US3891351A - Turbine disc - Google Patents

Turbine disc Download PDF

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Publication number
US3891351A
US3891351A US454372A US45437274A US3891351A US 3891351 A US3891351 A US 3891351A US 454372 A US454372 A US 454372A US 45437274 A US45437274 A US 45437274A US 3891351 A US3891351 A US 3891351A
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United States
Prior art keywords
disc
rim
portions
bore
web
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Expired - Lifetime
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US454372A
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English (en)
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Theodore J Norbut
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Individual
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Priority to US454372A priority Critical patent/US3891351A/en
Priority to CA221,211A priority patent/CA1018462A/en
Priority to GB9431/75A priority patent/GB1500044A/en
Priority to DE19752512347 priority patent/DE2512347A1/de
Priority to JP50034260A priority patent/JPS50129811A/ja
Priority to FR7509098A priority patent/FR2265975B3/fr
Application granted granted Critical
Publication of US3891351A publication Critical patent/US3891351A/en
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    • 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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type

Definitions

  • ABSTRACT This disclosure is directed to turbine machinery discs having improved elevation and contouring of the disc rim lugs and blade attachment slots local to the outer diameter blade attachment lug and slot surfaces of said discs thus providing a strain-conforming and re straining surface for redistributing and resisting the transmission of blade shank tang stresses and strains as they develop in the root attachment lands and transition zones of the turbomachinery blades.
  • these disc rims suitable for use in turbomachinery attachment devices, exhibit restraining surfaces different from prior art rims in that they afford additional restraining surfaces due to the elevated rim lug height at the uppermost portions of the rim lugs thereby providing additional, smooth contacting lug surfaces for absorbing and distributing stresses, such as, centrifugal, centrifugal untwist, gas bending, vibratory, foreign object impact and other forms of complex stresses.
  • the outer portions of the disc rim lugs are raised (elevated) adjacent to the slots in contrast with lower disc rim portions between said raised lugs.
  • These raised portions have a gradual radius of curvature, which is substantially equal and symmetrical for each rim lug set accommodating each blade.
  • the curvature of the outer rim lugs is more gradual than that of the lower ends of the rim slots which accommodate the blade tang portions.
  • Each symmetrical rim slot accommodating each peripherally mounted blade, has a pair of extended (raised) lug portions, the height (diameter) of which approximately equals that of each other.
  • Each disc rim has symmetrical approximately equal respective lower intermediate portions (between the raised lugs), said lower portions being of approximately equal diameter.
  • FIG. I of the drawing is a perspective view, partly in section, illustrating an individual turbine blade in its individual disc attachment. It will be realized that actual turbine rotors have a plurality of such blades and disc attachments customarily spaced peripherally about the rim portion of a disc for rotation. These blades are arranged circumferentially in fluid flow machines such, for example, as turbomachinery compressors and turbines.
  • FIGS. 2 and 3 are likewise perspective views, partly in section, showing further configurations of prior art devices evidencing similar disc rim and blade root attachment relationships.
  • FIGS. 4(A) and 4(8) are both side views showing a characteristic prior art disc rim having a plurality of rim slot and lug portions in christmas tree arrangement.
  • FIG. 5 is a sectional view taken along the line 55 of FIG. 4( B) illustrating in detail the dead rim, live rim, web and bore portions of such a disc rim.
  • FIGS. 6 and 7 are perspective views, partly in section, illustrating the disc rims of this invention resulting in the improved features which will be pointed out hereinafter.
  • FIG. 8(A) is a schematic showing of a typical positioning of a prior art turbine blade in relation to the characteristic root attachments, surfacing and disc rim attachment configuration typical of FIGS. 1, 2 and 3.
  • FIG. 8(B) is a schematic view of the blade attachment of FIG. 8(A) in perspective showing the blade attachment land surface 5.
  • FIG. 9 is a diagrammatic view vectorially illustrating the strain distribution typically occurring on the blade root attachment tang, adjoining blade shank and transition surfaces resulting from steady centrifugal body forces during rotation of turbine blades mounted in prior art rims.
  • a high strain gradient results at this point where the local tensile and compressive strains become additive and reinforce each other.
  • the strain field is entirely tensile above the point of contact and changes to compression as the load is introduced into the disc lug at the zone of contact.
  • FIG. 10 is a similar diagrammatic view showing in section the strain field amplification to which prior art devices are subjected when a bending moment is applied in conjunction with centrifugal body forces.
  • Such bending moments are characteristically introduced by such causes as steady and unsteady gas dynamic pressure forces, airfoil untwist, natural resonance vibrations and instantaneous impacts from foreign object debris.
  • FIGS. 11 and 12 diagrammatically illustrate by vectorial notation the effect of the devices of the invention in providing a reduction in the magnitude of the peak strains through redistribution.
  • turbine blade 1 has a platform portion 2. Beneath the blade platform is a centrally located blade shank 3 which merges into a root attachment transition zone shown at 4 and thence downwardly to the root attachment land surfaces, viz., such as at surfaces 5, FIG. 8(B), of the blade tang portions 6.
  • the blade root attachment is thus made up of blade shank portion 3 and tang portions 6 which underlie transition zone 4.
  • the blade root attachment is received in the cavities or slot portions 9 of disc rim portions 7 of disc 8. See FIGS. 4(A) and 4(8).
  • the mounting disc 8 has a disc rim portion 7 in which there are a plurality of circumferentially located slots 9, of varying configurations depending on blade configuration.
  • the rim portion 7 of the disc can be further divided into an upper (dead) rim portion R and a lower live rim portion R as shown in FIG. 5.
  • the disc portions underlying the rim are the web portion W and the bore portion B.
  • Each disc rim has lug portions 11.
  • the upper portions U of the prior art disc rim lugs are of generally uniform. height (diameter) and curvature in the outer rim periphery.
  • the discs of this invention have rims whose outer periphery have raised (elevated) lug portions 13 adjacent to the slots and lower intermediate rim portions 12 between raised portions 13.
  • the disc rim cavities or lugs 9 receive the root attachment in a position where the shank to root attachment transition zone 4 lies closer to the upper portion of blades 1.
  • the zones of immediate stress-strain reaction are the blade root attachment tang zones shown by cross-hatching at 10. Such stress-strain reaction zones 10 are shown on both the left and right hand sides of the root attachment for blade 1 of FIG. 2.
  • FIGS. 3, 4(A) and 4(8) illustrate characteristic prior art blade root and disc lug attachment configuration referred to in the art as a Christmas tree.
  • the blade root attachment is defined by a plurality of blade tang portions 6 (FIG. 3), each such portion having mating lugs 11 (FIG. 4(A)) defining the slot portions 9 in the disc rim 7 which terminate upwardly at the outer rim periphery in outermost portions U of uniform height (diameter) and curvature in the outer rim periphery.
  • FIGS. 6 and 7, illustrating the present invention characteristically show disc rim lugs 11 and corresponding disc rim slots 9 having both elevated, raised or extended portions 13 above the lower intermediate rim portions 12 (which are the adjacent and lower lying portions of the disc rim periphery).
  • the elevated rim lug portions 13 provide increased restraint for reducing the bending deflections reacted as moments in the blade shank/transition regions. Positioning of the extended disc rim lugs in close proximity to the blade shank provides restraint of the shank which limits movement of the blade attachment tangs when centrifugal body forces load the blade attach ment tangs against the disc raised lugs portions 13 during rotation. This provides more uniform strain distribution for the attachment surfaces.
  • the smoothly radiused raised lug surfaces 13 of this invention tend to avoid stress/strain concentrations on blade shank surfaces such as occur when the shank comes in contact with the upper uniform surface portions U of the disc lug 11 typical of FIGS. 1 3, 4(A), 4(3) and 5.
  • the smoothly radiused surfaces provide, at a distance removed from the local origins of normal high strain intensity, non-linear contact surfaces that absorb bending induced contact pressure forces in a graduated manner.
  • the uniform geometric contouring of the elevated rim lug portions 13 is proportioned to accommodate the magnitude and rate of blade deflection during bending.
  • the net effect of the features of this invention is to reduce or substantially eliminate abrupt stress/strain transitions and load non-uniformities as compared with known art root attachments such as shown in FIGS. 1, 2, 3, 4(A), 4(8), and 5.
  • Such concentrated stress/strain fields are normally accommodated by the inherent ductility of conventional materials such as steel, titanium and nickel-based, so-called superalloys.
  • Brittle materials such as ceramics and composites possess limited ductility and must avoid such abrupt contour changes to prevent stress concentrations from interacting.
  • FIG. 2. there can exist a zone of comparatively severe stress-strain interaction in a deflected blade.
  • a further advantage of this invention resides in the fact that not only monolithic materials but also ceramics and composite material systems can be utilized to make integral discs within the purview of this invention.
  • materials such as composites and ceramics, while usually classified as brittle because they possess little or no ductility for redistributing local stress-strain concentrations, can be utilized in turbomachinery in-- corporating this invention.
  • the restraining effect provided by this invention suppresses load shifting from one blade root attachment to its opposing partner.
  • the elevated rim lug 11 can be in intimate contact with the blade shank portion prior to rotation or separated therefrom by a normal assembly tolerance gap.
  • FIGS. 9 and 10 depict characteristic prior art stressstrain relationships vectorially and illustrate contrasts between disc rims of FIGS. 1, 2 and 3. Such relationships can be compared with those characteristic of this invention as illustrated by the diagrams of FIGS. 11 and 12 with FIG. 11 referring to FIG. 6 and FIG. 12 illustrating the general effect of FIG. 7s configuration on strain distribution.
  • FIG. 8(A) depicts one of the typical disc-to-blade root attachment configurations known within the art in reference to FIGS. 1 and 2.
  • FIG. 9 illustrates the strain distribution existing on the outer portions of the blade attachment surfaces under uniformly loaded conditions for the same configuration as FIG. 8(A).
  • a strain reversal occurs at the initial point of contact of the disc rim lug (upper portion) with the blade attachment shank.
  • the reversal occurs as the blade shank load is transferred to the root attachment tang.
  • the outer surface strain distribution shown in FIGS. 9 12 is tensile as it approaches the contact point and it then converts to compression
  • the intensity of the strain reversal is illustrated in FIG. 10 and occurs as a consequence of load redistribution in the form of bending.
  • FIG. 11 illustrates the effect of the configuration of FIG. 6 on load distribution.
  • the magnitude of the stress reversal is reduced (as compared with FIG. I as illustrated in FIG. 9) and taken up over a greater distance upwards along the shank surface.
  • FIG. 12 illustrates the effect of the configuration of FIG. 7 on load distribution. Similarly, the magnitude of the stress reversal is reduced (as compared with FIG. 2 as illustrated in FIG. 10) and is distributed over a significantly greater distance upwards along the blade shank surface in like manner to that shown in FIG. II.
  • the present invention differs significantly from conventional prior art disc rims which differ from one another based on metal characteristics which provide stress redistributing capability through inherent ductility of the metal.
  • This invention offers a distinct advantage of flexibility in choice of materials because these configurations avoid the generation of strain gradients critical to material having low ductility such as composites and ceramics.
  • the significance of this is that the present invention permits the utilization of not only monolithic materials but also ceramics, and composite material systems of ceramics and metals,-viz., ceramets in addition to the so-called superalloys.
  • the present invention can utilize such integral disc materials as: monolithic material, such stainless steel; titanium alloys customarily usable at temperatures of 900F.
  • nickel and cobalt-based so-called superalloys viz., metal alloys containing nickel and/or cobalt and having a melting point range of approximately 2400F. to 2500F. and usable at temperatures up to 1800F.; ceramics stable at temperatures up to about 2500F.; fiber-reinforced metallic or inorganic and organic composite material systems, such as Boron/Aluminum, Graphite/Epoxy, Borsic Titanium etc.
  • Other organic polymeric materials can be used, e.g., silicone resins.
  • a turbine machinery disc having bore, web and rim portions, the rim portion of which is comprised of:
  • each lug having raised outer portions which are substantially of the same height and gradual radius of curvature, which radius of curvature exceeds that of said blade-tang accommodating slot portions;
  • said disc being further characterized as avoiding direct sharing of tension and compression between adjacent blades.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US454372A 1974-03-25 1974-03-25 Turbine disc Expired - Lifetime US3891351A (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
US454372A US3891351A (en) 1974-03-25 1974-03-25 Turbine disc
CA221,211A CA1018462A (en) 1974-03-25 1975-03-04 Turbine discs
GB9431/75A GB1500044A (en) 1974-03-25 1975-03-06 Turbomachinery discs
DE19752512347 DE2512347A1 (de) 1974-03-25 1975-03-20 Turbinenlaeufer
JP50034260A JPS50129811A (sv) 1974-03-25 1975-03-20
FR7509098A FR2265975B3 (sv) 1974-03-25 1975-03-24

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US454372A US3891351A (en) 1974-03-25 1974-03-25 Turbine disc

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US3891351A true US3891351A (en) 1975-06-24

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US454372A Expired - Lifetime US3891351A (en) 1974-03-25 1974-03-25 Turbine disc

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US (1) US3891351A (sv)
JP (1) JPS50129811A (sv)
CA (1) CA1018462A (sv)
DE (1) DE2512347A1 (sv)
FR (1) FR2265975B3 (sv)
GB (1) GB1500044A (sv)

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4335998A (en) * 1978-05-24 1982-06-22 Volkswagenwerk Aktiengesellschaft Ceramic-metal assembly
US5100292A (en) * 1990-03-19 1992-03-31 General Electric Company Gas turbine engine blade
USRE33954E (en) * 1982-02-22 1992-06-09 United Technologies Corporation Rotor blade assembly
US5160243A (en) * 1991-01-15 1992-11-03 General Electric Company Turbine blade wear protection system with multilayer shim
US5183389A (en) * 1992-01-30 1993-02-02 General Electric Company Anti-rock blade tang
FR2697051A1 (fr) * 1992-10-21 1994-04-22 Snecma Rotor de turbomachine comprenant un disque dont le pourtour est occupé par des alvéoles obliques qui alternent avec des dents de section transversale variable.
US5435694A (en) * 1993-11-19 1995-07-25 General Electric Company Stress relieving mount for an axial blade
US5573862A (en) * 1992-04-13 1996-11-12 Alliedsignal Inc. Single crystal oxide turbine blades
US5573377A (en) * 1995-04-21 1996-11-12 General Electric Company Assembly of a composite blade root and a rotor
US5593282A (en) * 1994-09-16 1997-01-14 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Turbomachine rotor construction including a serrated root section and a rounded terminal portion on a blade root, especially for an axial-flow turbine of a gas turbine engine
US6511294B1 (en) * 1999-09-23 2003-01-28 General Electric Company Reduced-stress compressor blisk flowpath
US20040005219A1 (en) * 2002-04-02 2004-01-08 Phipps Anthony B. Rotor disc for gas turbine engine
US20120027605A1 (en) * 2010-07-27 2012-02-02 Snecma Propulsion Solide Turbomachine blade, a rotor, a low pressure turbine, and a turbomachine fitted with such a blade
US20120269637A1 (en) * 2011-04-19 2012-10-25 Rolls-Royce Plc Methods for controlling friction between heterogeneous contact surfaces
CN102817639A (zh) * 2012-06-18 2012-12-12 北京航空航天大学 一种低应力波浪型接触面直榫连接结构
RU2495255C2 (ru) * 2012-01-13 2013-10-10 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Лопатка осевой лопаточной машины
US9039375B2 (en) 2009-09-01 2015-05-26 General Electric Company Non-axisymmetric airfoil platform shaping
EP2372096A3 (en) * 2010-03-10 2015-07-01 United Technologies Corporation Composite fan blade dovetail root
US10215040B2 (en) 2014-01-16 2019-02-26 Ihi Corporation Coupling part structure for vane and jet engine including the same
US11371527B2 (en) * 2017-09-14 2022-06-28 Doosan Heavy Industries & Construction Co., Ltd. Compressor rotor disk for gas turbine

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4191509A (en) * 1977-12-27 1980-03-04 United Technologies Corporation Rotor blade attachment
JPS61106974A (ja) * 1984-10-30 1986-05-24 Nippon Denso Co Ltd 遊星歯車減速機構付スタ−タ
US4824328A (en) * 1987-05-22 1989-04-25 Westinghouse Electric Corp. Turbine blade attachment
US5480285A (en) * 1993-08-23 1996-01-02 Westinghouse Electric Corporation Steam turbine blade
EP2322764A1 (de) * 2009-11-17 2011-05-18 Siemens Aktiengesellschaft Turbinenschaufelbefestigung für eine Strömungsmaschine
JP2017120046A (ja) * 2015-12-28 2017-07-06 株式会社東芝 ダブテールジョイント
CN111795000B (zh) * 2020-07-06 2022-02-18 江苏大学镇江流体工程装备技术研究院 一种导轨固定叶片的旋流泵叶轮

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3294364A (en) * 1962-01-02 1966-12-27 Gen Electric Rotor assembly
US3612718A (en) * 1968-12-16 1971-10-12 Rolls Royce Bladed member for a fluid flow machine
US3809495A (en) * 1973-03-27 1974-05-07 Westinghouse Electric Corp Turbine rotor having cushioned support surfaces for ceramic blades mounted thereon

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3294364A (en) * 1962-01-02 1966-12-27 Gen Electric Rotor assembly
US3612718A (en) * 1968-12-16 1971-10-12 Rolls Royce Bladed member for a fluid flow machine
US3809495A (en) * 1973-03-27 1974-05-07 Westinghouse Electric Corp Turbine rotor having cushioned support surfaces for ceramic blades mounted thereon

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4335998A (en) * 1978-05-24 1982-06-22 Volkswagenwerk Aktiengesellschaft Ceramic-metal assembly
USRE33954E (en) * 1982-02-22 1992-06-09 United Technologies Corporation Rotor blade assembly
US5100292A (en) * 1990-03-19 1992-03-31 General Electric Company Gas turbine engine blade
US5160243A (en) * 1991-01-15 1992-11-03 General Electric Company Turbine blade wear protection system with multilayer shim
US5183389A (en) * 1992-01-30 1993-02-02 General Electric Company Anti-rock blade tang
US5573862A (en) * 1992-04-13 1996-11-12 Alliedsignal Inc. Single crystal oxide turbine blades
FR2697051A1 (fr) * 1992-10-21 1994-04-22 Snecma Rotor de turbomachine comprenant un disque dont le pourtour est occupé par des alvéoles obliques qui alternent avec des dents de section transversale variable.
US5395213A (en) * 1992-10-21 1995-03-07 Societe Nationale D'etude Et De Construction De Motors D'aviation "Snecma" Turbojet engine rotor
US5435694A (en) * 1993-11-19 1995-07-25 General Electric Company Stress relieving mount for an axial blade
US5593282A (en) * 1994-09-16 1997-01-14 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Turbomachine rotor construction including a serrated root section and a rounded terminal portion on a blade root, especially for an axial-flow turbine of a gas turbine engine
US5573377A (en) * 1995-04-21 1996-11-12 General Electric Company Assembly of a composite blade root and a rotor
EP1087100A3 (en) * 1999-09-23 2004-01-02 General Electric Company Compressor rotor configuration
US6511294B1 (en) * 1999-09-23 2003-01-28 General Electric Company Reduced-stress compressor blisk flowpath
US20040005219A1 (en) * 2002-04-02 2004-01-08 Phipps Anthony B. Rotor disc for gas turbine engine
US6893226B2 (en) * 2002-04-02 2005-05-17 Rolls-Royce Plc Rotor disc for gas turbine engine
US9039375B2 (en) 2009-09-01 2015-05-26 General Electric Company Non-axisymmetric airfoil platform shaping
EP2372096A3 (en) * 2010-03-10 2015-07-01 United Technologies Corporation Composite fan blade dovetail root
US20120027605A1 (en) * 2010-07-27 2012-02-02 Snecma Propulsion Solide Turbomachine blade, a rotor, a low pressure turbine, and a turbomachine fitted with such a blade
US8951017B2 (en) * 2010-07-27 2015-02-10 Snecma Turbomachine blade, a rotor, a low pressure turbine, and a turbomachine fitted with such a blade
US20120269637A1 (en) * 2011-04-19 2012-10-25 Rolls-Royce Plc Methods for controlling friction between heterogeneous contact surfaces
US9140131B2 (en) * 2011-04-19 2015-09-22 Rolls-Royce Plc Methods for controlling friction between heterogeneous contact surfaces
RU2495255C2 (ru) * 2012-01-13 2013-10-10 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Лопатка осевой лопаточной машины
CN102817639B (zh) * 2012-06-18 2014-12-24 北京航空航天大学 一种低应力波浪型接触面直榫连接结构
CN102817639A (zh) * 2012-06-18 2012-12-12 北京航空航天大学 一种低应力波浪型接触面直榫连接结构
US10215040B2 (en) 2014-01-16 2019-02-26 Ihi Corporation Coupling part structure for vane and jet engine including the same
US11371527B2 (en) * 2017-09-14 2022-06-28 Doosan Heavy Industries & Construction Co., Ltd. Compressor rotor disk for gas turbine

Also Published As

Publication number Publication date
FR2265975A1 (sv) 1975-10-24
DE2512347A1 (de) 1975-10-09
FR2265975B3 (sv) 1977-11-25
CA1018462A (en) 1977-10-04
JPS50129811A (sv) 1975-10-14
GB1500044A (en) 1978-02-08

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