan Vickers Electrical Co Ltd
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Publication of US2492833A publication Critical patent/US2492833A/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
    • F01D5/02—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
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • 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
    • F01D5/063—Welded rotors
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • ther are, as he number and diameter of the bladi sta es inc ea serio s limitations to the use ofrotor constructions: of the drum type and also of the type inv ving separate discs mounted u on a shaf th se lime itations being accentuated in circumstances W ere m nimisa ion .ef eve a Wei t-is su eially mpo tant a fo exam e, is the ease wit t rotors of turbines o com nd rs int nd d for use on a rc af mor particu ar in the f a rot r o th rum t e, h ho p s r s is ab to bec me i ssiv w
  • cent disc a similar projection or projections on the adja: cent disc, and the projection or projections on one disc being secured by pinning or riveting or bolting to an annular member which is rigidly attached, by welding, to an annular member'selcured by pinning or riveting or bolting t9 thepro; jection or projections on the adjacent disc,
  • the annular member secured to the projection or projections on one disc is spigoted withrespect to the annular member secured to the projection or projections on the adjacent disc; advantageously the'annular member for one disc may be machined on a radial face remote from the disc so as to register with a'spigo't on to a corresponding face of the annular member for the adjacent disc.
  • the annular members for adjacent discs may be formed at the radially outer ed ges'of their contiguous radial end faces in such manner as jointly to form a recess for receiving wld'meta'l rigidly to attach the rings one to the other.
  • the projection or projections on the discs may be of any suitable form but it is'preferred to use a single continuous projection of cylindrical shape.
  • the radial positionof the projection or projections will preferably be chosen so that during rotation at normal working speed there will be little or no sheer stress at the radial plane between the projection or projections of a disc and the face of'th disc F ggpgflflm I 'Wlth the projection or projections on a disc formed oylindrically and adapted to into annular space formed between a radially inner flange and a radially outer flange on the annular member to which said projection or projections will be secured by pinning or riveting or bolting as aforesaid, the said annular member will be constructed with said flanges spaced apart in the radial direction by a distance at least equal to the depth of the projection in the radial direction together with an amount corresponding to the distances by which the radially outer face' of the inner flange and
  • the annular members are secured each to the appertaining disc by means of radial pins inserted at the radially inner end of a series of radial holes formed in the annular members and the projection or projections of the disc, the contiguous annular members being secured together by welding effected whilst the discs are temporarily held tightly together and in coaxial relationship with each other.
  • the discs may be formed without central bores, the two end discs in the assembly being attached, in similar manner to that described, to members forming stub shafts for the bearings.
  • the overall length of the rotor to accommodate a given number of stages may be reduced since the disc hubs will be more lightly stressed and may therefore be made narrower than is possible in the case where the discs are formed with central bores.
  • the rotor shown comprises a rigid assembly of discs I, 2, 3 which are formed separately and secured together in side-by-side and coaxial relationship in a manner presently to be described. It will be appreciated that the discs will be shaped at the outer periphery as indicated for disc I at la so as to form a base for attachment thereto of one or more rows of blades (not shown).
  • said disc I is formed on opposite end faces with integral cylindrical projections lb and la respectively; said projections are preferably located at such radial distance from the axis of the disc that under the normal speed of rotation about said axis there will be little or no sheer stress in the neighbourhood of the plane indicated at XX.
  • Discs 2 and 3 are formed with similar projections 20, 3b respectively facing, and at the same radial distance from the axis as, the projections lb, lc for disc I.
  • Rin 4 is formed with flanges 4a and 4b to provide a recess into which the disc projection lb fits with radial clearance 6.
  • ring 5 is formed with flanges 5a and 5b providing a recess for receiving disc projection 2c also with radial clearance 6.
  • the ring is rigidly secured to the projection by headed pins 1 inserted in corresponding radial holes in the ring inner flange 4b and extending through corresponding holes in the disc projection lb into holes in the ring outer flange 4a.
  • ring 5 is rigidly secured to disc projection 20 by pins 8 passing through holes in the ring flanges 5a, 5b and the disc projection 20.
  • rings 4 and 5 are shaped jointly to provide a circumferential recess for the reception of weld metal 9 for rigidly attaching together the rings 4 and 5 and therewith the discs I and 2. It will be appreciated that the weldin operation will be effected while the discs I and 2 are temporarily held tightly together and in coaxial relationship with each other so that the rings 4 and 5 will be firmly held together with their facin radial end surfaces closely engaged.
  • the discs I and 3 are rigidly attached together by means of rings l4 and I5 fitting over the disc projections 3b and [0 respectively with radial clearance l6, which rings after being secured to said disc projections by pins l1 and I8 respectively are subsequently welded together at l 9.
  • the discs I, 2 and 3 can be rigidly connected together without introduction of local stresses into the discs during the welding operation.
  • the discs I, 2 and 3 are formed with a central bore l0 for assembly on a shaft.
  • the discs may be formed without central bores and the outer faces of the two end discs of the rotor are formed each with a projection or projections to which a member may be secured in the manner described above, which members form stub shafts for the bearings.
  • the disc hubs will be more lightly stressed and may therefore be made narrower than is indicated in the drawing, thus enabling the overall length of the rotor to be reduced.
  • a rotor for a multi-stage turbine or compressor comprising a plurality of discs having projections integral therewith and directed from the opposing sides of adjacent discs, annular members mounted on said projections, and a weld securing said members together, said annular members being formed with two axially directed radially spaced annular flanges which receive the projections with clearance between the projections and the radially inner flanges of the respective annular members, and fastening means extending radially through the flanges
  • the attachment f is I to dis 2 i ef e of the annular members and the respective projections and securing the annular members to the respective discs.
  • a rotor for a multi-stage turbine or compressor comprising a plurality of discs having annular projections integral .with the respective discs and directed toward one another from the opposing side faces of adjacent discs, annular members mounted on the projections on the respective discs, and a weld securing said members together, each of said annular members being formed with two axiall directed radially spaced annular flanges which receive the annular projection on the respective disc with clearance between the projection and the radially inner flange of the respective annular member, and fastening means extending radially through the flanges of each annular member and the respective projection and securing the annular members to the respective discs.
  • a rotor for a multi-stage turbine or compressor comprising a plurality of discs each having an annular projection on a side face thereof and integral therewith and directed axially toward the opposing side face of an adjacent disc, an annular member mounted on the projection on one disc, an annular member mounted on the projection on an adjacent disc, and a weld securing the annular members together, each of said annular -members bein formed with two axially directed annular flanges spaced radially to receive the axially directed annular projection on the respective disc with clearance between the radially inner flange of the annular member and the respective projection, and the annular members being formed on their meeting faces one with a surface and the other with a cooperating flange to locate said members concentrically with the discs for welding together.
  • a rotor for a multi-stage turbine or compressor comprising at least two coaxially arranged discs each having a plurality of projections integral therewith and extending axially therefrom toward the adjacent disc, an annular member secured on the projections on each disc and having two axially directed flanges forming a housing for the respective projections with clearance between each projection and the radially inner of said two flanges of the respective annular member, said annular members bein formed on their meeting faces one with a surface and the other with a flange which cooperate to locate said members and the discs secured thereto concentrically for welding together.
  • a rotor for a multi-stage turbine or compressor comprising at least two coaxially arranged discs, each of the discs having on the surface thereof which faces the other disc an annular axially directed projection arranged concentrically with the rotor axis and intermediately between said axis and the periphery of the disc, an annular member mounted on each of said projections and having radially inner and radially outer axially projecting flanges forming a space for receiving the respective projection with clearance between the radially inner flange and the projection, and fastening means extending radially through said flanges of each annular member and the respective projection, the meeting surfaces of the annular members of the two discs being provided with cooperating parts which locate said members and the discs secured thereto concentrically with the axis of the rotor, and the radially outer edges of said members adjacent to their meeting surfaces being shaped to provide a recess for receiving weld metal.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US710762A 1945-11-20 1946-11-19 Rotor for multistage turbines and compressors Expired - Lifetime US2492833A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB257531X 1945-11-20

Publications (1)

Publication Number Publication Date
US2492833A true US2492833A (en) 1949-12-27

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ID=10232721

Family Applications (1)

Application Number Title Priority Date Filing Date
US710762A Expired - Lifetime US2492833A (en) 1945-11-20 1946-11-19 Rotor for multistage turbines and compressors

Country Status (6)

Country Link
US (1) US2492833A (ko)
BE (1) BE469282A (ko)
CH (1) CH257531A (ko)
FR (1) FR1017742A (ko)
GB (1) GB603996A (ko)
NL (1) NL69944C (ko)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2702687A (en) * 1950-11-13 1955-02-22 United Aircraft Corp Rotor construction
US2801070A (en) * 1952-01-28 1957-07-30 A V Roe Canada Ltd Mounting means for turbine rotors
US2818228A (en) * 1954-04-30 1957-12-31 Rolls Royce Rotor for gas-turbine engine with means to locate rotor discs with respect to one another
US2931621A (en) * 1952-12-15 1960-04-05 Anthony J O'donnell Supporting plates for turbine blades
US3617150A (en) * 1970-06-01 1971-11-02 Gen Motors Corp Rotor drum
EP0846844A1 (de) * 1996-12-04 1998-06-10 Asea Brown Boveri AG Rotorzusammenbau mit kraftschlüssig und gleichzeitig form- bzw. materialschlüssig verbundenen Rotorscheiben
US20070119830A1 (en) * 2004-02-07 2007-05-31 Mtu Aero Engines Gmbh Method for connecting components
US7473475B1 (en) * 2005-05-13 2009-01-06 Florida Turbine Technologies, Inc. Blind weld configuration for a rotor disc assembly
US20110164982A1 (en) * 2010-01-06 2011-07-07 General Electric Company Apparatus and method for a low distortion weld for rotors
EP2586970A3 (en) * 2011-10-28 2017-05-24 United Technologies Corporation Spoked spacer for a gas turbine engine
US9790792B2 (en) 2011-10-28 2017-10-17 United Technologies Corporation Asymmetrically slotted rotor for a gas turbine engine
WO2022022773A1 (de) * 2020-07-28 2022-02-03 MTU Aero Engines AG Verdrehgesicherter rotorspannverbund einer strömungsmaschine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2620589A1 (de) * 2012-01-25 2013-07-31 Siemens Aktiengesellschaft Geschweisster Turbinenrotor
KR101872808B1 (ko) 2017-04-28 2018-06-29 두산중공업 주식회사 길이조절구조를 포함하는 가스터빈 로터, 및 이를 포함하는 가스터빈

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE341892C (de) * 1919-03-22 1921-10-10 Escher Wyss Maschf Ag Aus Radscheiben zusammengesetzter Laeufer fuer raschlaufende Turbinen, Pumpen und Verdichter
US1399816A (en) * 1919-04-12 1921-12-13 Spiess Paul Rotor for multistage high-speed engines
US2369051A (en) * 1942-07-10 1945-02-06 Sulzer Ag Welded turbine rotor

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE341892C (de) * 1919-03-22 1921-10-10 Escher Wyss Maschf Ag Aus Radscheiben zusammengesetzter Laeufer fuer raschlaufende Turbinen, Pumpen und Verdichter
US1399816A (en) * 1919-04-12 1921-12-13 Spiess Paul Rotor for multistage high-speed engines
US2369051A (en) * 1942-07-10 1945-02-06 Sulzer Ag Welded turbine rotor

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2702687A (en) * 1950-11-13 1955-02-22 United Aircraft Corp Rotor construction
US2801070A (en) * 1952-01-28 1957-07-30 A V Roe Canada Ltd Mounting means for turbine rotors
US2931621A (en) * 1952-12-15 1960-04-05 Anthony J O'donnell Supporting plates for turbine blades
US2818228A (en) * 1954-04-30 1957-12-31 Rolls Royce Rotor for gas-turbine engine with means to locate rotor discs with respect to one another
US3617150A (en) * 1970-06-01 1971-11-02 Gen Motors Corp Rotor drum
EP0846844A1 (de) * 1996-12-04 1998-06-10 Asea Brown Boveri AG Rotorzusammenbau mit kraftschlüssig und gleichzeitig form- bzw. materialschlüssig verbundenen Rotorscheiben
US20070119830A1 (en) * 2004-02-07 2007-05-31 Mtu Aero Engines Gmbh Method for connecting components
US7473475B1 (en) * 2005-05-13 2009-01-06 Florida Turbine Technologies, Inc. Blind weld configuration for a rotor disc assembly
US20110164982A1 (en) * 2010-01-06 2011-07-07 General Electric Company Apparatus and method for a low distortion weld for rotors
EP2586970A3 (en) * 2011-10-28 2017-05-24 United Technologies Corporation Spoked spacer for a gas turbine engine
EP2586971A3 (en) * 2011-10-28 2017-05-24 United Technologies Corporation A spacer, a rotor, a spool and a method of orienting a rotor stack load path
US9790792B2 (en) 2011-10-28 2017-10-17 United Technologies Corporation Asymmetrically slotted rotor for a gas turbine engine
WO2022022773A1 (de) * 2020-07-28 2022-02-03 MTU Aero Engines AG Verdrehgesicherter rotorspannverbund einer strömungsmaschine

Also Published As

Publication number Publication date
FR1017742A (fr) 1952-12-18
NL69944C (ko)
CH257531A (de) 1948-10-15
GB603996A (en) 1948-06-25
BE469282A (ko)

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