US3527546A - Tie pins for turbine buckets - Google Patents

Tie pins for turbine buckets Download PDF

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Publication number
US3527546A
US3527546A US788538A US3527546DA US3527546A US 3527546 A US3527546 A US 3527546A US 788538 A US788538 A US 788538A US 3527546D A US3527546D A US 3527546DA US 3527546 A US3527546 A US 3527546A
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United States
Prior art keywords
buckets
pin
tie
bucket
tie pin
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Expired - Lifetime
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US788538A
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English (en)
Inventor
Kenneth P Zeman
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General Electric Co
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General Electric Co
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Publication date
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Publication of US3527546A publication Critical patent/US3527546A/en
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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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/24—Blade-to-blade connections, e.g. for damping vibrations using wire or the like

Definitions

  • This invention relates generally to turbo machinery rotors and more particularly to an improved lashing or tying construction for turbine rotor buckets.
  • tie wires between groups of adjacent buckets.
  • a group of buckets are connected together, generally at a point midway between root and tip, by a rod or wire of small diameter which runs through holes in each bucket and which may be loose or brazed to the buckets.
  • this type of tie wire is not effective in all cases.
  • Another method commonly used is to dispose individual diagonal tie pins between adjacent buckets.
  • a short pin is inserted between bucket-s which runs from the leading edge region of one bucket to the trailing edge region of the adjacent bucket.
  • These may be loosely disposed or tightly disposed, an example of the latter being seen in US. Pat. 3,131,461 issued to A. J. Miller on May 5, 1964.
  • one object of the present invention is to provide an improved diagonal tie pin that decreases the chances of the pin coming out when the buckets rock apart.
  • Another object is to provide a pin which requires no cold working or welding to restrain the pin in only one of two supporting buckets.
  • Still a further object is to provide a bucket-tie pin assembly wherein no special tie pin is required for the last assembled bucket.
  • FIG. 1 is a perspective view of a partial turbine stage embodying this invention.
  • FIG. 2 is a radially inward view, partly in section, of two assembled buckets and the next to be assembled bucket and tie pin of the turbine stage of FIG. 1.
  • FIG. 3 is a radially inward view, partly in section, of the last two buckets and pins to be assembled with the first assembled bucket.
  • my invention is practiced in one form by providing a hooked diagonal tie pin between two adjacent buckets which are disposed on a turbine wheel.
  • the diagonal tie pin is loosely disposed in holes in each bucket but maintains a locked orientation after final assembly by the tapered hook, partially tapered neck, and flange portion of the tie pin which is disposed in the hole toward the leading edge.
  • FIG. 1 a typical environment of this invention is shown including a turbine rotor 1, comprising one stage of a steam or gas turbine.
  • the rotor 1 has buckets 2 mounted thereon by some form of dovetail 3.
  • Buckets 2 are of the axially insertable type with means provided to lock the buckets in place after final assembly.
  • In the area intermediate the roots and tips of buckets 2 are the booked and flanged diagonal tie pins 4 connecting adjacent buckets to provide torsional vibration damping.
  • the pins 4 are loosely disposed and in a locked position so they cannot come out, except by special procedure to be described later.
  • transverse holes 5 and 7 are formed such that an extension of their centerlines would meet and be substantially coplanar with the other.
  • transverse hole 5 is formed such that a partially tapered surface 5a is provided.
  • Transverse hole 7 is formed, such that its corners 7a, 7b are rounded so as to allow a pivoting motion of the pin during assembly.
  • the hooked diagonal tie pins 4a and 4b in relation to buckets 2a, 2b and 2c.
  • the hooked diagonal tie pin is formed in any suitable manner, such as casting, so that it is comprised of a flange portion 10, a tapered hook portion 11, a partially tapered neck portion 12, and the remaining body 13.
  • Flange 10 is formed generally in the shape of a cone extending around the circumference of the pin.
  • the hook 11 and part of neck portion 12 have a tapered offset generally shown at 14, with respect to the circumference of the pin. It is the purpose of the various parts just described to maintain the tie pin in a locked orientation after final assembly, but allowing sufficient clearance between bucket and pin so as to facilitate easy assembly. It is understood that after final assembly, the pins are loosely disposed in the bucket holes but in a locked orientation.
  • FIG. 2 The three buckets shown in FIG. 2 with diagonal tie pins 4a and 4b are shown with respect to reference plane 15, which represents the plane on which the leading edge of the buckets rest when all buckets are finally assembled.
  • reference plane 15 represents the plane on which the leading edge of the buckets rest when all buckets are finally assembled.
  • This shows the first two assembled buckets 2a and 2b with tie pin 4a disposed diagonally therebetween with the next assembled bucket 2c and tie pin 4b axially displaced so as to allow axial insertion of the bucket and pin by the use of dovetail 3.
  • bucket 20 is axially displaced in its dovetail 3 toward the upstream side of reference plane 15.
  • the body portion 13 of tie pin 4b is inserted through transverse hole 7. Due to rounded corners 7a, 7b of hole 7, tie pin 4b is allowed to pivot as previously mentioned.
  • the tapered hook portion is freely slidable into hole 5. Further movement causes the diagonal tie pin 4b to move into its locked orientation as bucket 2c is aligned with reference plane 15.
  • tapered hook 11 extends over the leading edge region 6 while the flange rests on tapered surface 5a providing the locked orientation.
  • the next bucket and tie pin is inserted in the same manner following a left to right sequence around turbine rotor 1.
  • the method for inserting the last tie pin is a simple matter requiring a slightly different technique as compared to normal assembly. Referring now to FIG. 3, that method will be described.
  • the first assembled bucket 2a and partially drawn tie pin 4a are shown in their final assembled position, i.e., directly aligned with reference plane 15.
  • the next-to-the-last pin to be assembled 4c is inserted between adjacent buckets 2d and 2e by the normal method previously described.
  • the last two buckets to be assembled 2d and 2e are then moved axially along their dovetails 3 to a downstream position with respect to reference plane so that there is sufficient clearance for the insertion of last pin 4d.
  • pin 4d will slide into holes 5 and 7 when the last buckets are moved toward reference plane 15 from their downstream position.
  • the last pin reaches a locked orientation as the last bucket 2e reaches reference plane 15.
  • the last assembled buckets are then locked in place.
  • a turbomachine rotor having a plurality of axiallyinsertable buckets disposed thereon with a diagonal tie pin dampening structure comprising:
  • said pin having a hook portion on one end thereof shaped so that the pin will slide into one of said bucket holes when the buckets are axially offset relative to one another.
  • a turbomachine rotor according to claim 1 in which said tie pin comprises a flange portion toward one end thereof, a tapered hook portion on said end thereof, a partially tapered neck portion between said flange and said hook, and a remaining body portion.
  • a turbomachine rotor according to claim 1 in which said tapered hook and partially tapered neck portions are disposed through said tie pin hole toward the leading edge.
  • a turbomachine rotor according to claim 1 in which said tie pin hole toward the leading edge has a partially tapered surface to provide a resting surface for said flange portion.
  • a turbomachine rotor according to claim 1 in which said tie pin hole toward the trailing edge has rounded corners to allow pivoting motion of the tie pin.
  • a turbomachine rotor having a plurality of axiallyinsertable buckets disposed thereon,
  • each of said buckets defining a first tie pin hole toward the trailing edge, said first hole having rounded corners, and also defining a second tie pin hole located toward the leading edge, said second hole having a partially tapered surface
  • each of said pins comprising:
  • a body portion extending between buckets and passing through said first hole, a flange portion toward one end thereof and abutting said second hole tapered surface, a hook portion on the end of the pin and preventing movement through the second hole, and a tapered neck portion connecting said flange and hook.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US788538A 1969-01-02 1969-01-02 Tie pins for turbine buckets Expired - Lifetime US3527546A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US78853869A 1969-01-02 1969-01-02

Publications (1)

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US3527546A true US3527546A (en) 1970-09-08

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US788538A Expired - Lifetime US3527546A (en) 1969-01-02 1969-01-02 Tie pins for turbine buckets

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US (1) US3527546A (de)
CH (1) CH496163A (de)
NL (1) NL6919299A (de)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3778190A (en) * 1971-10-01 1973-12-11 Gen Electric Bucket cover attachment
US4191508A (en) * 1977-02-02 1980-03-04 Hitachi, Ltd. Turbine rotor construction
US4407634A (en) * 1981-09-08 1983-10-04 Northern Engineering Industries Plc Axial-flow steam turbine wheel
US5984638A (en) * 1994-08-12 1999-11-16 Elliott Turbomachinery Co., Inc. Turbomachine radial impeller vibration constraining and damping mechanism
US20070036642A1 (en) * 2005-08-10 2007-02-15 The Boeing Company Bridged inducer
US20110036068A1 (en) * 2009-08-17 2011-02-17 Guy Lefebvre Gas turbine engine exhaust mixer
CN102691674A (zh) * 2011-03-25 2012-09-26 台达电子工业股份有限公司 叶轮结构
US20120244008A1 (en) * 2011-03-25 2012-09-27 Shun-Chen Chang Impeller structure
US20190017393A1 (en) * 2015-07-20 2019-01-17 Nuovo Pignone Tecnologie Srl Unshrouded turbomachine impeller with improved rigidity
US11028778B2 (en) 2018-09-27 2021-06-08 Pratt & Whitney Canada Corp. Engine with start assist

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US937006A (en) * 1906-03-03 1909-10-12 Allis Chalmers Steam-turbine.
CH272378A (de) * 1949-02-17 1950-12-15 Escher Wyss Ag Beschaufelung an Rotoren von axial durchströmten, verwundene Schaufeln aufweisenden Kreiselmaschinen, insbesondere von Dampf-, Gasturbinen und Verdichtern.
GB696557A (en) * 1950-03-24 1953-09-02 Bbc Brown Boveri & Cie Vibration damper for the blades of elastic fluid turbines, compressors and the like
US3131461A (en) * 1961-04-20 1964-05-05 Carrier Corp Method of making vibration damped turbo machinery

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US937006A (en) * 1906-03-03 1909-10-12 Allis Chalmers Steam-turbine.
CH272378A (de) * 1949-02-17 1950-12-15 Escher Wyss Ag Beschaufelung an Rotoren von axial durchströmten, verwundene Schaufeln aufweisenden Kreiselmaschinen, insbesondere von Dampf-, Gasturbinen und Verdichtern.
GB696557A (en) * 1950-03-24 1953-09-02 Bbc Brown Boveri & Cie Vibration damper for the blades of elastic fluid turbines, compressors and the like
US3131461A (en) * 1961-04-20 1964-05-05 Carrier Corp Method of making vibration damped turbo machinery

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3778190A (en) * 1971-10-01 1973-12-11 Gen Electric Bucket cover attachment
US4191508A (en) * 1977-02-02 1980-03-04 Hitachi, Ltd. Turbine rotor construction
US4407634A (en) * 1981-09-08 1983-10-04 Northern Engineering Industries Plc Axial-flow steam turbine wheel
US5984638A (en) * 1994-08-12 1999-11-16 Elliott Turbomachinery Co., Inc. Turbomachine radial impeller vibration constraining and damping mechanism
US20070036642A1 (en) * 2005-08-10 2007-02-15 The Boeing Company Bridged inducer
US9284915B2 (en) 2009-08-17 2016-03-15 Pratt & Whitney Canada Corp. Gas turbine engine exhaust mixer
US8739513B2 (en) 2009-08-17 2014-06-03 Pratt & Whitney Canada Corp. Gas turbine engine exhaust mixer
US20110036068A1 (en) * 2009-08-17 2011-02-17 Guy Lefebvre Gas turbine engine exhaust mixer
US10760527B2 (en) 2009-08-17 2020-09-01 Pratt & Whitney Canada Corp. Gas turbine engine exhaust mixer
CN102691674A (zh) * 2011-03-25 2012-09-26 台达电子工业股份有限公司 叶轮结构
US20120244008A1 (en) * 2011-03-25 2012-09-27 Shun-Chen Chang Impeller structure
US20190017393A1 (en) * 2015-07-20 2019-01-17 Nuovo Pignone Tecnologie Srl Unshrouded turbomachine impeller with improved rigidity
US10669864B2 (en) * 2015-07-20 2020-06-02 Nuovo Pignone Srl Unshrouded turbomachine impeller with improved rigidity
US11028778B2 (en) 2018-09-27 2021-06-08 Pratt & Whitney Canada Corp. Engine with start assist
US11466623B2 (en) 2018-09-27 2022-10-11 Pratt & Whitney Canada Corp. Engine with start assist

Also Published As

Publication number Publication date
NL6919299A (de) 1970-07-06
CH496163A (de) 1970-09-15

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