US2925997A - Rotors for axial-flow fluid machines with pivoted blades and blade pivot retaining means - Google Patents

Rotors for axial-flow fluid machines with pivoted blades and blade pivot retaining means Download PDF

Info

Publication number
US2925997A
US2925997A US533782A US53378255A US2925997A US 2925997 A US2925997 A US 2925997A US 533782 A US533782 A US 533782A US 53378255 A US53378255 A US 53378255A US 2925997 A US2925997 A US 2925997A
Authority
US
United States
Prior art keywords
plates
pivot pins
axial
disc
facing
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
US533782A
Other languages
English (en)
Inventor
Hart Raymond
Hodgkinson Peter Rex
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 claimed from GB1482553A external-priority patent/GB745073A/en
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Application granted granted Critical
Publication of US2925997A publication Critical patent/US2925997A/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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3053—Fixing blades to rotors; Blade roots ; Blade spacers by means of pins

Definitions

  • This invention relates to bladed rotors for axial-flow iluid machines and is concerned with bladed rotors of the kind in which blade elements are secured to the periphery of a disc bymeans of pivot pins which engage aligned holes in flanges onl the disc periphery and lugs forming part of the blade roots.
  • a bladed rotor will be referred to hereinafter as a bladed rotor of the kind specified.
  • a bladed rotor of the kind specified comprises means for retaining the pivot pins against disengagement from the holes in the flanges and in the lugs, which means comprises radially-extending plates mounted on and having interlocking engagement with the periphery of the disc and adapted to engage the ends of the pivot pins to prevent their disengagement from. the holes.
  • the pivot pins are provided with reduced-diameter portions terminating in ilange-like heads and the plates are of arcuate form and are provided with a number of circumferentiallyspaced circumferentially-extending keyhole type slots disposed to co-operate with the heads of a number of the pivot pins to prevent their disengagement.
  • either the plates are positioned by engaging the slots over the flange-like heads of the pivot pins or the pins are inserted after the positioning of the plates by passing their heads through the keyhole slots; thereafter, in either case, the plates are displaced circumferentially to enable the smaller-dimensioned ends of the keyhole slots to engage with thereduced-diameter portions between the flangelike heads and the main portions of the pivot pins, and
  • the plates are also provided with parts which, during the circumferential movement of the plates into their pivot pin retaining positions, interlock with the disc periphery to retain the plates axially in position. Means is also provided to retain the plates circumferentially in position.
  • the pivot pins are provided with enlarged heads to prevent disengagement of the pivot pins from the disc periphery in one direction and the retaining plates are provided to bear against the heads of the pivot pins to prevent their disengagement in the opposite direction.
  • the retaining plates are provided with features which interlock with the disc periphery by a circumferential displacement to retain the plates axially in position and that means is also provided to hold the plates against circumferential ⁇ displacement after assembly.
  • the pivot pins are plain cylindrical pins and retaining plates are provided on each side of the disc periphery to prevent disengagement of the pivot pins.
  • the plates be adapted to interlock with features on the disc periphery by a circumferential movement to retain then; axially against the disc periphery and that means be also provided to retain the retaining plates against circumferential displacement after assembly.
  • Figure 1 is an axial view of part of a rotor disc carrying a number of pivoted blades at its periphery
  • Figure 2 is a section on the line 2-2 of Figure l
  • Figure 3 is a view corresponding to Figure 1 of a second embodiment, Y
  • Figure 4 is a section on the line 4 4 of Figure 3, and
  • Figure 5 is a view corresponding to Figures 2 and 4 of yet another embodiment.
  • the rotor comprises a disc 10 provided with an axially-thickened periphery formed with a circumferential channel 11 so as to provide a pair of radially-extending axially-spaced flanges 1'2, 13.
  • the rotor also comprises a row of blade elements each of which comprises an aerofoil portion 14, a platform portion 15 and a lug 16 extending from the side of the platform remote from the aerofoil portion 14.
  • the lugs 16 When the blades are assembled to the disc 10 the lugs 16 extend into the channel 11 between the flanges 12 and 13 to which the blades are pivotally connected each by means ofa pivot pin 17 extending through aligned holes 12a, 13a and 16a in the flanges 12 and 13 and inthe correspond-ing lug 16. l
  • Each pivot pin 17 is provided at one end with a reduced diameter portion 17a having at its outer end a flanged head 17b so that there is thereby formed near the end of each pivot pin a circumferential channel 17d.
  • a number of retaining plates 18 are ⁇ provided to interlock with features provided on the disc periphery.
  • the slot nearest one end of the retaining plate 18 may be a parallel-sided slot 19a which extends to one circumferential edge of the plate.
  • the retaining plates 18 are retained axially against the llange '13 on the disc periphery by arranging that their outer edges 18a engage in an inwardly-facing circumferential groove 20x cut in an axially-projecting flange 20 at the'outer edge of the flange 13 and by forming the radially-inner edges of the plates 18 with lugs or edge portions 18b extending into engagement in circumferentially extending radially-outwardly-facing grooves 20y cut in circurnferentially-spaced axial projections 21 pro vided at the inner radius lof the flange 13. j
  • the retaining plates 18 are limited as totheir circurnferential movement in one sense by tongues 22 which project -radially inwards adjacent the lugs 18b and bear against the ends of the axial projections 21.
  • the retaining plates 18 are placed in position, with the larger ends of the keyhole slots 19 aligned with the holes 13a in the flange 13, before attachment of the blades and then the blades are positioned and the pivot pins are inserted, their heads being passed through the larger ends of the keyhole slots 19.
  • the plates 18 are displaced circumferentiallyv to bring the smaller ends of the keyhole slots into engagement with the reduced-diameter portions 17a behind the flange-like heads 17b.
  • a locking piece 23 is fitted which prevents circumferential displacement of the locking plates in the opposite direction.
  • the locking piece 23 is in the form of a plate having a radially-disposed open-ended keyhole slot 24 to engage one pivot pin.
  • the locking plate 23 is positioned between the ends of a pair of the plates 18 and engages by its outer edge in the inwardly-facing circumferential groove 20x in the axially projecting flange 20 and by its inner edge in a circumferentially-extending, radially outwardly-facing groove a formed in a projection 25 corresponding to the outwardly facing grooves 20y in the projections 21.
  • the locking plate 23 is also provided with a pair of lugs 26 which extend one on each side of the projection 2S and wl ich during positioning of the plate 23 extend axially outwardly from the plate 23 to allow limited radial freedom of the plate 23 between the bottoms of the grooves Ztx and 25a in the flange 20 and projection 25, and which when the plate 23 is in position are bent inwards towards the disc periphery to overlie a circumferential shoulder 27 to retain the outer edge of plate 23 in its groove 20x by preventing radially inward displacement ofthe plate 23.
  • the groove 25a in the projection 25 is of such radial depth that with the lugs 26 bent axially outwards of the plate 23, the plate 23 can be displaced radially inwards to an amount sufficient to disengage its outer edge from the groove 20x in the axial flange 20.
  • the pivot pins 17 are retained against disengagement in the opposite direction by abutment of the axially-facing surfaces 17e of the heads 17e with retaining plates 28 which, as in the arrangement of Figures l and 2, co-operate by their outer edges 18a in an inwardly-facing groove 20x in an axial ange 20 at the outer edge of the ange 13.
  • the plates 28 are provided at their radially inner edges with radially-inwardly-projecting lugs or edge portions 28a to engage, by a circumferential movement of the plates, outwardly-facing grooves 20y in axial projections 21.
  • the plates 28 are fitted after attachment of the blades 14 and are retained circumferentially by providing the last plate 28 to be inserted with radially-inwardly-projecting tongues 28b which abut circumferentially against abutments formed by the circumferentially-facing ends 21a of a pair of the projections 21, the one to prevent circumferential displacement in one direction and the other to prevent a circumferential displacement in the opposite direction.
  • the tongues 28h during assembly project axially outwards from the plate 28, and, after circumferential displacement of all of the plates 28 simultaneously to engage the lugs 28a in the grooves 20y of projections 21, the tongues 28b are bent down axially to the position shown.
  • pivot pins are plain cylindrical pivot pins.
  • the pivot pins 17 in this case are retained by abutment of their axially-facing end surfaces 17f with retaining plates 38, similar to those described with reference to Figures 3 and 4, on each side of the disc periphery, which retaining plates engage by their outer edges 38b in grooves 20y in axialprojections 20 at the outer ends of the flanges 12 Vand 13 and engage through lugs 38a in outwardly-facing grooves 20y in axial projections 21 from the inner ends of the anges 12 and 13.
  • the retaining plates are conveniently formed from resilient exible sheet metal to facilitate their assembly.
  • a bladed rotor for an axial-flow uid machine having a disc formed with anges at its periphery and blade elements having lugs overlapping the flanges by means of which they are mounted on the disc, the flanges and lugs being formed with aligned holes, and pivot pins engaging with said holes, comprising means' for retaining the pivot pins against disengagement, which means comprises a plurality of part-annular plates mounted on the disc to -form together a substantially complete annulus around the disc, said plates engaging at least one axially-facing surface of the pivot pins to prevent axial disengagement of the pins from said holes in one sense at least, the disc having at a first radial distance from its axis a radially-inwardly-facing circumferential groove and having at a lesser radial distance from its axis a plurality of circumferentially-spaced axially-directed projections, each of which projections is provided with a radially-outwardly-facing
  • a bladed rotor as claimed in claim l wherein the pivot pins are formed with reduced-diameter portions terminating in anged heads, and wherein the plates are of arcuate form and are provided with a number of circnmferentially-spaced circumferentially-extending keyhole-shape slots, the slots each having a reduced portion of less width than the dimension of the heads of the pivot pins, the reduced portions of the slots receiving the reduced-diameter portions of the pivot pins on circumferential movement of the plates, thereby to prevent the disengagement of the pins from the holes.
  • a bladed rotor as claimed in claim 2 wherein the means locking the plates circumferentially in position comprises a locking plate fitting between the ends of a pair of the arcuate plates and mounted on the disc, said locking plate being formed with a radially-extending slot having a reduced portion of less width than the dimension of the heads of the pivot pins, the reduced portion of the slot engaging the reduced-diameter portion of one of the pivot pins, and comprising interengaging parts on said locking plate and on the disc retaining the locking plate against axial and radial displacement relative to the disc.
  • a bladed rotor as claimed in claim 3 wherein said disc is also formed with an axially-projecting shoulder, the locking plate has a radially-outer edge which engages in said inwardly-facing -groove and a radially-inner edge which engages in said outwardly-facing groove, the locking plate has a radial dimension between said edges less than that between the bottoms of the groovesand wherein said locking plate is provided with lugs which are bent inwardly to radially overlie said shoulder to prevent radial displacement of the locking plate and disengagement from said grooves.
  • a bladed rotor as claimed in claim l wherein thc pivot pins are formed with enlarged heads abutting against one of said disc flanges thereby to prevent axial disengagement of the pivot pins from said holes in one direction, and wherein the plates engage the heads of the pivot pins to prevent the axial disengagement of the pins from said holes in the opposite direction.
  • a bladedrotor as claimed in ⁇ claim 5 wherein ⁇ the means locking the plates against circumferential movement comprises lugs on one at least of the plates engaging oppositely-facing circumferential abutments on the disc afforded by adjacent circumferentially-facing ends of a pair of said projections.
  • a bladed rotor as claimed in claim 7 wherein the means to retain the plates against circumferential movement comprises a pair of oppositely-facing circumferential abutments on the disc and lugs on one at least of the plates engaging said oppositely-facing circumferential 'abutments on the disc aiorded by adjacent circumferentially-facing ends of a pair of said projections.

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)
US533782A 1953-05-27 1955-09-12 Rotors for axial-flow fluid machines with pivoted blades and blade pivot retaining means Expired - Lifetime US2925997A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB1482553A GB745073A (en) 1953-05-27 1953-05-27 Improvements in or relating to rotors for axial-flow compressors and like machines
GB391459A GB815507A (en) 1953-05-27 1954-10-01 Improvements in or relating to bladed rotors for axial-flow fluid machines

Publications (1)

Publication Number Publication Date
US2925997A true US2925997A (en) 1960-02-23

Family

ID=32395787

Family Applications (1)

Application Number Title Priority Date Filing Date
US533782A Expired - Lifetime US2925997A (en) 1953-05-27 1955-09-12 Rotors for axial-flow fluid machines with pivoted blades and blade pivot retaining means

Country Status (4)

Country Link
US (1) US2925997A (xx)
BE (1) BE541578A (xx)
FR (1) FR1136390A (xx)
GB (1) GB815506A (xx)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3043562A (en) * 1961-04-10 1962-07-10 Gen Electric Combination sealing and restraining member for long-shank turbo-machine buckets
DE1167852B (de) * 1962-08-10 1964-04-16 Bbc Brown Boveri & Cie Schwingungdaempfende Laufschaufelbefestigung bei Axialturbomaschinen
US3734645A (en) * 1969-12-12 1973-05-22 Bbc Sulzer Turbomaschinen Turbine blade assembly
US4247257A (en) * 1978-03-08 1981-01-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Rotor flanges of turbine engines
US4344740A (en) * 1979-09-28 1982-08-17 United Technologies Corporation Rotor assembly
JPH02191802A (ja) * 1988-10-05 1990-07-27 Soc Natl Etud Constr Mot Aviat <Snecma> 羽根の固定装置を備えたタービンエンジンの動翼
US20190277198A1 (en) * 2018-03-07 2019-09-12 Rolls-Royce North American Technologies Inc. Adaptive-curvature inertial particle separators

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2906496A (en) * 1957-05-28 1959-09-29 Ransom S Thompson Retaining means for pin used for rotor blade attachment
US3039739A (en) * 1958-11-28 1962-06-19 Gen Motors Corp Pinned blade connecting means
US3042369A (en) * 1959-02-11 1962-07-03 Gen Motors Corp Pinned blade sealing means
US4119389A (en) * 1977-01-17 1978-10-10 General Motors Corporation Radially removable turbine vanes
US5131814A (en) * 1990-04-03 1992-07-21 General Electric Company Turbine blade inner end attachment structure

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR960069A (xx) * 1947-04-02 1950-04-12
US2537739A (en) * 1946-10-26 1951-01-09 Wright Aeronautical Corp Fan blade mounting
GB667979A (en) * 1949-07-28 1952-03-12 Rolls Royce Improvements in or relating to axial flow compressors and turbines
GB679714A (en) * 1949-04-21 1952-09-24 Rolls Royce Improvements in or relating to axial-flow compressors and turbines

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2537739A (en) * 1946-10-26 1951-01-09 Wright Aeronautical Corp Fan blade mounting
FR960069A (xx) * 1947-04-02 1950-04-12
GB679714A (en) * 1949-04-21 1952-09-24 Rolls Royce Improvements in or relating to axial-flow compressors and turbines
GB667979A (en) * 1949-07-28 1952-03-12 Rolls Royce Improvements in or relating to axial flow compressors and turbines

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3043562A (en) * 1961-04-10 1962-07-10 Gen Electric Combination sealing and restraining member for long-shank turbo-machine buckets
DE1167852B (de) * 1962-08-10 1964-04-16 Bbc Brown Boveri & Cie Schwingungdaempfende Laufschaufelbefestigung bei Axialturbomaschinen
US3734645A (en) * 1969-12-12 1973-05-22 Bbc Sulzer Turbomaschinen Turbine blade assembly
US4247257A (en) * 1978-03-08 1981-01-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Rotor flanges of turbine engines
US4344740A (en) * 1979-09-28 1982-08-17 United Technologies Corporation Rotor assembly
JPH02191802A (ja) * 1988-10-05 1990-07-27 Soc Natl Etud Constr Mot Aviat <Snecma> 羽根の固定装置を備えたタービンエンジンの動翼
US5007800A (en) * 1988-10-05 1991-04-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Rotor blade fixing for turbomachine rotors
JPH07109161B2 (ja) 1988-10-05 1995-11-22 ソシエテ・ナシオナル・デテユード・エ・ドウ・コンストリユクシオン・ドウ・モトール・ダヴイアシオン、“エス．エヌ．ウ．セ．エム．アー．” タービンエンジンのロータ
US20190277198A1 (en) * 2018-03-07 2019-09-12 Rolls-Royce North American Technologies Inc. Adaptive-curvature inertial particle separators
US10767558B2 (en) * 2018-03-07 2020-09-08 Rolls-Royce North American Technologies Inc. Adaptive-curvature inertial particle separators

Also Published As

Publication number Publication date
GB815506A (en) 1959-06-24
BE541578A (xx)
FR1136390A (fr) 1957-05-13

Similar Documents

Publication Publication Date Title
US3008689A (en) Axial-flow compressors and turbines
US2985426A (en) Bladed rotor construction for axialflow fluid machine
US2998959A (en) Bladed rotor of axial-flow fluid machine with means to retain blades in position on rotor
US2755063A (en) Rotor constructions for gas-turbine engines
US5302086A (en) Apparatus for retaining rotor blades
US2925997A (en) Rotors for axial-flow fluid machines with pivoted blades and blade pivot retaining means
US3096074A (en) Bladed rotors of machines such as gas turbines
EP2660426B1 (en) Turbine assembly
US8459953B2 (en) Seal plate and bucket retention pin assembly
US3014695A (en) Turbine bucket retaining means
US5161949A (en) Rotor fitted with spacer blocks between the blades
US3807898A (en) Bladed rotor assemblies
US2843356A (en) Turbo-machine rotor assembly
US5018941A (en) Blade fixing arrangement for a turbomachine rotor
US3734646A (en) Blade fastening means
US5007800A (en) Rotor blade fixing for turbomachine rotors
GB2058945A (en) Rotor assembly
US3455537A (en) Air-cooled turbine rotor self-sustaining shroud plate
KR102273496B1 (ko) 터빈 버킷 클로져 조립체 및 그 조립 방법
US3018085A (en) Floating labyrinth seal
US2640679A (en) Turbine or compressor stator ring
GB2097480A (en) Rotor blade fixing in circumferential slot
US3397865A (en) Bladed rotor for a fluid flow machine such as a gas turbine engine
US4189282A (en) Device to secure vanes to a rotor
US4604033A (en) Device for locking a turbine blade to a rotor disk