US3841792A - Turbomachine blade lock and seal device - Google Patents

Turbomachine blade lock and seal device Download PDF

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Publication number
US3841792A
US3841792A US00339700A US33970073A US3841792A US 3841792 A US3841792 A US 3841792A US 00339700 A US00339700 A US 00339700A US 33970073 A US33970073 A US 33970073A US 3841792 A US3841792 A US 3841792A
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United States
Prior art keywords
disc
locking
sealing member
recited
disposed
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
US00339700A
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English (en)
Inventor
D Amos
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.)
CBS Corp
Original Assignee
Westinghouse Electric Corp
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Filing date
Publication date
Application filed by Westinghouse Electric Corp filed Critical Westinghouse Electric Corp
Priority to US00339700A priority Critical patent/US3841792A/en
Priority to JP612174A priority patent/JPS5318726B2/ja
Application granted granted Critical
Publication of US3841792A publication Critical patent/US3841792A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • 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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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

  • the present invention relates to turbomachin'es and particularly to a combined structure for locking rotor blades to the disc and sealing fluid in the fluid flowpath.
  • Blade locking devices have heretofore been separate and distinct from the sealing devices on turbomachines. Blade locks are often some type of clip or bolt-on device, and seals are often bolted to portions of the disc near the blade lock. Arrangements such as these are undesirable in that bolt holes must be machined in the rotor disc taking valuable manufacturing time and money, while creating potentially hazardous situations due to high stress concentrations and unbalance near the bolt holes in the vicinity of the periphery of the rotor disc. Some sealing methods make use of the rotor land, or platform, but in the present invention, these are obviated. requiring a thinner rotor casting, less material and less machining, to reach the operational size of the rotor disc. t
  • a locking and sealing member is associated with each blade on a turbomachine rotor disc.
  • the lock and seal device has one member which is'disposed in the groove beneath the blade root on the rotor periphery. It locks the blade in place with respect to the disc, the seal members extend beyond both sides of the disc and form a fluid seal with shrouds that are attached to the radially inner ends of stationary vanes circumferentially disposed about both sides of the rotor disc.
  • FIG. 1 is a partial longitudinal sectional view of a turbomachine showing a locking and sealing device constructed in accordance with this invention
  • FIG. 2 is a fragmentary perspective view showing an H" shaped member of the lock and seal device
  • FIG. 3 is a plan view of an alternative embodiment of the H" shaped member
  • FIG. 4 is an elevational view of the IV-shaped member shown in FIG. 3;
  • FIG. 5 is a perspective view of a turbomachine blade used in this invention.
  • FIG. 6 is a fragmentary sectional view showingthe lock and seal device assembled, and a fragmentary sectional view of an assembly-disassembly tool;'
  • FIG. 7 is a sectional view of an alternative embodiment of the sealing device.
  • an axial flow turbomachine 10 which includes a rotor disc 12, a series of generally axially disposed grooves I4 on the periphery of disc 12, a blade lock and seal device 16 longitudinally disposed in each groove 14, a series of I ally directed plurality of stationary vanes 20 circumferentially disposed both upstream and downstream of the rotor disc 12, supported on their radially outer ends by a turbomachine casing 22, and on their inner ends by a shroud 24.
  • the blade lock and seal device 16 includes an H"- shaped member 26 as shown in FIG. 2, having a bridge member 27, a hole 28 in the bridge member 27, a pair of parallel trough-shaped members 30, each having a flange member 32 that forms a seal with the stationary shrouds 24 on both sides of the disc 12, and a pin 34 attached to a bias producing spring member 36 the latter two being shown in FIG. 1.
  • FIGS. 3 and 4 An alternative embodiment of the H-sh aped member 26 is shown in FIGS. 3 and 4 wherein member 26 has trough segments 29 and 31 of unequal length. This offset in length induces a twisting moment, M, during disc rotation. This creates an improved seal between adjacent trough members.
  • Shown in FIG. 4 is an overlap arrangement where the abutting inclined surfaces 38 and 38' of adjacent troughs overlap.
  • the inclined contiguous surfaces 38 and 38 can be parallel or nonparallel.
  • FIG. 4 shows an example of a non-parallel arrangement, that is, where 0 6,. This non-parallelism in mating surfaces improves the sealing between the adjacent troughs because the surfaces will mate more closely as moment M increases.
  • the blade 18 as shown in FIG. 5, has a root portion 40, an axially aligned slot 42 disposed in root portion 40, and an indentation 44 located in slot 42.
  • the slot 42 is used to facilitate ingress and egress of a blade insertion-removal tool 46, partially illustrated in FIG. 6,.
  • the rotor disc 12 in FIG. 6 is shown with the bridge member 27 portion of the lock and seal device 16 disposed in groove 14.
  • the trough-shaped members 30 extend beyond and overhang both ends of the groove 14 in an abutting relationship with the sides of the disc 12.
  • bias producing spring member 36 Disposed in the groove 14 is bias producing spring member 36, and attached thereto is a pin member 34.
  • the pin 34 registers through hole 28 in the bridge member 27, and is forced by the spring 36 into interlocking engagement with the indentation 44 in the blade root 40 of the turbomachine blade 18.
  • Assembly of the arrangement includes: positioning the spring member 36 and the attached pin 34 against the radially inward surface of the groove 14; placing the lock and seal device 16 radially outward of the spring 36 so that the pin 34 registers through the hole 28 on the bridge member 27 of the lock and seal device 16; applying a pressure on the device 16 by depressing the tool 46 in the radially inward direction to compress the spring 36; sliding the blade root 40 into the groove 14 radially outward of the device 16, until the indentation 44 is aligned with the pin 34.
  • FIG. 7 An alternative embodiment of the sealing means is shown in FIG. 7, wherein a plurality of parallel radially directed flanges 48 form a labyrinth sealing arrangement with the stationary shrouds 24. Methods for restraining the lock and seal device 16 from movement with respect to the disc 12 other than that due to the overhanging abutting troughs 30 on each side of the disc 12 could be accomplished by arrangements of biased pins, bolts or guides.
  • the invention provides a combined blade lock and fluid seal assembly for use with turbomachines, rotor blades and discs, wherein undesirable stress concentration in the rotor discs are reduced; fluid leakage between rotor discs and stator vanes is reduced, efficiencies of the turbomachines are increased; weight of the rotor disc forging is decreased. All of which is due to an economically produced, easily assembled and disassembled combined locking device for turbomachine rotor baldes and sealing device for turbomachine fluid flow paths.
  • a turbomachine assembly having at least one rotatable disc member having a plurality of generally axially disposed grooves therein, a plurality of radial blades having root portions engaged on said grooves, an annular array of stationary radially directed vanes on each side of said disc, each of said stationary arrays of vanes including a shroud joining the radially inner ends of the vanes, and a locking and sealing member associated with each of said radialv blades, each locking and sealing member being disposed longitudinally within one of said generally axially disposed grooves between said groove and said blade root, and engaging the blade root disposed therein by a pin member biasedly registered therebetween to lock the blade'in its axial position with respect to said locking and sealing member, and each locking and sealing member having portions extending on each side of the disc adapted to secure said locking and sealing member axially in said groove and to form a seal with the adjacent shroud.
  • each of said root portions of said radial blades has an axially extending slot and an indentation in said slot, said indentation receiving said biased pin member, said axially extending slot permitting disposition of said locking and sealing member therein.
  • said locking and sealing member comprises a strip of material disposed throughout said groove and extending beyond both sides of said disc, said strip of material having a hole therethrough, a bias producing means, and a radially movable pin attached to said bias producing means, said pin registering through said hole and forcibly held in interlocking engagement with said indentation by said bias producing means.

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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)
US00339700A 1973-03-09 1973-03-09 Turbomachine blade lock and seal device Expired - Lifetime US3841792A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US00339700A US3841792A (en) 1973-03-09 1973-03-09 Turbomachine blade lock and seal device
JP612174A JPS5318726B2 (th) 1973-03-09 1974-01-11

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US00339700A US3841792A (en) 1973-03-09 1973-03-09 Turbomachine blade lock and seal device

Publications (1)

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US3841792A true US3841792A (en) 1974-10-15

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US (1) US3841792A (th)
JP (1) JPS5318726B2 (th)

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4017209A (en) * 1975-12-15 1977-04-12 United Technologies Corporation Turbine rotor construction
NL7706758A (nl) * 1976-06-29 1978-01-02 United Technologies Corp Afdichtingsinrichting voor een schijf.
US4088422A (en) * 1976-10-01 1978-05-09 General Electric Company Flexible interstage turbine spacer
US4279572A (en) * 1979-07-09 1981-07-21 United Technologies Corporation Sideplates for rotor disk and rotor blades
US4451959A (en) * 1980-12-29 1984-06-05 Elliott Turbomachinery Company, Inc. Methods for securing a rotor blade within a rotor assembly and removing a rotor blade therefrom
US4473337A (en) * 1982-03-12 1984-09-25 United Technologies Corporation Blade damper seal
US4505642A (en) * 1983-10-24 1985-03-19 United Technologies Corporation Rotor blade interplatform seal
US4653984A (en) * 1985-05-01 1987-03-31 United Technologies Corporation Turbine module assembly device
US4781534A (en) * 1987-02-27 1988-11-01 Westinghouse Electric Corp. Apparatus and method for reducing windage and leakage in steam turbine incorporating axial entry blade
US5127799A (en) * 1990-12-17 1992-07-07 Allied-Signal Inc. Interstage coupling seal and method of assembling a gas turbine engine
US5558500A (en) * 1994-06-07 1996-09-24 Alliedsignal Inc. Elastomeric seal for axial dovetail rotor blades
US6042336A (en) * 1998-11-25 2000-03-28 United Technologies Corporation Offset center of gravity radial damper
US20020182081A1 (en) * 2001-04-26 2002-12-05 Rene Bachofner Device for fastening a moving blade to the rotor of a turbomachine
US20080044284A1 (en) * 2006-08-16 2008-02-21 United Technologies Corporation Segmented fluid seal assembly
US20090110548A1 (en) * 2007-10-30 2009-04-30 Pratt & Whitney Canada Corp. Abradable rim seal for low pressure turbine stage
US7540709B1 (en) 2005-10-20 2009-06-02 Florida Turbine Technologies, Inc. Box rim cavity for a gas turbine engine
US20090208326A1 (en) * 2006-09-08 2009-08-20 Eric Durocher Rim seal for a gas turbine engine
US20100111673A1 (en) * 2008-11-05 2010-05-06 General Electric Company Turbine with interrupted purge flow
US20180258781A1 (en) * 2017-03-08 2018-09-13 Pratt & Whitney Canada Corp. Rim seal

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS59124747U (ja) * 1983-02-11 1984-08-22 いすゞ自動車株式会社 車両用シ−ト
JPS59143836U (ja) * 1983-03-16 1984-09-26 ダイハツ工業株式会社 自動車用シ−トにおけるウオ−クイン機構
JPS59149535U (ja) * 1983-03-28 1984-10-05 車体工業株式会社 自動車の座席の摺動機構
EP2184443A1 (de) 2008-11-05 2010-05-12 Siemens Aktiengesellschaft Gasturbine mit Sicherungsplatte zwischen Schaufelfuss und Scheibe

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3023998A (en) * 1959-03-13 1962-03-06 Jr Walter H Sanderson Rotor blade retaining device
US3295825A (en) * 1965-03-10 1967-01-03 Gen Motors Corp Multi-stage turbine rotor
US3455537A (en) * 1967-09-27 1969-07-15 Continental Aviat & Eng Corp Air-cooled turbine rotor self-sustaining shroud plate
US3656864A (en) * 1970-11-09 1972-04-18 Gen Motors Corp Turbomachine rotor
US3761200A (en) * 1970-12-05 1973-09-25 Secr Defence Bladed rotors

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3023998A (en) * 1959-03-13 1962-03-06 Jr Walter H Sanderson Rotor blade retaining device
US3295825A (en) * 1965-03-10 1967-01-03 Gen Motors Corp Multi-stage turbine rotor
US3455537A (en) * 1967-09-27 1969-07-15 Continental Aviat & Eng Corp Air-cooled turbine rotor self-sustaining shroud plate
US3656864A (en) * 1970-11-09 1972-04-18 Gen Motors Corp Turbomachine rotor
US3761200A (en) * 1970-12-05 1973-09-25 Secr Defence Bladed rotors

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4017209A (en) * 1975-12-15 1977-04-12 United Technologies Corporation Turbine rotor construction
NL7706758A (nl) * 1976-06-29 1978-01-02 United Technologies Corp Afdichtingsinrichting voor een schijf.
US4088422A (en) * 1976-10-01 1978-05-09 General Electric Company Flexible interstage turbine spacer
US4279572A (en) * 1979-07-09 1981-07-21 United Technologies Corporation Sideplates for rotor disk and rotor blades
US4451959A (en) * 1980-12-29 1984-06-05 Elliott Turbomachinery Company, Inc. Methods for securing a rotor blade within a rotor assembly and removing a rotor blade therefrom
US4473337A (en) * 1982-03-12 1984-09-25 United Technologies Corporation Blade damper seal
US4505642A (en) * 1983-10-24 1985-03-19 United Technologies Corporation Rotor blade interplatform seal
US4653984A (en) * 1985-05-01 1987-03-31 United Technologies Corporation Turbine module assembly device
US4781534A (en) * 1987-02-27 1988-11-01 Westinghouse Electric Corp. Apparatus and method for reducing windage and leakage in steam turbine incorporating axial entry blade
US5127799A (en) * 1990-12-17 1992-07-07 Allied-Signal Inc. Interstage coupling seal and method of assembling a gas turbine engine
US5558500A (en) * 1994-06-07 1996-09-24 Alliedsignal Inc. Elastomeric seal for axial dovetail rotor blades
US6042336A (en) * 1998-11-25 2000-03-28 United Technologies Corporation Offset center of gravity radial damper
US20020182081A1 (en) * 2001-04-26 2002-12-05 Rene Bachofner Device for fastening a moving blade to the rotor of a turbomachine
US7540709B1 (en) 2005-10-20 2009-06-02 Florida Turbine Technologies, Inc. Box rim cavity for a gas turbine engine
US20080044284A1 (en) * 2006-08-16 2008-02-21 United Technologies Corporation Segmented fluid seal assembly
US20090208326A1 (en) * 2006-09-08 2009-08-20 Eric Durocher Rim seal for a gas turbine engine
US8172514B2 (en) 2006-09-08 2012-05-08 Pratt & Whitney Canada Corp. Rim seal for a gas turbine engine
US20090110548A1 (en) * 2007-10-30 2009-04-30 Pratt & Whitney Canada Corp. Abradable rim seal for low pressure turbine stage
US20100111673A1 (en) * 2008-11-05 2010-05-06 General Electric Company Turbine with interrupted purge flow
JP2010112376A (ja) * 2008-11-05 2010-05-20 General Electric Co <Ge> パージ流を遮断したタービン
US8137067B2 (en) 2008-11-05 2012-03-20 General Electric Company Turbine with interrupted purge flow
US20180258781A1 (en) * 2017-03-08 2018-09-13 Pratt & Whitney Canada Corp. Rim seal
US10633992B2 (en) * 2017-03-08 2020-04-28 Pratt & Whitney Canada Corp. Rim seal

Also Published As

Publication number Publication date
JPS49120205A (th) 1974-11-16
JPS5318726B2 (th) 1978-06-16

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