US2761648A - Rotor blade locking device - Google Patents

Rotor blade locking device Download PDF

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Publication number
US2761648A
US2761648A US247078A US24707851A US2761648A US 2761648 A US2761648 A US 2761648A US 247078 A US247078 A US 247078A US 24707851 A US24707851 A US 24707851A US 2761648 A US2761648 A US 2761648A
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US
United States
Prior art keywords
shank
blade
tip
stop
bend
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
US247078A
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English (en)
Inventor
Purvis Joseph Thompson
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.)
AV Roe Canada Ltd
Original Assignee
AV Roe Canada Ltd
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 AV Roe Canada Ltd filed Critical AV Roe Canada Ltd
Priority to US247078A priority Critical patent/US2761648A/en
Priority to FR1062938D priority patent/FR1062938A/fr
Priority to DEC6396A priority patent/DE925026C/de
Priority to CH314093D priority patent/CH314093A/fr
Priority to GB23316/52A priority patent/GB722233A/en
Application granted granted Critical
Publication of US2761648A publication Critical patent/US2761648A/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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining
    • Y10T29/49908—Joining by deforming
    • Y10T29/49915—Overedge assembling of seated part

Definitions

  • This invention relates to blading for rotary power conversion machines and the like and particularly to improved fastening means for such blading.
  • Fig. 1 illustrates a gas turbine engine having a turb ne rotor with blades attached thereto in accordance with the invention
  • Fig. 2 is a fragmentary side elevational view of a port on of the turbine rotor with blades attached, one blade being shown with the locking device removed for greater clarity;
  • Fig. 3 is a sectional view taken on the line 33 1n Fig. 2;
  • Fig. 4 is an elevational view on a slightly reduced scale of one form of the retaining pin before assembly
  • Fig. 5 is a cross sectional view on the line 5--5 m Fig. 4;
  • Fig. 6 is an elevationalview, on the same scale as Fig. 4, of another form of the retaining pin before assembly, and
  • Fig. 7 is an elevational view, on the same scale as Flg. 4, of the retaining pin after assembly, shown apart from the associated structure.
  • the gas turbine illustrated in Fig. 1 1s of conventional design, with a compressor 10, a turbine assembly 11 and a combustion system 12 located between them.
  • the turbine assembly comprises a blade supporting element or rotor 13 supporting a series of radially extending blades 14, the blades being mounted in a series of perlpheral slot: 15 which in the embodiment illustrated are of fir tree crdss-section, as shown in Fig. 2.
  • the slots extend from the front or upstream face 16 of the rotor to 1115 rear or downstream face 17 in a substantially axial direction, parallel to the general flow of air through the engine as indicated by the arrow A in Fig. 3.
  • the blades 14 are formed with blade roots 18 of fir tree shape conforming to the shape of the slots, the length of the roots being equal to the length of the slots so that upon assembly the exposed end faces 19 and 20 of the roots are flush with the adjacent end faces 16 and 17 respectively of the rotor.
  • the basal extremity of each of the blade roots is machined flat to provide a passage 21 running axially between the basal extremity of the root and the base of the slot; further, the downstream end face 20 of the root is machined at its tip to provide a recess 22.
  • a retaining pin 23 (Fig. 7) is formed from a strip of metal of flattened cross-section, the pin having a shank 24 of the 'same length as the blade root 18 less the depth of the recess 22.
  • stops 25 and 26 extend on opposite sides of the shank, each of the stops being formed by bending the pin at an end of the shank through to provide a shoulder 27 or 28, as the case may be, on one side of the shank 24, and making a further bend through about ata location spaced from the axis of the shank to dispose the tip part 29 or 30, as the case may be, laterally near the first bend to bring its extreme tip 29 or 30, as the case may be, into final position beyond the axis of the shank from the shoulder; the bends are made so that the shoulder 27 of the stop 25 and the shoulder 28 of the stop 26 are located on opposite sides of the shank With respect to each other.
  • each of the stops 25 and 26 is formed by making a bend having one reversal of curvature.
  • the dimensional conformation of the stop 26 is such that its reverse bend will fit closely into the recess 22 and its tip 30' will overlie the rear face 17 of the rotor, whereas the tip portion 29 of the stop 25 is so bent that the tip 29 is laterally opposite the shoulder 27, meeting the forward face 19 of the blade root obliquely and holding the face 19 substantially flush with the face 16 of the rotor.
  • the shoulders 27 and 28 may fail to provide firm location of the blade root in the rotor if they are formed on assembly. Consequently it is preferable to pre-form the shoulder 28 and both bends of the stop 25 before assembly, as shown in Fig. 4, the reverse bend of the other stop 26 not being completed so that the tip 30' does not come below the longitudinal axis of the shank 24; alternatively, the shoulder 27 and both bends of the stop 26 may be pre-formed and the reverse bend of the other stop 25 left incomplete so that the tip 29' does not come above the longitudinal axis of the shank as in Fig. 6.
  • the pin 23 is first fitted to the root 18 so that the shank 24 of the pin butts against the basal portion of the root, the shoulder 28 of the stop 26 engaging the forward face of the recess 22 and the tip 29' of the stop 25 engaging the front face 19 of the blade root.
  • the root is then fitted into the slot 15 and, with the tip 30 of the stop 26 clearing the base of the slot, the root and the attached pin is slid rearwardly in the slot until shoulder 27 of the stop 25 meets the front face 16 of the rotor.
  • the reverse bend of the stop 26 is then completed to bring the tip 30' into engagement with the rear face 17 of the rotor and lock the blade in the rotor.
  • the blade is held against the main air loading (indicated by the direction of the arrow A in Fig. 3) by the pro-formed shoulders 27 and 28, while the tips 39' and 30' of the stops serve to locate the blade against reverse loading, which is of lesser magnitude than the main air loading.
  • the pin is first fitted to the base of the slot 15, rather than to the blade root, with the shoulder 27 of the stop 25 and tip 30 of the stop 26 engaging the front face 16 and the rear face 17 of the rotor respectively.
  • the blade root 18 is then slid rearwardly into the slot 15 until the forward face of the recess 22 meets the shoulder 28 of the stop 25; and the reverse bend of the stop 25 is then completed to bring, the tip 29 into engagement with the front face 19 of the blade root, and lock the blade in position.
  • the tip of the inc o npleteiy formed stop does not interfere with the insertion of the root because, in this case, it lies below the basal portion of the root.
  • the tip portion 3-9 of the stop can be bent through the remainder of the 180 with, a. larger radius of bend since the bend lies within the recess. 22,. and the bend may be compressed slightly to compensate for spring back in the metal without danger of breaking the metal at the bend.
  • the tip of the. stop can be made to engage the adiacent rotor face more tightly than is the case if the configuration shown in Fig. 6 is. used, unless by an additional step in assembly the. stop 26 in the latter case is given a final tightening bend after the reverse bend of the stop 25 is completed.
  • the construction described in the foregoing provides a form of blade locking which. has the, advantage of lightness and at the same time is simple and inexpensive to manufacture. Not only does it permit individual blades to be replaced without disturbing the remaining blades, but it also provides positive predetermined location of the blades in the sense counter to that of the main air loads.
  • a locking pin for locking the blading of a rotary power conversion machine having a shank of flattened cross section, a bent part at each end of the shank. and a tip part at each end of the pin on the side of the bent part remote from the shank, the bent parts each having a first bend away from the axis of the shank and a second band of reverse curvature at a location spaced from the axis of the shank, the first bends forming shoulders at the ends of the shank and the second bends disposing the tip parts laterally near the first bends, the tip part at one end of the pin extending and protruding in a lateral direction beyond the axis of the shank from the shoulder at that end of the shank, and the tip part at the other end of the shank extending in an oblique direction with respect to the axis of the shank from the adjacent second bend to a point axially spaced from that end of the shank and not protruding beyond the axis of the sh shank
  • a locking pin for lockingthe blading of a rotary power conversion machine comprising a shank, a bent part at each end of the shank, and a tip part at each end of the pin on the side of the bent part remote from the shank, the bent parts each having a first bend away from the axis of the shank and forming a transverse shoulder at the end of the shank, the said shoulders extending at opposite sides of the shank at opposite ends thereof, and the bent parts each havinga second bend of reverse curvature, at a location spaced from the axis of the shank, the tip parts each extending and protruding in a lateral direction beyond the axis of the shank from the shoulder at that end of the shank.
  • a locking structure for the blading of a rotary power conversion machine in which a stream of fluid flows past a ring of rooted blades in a blade supporting member comprising, a blade supporting element, and a blade having a blade root, the blade and the supporting element each having exposed upstream and downstream end faces, interlocking means on the blade root and on the support element securing the said element against relative movement in all directions save one which intersects the said faces, the said means being inoperative to secure the said elements against relative sliding movement in the said one direction, a recess in one or" the said faces, and a pin having a shank of flattened cross section fittingly positioned between the blade root and the support element and having a bent part at each end of the shank and a tip part at each end of the pin on the side of the bent part remote from the shank, the bent part and the tip part, engaging the said faces to prevent relative movement in the said one direction, each bent part having a first bend away from the axis of the shank and a second bend of
  • each of the first bends forming a transverse shoulder at one side of the axis of the shank, one of the shoulders extending into the recess in they said one. of the faces, and the other shoulder overlying another one of the said faces, the second bends disposing the tip parts laterally near the first bends, each of the tip parts extending generally radially with respect to the ring of blades from the corresponding shoulder to the other side of the axis of the shank to overlie one of the remaining two faces.
  • A. locking structure for the blading of a rotary power conversion machine in which a stream of fluid flows past a ring of rooted blades in a blade support comprising, a blade supporting element and a blade having a blade root, the. blade having an exposed downstream end face and the supporting element having an exposed upstream end face, interlocking means on the blade root and on the supporting element securing the blade root and supporting element against relative movement in all directions save one which intersects the said faces, the said means being inoperative to secure the said elements against relative sliding movement in the said.
  • the bent parts and tip parts engaging the said faces to restrain the supporting element and the blade against relative movement, the bent parts each having a first bend away from the axis of the shank and a second bend of reverse curvature.
  • each of the first bends forming a transverse shoulder at one side of the axis of the shank, one of the shoulders extending into the recess in the said one of the said faces and the other shoulder overlying the other one of the said faces, the second bend disposing the tip parts laterally near the first bends, each of the tip parts extending generally radially with respect to the ring of blades from the corresponding shoulder to the other side of the axis of the shank.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US247078A 1951-09-18 1951-09-18 Rotor blade locking device Expired - Lifetime US2761648A (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US247078A US2761648A (en) 1951-09-18 1951-09-18 Rotor blade locking device
FR1062938D FR1062938A (fr) 1951-09-18 1952-09-12 Dispositif de fixation des aubes de machines rotatives de transformation de force, telles que turbines et compresseurs
DEC6396A DE925026C (de) 1951-09-18 1952-09-13 Befestigungsvorrichtung fuer Schaufeln von Kreiselradmaschinen, z. B. Gasturbinen
CH314093D CH314093A (fr) 1951-09-18 1952-09-15 Dispositif de verrouillage de l'aubage d'une turbo-machine
GB23316/52A GB722233A (en) 1951-09-18 1952-09-17 Rotor blade locking device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US247078A US2761648A (en) 1951-09-18 1951-09-18 Rotor blade locking device

Publications (1)

Publication Number Publication Date
US2761648A true US2761648A (en) 1956-09-04

Family

ID=22933458

Family Applications (1)

Application Number Title Priority Date Filing Date
US247078A Expired - Lifetime US2761648A (en) 1951-09-18 1951-09-18 Rotor blade locking device

Country Status (5)

Country Link
US (1) US2761648A (fr)
CH (1) CH314093A (fr)
DE (1) DE925026C (fr)
FR (1) FR1062938A (fr)
GB (1) GB722233A (fr)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3039740A (en) * 1959-11-27 1962-06-19 Gen Motors Corp Blade retainer
US3045329A (en) * 1959-07-30 1962-07-24 Gen Electric Method for assembling tongue-and-groove members with locking keys
US3157385A (en) * 1961-10-17 1964-11-17 Ass Elect Ind Blade locking means for turbines or compressors
EP0597586A1 (fr) * 1992-11-11 1994-05-18 ROLLS-ROYCE plc Montage d'aube pour turbomoteur à ventilateur caréné
WO1996018803A1 (fr) * 1994-12-15 1996-06-20 Pratt & Whitney Canada Inc. Maintien d'aubes de turbines a gaz
WO2000031378A1 (fr) 1998-11-23 2000-06-02 Pratt & Whitney Canada Corp. Fixation d'aubage sur le disque de turbine
US6837686B2 (en) 2002-09-27 2005-01-04 Pratt & Whitney Canada Corp. Blade retention scheme using a retention tab
US20080253895A1 (en) * 2007-04-12 2008-10-16 Eugene Gekht Blade retention system for use in a gas turbine engine
US8753090B2 (en) 2010-11-24 2014-06-17 Rolls-Royce Corporation Bladed disk assembly
US20140199172A1 (en) * 2013-01-11 2014-07-17 General Electric Company Turbomachine and method of handling turbomachine components
US20140301853A1 (en) * 2013-04-09 2014-10-09 MTU Aero Engines AG Securing blade assortment
JP2018155240A (ja) * 2017-03-16 2018-10-04 ドゥサン ヘヴィー インダストリーズ アンド コンストラクション カンパニー リミテッド バケットの軸方向固定装置とバケット組立体およびこれを含むガスタービン
EP4006305A3 (fr) * 2020-11-20 2022-07-20 Solar Turbines Incorporated Couplage de rigidité et amortissement des vibrations pour carénage d'aube de turbine

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2841363A (en) * 1953-09-17 1958-07-01 A V Roe Canada Ltd Turbine disc and blade mounting
US2847187A (en) * 1955-01-21 1958-08-12 United Aircraft Corp Blade locking means
DE1033676B (de) * 1956-11-27 1958-07-10 Joseph Szydlowski Verriegelung der Laufschaufeln in Laengsnuten der Laeuferscheiben von Kreiselmaschinen mittels Splinten
DE1051286B (de) * 1958-06-02 1959-02-26 Her Majesty The Queen In The R Sicherung fuer eine in einer Axialnut einer Kreiselmaschine gehaltene Schaufel
US3001759A (en) * 1958-06-11 1961-09-26 Gen Motors Corp Rotor blade lock
US3033520A (en) * 1958-06-11 1962-05-08 Gen Motors Corp Rotor blade lock
DE1115992B (de) * 1959-08-07 1961-10-26 Entwicklungsbau Pirna Veb Sicherung gegen axiale Verschiebung von Laufschaufeln mit Tannenbaumfuss an Gasturbinen
DE19757188A1 (de) * 1997-12-22 1999-06-24 Asea Brown Boveri Einrichtung zur Befestigung der Laufschaufeln einstufiger Axialturbinen
DE102008013118B4 (de) * 2008-03-07 2014-03-27 Man Diesel & Turbo Se Anordnung zum Befestigen von Turbinenschaufeln

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1046986A (en) * 1911-05-13 1912-12-10 Homer F Crocker Nut-lock.
US1070385A (en) * 1912-08-01 1913-08-19 Joseph Adams Jr Key-bolt lock.
US1149658A (en) * 1913-10-01 1915-08-10 Terry Steam Turbine Company Turbine-blading.
US1237515A (en) * 1917-01-15 1917-08-21 Clarence E Schmitt Locking-pin.
US1574619A (en) * 1923-05-23 1926-02-23 Felix A Gibson Nut lock
US2297770A (en) * 1941-03-07 1942-10-06 Jepson Percy Cotter pin
US2317347A (en) * 1939-03-24 1943-04-27 Michael F Saylor Nut locking device
US2434935A (en) * 1946-02-08 1948-01-27 Westinghouse Electric Corp Turbine apparatus
GB620877A (en) * 1947-01-28 1949-03-31 Bristol Aeroplane Co Ltd Improvements in or relating to attachment means for the blades of fans, compressors,turbines or the like apparatus
FR976790A (fr) * 1948-10-19 1951-03-22 Pied d'aubes de compresseurs et de turbines ou analogues

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB643914A (en) * 1948-03-08 1950-09-27 Joseph Stanley Hall Improvements in and relating to turbine or like blade securing means

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1046986A (en) * 1911-05-13 1912-12-10 Homer F Crocker Nut-lock.
US1070385A (en) * 1912-08-01 1913-08-19 Joseph Adams Jr Key-bolt lock.
US1149658A (en) * 1913-10-01 1915-08-10 Terry Steam Turbine Company Turbine-blading.
US1237515A (en) * 1917-01-15 1917-08-21 Clarence E Schmitt Locking-pin.
US1574619A (en) * 1923-05-23 1926-02-23 Felix A Gibson Nut lock
US2317347A (en) * 1939-03-24 1943-04-27 Michael F Saylor Nut locking device
US2297770A (en) * 1941-03-07 1942-10-06 Jepson Percy Cotter pin
US2434935A (en) * 1946-02-08 1948-01-27 Westinghouse Electric Corp Turbine apparatus
GB620877A (en) * 1947-01-28 1949-03-31 Bristol Aeroplane Co Ltd Improvements in or relating to attachment means for the blades of fans, compressors,turbines or the like apparatus
FR976790A (fr) * 1948-10-19 1951-03-22 Pied d'aubes de compresseurs et de turbines ou analogues

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3045329A (en) * 1959-07-30 1962-07-24 Gen Electric Method for assembling tongue-and-groove members with locking keys
US3039740A (en) * 1959-11-27 1962-06-19 Gen Motors Corp Blade retainer
US3157385A (en) * 1961-10-17 1964-11-17 Ass Elect Ind Blade locking means for turbines or compressors
EP0597586A1 (fr) * 1992-11-11 1994-05-18 ROLLS-ROYCE plc Montage d'aube pour turbomoteur à ventilateur caréné
WO1996018803A1 (fr) * 1994-12-15 1996-06-20 Pratt & Whitney Canada Inc. Maintien d'aubes de turbines a gaz
WO2000031378A1 (fr) 1998-11-23 2000-06-02 Pratt & Whitney Canada Corp. Fixation d'aubage sur le disque de turbine
US6109877A (en) * 1998-11-23 2000-08-29 Pratt & Whitney Canada Corp. Turbine blade-to-disk retention device
US6837686B2 (en) 2002-09-27 2005-01-04 Pratt & Whitney Canada Corp. Blade retention scheme using a retention tab
US20080253895A1 (en) * 2007-04-12 2008-10-16 Eugene Gekht Blade retention system for use in a gas turbine engine
US7806662B2 (en) 2007-04-12 2010-10-05 Pratt & Whitney Canada Corp. Blade retention system for use in a gas turbine engine
US8753090B2 (en) 2010-11-24 2014-06-17 Rolls-Royce Corporation Bladed disk assembly
US20140199172A1 (en) * 2013-01-11 2014-07-17 General Electric Company Turbomachine and method of handling turbomachine components
US20140301853A1 (en) * 2013-04-09 2014-10-09 MTU Aero Engines AG Securing blade assortment
US9695699B2 (en) * 2013-04-09 2017-07-04 MTU Aero Engines AG Securing blade assortment
JP2018155240A (ja) * 2017-03-16 2018-10-04 ドゥサン ヘヴィー インダストリーズ アンド コンストラクション カンパニー リミテッド バケットの軸方向固定装置とバケット組立体およびこれを含むガスタービン
EP4006305A3 (fr) * 2020-11-20 2022-07-20 Solar Turbines Incorporated Couplage de rigidité et amortissement des vibrations pour carénage d'aube de turbine

Also Published As

Publication number Publication date
GB722233A (en) 1955-01-19
CH314093A (fr) 1956-05-31
DE925026C (de) 1955-03-10
FR1062938A (fr) 1954-04-28

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