US2628065A - Turbine disk - Google Patents

Turbine disk Download PDF

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Publication number
US2628065A
US2628065A US201644A US20164450A US2628065A US 2628065 A US2628065 A US 2628065A US 201644 A US201644 A US 201644A US 20164450 A US20164450 A US 20164450A US 2628065 A US2628065 A US 2628065A
Authority
US
United States
Prior art keywords
disc
ring
parts
turbine
blade
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
US201644A
Other languages
English (en)
Inventor
Lombard Adrian Albert
Morley Frederick Willia Walton
Davis Christopher Ainsworth
Wilkinson Stanley Clarke
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 to BE488202D priority Critical patent/BE488202A/xx
Priority claimed from US777506A external-priority patent/US2628066A/en
Priority to FR1019591D priority patent/FR1019591A/fr
Priority to CH265628D priority patent/CH265628A/de
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to US201644A priority patent/US2628065A/en
Application granted granted Critical
Publication of US2628065A publication Critical patent/US2628065A/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
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages of the rotor disc
    • 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
    • F01D5/021—Blade-carrying members, e.g. rotors for flow machines or engines with only one axial stage
    • 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
    • F01D5/3069—Fixing blades to rotors; Blade roots ; Blade spacers between two discs or rings
    • 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

  • This invention relates to gas-turbines and more particularly to turbine-disc-assemblies of the kind in which the turbine-disc comprises two complementary parts spaced axially and supporting peripherally the turbine-blading therebetween.
  • the turbine-disc comprises two complementary parts spaced axially and supporting peripherally the turbine-blading therebetween.
  • turbine-discs In gas-turbine engines for aircraft-propulsion, to which the invention is particularly though not exclusively applicable, it has been the practice to manufacture turbine-discs from solid forgings, which in order to accommodate for high centrifugal loading and to avoid vibration or whip,
  • Figure 1 is a local radial section through a I turbine disc
  • Figure 2 is a partial end view of Figure 1 with parts broken away.
  • FIG. 1 there is illustrated an axial flow turbine assembly comprising two slightly dished disc parts with the turbine blading mounted in a blade-supporting ring received between the peripheral portions of the discs.
  • the two disc parts II), II are generally similar to one another, decrease in thickness from their centres towards their peripheries to economise in material and are assembled with the concave faces together.
  • the disc material may be a high tensile steel, such as that known under the trademark Hykro, having the desired properties at the moderate temperature at which it runs.
  • the disc part is provided with a mounting flange l2 at its outer side by means of which the disc can be secured to a turbine-rotor shaft.
  • Each disc is formed with an internal axial flange It at about the same radius as the mounting flange l2, and the flanges l3 abut one another to space the two disc parts In, I l the correct distance apart at their centres.
  • One of the flanges is arranged to fit, in the manner of a spigot, within the other so as to resist centrifugal and gyroscopic forces, and thermal loading tending to cause relative radial displacement between the disc-parts.
  • Each disc part is formed with a central hole to receive a sleeve [4 and the two disc parts are clamped together at their centres between a flange IE on the sleeve I4 and a nut 16 on the sleeve.
  • the sleeve I4 is open at one end to the shaft and is closed at the other so that cooling air can pass from the shaft into the sleeve and then through openings ll in the sleeve l4 and flanges l3 into the turbine disc.
  • Each disc part I0, H is formed with an internal shoulder l8 near its periphery and these shoulders face radially inwards so as to form sockets of large diameter.
  • the disc parts are formed with two sets of annular facings I9 between which the blade supporting ring 20 is located.
  • the material of this ring may be that known as G.18.b (manufacturer's specification or trade-mark), having the desired properties at the elevated temperature to which the ring is subjected.
  • the ring 20 is formed with-two outwardly facing shoulders 2
  • the disc parts are secured towards their peripheries against moving apart axially by counter-sunk bolts which are arranged in a circle along the centre-line of the facings l9 and are thus in a portion of the disc which is subject to a considerably reduced centrifugal loading, the centrifugal loading due to the blades 23 and blade supporting ring 20 being applied to the disc through the engaging shoulders I8, 2 I.
  • peripheral portions of the disc parts 10, II beyond the facings [Bf-are shaped to provide between them a wide trough 24 and the blade-supporting ring 20 extends radially outwards beyond the trough, the part of the ring 20 beyond the trough 24 being widened to close the trough. There is, however, a space inside the trough on either side of the blade-supporting ring 20.
  • the facings l9 are formed with a plurality of radial slots 25 extending across them and also with arcuate slots 26 joining pairs of slots 25.
  • on the ring 20 are also formed with radial slots 21 to register with the slots 25.
  • the cooling air can thus pass into the trough 24 through the passages provided by these slots and will adequately cool the periphery of the disc parts III, II and the in'n'er'part of the blade-supporting ring 20.
  • the peripheral part of the ring is formed with shaped recesses 29 to receive and retain the roots 28 of the blades 23, the roots being conveniently provided with peripherally extending shoulders so that they are of the fir-tree type which are mounted in the blade-carrying ring by being slid into itin an axial direction.
  • Slots 30 are cut across the bottom of the recesses 29 so that cooling air can escape from one side of the trough 24 underneath the roots 28 of the blades.
  • the blades 23 may be hollow and part of the air will then pass up through the blades to cool them.
  • Passages 31 are formed in the portions of the ring 2 3 between the blade roots 28 to permit the escape .ofcooling air from the trough 24 and to assist in cooling the blade roots.
  • Each of the disc parts Hi, It is provided with .an axial flange 32 on its inner surface at a short distance inwards from the blade supporting ring 20 and these flanges abut one another when the discs are assembled. Slots 33 are formed in the flanges 32 to register and form passages for the outward flow of cooling air.
  • the flanges 32 interabut to determine the spacing of the discs l6 flanges 35 provide inwardly facing shoulders a forming sockets to receive a ring 35 which acts as a spigot in each of them.
  • the ring 35 is preferably formed from a material, having a high coefllcient of expansion, such as aluminium, so that it will tend to tighten in the sockets as the temperature rises.
  • the ring 35 is formed with slot 38 on each of its side faces to provide passages through which cooling air can pass outwards and each slot 35 is made deeper at its outer end in order to clear the flanges 34.
  • This arrangement has the result that the air will tend to flow outwardly along the inner faces of the discs W, H to the slots 36 and will escape from these slots towards the central plane of the turbine-disc-assembly so that the two streams of air flowing on the opposite sides ofv the ring 35 will be directed towards the central plane of the turbinedisc and towards one another to produce turbulence.
  • This turbulence reduces the tendency for a Stratified air flow in which the air flowing over the parts of the disc will be hotter than that flowing up the central plane of the disc.
  • the clamp device at the centre of the turbine disc assembly provided by sleeve i i, flanges i5 and nut 15, avoids the use of a series of bolts passing through the disc parts, and localizes the bore through the centre of the disc, thereby avoiding undue reduction in structural strength.
  • the provision of the flange l2 avoids the passage of bolts through the disc-parts in their attachment to the turbine shaft.
  • the disc parts l0, vll being coned will tend to separate under centrifugal force at full speed.
  • The-bolts 22 are tightened up so that the axial load between the flanges on the disc parts and between the disc parts and the ring 35 are greater than the maximum force tending to separate the disc parts when running at maximum speed.
  • turbine disc above described is light in weight and yet is capable of withstanding the high stresses experienced when in use, is relatively simple to manufacture, and, by virtue of the method of blade-root fixing, has an improved cooling efiiciency as regards the blade-root cool- Moreover, by locating the screws, bolts or rivets for securing the disc together outside the region of the part of their peripheries subjected to high centrifugal stresses, the discs are not unduly weakened by the provision of the holes to receive the bolts, screws or rivets.
  • turbine disc of this invention enables the various parts of the disc to be manufactured from a material having the desired strength properties at the temperature at which it will operate.
  • the dished discs may be formed from a material having desired strength properties at a temperature which is moderate as compared with that at which the biading or the blade-supporting ring will operate and the blading or blade-supporting ring will be made from a material having desired strength properties at a more elevated temperature.
  • An axial flow turbine assembly comprising in combination a first disc part having means for securing it to a hollow rotor shaft; a second disc part mounted coaxially with the first and axially spaced therefrom to provide a hollow space therebetween; a duct leading to said space for the supply of coolinggas; shoulder means on said disc parts adjacent the peripheries thereof and extending axially towards one another; an annular blade supporting ring mounted in said space and provided with axially extending circumferential spigot means abutting the radially inward faces of said axially extending shoulder means on said disc parts; axial flow turbine blading supported by said blade supporting ring; securing members to secure said disc parts against axial separation extending through the disc parts, and through said ring and located at a radius outside said spigot means; and passages in said axially extending shoulder means and said axially extending circumferential spigot means communicating between said space and the exterior of the disc assembly to permit the flow of cooling gas from said space, such flow
  • An axial flow turbine assembly comprising in combination two complementary disc parts secured to each other and axially spaced to provide a hollow space therebetween means for supplying cooling gas to said space; axial abutment means on said disc parts defining said axial spacing at an inner radius; shoulder means on said disc parts at a radius outside said abutment means and extending axially towards one another; an annular blade supporting ring provided with axially extending circumferential spigot means abutting the radial inward faces or" said axially extending shoulder means; axial flow turbine blading supported by said blade supporting ring; securing members to secure said discs against axial separation extending through said disc parts an through said ring and located at a radius outside said spigot means; circumferential shoulder means on said disc parts extending axially towards each other into said space and located at radius between said first mentioned shoulder means and said abutment means defining the axial spacing of the disc parts at inner radius; a spacer ring in said space engaged in axial a
  • An axial flow turbine disc assembly comprising in combination a first disc part; a second disc part mounted coaxially with said first disc part, said first and second disc parts having coaxial bores; a hollow bolt member extending through said bores; a nut member engaged on said bolt member; spacing means axially nipped between said discs by said bolt and nut members and holding said discs apart to provide a hollow space therebetween radially outside said spacing means; a communicating duct from said coaxial bores to said space, said communicating duct passing through said bolt; shoulder mean on said disc parts adjacent the peripheries thereof and extending axially towards one another; an annular blade supporting ring provided with axially extending circumferential spigot means abutting radially inward faces of said axially extending shoulder means on said disc parts; axial flow turbine blading supported by said blade supporting ring; securing members to secure said disc parts against axial separation extending through said disc parts and through said ring and located at a radius outside said spigot means;

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US201644A 1946-10-02 1950-12-19 Turbine disk Expired - Lifetime US2628065A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
BE488202D BE488202A (fr) 1946-10-02
FR1019591D FR1019591A (fr) 1946-10-02 1947-10-16 Perfectionnements aux moteurs à turbine à gaz
CH265628D CH265628A (de) 1946-10-02 1947-11-19 Axial-Turbinenrotor.
US201644A US2628065A (en) 1946-10-02 1950-12-19 Turbine disk

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
GB265628X 1946-10-02
US777506A US2628066A (en) 1946-10-02 1947-10-02 Turbine disk
US201644A US2628065A (en) 1946-10-02 1950-12-19 Turbine disk

Publications (1)

Publication Number Publication Date
US2628065A true US2628065A (en) 1953-02-10

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Family Applications (1)

Application Number Title Priority Date Filing Date
US201644A Expired - Lifetime US2628065A (en) 1946-10-02 1950-12-19 Turbine disk

Country Status (4)

Country Link
US (1) US2628065A (fr)
BE (1) BE488202A (fr)
CH (1) CH265628A (fr)
FR (1) FR1019591A (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2921769A (en) * 1953-06-08 1960-01-19 Peerless Turbine Corp Turbine rotor
US4797065A (en) * 1986-10-17 1989-01-10 Transamerica Delaval Inc. Turbine blade retainer
WO2010081467A1 (fr) * 2009-01-16 2010-07-22 Mtu Aero Engines Gmbh Disque séparé d'un étage de turbine ou de compresseur comportant des ailettes fixées par soudage
EP2348191A3 (fr) * 2010-01-22 2017-10-18 Rolls-Royce plc Disque de rotor
US12000308B2 (en) 2022-08-23 2024-06-04 General Electric Company Rotor blade assemblies for turbine engines

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1144537B (de) * 1960-07-13 1963-02-28 Henschel Werke Ag Anordnung zur Kuehlung der Laufraeder und Beschaufelungen von Turbomaschinen, insbesondere Gasturbinen

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US841503A (en) * 1905-12-04 1907-01-15 Victor Gelpke Attachment of blades for turbines.
US1959220A (en) * 1933-05-26 1934-05-15 Gen Electric Rotary disk turbine bucket wheel, or the like
GB452412A (en) * 1933-11-25 1936-08-24 Michael Martinka Improvements relating to apparatus for cooling the rotors of turbines
US2401826A (en) * 1941-11-21 1946-06-11 Dehavilland Aircraft Turbine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US841503A (en) * 1905-12-04 1907-01-15 Victor Gelpke Attachment of blades for turbines.
US1959220A (en) * 1933-05-26 1934-05-15 Gen Electric Rotary disk turbine bucket wheel, or the like
GB452412A (en) * 1933-11-25 1936-08-24 Michael Martinka Improvements relating to apparatus for cooling the rotors of turbines
US2401826A (en) * 1941-11-21 1946-06-11 Dehavilland Aircraft Turbine

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2921769A (en) * 1953-06-08 1960-01-19 Peerless Turbine Corp Turbine rotor
US4797065A (en) * 1986-10-17 1989-01-10 Transamerica Delaval Inc. Turbine blade retainer
WO2010081467A1 (fr) * 2009-01-16 2010-07-22 Mtu Aero Engines Gmbh Disque séparé d'un étage de turbine ou de compresseur comportant des ailettes fixées par soudage
EP2348191A3 (fr) * 2010-01-22 2017-10-18 Rolls-Royce plc Disque de rotor
US12000308B2 (en) 2022-08-23 2024-06-04 General Electric Company Rotor blade assemblies for turbine engines

Also Published As

Publication number Publication date
FR1019591A (fr) 1953-01-23
BE488202A (fr)
CH265628A (de) 1949-12-15

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