US2771267A - Lacing for compressor blades - Google Patents

Lacing for compressor blades Download PDF

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Publication number
US2771267A
US2771267A US290116A US29011652A US2771267A US 2771267 A US2771267 A US 2771267A US 290116 A US290116 A US 290116A US 29011652 A US29011652 A US 29011652A US 2771267 A US2771267 A US 2771267A
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Prior art keywords
blades
wire
hub
tube
extending
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Expired - Lifetime
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US290116A
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Jr Leon J Weymouth
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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
    • F01D5/12—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

  • the present invention relates to a vibration damping means for blad-ing and is particularly applicable to blades in axial flow compressors.
  • One feature of the invention is an arrangement of damping means which extends between adjacent blades in a rotor disc and is located between the tips of the blades and the roots to effect a damping action other than at the tip or the root.
  • Another feature of the invention is an arrangement of a lacing wire extending through a number of blades on the periphery of the disc and connected to each blade through a damping medium thereby to effect a damping action for each of the blades indiv-idually.
  • one feature of the invention is a lacing wire having an enlarged portion at each compressor blade which is receivable in a tube fixed to the blade with a damping medium within the tube for restricting the movement of the wire within the tube.
  • Fig. l is a firagmentary perspective view of a rotor disc having a number of blades on its periphery with the damping means applied thereto.
  • Fig. 2 is a sectional view through one of the blades showing the damping arrangement in greater detail.
  • the hub 2 which is shown as a hub for use in an axial flow compressor has a number of blades 4 projecting radially outward from its periphery, the blade being secured in place by blade roots 6 received in slots 8 extending in an axial direction through the hub at its periphery.
  • the blades are angularly spaced apart on the hub as will be apparent.
  • the hub with the blades thereon form a disc which may be one of several in a multistage rotor.
  • Each of the blades has positioned therein, at a point between the tip 10 of the blade and the root and preferably substantially midway of the blade length, a tube 12 which is permanently attached to the blade as by soldering or welding 14, Fig. 2.
  • the tube extends in a circumferential direction and is open at both ends as shown to permit the insertion of a lacing rod or wire 16 which extends through a number of adjacent blades on the periphery and preferably is a continuous wire extending entirely around the disc.
  • the lacing wire has a number of integral piston elements 18 which are spaced apart to correspond to the spacing of the blades. These piston elements are received within the tubes 12 as shown in Fig. 2 with the elements preferably midway of the length of the tubes.
  • the piston elements 18 are a loose tit within the tube and are resiliently supported against circumferential movement within the tube by elastic damping material 20 such as rubber or a similar damping compound which may be bonded to the sides of the piston element 18 and to the tube.
  • elastic damping material 20 such as rubber or a similar damping compound which may be bonded to the sides of the piston element 18 and to the tube.
  • the ends of the tube may be crimped as shown at 22 in order to retain the damping material more securely within the tube.
  • a compressor rotor having a hub with slots in its periphery and a number of radially extending blades surrounding the hub, the blades having root portions at one end fitting within the slots, in combination with a wire extending between adjacent blades between the tips of the blades and the roots and rubber damping means between and connecting said wire and blades and bonded to the wire and blades.
  • a compressor rotor having a hub with slots in its periphery and a number of radially extending blades surrounding the hub, the blades having root portions at one end fitting within the slots, in combination with damping means extending between adjacent blades between the tips of the blades and the roots, said damping means including a wire extending through several of the blades in a circumferential direction and rubber damping means conmeeting the wire to the blades and bonded to the wire.
  • a compressor rotor having a hub with slots in its periphery and a number of radially extending blades surrounding the hub, the blades having root portions at one end fitting within the slots, in combination with damping means extending between adjacent blades between the tips of the blades and the roots, said damping means including a wire extending through several of the blades in a circumferential direction, a tube fixed within each blade and receiving the wire, and rubber damping means within the tubes and surrounding the wire, said damping means being secured to the wire and to each of the tubes.
  • a rotor having a hub and a plurality of blades extending radially outward from the hub, each of said blades having a tube extending circumferentially therethrough :and secured against movement therein, a lacing wire extending circumferentially of the rotor and through several of the tubes, and rubber damping means within each tube and surrounding the wire, said damping means being secured to said wire and tubes and thereby providing a damping connection between the wire and each of said tubes.
  • a rotor having a hub and a plurality of blades extending radially outward from the hub, each of said blades having a tube extending circumferentially therethrough and secure-d against movement therein, a lacing wire extending circumferentially through several of the tubes, said wire having piston elements thereon at each blade fitting within the adjacent tube, and an elastic damping means secured in each tube and providing an elastic connection from each piston element to the associated tube to damp the circumferential movement of each blade with re spect to the piston element associated therewith.
  • a rotor having a hub and a plurality of blades ex-' tending radially outward from the hub, each of said blades having a tube extending ci-rcumferentially the-rethrough between the ends of the blade, said tube being secured in said blade, a lacing wire extending .circumferentially of the rotor and through said tubes, said wire having enlargements thereon fitting in said tubes and movable therein, and an elastic darnping means secured within each of said tubes at each side of the enlargement.
  • a rotor having a hub and a plurality of blades extending radially outward from the hub, each of said blades having a tube extending ciroum ferentially therethrough between the ends of the blade, said tube being secured in said blade, a lacing Wire extending circumferentially of the rotor and through said tubes, sa-id Wire having enlargements thereon fitting in said tubes and movable therein, and an elastic damping means secured within each of said tubes at each side of the enlargement, the ends of the tubes being crimped to retain the damping material in position.
  • a rotor having a hub with slots in its periphery and A a number of radially extending blades surrounding the hub, the blades having root portions at one end fitting within the slots, in combination with a tube extending through each of at least two adjacent blades, a Wire eX- tending 'between said blades and into said tubes, the wire having an enlargement thereon located within each tube, and elastic damping means positioned within each both said tube and enlargement, said damping means tube and surrounding the enlargement and connected to providing an elastic connection from the wire to each tube.
  • a compressor rotor including a hub and blades extending in a row radially outward from the hub, in combination with a Wire extending circumferentially between adjacent blades and spaced radially outward from the hub, and rubber damping means between and connecting said wire and blades and bonded to the wire and blades.
  • a compressor rotor including a hub and blades extending in a row radially outward from the hub, in combination with a wire extending through several of the blades in a circumferential direction and spaced radially outward from the hub, and rubber damping means connecting the wire to the blades and bonded to the wire.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Nov. 20, 1956 J. WEYMOUTH, JR 2,
LACING FOR COMPRESSOR BLADES Filed May 27, 1952 FIG. 2
INVENTOR LEON J. WEYMOUZ'H JR.
A T TORNEV United States Patent LACING FOR COMPRESSOR BLADES Leon J. Weymouth, Jr., Manchester, Conn, assignor to United Aircraft Corporation, East Hartford, Conn, a corporation of Delaware Application May 27, 1952, Serial No. 290,116
Claims. (Cl. 253-77) The present invention relates to a vibration damping means for blad-ing and is particularly applicable to blades in axial flow compressors.
One feature of the invention is an arrangement of damping means which extends between adjacent blades in a rotor disc and is located between the tips of the blades and the roots to effect a damping action other than at the tip or the root. Another feature of the invention is an arrangement of a lacing wire extending through a number of blades on the periphery of the disc and connected to each blade through a damping medium thereby to effect a damping action for each of the blades indiv-idually.
More specifically, one feature of the invention is a lacing wire having an enlarged portion at each compressor blade which is receivable in a tube fixed to the blade with a damping medium within the tube for restricting the movement of the wire within the tube.
Other objects and advantages will be apparent from the specification and claims, and from the accompanying drawings which illustrate an embodiment of the invention.
Fig. l is a firagmentary perspective view of a rotor disc having a number of blades on its periphery with the damping means applied thereto.
Fig. 2 is a sectional view through one of the blades showing the damping arrangement in greater detail.
The hub 2 which is shown as a hub for use in an axial flow compressor has a number of blades 4 projecting radially outward from its periphery, the blade being secured in place by blade roots 6 received in slots 8 extending in an axial direction through the hub at its periphery. The blades are angularly spaced apart on the hub as will be apparent. The hub with the blades thereon form a disc which may be one of several in a multistage rotor.
Each of the blades has positioned therein, at a point between the tip 10 of the blade and the root and preferably substantially midway of the blade length, a tube 12 which is permanently attached to the blade as by soldering or welding 14, Fig. 2. The tube extends in a circumferential direction and is open at both ends as shown to permit the insertion of a lacing rod or wire 16 which extends through a number of adjacent blades on the periphery and preferably is a continuous wire extending entirely around the disc. The lacing wire has a number of integral piston elements 18 which are spaced apart to correspond to the spacing of the blades. These piston elements are received within the tubes 12 as shown in Fig. 2 with the elements preferably midway of the length of the tubes. The piston elements 18 are a loose tit within the tube and are resiliently supported against circumferential movement within the tube by elastic damping material 20 such as rubber or a similar damping compound which may be bonded to the sides of the piston element 18 and to the tube. The ends of the tube may be crimped as shown at 22 in order to retain the damping material more securely within the tube.
ice
With this arrangement it will be apparent that vibration of any individual blade will be effectively damped by the damping material since the attempt of any blade to move circumferentially will tend to cause a movement of the tube with respect to the piston element with the damping material resiliently resisting this movement.
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.
I claim:
-1. A compressor rotor having a hub with slots in its periphery and a number of radially extending blades surrounding the hub, the blades having root portions at one end fitting within the slots, in combination with a wire extending between adjacent blades between the tips of the blades and the roots and rubber damping means between and connecting said wire and blades and bonded to the wire and blades.
2. A compressor rotor having a hub with slots in its periphery and a number of radially extending blades surrounding the hub, the blades having root portions at one end fitting within the slots, in combination with damping means extending between adjacent blades between the tips of the blades and the roots, said damping means including a wire extending through several of the blades in a circumferential direction and rubber damping means conmeeting the wire to the blades and bonded to the wire.
3. A compressor rotor having a hub with slots in its periphery and a number of radially extending blades surrounding the hub, the blades having root portions at one end fitting within the slots, in combination with damping means extending between adjacent blades between the tips of the blades and the roots, said damping means including a wire extending through several of the blades in a circumferential direction, a tube fixed within each blade and receiving the wire, and rubber damping means within the tubes and surrounding the wire, said damping means being secured to the wire and to each of the tubes.
4. A rotor having a hub and a plurality of blades extending radially outward from the hub, each of said blades having a tube extending circumferentially therethrough :and secured against movement therein, a lacing wire extending circumferentially of the rotor and through several of the tubes, and rubber damping means within each tube and surrounding the wire, said damping means being secured to said wire and tubes and thereby providing a damping connection between the wire and each of said tubes.
5. A rotor having a hub and a plurality of blades extending radially outward from the hub, each of said blades having a tube extending circumferentially therethrough and secure-d against movement therein, a lacing wire extending circumferentially through several of the tubes, said wire having piston elements thereon at each blade fitting within the adjacent tube, and an elastic damping means secured in each tube and providing an elastic connection from each piston element to the associated tube to damp the circumferential movement of each blade with re spect to the piston element associated therewith.
6. A rotor having a hub and a plurality of blades ex-' tending radially outward from the hub, each of said blades having a tube extending ci-rcumferentially the-rethrough between the ends of the blade, said tube being secured in said blade, a lacing wire extending .circumferentially of the rotor and through said tubes, said wire having enlargements thereon fitting in said tubes and movable therein, and an elastic darnping means secured within each of said tubes at each side of the enlargement.
7. A rotor having a hub and a plurality of blades extending radially outward from the hub, each of said blades having a tube extending ciroum ferentially therethrough between the ends of the blade, said tube being secured in said blade, a lacing Wire extending circumferentially of the rotor and through said tubes, sa-id Wire having enlargements thereon fitting in said tubes and movable therein, and an elastic damping means secured within each of said tubes at each side of the enlargement, the ends of the tubes being crimped to retain the damping material in position.
8. A rotor having a hub with slots in its periphery and A a number of radially extending blades surrounding the hub, the blades having root portions at one end fitting within the slots, in combination with a tube extending through each of at least two adjacent blades, a Wire eX- tending 'between said blades and into said tubes, the wire having an enlargement thereon located within each tube, and elastic damping means positioned within each both said tube and enlargement, said damping means tube and surrounding the enlargement and connected to providing an elastic connection from the wire to each tube.
9. A compressor rotor including a hub and blades extending in a row radially outward from the hub, in combination with a Wire extending circumferentially between adjacent blades and spaced radially outward from the hub, and rubber damping means between and connecting said wire and blades and bonded to the wire and blades.
'10. A compressor rotor including a hub and blades extending in a row radially outward from the hub, in combination with a wire extending through several of the blades in a circumferential direction and spaced radially outward from the hub, and rubber damping means connecting the wire to the blades and bonded to the wire.
References Cited in the file of this patent UNITED STATES PATENTS 1,542,402 Meissner June 1 6, 1925 1,618,285 Kasley Feb. 22, 1927 2,412,615 Howard Dec. 17, 1946 2,436,087 Benson Feb. 17, 1948 FOREIGN PATENTS 427,963 Germany Apr. 22, 1926 430,429 Germany June 18, 1926 623,525 Great Britain May 1 8, 1949 685,110 France Mar. 25, 1930
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Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2962259A (en) * 1956-02-03 1960-11-29 Napier & Son Ltd Turbine blade rings and methods of assembly
US3327995A (en) * 1965-07-31 1967-06-27 Rolls Royce Bladed rotor
US3451654A (en) * 1967-08-25 1969-06-24 Gen Motors Corp Blade vibration damping
FR2403450A1 (en) * 1977-09-14 1979-04-13 Bbc Brown Boveri & Cie VIBRATION DAMPER FOR TURBINE BLADES
US4699569A (en) * 1985-07-05 1987-10-13 Bbc Brown, Boveri & Company, Limited Rotor blade ring of an axial flow turbomachine
FR2697284A1 (en) * 1992-10-27 1994-04-29 Europ Propulsion Method for manufacturing a turbine wheel with inserted blades and wheel obtained by the method.
WO2010043666A1 (en) * 2008-10-16 2010-04-22 Siemens Aktiengesellschaft Axial turbomachine comprising a rotor blade ring and a damping device
DE102009010502A1 (en) * 2009-02-25 2010-09-09 Siemens Aktiengesellschaft Airfoil for blade of e.g. steam turbine, has lugs provided at side, which is turned towards rotation axis of turbine blade, of wall for placing damper wire, where lugs are directed to longitudinal axis of blade eye
US20110194939A1 (en) * 2010-02-05 2011-08-11 Marra John J Snubber Assembly for Turbine Blades
US20110274549A1 (en) * 2010-05-06 2011-11-10 General Electric Company Blade having asymmetrical mid-span structure portions and related bladed wheel structure
US10385702B2 (en) * 2015-06-30 2019-08-20 Napier Turbochargers Ltd Turbomachinery rotor blade
US20240035384A1 (en) * 2022-07-27 2024-02-01 General Electric Company Nested damper pin and vibration dampening system for turbine nozzle or blade

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1542402A (en) * 1924-12-17 1925-06-16 Westinghouse Electric & Mfg Co Elastic-fluid turbine
DE427963C (en) * 1924-09-16 1926-04-22 Vickers Electrical Co Ltd Device for connecting turbine blades with their stiffening wires
DE430429C (en) * 1925-04-05 1926-06-18 Allg Elek Citaets Ges Fa Wire stiffening of steam turbine blades
US1618285A (en) * 1927-02-22 Blade lashing
FR685110A (en) * 1928-12-13 1930-07-04 Brown Method and tools for making the connection between the fins of steam or gas turbines by means of a metal wire and intermediate parts
US2412615A (en) * 1943-04-16 1946-12-17 Gen Electric Bladed machine element
US2436087A (en) * 1944-12-04 1948-02-17 Ernest H Benson Cooling fan for aircraft engines
GB623525A (en) * 1947-05-13 1949-05-18 Svenska Turbinfab Ab Vibration damper for blades of turbines and compressors

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1618285A (en) * 1927-02-22 Blade lashing
DE427963C (en) * 1924-09-16 1926-04-22 Vickers Electrical Co Ltd Device for connecting turbine blades with their stiffening wires
US1542402A (en) * 1924-12-17 1925-06-16 Westinghouse Electric & Mfg Co Elastic-fluid turbine
DE430429C (en) * 1925-04-05 1926-06-18 Allg Elek Citaets Ges Fa Wire stiffening of steam turbine blades
FR685110A (en) * 1928-12-13 1930-07-04 Brown Method and tools for making the connection between the fins of steam or gas turbines by means of a metal wire and intermediate parts
US2412615A (en) * 1943-04-16 1946-12-17 Gen Electric Bladed machine element
US2436087A (en) * 1944-12-04 1948-02-17 Ernest H Benson Cooling fan for aircraft engines
GB623525A (en) * 1947-05-13 1949-05-18 Svenska Turbinfab Ab Vibration damper for blades of turbines and compressors

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2962259A (en) * 1956-02-03 1960-11-29 Napier & Son Ltd Turbine blade rings and methods of assembly
US3327995A (en) * 1965-07-31 1967-06-27 Rolls Royce Bladed rotor
DE1301638B (en) * 1965-07-31 1969-08-21 Rolls Royce Blade ring for gas turbine engines
US3451654A (en) * 1967-08-25 1969-06-24 Gen Motors Corp Blade vibration damping
FR2403450A1 (en) * 1977-09-14 1979-04-13 Bbc Brown Boveri & Cie VIBRATION DAMPER FOR TURBINE BLADES
US4699569A (en) * 1985-07-05 1987-10-13 Bbc Brown, Boveri & Company, Limited Rotor blade ring of an axial flow turbomachine
CH666722A5 (en) * 1985-07-05 1988-08-15 Bbc Brown Boveri & Cie Vane ring of an axially flowed turbo machine.
WO1994010426A1 (en) * 1992-10-27 1994-05-11 Societe Europeenne De Propulsion Process for the manufacture of a wheel for a turbine with inserted blades and wheel so obtained
FR2697284A1 (en) * 1992-10-27 1994-04-29 Europ Propulsion Method for manufacturing a turbine wheel with inserted blades and wheel obtained by the method.
US5536145A (en) * 1992-10-27 1996-07-16 Societe Europeenne De Propulsion Method of manufacturing a turbine wheel having inserted blades, and a wheel obtained by performing the method
WO2010043666A1 (en) * 2008-10-16 2010-04-22 Siemens Aktiengesellschaft Axial turbomachine comprising a rotor blade ring and a damping device
DE102009010502A1 (en) * 2009-02-25 2010-09-09 Siemens Aktiengesellschaft Airfoil for blade of e.g. steam turbine, has lugs provided at side, which is turned towards rotation axis of turbine blade, of wall for placing damper wire, where lugs are directed to longitudinal axis of blade eye
DE102009010502B4 (en) * 2009-02-25 2012-08-23 Siemens Aktiengesellschaft Turbine blade, turbine blade and turbine
US20110194939A1 (en) * 2010-02-05 2011-08-11 Marra John J Snubber Assembly for Turbine Blades
US8523525B2 (en) * 2010-02-05 2013-09-03 Siemens Energy, Inc. Snubber assembly for turbine blades
US20110274549A1 (en) * 2010-05-06 2011-11-10 General Electric Company Blade having asymmetrical mid-span structure portions and related bladed wheel structure
US10385702B2 (en) * 2015-06-30 2019-08-20 Napier Turbochargers Ltd Turbomachinery rotor blade
US20240035384A1 (en) * 2022-07-27 2024-02-01 General Electric Company Nested damper pin and vibration dampening system for turbine nozzle or blade
US11976565B2 (en) * 2022-07-27 2024-05-07 Ge Infrastructure Technology Llc Nested damper pin and vibration dampening system for turbine nozzle or blade

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