US2421855A - Turbine blade locking device - Google Patents

Turbine blade locking device Download PDF

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Publication number
US2421855A
US2421855A US495923A US49592343A US2421855A US 2421855 A US2421855 A US 2421855A US 495923 A US495923 A US 495923A US 49592343 A US49592343 A US 49592343A US 2421855 A US2421855 A US 2421855A
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Prior art keywords
pieces
wedge
discs
engaging
locking device
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Expired - Lifetime
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US495923A
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Carl R Soderberg
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Raytheon Technologies Corp
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United Aircraft Corp
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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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides

Definitions

  • a feature of this invention is a locking device for filling the opening through which blade roots of this type are inserted between the discs;
  • Another feature is a locking device made up.
  • Fig. 1 is a sectional view through a section of the turbine rotor.
  • Fig. 2 is a perspectiveview of the locking device.
  • Fig. 3 is a fragmentary perspective view of the The rotor H) has a pair of opposed'integral discs l2 and I4 supporting a row of turbine blades H5 at their peripheries.
  • the rotor may have a number of axially spaced rows of blades alternating with rows of nozzles on a. turbine casing surrounding the rotor.
  • Discs l2 and II have opposed converging surfaces l8 and 20 adjacent to and facing toward each other for engagement with cooperating converging surfaces 22 and 2
  • Disc l2 and M also have peripheral flanges 28 and 3D.
  • slots 44 and 46 are formed in the adiacent surfaces of the discs at their outer end.
  • said device opposed surfaces of said discs, the opposed sur-' verging toward the These slots form an opening between the discs which is slightly greater than the axial width of the blade root which must pass through the opening.
  • the locking device including filling pieces 48 and 50 which at their inner ends have obliquely extending surfaces 52 and '54 engaging with the converging surfaces I fltting between said converging surfaces and means for fastening saidv 12 Claims. (Cl. 25349) :2 and u on the discs. tween the inner ends of A wedge extends befilling pieces and en- Jacent to each other on pieces 48 and 50.
  • a stud 62-011 wedge 56 extends through an opening formed in opposed lugs 64 and 68 on the inner surfaces of flllingpieces 4B and '50 and has of these lugs for tightening the wedge in position Pieces #8 and n have outwardly P jecting with the substantiallycylindrical surfaces 38 and III on the opposed discs and locate the pieces on the discs.
  • the thickness of wedge 56 is less than the thickness of pieces 48 and '50 so that if the filling pieces are too thick to fit between the blades on the rotor, the pieces may be reduced in thickness by machining on one of the side surfaces. In this way the locking device is adapted to fill the space between the turbine blades in spite of variations in the width of this space.
  • a locking device for a turbine rotorhavingspaced discs between which blades are mounted said device including filling pieces engaging opposed surfaces of said discs, the'opposed surfaces of the pieces adjacent to each other converging toward the periphery of the disc, and a. wedge fitting between said pieces and engaging said converging surfaces.
  • a locking device for a turbine rotor which blades are mountincluding filling pieces enga in ingspaced discs faces of the pieces adjacent to each other conperiphery of the disc,a wedge pieces, and engaging said wedge in position.
  • a locking device for aturbine rotor havin spaced discs between which blades are mounted said device including filling pieces engagin opposed surfaces of said discs, at least one of said pieces having a projecting lug on its inner surface. a wedge fitting between said pieces, a
  • a locking device for a turbine rotor having spaced discs between which blades are mounted,
  • said device including filling pieces engaging opposed suriacesof said discs, each or said pieces J having all projecting ugfli extending-, toward the other piece, a wedge between said pieces ⁇ 'a'stud on said wedge extending between said lugs, and,
  • a locking device for a turbinekrotor havs ing spaced discs between which blades are rnounted, the opposed surfaces of iildidiscsihaving portions converging towardftheperlphries of the discs, said device including filling pieces eac engaging a disc, the pieces liavingioblique;seci tions engaging the converging portions, of gthei aid i e i sit a y kingd for a tiirbifie rotor'havingi v v whiclrbladesaremounted, the opposeds'urtaces of said discs having portions converging" toward thej piei'iphei'ies of the "discs; saiddevice cmamgnmsg pieces'each engaging disc surfaces, and clamping means for holding locking detieflorga turbin'eii' spaceu s s s between' which blades areiihountedg' thecppcsed surfaces blis
  • a locking device for a turbine rotor having spaced discs between which the root sections of a row of blades are mounted, said device being positioned between and filling the space between a the roots of adjacent turbine blades in the row.
  • said device including spaced filling pieces engaging opposed surfaces ofsaid disc and a wedge betweenand' engaging with said pieces for holding them in position, said wedge having opposed surfaces engaging with said filling pieces and said wedge: extending. substantially radially between said filling pieces, the inner end of said wedge adjacent'totheaxis of the disc being wider than H the outer'iend so that said wedge converges in a"direction*radiallyoutward of the disc in order :qto;wedge the filling pieces apart by radial outwar' movement'o'f the wedge.
  • -ll-"A locking device for a turbine rotor having spaced discs between which the root sections of ja row of, blades are-mounted, said device being: positioned between and filling the space between the roots of-adjacent turbine blades in the row, said device including spaced filling pieces 5 engagingvopposed surfaces of saiddiscs and a wedgebetween and engaging with said pieces for holding themin position, aid wedge having opposed .suri'aces engaging with said filling pieces, said-wedge extending substantially radially between saidfilling ,pi'ecesgthe inner end of said wedge adj acent to'the 'axis oi'the disc being wider thanthe outer end so that said wedge converges in adirectipn radially outward of the disc in order to wedgethe filling'piecesapart by radial outward movement of thegw'edge, and means for fastening said-wedge in position'lbetween said filling pieces.
  • the disc in order to ,wedge'ithelfiilihg pieces apart by radial outward .mpvemen ior the wedge, and means accessible exfter'nally oi the discs for fastening said wedge in position'betweenjsaid idiscs.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

June 10, 1947. c.. R. SODERBERG 2,421,355
Y TURBINE BLADE LOCKING DEVICE Filed July 2s, 1943 2 Sheets-Sheetl FIG. "l
June 10, 194.7;
' I I INVENT R Patented June 10,1947
Carl R. Seder-berg, Weston,
United Aircraft Corporation, Conn, a corporation of Delaware mas, assignor to East Hartford,
' Application July 23,1943, serial No. 495.923
The copending application of Soderberg, Serial No. 495,924, filed July 23, 1943, which issued as Patent No. 2,414,278 on January 14, 1947,
shows a blade mounting in which the root has opposed converging surfaces fitting between similar surfaces on spaced integral discs forming the rotor. A feature of this invention is a locking device for filling the opening through which blade roots of this type are inserted between the discs;
Another feature is a locking device made up.
L "of filler pieces engaging the opposed discs and a a clamping nut 88 engaging the upper surfaces lugs Ill and II which engage cut from the specification and claims, and from the accompanying drawings which illustrate an embodiment of the invention.
Fig. 1 is a sectional view through a section of the turbine rotor.
Fig. 2 is a perspectiveview of the locking device.
rotor. I
Fig. 3 isa fragmentary perspective view of the The rotor H) has a pair of opposed'integral discs l2 and I4 supporting a row of turbine blades H5 at their peripheries. The rotor may have a number of axially spaced rows of blades alternating with rows of nozzles on a. turbine casing surrounding the rotor. Discs l2 and II have opposed converging surfaces l8 and 20 adjacent to and facing toward each other for engagement with cooperating converging surfaces 22 and 2| on root 26 of blade l6. Surfaces l8 and 20 and also surfaces i land 24 converge toward the periphery. Disc l2 and M also have peripheral flanges 28 and 3D.
To pej'mit insertion of the blade root between the discs, slots 44 and 46 are formed in the adiacent surfaces of the discs at their outer end.
ed, said device opposed surfaces of said discs, the opposed sur-' verging toward the These slots form an opening between the discs which is slightly greater than the axial width of the blade root which must pass through the opening.
After all of the blades have been assembled, the remaining space is filled by the locking device including filling pieces 48 and 50 which at their inner ends have obliquely extending surfaces 52 and '54 engaging with the converging surfaces I fltting between said converging surfaces and means for fastening saidv 12 Claims. (Cl. 25349) :2 and u on the discs. tween the inner ends of A wedge extends befilling pieces and en- Jacent to each other on pieces 48 and 50.
A stud 62-011 wedge 56 extends through an opening formed in opposed lugs 64 and 68 on the inner surfaces of flllingpieces 4B and '50 and has of these lugs for tightening the wedge in position Pieces #8 and n have outwardly P jecting with the substantiallycylindrical surfaces 38 and III on the opposed discs and locate the pieces on the discs.
As shown in Fig. 2, the thickness of wedge 56 is less than the thickness of pieces 48 and '50 so that if the filling pieces are too thick to fit between the blades on the rotor, the pieces may be reduced in thickness by machining on one of the side surfaces. In this way the locking device is adapted to fill the space between the turbine blades in spite of variations in the width of this space. g
when the locking device has been clamped between the discs, nut is locked in place by a pin 14 extending throughan opening 16 in piece '50 and into the nut.
It is to be understood that the invention is not limited to the specific embodiment herein illustrated and described, but may be used in other ways without departure from its spirit as defined by the following claims.
Iclaiin: v r
1. A locking device for a turbine rotorhavingspaced discs between which blades are mounted, said device including filling pieces engaging opposed surfaces of said discs, the'opposed surfaces of the pieces adjacent to each other converging toward the periphery of the disc, and a. wedge fitting between said pieces and engaging said converging surfaces.
7 2. A locking device for a turbine rotor havbetween which blades are mountincluding filling pieces enga in ingspaced discs faces of the pieces adjacent to each other conperiphery of the disc,a wedge pieces, and engaging said wedge in position.
3. A locking device for aturbine rotor havin spaced discs between which blades are mounted, said device including filling pieces engagin opposed surfaces of said discs, at least one of said pieces having a projecting lug on its inner surface. a wedge fitting between said pieces, a
' stud on said wedge, and a nut onsald stud engaging said lug.
4. A locking device for a turbine rotor having spaced discs between which blades are mounted,
said device including filling pieces engaging opposed suriacesof said discs, each or said pieces J having all projecting ugfli extending-, toward the other piece, a wedge between said pieces} 'a'stud on said wedge extending between said lugs, and,
. a nut on said stud engaging said lugs.
5. A locking device for a turbinekrotor; havs ing spaced discs between which blades are rnounted, the opposed surfaces of iildidiscsihaving portions converging towardftheperlphries of the discs, said device including filling pieces eac engaging a disc, the pieces liavingioblique;seci tions engaging the converging portions, of gthei aid i e i sit a y kingd for a tiirbifie rotor'havingi v v whiclrbladesaremounted, the opposeds'urtaces of said discs having portions converging" toward thej piei'iphei'ies of the "discs; saiddevice cmamgnmsg pieces'each engaging disc surfaces, and clamping means for holding locking detieflorga turbin'eii' spaceu s s s between' which blades areiihountedg' thecppcsed surfaces blisid discs havingportions emer in t aril-" the peripliei'ies of s'the discs,
said devicelncludlngfilling piecesfeach engaging 2;
a j disc; the pieces having -Obliqiiefsectidns engagm the ccriverg'in'gportionsotthe: disc surf aces, dor holding' saidpiecesimpoe ieoe havingaaproiection, at
sition each fillingt' i iite a a 1 AL 3 8, Alocking device for a turbine rotor aving spa d disks'be'tfween which bla'd'es iaregi-mounted,
nt i opposed surfaces ionantagon ze/ham ers "tions convrging-itowarda thei 'per iihelties of the disks, said device including spaced-filling pieces, e ei h engaging one ol: thei'oppose'd surfaces; otthe "disks,thepiecesjhavingzoblicuesections,Lengaging a wedge locatd'betweeii and*engaging ;-s aid pieces for holding said pieces in= position,z; aid. wedge ing' the wedge iiitorpositioniabfiiween the pieces.
9: 1 locking-*devi'ce iion'iiaturbine rotor having,
spaced disks-:between=which;:blades a retmounied. the opposed esurfacesiof saiddislrs having rtions converging toward the DQ Tipheries the said wedge'taperingt'owardithe petiphery of the diskifjor', proving the fillin pieces -,.apart, said wedge; havi'nsfa radially projecting threadedpgtiomandsameing nut engaging aid portion 0 moving said wedge to piece-locking positio tending'foverathesouter sur- 4 10. A locking device for a turbine rotor having spaced discs between which the root sections of a row of blades are mounted, said device being positioned between and filling the space between a the roots of adjacent turbine blades in the row.
said device including spaced filling pieces engaging opposed surfaces ofsaid disc and a wedge betweenand' engaging with said pieces for holding them in position, said wedge having opposed surfaces engaging with said filling pieces and said wedge: extending. substantially radially between said filling pieces, the inner end of said wedge adjacent'totheaxis of the disc being wider than H the outer'iend so that said wedge converges in a"direction*radiallyoutward of the disc in order :qto;wedge the filling pieces apart by radial outwar' movement'o'f the wedge.
-ll-"A locking device for a turbine rotor having spaced discs between which the root sections of ja row of, blades are-mounted, said device being: positioned between and filling the space between the roots of-adjacent turbine blades in the row, said device including spaced filling pieces 5 engagingvopposed surfaces of saiddiscs and a wedgebetween and engaging with said pieces for holding themin position, aid wedge having opposed .suri'aces engaging with said filling pieces, said-wedge extending substantially radially between saidfilling ,pi'ecesgthe inner end of said wedge adj acent to'the 'axis oi'the disc being wider thanthe outer end so that said wedge converges in adirectipn radially outward of the disc in order to wedgethe filling'piecesapart by radial outward movement of thegw'edge, and means for fastening said-wedge in position'lbetween said filling pieces. =42.,Alocking devicef'for a; turbine rotor having spac d discs between which the root sections or a ;rowo f blades' aremounteisaid device being positioned between and filling the space between the'rootsof-adiacent turbine bladesin the row, said devicejincludingi spaced filling pieces engagis h e s dsi if s j .9 id di and a Wedge betweenand ngagingjwithsaid pieces for holding thezn, in position, said wedge having opposed surfaces engaging with saidfilling pieces, said wedge extending substantially radially between said filling pieces, the inner end of said wedge tadjacentto the axisqf the disc being wider than the outer end'so'that saidwedge converges in a ;direction radially outward oi. the disc in order to ,wedge'ithelfiilihg pieces apart by radial outward .mpvemen ior the wedge, and means accessible exfter'nally oi the discs for fastening said wedge in position'betweenjsaid idiscs.
' 'CARL R. SODERBERG.
CITED The following, references are of record in the xfll 1 :.thi .,nateut; l
s'raTEs PATENTS Number Name Date $2,315,631 Lloyd '..'I"Apr. 6. 1943 B5 1 FOR IGN PATENTS samba Coimtry I Date j 23,3187 i Great' Britain Oct. 10. 1910
US495923A 1943-07-23 1943-07-23 Turbine blade locking device Expired - Lifetime US2421855A (en)

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Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2601969A (en) * 1946-01-25 1952-07-01 United Specialties Co Turbine wheel
US2686655A (en) * 1949-09-02 1954-08-17 Maschf Augsburg Nuernberg Ag Joint between ceramic and metallic parts
US5318404A (en) * 1992-12-30 1994-06-07 General Electric Company Steam transfer arrangement for turbine bucket cooling
US6565311B2 (en) * 2000-11-21 2003-05-20 Mitsubishi Heavy Industries, Ltd. Gas turbine steam passage seal structure between blade ring and stationary blade
EP1803900A1 (en) * 2006-01-02 2007-07-04 Siemens Aktiengesellschaft Closure unit for the remaining space between the first and the last blades of a bladed ring inserted in a circumferencial slot of a turbomachine, and corresponding turbomachine
EP1803899A1 (en) * 2006-01-02 2007-07-04 Siemens Aktiengesellschaft Blade locking assembly for a turbomachine
US20110110782A1 (en) * 2009-11-11 2011-05-12 General Electric Company Locking spacer assembly for a circumferential entry airfoil attachment system
CN102116313A (en) * 2010-01-05 2011-07-06 通用电气公司 Locking spacer assembly
US20150101351A1 (en) * 2013-10-16 2015-04-16 General Electric Company Locking spacer assembly
EP2886799A1 (en) 2013-12-20 2015-06-24 Siemens Aktiengesellschaft Blade ring for a turbomachine and method for mounting blades of a blade ring of a turbomachine
US10570756B2 (en) * 2015-02-05 2020-02-25 Siemens Aktiengesellschaft Closing assembly for closing a blade ring, associated blade supports, turbomachine, and method for inserting a closing assembly
US11319821B2 (en) * 2018-04-18 2022-05-03 Siemens Energy Global GmbH & Co. KG Locking spacer assembly, corresponding blade assembly, method for installing a locking spacer

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB191023387A (en) * 1910-10-10 1910-12-08 James Howden Improvements in or relating to Fluid Pressure Turbines.
US2315631A (en) * 1942-02-14 1943-04-06 Westinghouse Electric & Mfg Co Turbine blade locking apparatus

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB191023387A (en) * 1910-10-10 1910-12-08 James Howden Improvements in or relating to Fluid Pressure Turbines.
US2315631A (en) * 1942-02-14 1943-04-06 Westinghouse Electric & Mfg Co Turbine blade locking apparatus

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2601969A (en) * 1946-01-25 1952-07-01 United Specialties Co Turbine wheel
US2686655A (en) * 1949-09-02 1954-08-17 Maschf Augsburg Nuernberg Ag Joint between ceramic and metallic parts
US5318404A (en) * 1992-12-30 1994-06-07 General Electric Company Steam transfer arrangement for turbine bucket cooling
US6565311B2 (en) * 2000-11-21 2003-05-20 Mitsubishi Heavy Industries, Ltd. Gas turbine steam passage seal structure between blade ring and stationary blade
EP1803900A1 (en) * 2006-01-02 2007-07-04 Siemens Aktiengesellschaft Closure unit for the remaining space between the first and the last blades of a bladed ring inserted in a circumferencial slot of a turbomachine, and corresponding turbomachine
EP1803899A1 (en) * 2006-01-02 2007-07-04 Siemens Aktiengesellschaft Blade locking assembly for a turbomachine
WO2007077183A1 (en) * 2006-01-02 2007-07-12 Siemens Aktiengesellschaft Closing assembly for closing the gap remaining between the first and last blade of a blade ring that is inserted into the peripheral groove of turbomachinery and corresponding turbomachinery
WO2007077185A1 (en) * 2006-01-02 2007-07-12 Siemens Aktiengesellschaft Closing assembly for a blade ring of turbomachinery
US20090016889A1 (en) * 2006-01-02 2009-01-15 Joachim Krutzfeldt Locking Sub-Assembly for Closing The Remaining Gap Between The First and The Last blade of a Blade Ring Which Are Inserted in a Circumferential Groove of a Turbomachine, and Corresponding Turbomachine
US20090220345A1 (en) * 2006-01-02 2009-09-03 Siemens Aktiengesellschaft Closing Assembly for a Blade Ring of Turbomachinery
CN101351619B (en) * 2006-01-02 2011-10-19 西门子公司 Closing assembly for a blade ring of turbomachinery
US8157530B2 (en) 2006-01-02 2012-04-17 Siemens Aktiengesellschaft Locking sub-assembly for closing the remaining gap between the first and the last of a blade ring which are inserted in a circumferential groove of a turbomachine, and corresponding turbomachine
US8157531B2 (en) 2006-01-02 2012-04-17 Siemens Aktiengesellschaft Closing assembly for a blade ring of turbomachinery
US20110110782A1 (en) * 2009-11-11 2011-05-12 General Electric Company Locking spacer assembly for a circumferential entry airfoil attachment system
CN102062114A (en) * 2009-11-11 2011-05-18 通用电气公司 Locking spacer assembly for a circumferential entry airfoil attachment system
CN102062114B (en) * 2009-11-11 2015-05-06 通用电气公司 Locking spacer assembly for a circumferential entry airfoil attachment system
US8523529B2 (en) * 2009-11-11 2013-09-03 General Electric Company Locking spacer assembly for a circumferential entry airfoil attachment system
CN102116313A (en) * 2010-01-05 2011-07-06 通用电气公司 Locking spacer assembly
EP2354458A3 (en) * 2010-01-05 2013-12-18 General Electric Company Locking spacer assembly
US20150101351A1 (en) * 2013-10-16 2015-04-16 General Electric Company Locking spacer assembly
CN104763478A (en) * 2013-10-16 2015-07-08 通用电气公司 Locking spacer assembly
US9341071B2 (en) * 2013-10-16 2016-05-17 General Electric Company Locking spacer assembly
CN104763478B (en) * 2013-10-16 2017-11-28 通用电气公司 Lockout interval component
EP2886799A1 (en) 2013-12-20 2015-06-24 Siemens Aktiengesellschaft Blade ring for a turbomachine and method for mounting blades of a blade ring of a turbomachine
US10570756B2 (en) * 2015-02-05 2020-02-25 Siemens Aktiengesellschaft Closing assembly for closing a blade ring, associated blade supports, turbomachine, and method for inserting a closing assembly
US11319821B2 (en) * 2018-04-18 2022-05-03 Siemens Energy Global GmbH & Co. KG Locking spacer assembly, corresponding blade assembly, method for installing a locking spacer

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