US2967043A - Blades and blade mounting assemblies for turbines and axial flow compressors - Google Patents

Blades and blade mounting assemblies for turbines and axial flow compressors Download PDF

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Publication number
US2967043A
US2967043A US695841A US69584157A US2967043A US 2967043 A US2967043 A US 2967043A US 695841 A US695841 A US 695841A US 69584157 A US69584157 A US 69584157A US 2967043 A US2967043 A US 2967043A
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United States
Prior art keywords
blade
root
blades
tongues
groove
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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
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US695841A
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English (en)
Inventor
Leonard J Dennis
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.)
Napier Turbochargers Ltd
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D Napier and Son Ltd
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Filing date
Publication date
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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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • 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 blades and blade mounting assemblies for turbines or axial flow compressors, of the kind in which the mounting is provided with a ring of substantially axial grooves to receive the blade roots and each blade is made of sheet metal or tube manipulated into hollow aerofoil form.
  • each blade is made of sheet metal or tube manipulated into hollow aerofoil form with two root tongues, one tongue extending from the concave flank and fitting in one of the said grooves in the mounting together with the root tongue extending from the convex flank of the adjacent blade on one side, and the other tongue extending from the convex flank and fitting in the adjacent groove together with the root tongue extending from the concave flank of the adjacent blade on the other side, and there are platform members between adjacent blades each platform member having a projection which enters the groove occupied by root tongues of the blades on each side of it.
  • This arrangement enables the root tongues to be spaced a substantial distance apart to lend lateral rigidity to the blades while the grooves can be made relatively narrow, and it also permits the provision of platform members which are separate from the blades and which therefore do not increase the weight or complicate the construction of the blades.
  • each platform member is approximately T- or L-shaped in cross-section, the stem of the T or L constituting the projection which enters the groove and the cross piece of the T or L constituting a barrier which extends between adjacent blades.
  • the side walls of each groove may be undercut, the root tongues being formed to extend into these undercut portions of the groove and the projection of the platform member having an enlarged and the width of which is wider than the gap between the root tongues at the mouth of the groove.
  • a retaining key may be inserted into each groove to wedge the two root tongues and the platform projection firmly in the groove.
  • At least one root tongue of each blade, in the transi tion zone between the aerofoil zone and the root zone of the blade, may be provided with a resilient lug engaging an adjacent platform member and serving to modify the vibration characteristics of the blade.
  • a tubular ferrule extends transversely through each blade in the transition zone between the aerofoil zone and the root zone, and at least one lacing wire passes through these ferrules and through the platform members, which wire serves to modify the vibration characteristics of the blades.
  • wire lacing has an advantageous effect on blade vibration characteristics, but it has hitherto been the customary practice to thread such lacing wires through the aerofoil portions of the blades. This has the disadvantage that the lacing wires are in the gas stream. By putting the lacing wire in the transition zone it is removed from the gas stream. The ferrules reduce wear in the thin metal of the blades where the lacing wire passes through the blades, and in the wire itself.
  • Figure l is an exploded perspective view of a fragment of a turbine rotor embodying the invention, showing part of the turbine disc, two adjacent turbine blades, a platform member shared by these two blades, and a retaining key for these parts;
  • Figure 2 is a fragmentary cross-section of the assembled turbine rotor of Figure l on a larger scale
  • Figure 3 is a fragmentary cross-section similar to Figure 2 showing a modification
  • Figure 4 is a fragmentary cross-section similar to Figure 2 showing another modification.
  • Figure 5 is a developed circumferential section taken on the line V-V in Figure 4.
  • the turbine rotor consists of a turbine disc 10 having straight axial grooves 11 formed around its periphery.
  • Each groove 11 is undercut so that in cross-section it has a circular inner portion 12 communicating with the periphery of the turbine disc through a relatively narrow mouth 13.
  • the side walls 51, 52 of each groove 11 have undercut lower portions defined by said circular inner portion 12, and overhanging upper extremities 53, 54 defining said mouth13.
  • Each blade is made of a single piece of sheet metal or tube manipulated into appropriate form, and consists of an aerofoil zone 14 having a convex flank 15 and a concave flank 16, and, extending from the flanks, root tongues 17 and 18 respectively.
  • Each root tongue comprises a transition zone 19 and terminates in a root zone 20.
  • the extremities of the root tongues are shaped to fit in the grooves 11, one tongue 17 in one groove and the other tongue 18 in the adjacent groove.
  • the root tongues 17 and 18 are splayed outwardly so as to provide a considerably wider base for the blade than is obtained in conventional constructions in which the root portion of a blade is received in one groove in the rotor.
  • Each platform member is approximately T-shaped in cross-section for the major portion of its length, except at and near its centre where it is approximately L-shaped as shown in Figure 2,
  • This top portion has a convex top edge 22 and a concave top edge 23.
  • the convex top edge 22 lies against the concave flank 16 of the blade on one side of the platform member, at the level of the junction between the aerofoil zone 14 and the transition zone 19, and the concave top edge 23 lies against the convex flank 15 of the blade on the other side, also at the level of the junction between the aerofoil and transition zones.
  • a perforated projection 24 which constitutes the stem of the T or L in cross-section is straight to conform to the groove 11 in which it is to be inserted.
  • the foot of the projection 24 is in the form of a semi-cylindrical bulge which lies within the circular undercut portion ,12 of the appropriate groove 11 in the assembled rotor,
  • the blades and platform members are first assembled into a ring on a suitable jig and the rotor disc is then applied in an axial direction so that the foot of the projection of each platform member and the adjacent root tongues of the blades on each side together enter one of the grooves in the rotor.
  • Semicylindrical keys 28 are then driven into thesemi-cylindrical spaces left in the grooves between the extremities of the root tongues therein and beneath the bulges 25 of the platform members, so as firmly to wedge the platform members and the root tongues in the grooves.
  • a resilient lug 30 is welded to the root tongue 18 of each blade.
  • Each lug is approximately L-shaped in crosssection, one limb 31 having a hole 32 in it through which the weld metal 33 isapplied, and the other limb 34 being doubled over to press against the underside of the top of they adjacent platform member 21.
  • the limb 34 of the lug by resiliently pressing against the platform member 21, provides frictional restraint against transverse vibrations of the blade and thereby modifies favourably thevibration characteristics of the blade.
  • a ferrule 37 extends through apertures in the root tongues 17 and 18 of each blade and is welded or brazed in position.
  • the bore of. the ferrule is reduced atv 38 as shown in Figure 5, and, a lacing wire 39 is threaded circumferentially through the bores of all the ferrules, this wire being a snug fit in the reduced bores 38..
  • the wire 39 may be bulged as shown at 40 or otherwise deformed in order to locate it circumferentially.
  • the lacing wire passes through the transition zone 19 of each blade and through one of the. perforations 41 in the projection 24 of each platform member.
  • the lacing wire-favourably modifies the vibration characteristics of the blades by applying frictional restraint against lateral flutter.
  • the ferrules prevent the lacing wire from causing wear on the root tongues where the wire passes through the latter.
  • apertures such as 56 may be provided between these tongues for the admission and/or discharge of cooling medium if it is desired to circulate this through the interior of the hollow blades.
  • a blade and blade mounting assembly comprising a plurality of blades each made of thin metal and having an aero'foil portion with 'a convex flank and a concave flank, a first root tongue extending from said convex flank and a second root tongue extending from said concave flank, said blade mounting having grooves therein including side walls defining a plurality of substantially axial blade root supports, said side walls having undercut lower portions and overhanging upper extremities defining a mouth to each of said grooves, platform membersdisposed between adjacent blades, each platform member having a projection received in one of said grooves which groove also receives said first root tongue of a blade adjacent one side of said platform member and said second root tongue of a blade adjacent the opposite side of said platform member, said first and second root tongues extending through said mouth into said undercut lower portions and fitting against said groove side walls with a gap between said root tongues at said mouth, said projection of said platform member extending through said gap and having an enlarged inner end the width of which is wider than said gap and which
  • each platform member has a crosspiece constituting a transverse barrier extending from the convex flank of said blade on one side of said plat- ;form member to the concave flank of said blade on the opposite side of said platform member.
  • each. root tongue has a root zone which lies within one of saidgrooves and a transition zone extending from said root zone to said aerofoil portion, and a resilient lug is provided on at least one root tongue of each blade in said transition zone which lug engages the adjacent platform member.
  • each root tongue has a root zone which lies within one of said grooves and a transition zone extending from said root zone to said aerofoil portion, a tubular ferrule extends transversely through the two root tongues of each blade in said transition zone, and at least'one lacing wire extends through said ferrules and said platform members.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US695841A 1956-11-30 1957-11-12 Blades and blade mounting assemblies for turbines and axial flow compressors Expired - Lifetime US2967043A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB345903X 1956-11-30

Publications (1)

Publication Number Publication Date
US2967043A true US2967043A (en) 1961-01-03

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Family Applications (1)

Application Number Title Priority Date Filing Date
US695841A Expired - Lifetime US2967043A (en) 1956-11-30 1957-11-12 Blades and blade mounting assemblies for turbines and axial flow compressors

Country Status (6)

Country Link
US (1) US2967043A (fr)
BE (1) BE562857A (fr)
CH (1) CH345903A (fr)
FR (1) FR1188652A (fr)
GB (1) GB822067A (fr)
NL (2) NL102164C (fr)

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3034764A (en) * 1959-12-18 1962-05-15 Gen Electric Damping means
US3294364A (en) * 1962-01-02 1966-12-27 Gen Electric Rotor assembly
US3393862A (en) * 1965-11-23 1968-07-23 Rolls Royce Bladed rotors
US3471127A (en) * 1966-12-08 1969-10-07 Gen Motors Corp Turbomachine rotor
US3741681A (en) * 1971-05-28 1973-06-26 Westinghouse Electric Corp Hollow turbine rotor assembly
US3801222A (en) * 1972-02-28 1974-04-02 United Aircraft Corp Platform for compressor or fan blade
US4019832A (en) * 1976-02-27 1977-04-26 General Electric Company Platform for a turbomachinery blade
US4045149A (en) * 1976-02-03 1977-08-30 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Platform for a swing root turbomachinery blade
US4277225A (en) * 1977-09-23 1981-07-07 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Rotor for jet engines
US5049035A (en) * 1988-11-23 1991-09-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Bladed disc for a turbomachine rotor
US5277548A (en) * 1991-12-31 1994-01-11 United Technologies Corporation Non-integral rotor blade platform
US20130343895A1 (en) * 2012-06-25 2013-12-26 General Electric Company System having blade segment with curved mounting geometry
US20140072436A1 (en) * 2012-09-11 2014-03-13 Seth J. Thomen Turbine airfoil platform rail with gusset
US20140133992A1 (en) * 2010-07-13 2014-05-15 Jeffrey Brooks Connection mechanism for mounting blades for a wind turbine
US20140286781A1 (en) * 2013-01-11 2014-09-25 United Technologies Corporation Integral fan blade wear pad and platform seal
US20150361798A1 (en) * 2013-02-12 2015-12-17 United Technologies Corporation Fan blade including external cavities
CN110566282A (zh) * 2019-10-24 2019-12-13 哈尔滨汽轮机厂有限责任公司 一种适用于低负荷工况运行的835mm末级动叶片
US10767498B2 (en) * 2018-04-03 2020-09-08 Rolls-Royce High Temperature Composites Inc. Turbine disk with pinned platforms
US11131197B2 (en) * 2018-04-20 2021-09-28 Safran Aircraft Engines Blade comprising a structure made of composite material and method for manufacturing the same

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2139295A (en) * 1983-05-05 1984-11-07 Tuomo Kaivola Thermal joint e.g. for a turbine
US5425622A (en) * 1993-12-23 1995-06-20 United Technologies Corporation Turbine blade attachment means
GB201106278D0 (en) 2011-04-14 2011-05-25 Rolls Royce Plc Annulus filler system

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB190815893A (en) * 1908-07-27 1909-01-28 Arthur William Cooper Improvements in Turbine Engines.
FR969413A (fr) * 1948-07-20 1950-12-20 Const Et D Equipements Ments M Perfectionnement dans la construction et la fixation des aubes creuses pour turbinesà gaz
FR998221A (fr) * 1949-10-26 1952-01-16 Soc D Const Et D Equipements M Perfectionnements dans la fixation des aubes de turbo-machines
GB701263A (en) * 1950-08-03 1953-12-23 Rolls Royce Improvements in or relating to turbo-machines

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB190815893A (en) * 1908-07-27 1909-01-28 Arthur William Cooper Improvements in Turbine Engines.
FR969413A (fr) * 1948-07-20 1950-12-20 Const Et D Equipements Ments M Perfectionnement dans la construction et la fixation des aubes creuses pour turbinesà gaz
FR59398E (fr) * 1948-07-20 1954-05-25 Const Et D Equipements Mecaniq Perfectionnements dans la construction et la fixation des aubes creuses pour turbines à gaz
FR998221A (fr) * 1949-10-26 1952-01-16 Soc D Const Et D Equipements M Perfectionnements dans la fixation des aubes de turbo-machines
GB701263A (en) * 1950-08-03 1953-12-23 Rolls Royce Improvements in or relating to turbo-machines

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3034764A (en) * 1959-12-18 1962-05-15 Gen Electric Damping means
US3294364A (en) * 1962-01-02 1966-12-27 Gen Electric Rotor assembly
US3393862A (en) * 1965-11-23 1968-07-23 Rolls Royce Bladed rotors
US3471127A (en) * 1966-12-08 1969-10-07 Gen Motors Corp Turbomachine rotor
US3741681A (en) * 1971-05-28 1973-06-26 Westinghouse Electric Corp Hollow turbine rotor assembly
US3801222A (en) * 1972-02-28 1974-04-02 United Aircraft Corp Platform for compressor or fan blade
US4045149A (en) * 1976-02-03 1977-08-30 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Platform for a swing root turbomachinery blade
US4019832A (en) * 1976-02-27 1977-04-26 General Electric Company Platform for a turbomachinery blade
US4277225A (en) * 1977-09-23 1981-07-07 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Rotor for jet engines
US5049035A (en) * 1988-11-23 1991-09-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Bladed disc for a turbomachine rotor
US5277548A (en) * 1991-12-31 1994-01-11 United Technologies Corporation Non-integral rotor blade platform
US20140133992A1 (en) * 2010-07-13 2014-05-15 Jeffrey Brooks Connection mechanism for mounting blades for a wind turbine
US20130343895A1 (en) * 2012-06-25 2013-12-26 General Electric Company System having blade segment with curved mounting geometry
US10633985B2 (en) * 2012-06-25 2020-04-28 General Electric Company System having blade segment with curved mounting geometry
US20140072436A1 (en) * 2012-09-11 2014-03-13 Seth J. Thomen Turbine airfoil platform rail with gusset
US9243501B2 (en) * 2012-09-11 2016-01-26 United Technologies Corporation Turbine airfoil platform rail with gusset
US20140286781A1 (en) * 2013-01-11 2014-09-25 United Technologies Corporation Integral fan blade wear pad and platform seal
US9650902B2 (en) * 2013-01-11 2017-05-16 United Technologies Corporation Integral fan blade wear pad and platform seal
US20150361798A1 (en) * 2013-02-12 2015-12-17 United Technologies Corporation Fan blade including external cavities
US10767498B2 (en) * 2018-04-03 2020-09-08 Rolls-Royce High Temperature Composites Inc. Turbine disk with pinned platforms
US11131197B2 (en) * 2018-04-20 2021-09-28 Safran Aircraft Engines Blade comprising a structure made of composite material and method for manufacturing the same
CN110566282A (zh) * 2019-10-24 2019-12-13 哈尔滨汽轮机厂有限责任公司 一种适用于低负荷工况运行的835mm末级动叶片

Also Published As

Publication number Publication date
CH345903A (fr) 1960-04-30
BE562857A (fr)
GB822067A (en) 1959-10-21
NL102164C (fr)
FR1188652A (fr) 1959-09-24
NL222612A (fr)

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