US3572969A - Turbomachine rotor - Google Patents

Turbomachine rotor Download PDF

Info

Publication number
US3572969A
US3572969A US824077A US3572969DA US3572969A US 3572969 A US3572969 A US 3572969A US 824077 A US824077 A US 824077A US 3572969D A US3572969D A US 3572969DA US 3572969 A US3572969 A US 3572969A
Authority
US
United States
Prior art keywords
rotor
ring
rings
drum
spokes
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
US824077A
Other languages
English (en)
Inventor
Henry S Mclimore
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.)
Motors Liquidation Co
Original Assignee
Motors Liquidation 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 Motors Liquidation Co filed Critical Motors Liquidation Co
Application granted granted Critical
Publication of US3572969A publication Critical patent/US3572969A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F01D5/028—Blade-carrying members, e.g. rotors the rotor disc being formed of sheet laminae

Definitions

  • a bladed rotor drum or wheel for an axial flow compressor or turbine is made up of an outer ring and an inner ring within the outer ring and spokes connecting the two rings, the spokes being so directed as to exert an inward component of force on both rings. Blades extend into the gas path from the inner ring through openings in the outer ring. Preferably, blades are also mounted on the outer ring. End bells or discs may be provided on one or the other or both of the rings.
  • My invention is directed to rotor structures of turbornachines, particularly axial-flow compressors and turbines. It is well known that such structures rotate at very high-speeds and bear blades of substantial construction to withstand the gas loads and centrifugal loads on the blades. The loads transmitted from the blades to the wheel or drum in which they are mounted are thus quite substantial. This requires a strong mounting structureor rotor drum.
  • the blade-mounting structure or rotor drum is made of two substantially concentric inner and outer rings or drums with tension members or spokes extending between the two rings. These spokes are so directed as to have an inward component of direction from both the inner and outer rings, so that they exert a compressive force on both rings tending to counteract to some extent the hoop stress in each ring due to centrifugal force exerted by the mass of the ring itself and of the blades, if any, mounted on the ring.
  • the invention also involves arrangements for sealing structures of this sort against flow of gas through the rotor below the active portion of the blade.
  • the principal object of my invention is to provide a strong lightweight rotor less likely to suffer from casualties and taking best advantage of the properties of materials now known, and particularly to take advantage of the tensile properties of materials which may be used as spokes to reduce hoop stress in the elements of the rotor.
  • PM]. i is a sectional view of a singlestage compressor or turbine rotor structure taken in a plane perpendicular to the axis of rotation.
  • FlG. 2 is a sectional view of such a structure taken on the plane indicated by the line 2-2 in FIG. 1.
  • H6. 3 is a similar view of .a second form of rotor.
  • MG. 4 is a detail of a spoke anchorage.
  • FIG. 5 is a detail of an adjustable spoke anchorage.
  • the rotor structure comprises an outer ring or drum 9 and an inner ring or drum 10,
  • Gas-directing blades lll mounted on the inner ring ll] extend through the outer ring 9.
  • the blades it may have any suitable known type of attachment to the inner ring, indicated by the dovetail root 13 mounted in slots 14 in the ring.
  • Each blade includes a stalk portion 15 between the rings and a flow-directing or airfoil portion 17 exteriorly of the outer ring 9.
  • the stalk portion may be in cross section a continuation of the airfoil portion if desired, but it is not intended that this portion be exposed to thefluid to be compressed or expanded in the turbomachine.
  • Blades ll are evenly distributed around the ring it) and may be closely spaced.
  • a second or outer row of blades lid mounted on the outer ring 9 may also be provided.
  • Blades 18 are mounted intermediate the blades 11.
  • Blades 18 may be attached by roots l9 similarly to the blades it but ordinarily would not include a stalk portion.
  • the airfoil portion 21 of these blades ordinarily would have the same configuration as the exposed portion 17 of the blades 11.
  • the outer ring 9 is made up of a forward ring 22 and the rear ring 23, these being connected in any suitable way as by the dovetail connection in dicated at 25, so that they may be assembled around the blades it.
  • the forward ring is integral with a disc as which in turn is integral with a hub or hollow shaft 27, and the rear ring 23 is integral with a disc 29 integral with a hub or shaft 39.
  • the parts 22, 23, 2d, 27, 29, and 39 comprise a rotor wheel or drum which may be mounted on or connected to a shaft in any suitable manner.
  • the inner ring 10 is connected to the discs and hubs only through the two portions of the outer ring 9 and the spokes 34 to be described.
  • These spokes are tension members interconnecting the two rings and preferably are disposed as indicated so that half the spokes exert a tangential pull in one direction and half in the other direction around the axis of rotation; also, so that some of the spokes pull forwardly on the inner ring and rearwardly on the outer ring whereas other spokes pull rearwardly on the inner ring and forwardly on the outer ring. This last feature may be utilized to hold the two rings together.
  • spokes 34 extend initially inwardly from the inner ring 10 so that they exert a component of force radially inwardly of this ring rather than radially outwardly as in a conventional spoke arrangement.
  • These spokes are of a material of high tensile strength to weight ratio.
  • the spokes may thus be considered as falling onto four groups; spokes 35 which extend from the forward outer ring 22 in a counterclockwise direction as illustrated in FIG. 1, spokes 37 which extend in the opposite direction from the outer ring 22; and spokes 38 and 39 extending in opposite circumferential directions inwardly from the rear outer ring portion 23 to the inner ring 10.
  • spokes 35 and 37 trend rearwardly from ring 22 and spokes 38 and 39 forwardly from ring 23.
  • each spoke extends through a hole 41 in the inner ring and a hole 42 inthe outer ring. It has a ball end 43 seated against the outer surface of the inner ring and a threaded end 45'upon which is threaded a nut 46 bearing against the outer surface of the outer ring 9.
  • These spokes may, therefore, be tensioned or relaxed by adjustment of the nuts 46. As will be appreciated, this is not greatly different from the adjustment of spokes for bicycle wheels.
  • Ribs or wings 47 may be provided on the end of the spokes adjacent to the threads 45 lodging in grooves in the ring 9 so as to prevent the outer end of the spoke from rotating as the nut dd is adjusted.
  • Disc 26 or 29 and the corresponding hub may be omitted if it is desired to have the rotor overhung from one hub only.
  • various other means of attachment of the rotating structure to a suitable shaft or other drum portions of the turbomachine may be employed if desired.
  • FIG. 3 illustrates a different form of rotor structure in which many of the parts are essentially the same as those previously described, the principal difference being the provision of a disc on the inner ring 11 at one end of the inner ring and a modification of the forward portion of the outer ring.
  • the outer ring is referred to as 59 and the inner ring as oil, the blades retaining the number 11 and the spokes 34 being the same as previously described.
  • inner ring 60 is integral with a disc or end bell 61 which terminates in a shaft or hub 62.
  • the forward portion 65 of the outer ring continues into an annular disc 66 whichsurrounds the shaft 62 with a piston ring seal 67 between them.
  • the centrifugal force exerted by the blades on the outer ring tends to counteract, through the force transmitted by the spokes 3d, the centrifugal force exerted outwardly on the inner ring by the blades Ill mounted upon it.
  • a bladed rotor for a turbomachine or the like comprising an outer drum, an inner drum coaxial with and substantially concentric with the outer drum mounted within the outer drum, a first disc and hub at one end of the rotor fixed to the outer drum, a second disc and hub at the other end of the rotor fixed to one of the drums, blades mounted on the inner drum and extending through the outer drum with fluid-directing portions of the blades externally of the outer drum, and tension spokes anchored at each end to the outer and inner drums, respectively, distributed around the peripheries of the drums, the spokes extending radially inwardly of each drum at the points of attachment so as to direct a radially inward force component on each drum.
  • a bladed rotor wheel for a turbomachine or the like comprising, in combination, a rigid outer ring, a rigid inner ring, the rings being coaxial and substantially concentric, fluiddirecting blades mounted on and supported by at least one of said rings and extending radially outward of the outer ring, and tension spokes fixed to and extending between the rings distributed around the perimeter of the rings, the spokes having'an inward component of direction from the point of attachment at each ring to the point of attachment at the other ring so as to put both rings in compression and oppose centrifugal forces on the rings.
  • a rotor as recited in claim 2 in which the blades are mounted on the inner ring and extend through the outer ring.
  • a rotor as recited in claim 3 including also blades mounted on and extending radially outwardly from the outer ring.
  • a rotor as recited in claim 3 in which the outer ring is split at a circumferential split line into a forward and a rear ring portion.
  • a rotor as recited in claim 5 in which the spokes are disposed so as to pull andsaid ring portions together.
  • a rotor as recited in claim 2 including also a disc integral with one of said rings providing a mounting for the rotor.
  • a rotor as recited in claim 2 including also means providing a barrier against fluid flow axially of the rotor between the rings.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US824077A 1969-05-13 1969-05-13 Turbomachine rotor Expired - Lifetime US3572969A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US82407769A 1969-05-13 1969-05-13

Publications (1)

Publication Number Publication Date
US3572969A true US3572969A (en) 1971-03-30

Family

ID=25240540

Family Applications (1)

Application Number Title Priority Date Filing Date
US824077A Expired - Lifetime US3572969A (en) 1969-05-13 1969-05-13 Turbomachine rotor

Country Status (2)

Country Link
US (1) US3572969A (es)
GB (1) GB1238434A (es)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2577515A1 (fr) * 1985-02-19 1986-08-22 Agusta Aeronaut Costr Moyeu metallique pour rotor d'helicoptere
US20080273981A1 (en) * 2005-03-30 2008-11-06 Zephyr Corporation Windmill
US20110048620A1 (en) * 2009-08-17 2011-03-03 Snecma Method to manufacture a hollow, single-piece bladed disc
US20130089426A1 (en) * 2010-07-02 2013-04-11 Vladimir Grigorievich Degtyar Rotor for Wind Power Installation
US9080448B2 (en) 2009-12-29 2015-07-14 Rolls-Royce North American Technologies, Inc. Gas turbine engine vanes
US10393136B2 (en) * 2014-09-22 2019-08-27 Mahle International Gmbh Fan wheel having a rib structure provided on a hub

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1010337A (en) * 1910-10-11 1911-11-28 Alfred Wunderlich Screw-propeller for flying-machines.
US1046385A (en) * 1911-09-21 1912-12-03 Herbert F Hawes Aerial propeller.
US1115162A (en) * 1908-08-11 1914-10-27 Emile Berliner Aeromobile.
US1184300A (en) * 1913-05-10 1916-05-23 Bayley Mfg Co Centrifugal fan.
FR927913A (fr) * 1946-04-19 1947-11-13 Procédé et dispositifs de construction et de montage des aubes de machines tournantes
DE819078C (de) * 1949-06-02 1951-10-29 Friedrich Koester Schnellaufendes Windrad mit grossem Anzugsmoment
US2844354A (en) * 1954-04-08 1958-07-22 Cincinnati Testing & Res Lab Rotor blade and method of making same
US2855179A (en) * 1955-01-05 1958-10-07 John K Brown High temperature ceramic turbine
US2857094A (en) * 1955-07-19 1958-10-21 John R Erwin Integral plastic rotors
US3032317A (en) * 1958-10-24 1962-05-01 Robert G Frank Jet turbine bucket wheel
US3403844A (en) * 1967-10-02 1968-10-01 Gen Electric Bladed member and method for making
US3456917A (en) * 1964-01-15 1969-07-22 Rolls Royce Bladed rotor,particularly for a compressor

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1115162A (en) * 1908-08-11 1914-10-27 Emile Berliner Aeromobile.
US1010337A (en) * 1910-10-11 1911-11-28 Alfred Wunderlich Screw-propeller for flying-machines.
US1046385A (en) * 1911-09-21 1912-12-03 Herbert F Hawes Aerial propeller.
US1184300A (en) * 1913-05-10 1916-05-23 Bayley Mfg Co Centrifugal fan.
FR927913A (fr) * 1946-04-19 1947-11-13 Procédé et dispositifs de construction et de montage des aubes de machines tournantes
DE819078C (de) * 1949-06-02 1951-10-29 Friedrich Koester Schnellaufendes Windrad mit grossem Anzugsmoment
US2844354A (en) * 1954-04-08 1958-07-22 Cincinnati Testing & Res Lab Rotor blade and method of making same
US2855179A (en) * 1955-01-05 1958-10-07 John K Brown High temperature ceramic turbine
US2857094A (en) * 1955-07-19 1958-10-21 John R Erwin Integral plastic rotors
US3032317A (en) * 1958-10-24 1962-05-01 Robert G Frank Jet turbine bucket wheel
US3456917A (en) * 1964-01-15 1969-07-22 Rolls Royce Bladed rotor,particularly for a compressor
US3403844A (en) * 1967-10-02 1968-10-01 Gen Electric Bladed member and method for making

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2577515A1 (fr) * 1985-02-19 1986-08-22 Agusta Aeronaut Costr Moyeu metallique pour rotor d'helicoptere
US20080273981A1 (en) * 2005-03-30 2008-11-06 Zephyr Corporation Windmill
US20110048620A1 (en) * 2009-08-17 2011-03-03 Snecma Method to manufacture a hollow, single-piece bladed disc
US8177933B2 (en) * 2009-08-17 2012-05-15 Snecma Method to manufacture a hollow, single-piece bladed disc
US9080448B2 (en) 2009-12-29 2015-07-14 Rolls-Royce North American Technologies, Inc. Gas turbine engine vanes
US20130089426A1 (en) * 2010-07-02 2013-04-11 Vladimir Grigorievich Degtyar Rotor for Wind Power Installation
US10393136B2 (en) * 2014-09-22 2019-08-27 Mahle International Gmbh Fan wheel having a rib structure provided on a hub

Also Published As

Publication number Publication date
GB1238434A (es) 1971-07-07

Similar Documents

Publication Publication Date Title
US3356339A (en) Turbine rotor
US3037742A (en) Compressor turbine
US3680979A (en) Rotor structure for turbo machines
US3625634A (en) Turbomachine rotor
US6283712B1 (en) Cooling air supply through bolted flange assembly
US2497151A (en) Multidisk rotor
US2771240A (en) Automatic dynamic balancer
US2654565A (en) Construction of rotors for compressors and like machines
US5624233A (en) Gas turbine engine rotary disc
JPH0580574B2 (es)
US2738126A (en) Construction of compressor rotors
JPH07109161B2 (ja) タービンエンジンのロータ
US2869820A (en) Rotors for axial flow compressors or turbines
US6499957B1 (en) Rotor for a turbomachine
US3572969A (en) Turbomachine rotor
GB621418A (en) Improvements relating to multi-stage axial compressors and turbines
US4008000A (en) Axial-flow rotor wheel for high-speed turbomachines
US3597109A (en) Gas turbine engine axial flow multistage compressor
US3085400A (en) Cooling fluid impeller for elastic fluid turbines
US3765795A (en) Compositely formed rotors and their manufacture
US2918252A (en) Turbine rotor disc structure
US3305166A (en) Centrifugal compressor
US2988324A (en) Rotors for multi-stage axial flow compressors or turbines
US3588277A (en) Bladed rotors
US3471127A (en) Turbomachine rotor