US2920868A - Dampened blade structure - Google Patents

Dampened blade structure Download PDF

Info

Publication number
US2920868A
US2920868A US538576A US53857655A US2920868A US 2920868 A US2920868 A US 2920868A US 538576 A US538576 A US 538576A US 53857655 A US53857655 A US 53857655A US 2920868 A US2920868 A US 2920868A
Authority
US
United States
Prior art keywords
blade
strands
vane
wire
blade structure
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
US538576A
Inventor
Sanford S Ackerman
Taranto Rocco A Di
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
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 Westinghouse Electric Corp filed Critical Westinghouse Electric Corp
Priority to US538576A priority Critical patent/US2920868A/en
Application granted granted Critical
Publication of US2920868A publication Critical patent/US2920868A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • 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
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12375—All metal or with adjacent metals having member which crosses the plane of another member [e.g., T or X cross section, etc.]
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12389—All metal or with adjacent metals having variation in thickness
    • Y10T428/12403—Longitudinally smooth and symmetrical
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12486—Laterally noncoextensive components [e.g., embedded, etc.]

Definitions

  • This invention relates to blading for axial flow elastic fluid machines such as axial fiow compressors and turbines and has for an object to provide a blade having improved operating characteristics.
  • a further object of the invention is to provide a blade of the above type in which blade vibration is minimized.
  • Another object is to provide a damped blade of the above type which is simple to manufacture, does not involve damping components machined to critical dimensions, has a pro-longed useful life, and maintains its damping characteristics in extreme conditions of service for the life of the blade.
  • a more specific object is to provide a blade damping structure which may be readily incorporated in a fabricated blade prior to completion of the blade.
  • a group of fine strands of wire are placed or inserted in the longitudinal opening of a hollow blade.
  • the strands are sufficiently numerous to occupy from about 60% to 80% of the cross-sectional area of the opening (although the above percentages are not critical and may vary) and are disposed at random in intimate side-by-side relation, so that they are in contact with each other and in contact with the walls of the opening.
  • any vibration induced in the blade during operation is transmitted through the walls of the opening to the wire strands which absorb or other wise dissipate the vibrational energy to effectively suppress the vibrational tendencies of the blade.
  • the wire strands preferably extend the full length of the vane portion of the blade and, when employed in a rotor blade, are anchored at the base of the blade by brazing or other desirable fastening means.
  • the wire strands may be made of any suitable metal having good wearing properties and when utilized in turbine blading must be formed of metal capable of withstanding high temperatures without fusing. Applicants have found that stainless steel and copper are highly satisfactory materials, however numerous other materials may be employed with similarly advantageous results.
  • Fig. l is a perspective view of an axial flow compressor rotor blade with a portion cut away from clarity;
  • Fig. 2 is a longitudinal sectional view taken on line IIII of Fig. 1 and looking in the direction of the arrows;
  • Fig. 3 is a cross-sectional view taken on line III-III of Fig. 1 and looking in the direction of the arrows;
  • Fig. 4 is a perspective view of the damping structure removed from the blade.
  • a blade designed for the rotor of an axial flow compressor of the class adapted for use in an aviation gas turbine power plant (not shown).
  • the blade 10 may be of conventional outward form, comprising a vane portion 11 of suitably warped airfoil contour, and an enlarged 2,920,858 Patented Jan. 12, 1960 ice base or root portion 12 which is adapted to be slidably engaged and suitably anchored in a mounting groove of the above mentioned rotor.
  • the blade 10 has an envelope or casing including curved envelope walls 13 and 14 having complementary edges or abutting margins which are adapted to be brazed or otherwise suitably secured together to form leading and trailing edge joints 15 and 16 and an offset tip portion 17 for wearing in purposes.
  • the base or root portion 12 is formed by the central portion of the envelope and is of tubular shape with its central axis extending transversely of the longitudinal axisof the vane portion '11 and having openings at opposite ends.
  • a solid core member 18 having attached thereto, by brazing or the like, a group of fine strands of wire 19 extending therefrom into the cavity 20 provided in the vane portion 11 by the complementary walls 13 and 14.
  • the wire strands 19 are disposed at random and in intimate rubbing or frictional contact with each other and with the inner wall surfaces 13a and 14a of the vane portion 11.
  • the strands of wire preferably extend the full length of the vane portion 11, as best shown in Fig. 2, and may be formed of any suitable metal having good Wearing properties, so that the coefiicient of friction between the strands does not change appreciably with wear, and capable of withstanding temperatures to which the blade is subjected in use.
  • the core member 18 is preferably formed with a longitudinal recess 18a in its periphery and the ends of the strands of Wire 19 are inserted in the recess 18a, and firmly anchored therein by means of brazing or the like to prevent detachment therefrom during rotation of the blade.
  • the blade envelope in a preformed state is then placed around the structure shown in Fig. 4 and brazed at the leading edge 15, the trailing edge 16, and the tip 17. Subsequently thereto or simultaneously therewith the core member 18 is brazed within the base 12, thereby providing a rigid unitary structure of simple yet effective configuration.
  • the diameter of the strands 19 may be selected as desired depending upon the material of the envelope and the proportions of the vane 11. However, in any event the diameter of the strands is of a very small order and the number of strands is of a relatively large order occupying about 60% to of the total cross-sectional area of the cavity 20.
  • any vibration induced in the vane portion 11 is transmitted through the interior wall surfaces 13a and 14a of the vane portion 11 to the wire strands 19 and then transmitted from strand to strand therebyabsorbing or otherwise dissipating the vibrational energy of the envelope and effectively damping the vibrational tendencies of the blade.
  • the invention provides a damped blade of relatively simple design and easy to manufacture, in which the dampening structure is formed of readily available material.
  • the invention provides a dampening structure which is not limited to any specific type of material for attaining the desired dampening and that stainless steel or copper strands may be utilized with equal effectiveness.
  • a fabricated blade for a rotor of an axial flow machine comprising a sheet metal envelope providing a hollow vane portion of air foil shape and a base portion adjacent one end of said vane portion, said base portion being of tubular shape and defining a passage open at both ends, said vane portion having interior wall surfaces defining a longitudinal opening therein communicating with the passage in said base portion, a group of fine strands of wire disposed at random and in closely packed side-byside relation within said vane opening, said group of strands extending lengthwise in said opening and contact- 4 7 ing said interior wall surfaces, means received within said base portion for anchoring said group of strands, said anchoring means comprising an elongated member having a longitudinal recess in its periphery and the terminal portions of said strands being firmly imbedded in said recess.

Description

Jan. 12, 1960 s. s. ACKERMAN ETAL 2,920,868
DAMPENED BLADE STRUCTURE Filed Oct. 5, 1955 INVENTORS SANFORD $.ACKERMAN ROCCO A.Dl TARANTO BY KW) ATTORNEY 2,920,868 DAMPENED BLADE STRUCTURE Sanford S. Ackerman, Swanwyck, Del., and Rocco A.
Di Taranto, Philadelphia, Pa., assignors to Westinghouse Electric Corporation, Pittsburgh, Pa., a crporation of Pennsylvania Application October 5, 1955, Serial No. 538,576
2 Claims. (Cl. 253-77) This invention relates to blading for axial flow elastic fluid machines such as axial fiow compressors and turbines and has for an object to provide a blade having improved operating characteristics.
A further object of the invention is to provide a blade of the above type in which blade vibration is minimized.
Another object is to provide a damped blade of the above type which is simple to manufacture, does not involve damping components machined to critical dimensions, has a pro-longed useful life, and maintains its damping characteristics in extreme conditions of service for the life of the blade.
A more specific object is to provide a blade damping structure which may be readily incorporated in a fabricated blade prior to completion of the blade.
In accordance with the invention, a group of fine strands of wire are placed or inserted in the longitudinal opening of a hollow blade. The strands are sufficiently numerous to occupy from about 60% to 80% of the cross-sectional area of the opening (although the above percentages are not critical and may vary) and are disposed at random in intimate side-by-side relation, so that they are in contact with each other and in contact with the walls of the opening. Hence any vibration induced in the blade during operation is transmitted through the walls of the opening to the wire strands which absorb or other wise dissipate the vibrational energy to effectively suppress the vibrational tendencies of the blade.
The wire strands preferably extend the full length of the vane portion of the blade and, when employed in a rotor blade, are anchored at the base of the blade by brazing or other desirable fastening means. The wire strands may be made of any suitable metal having good wearing properties and when utilized in turbine blading must be formed of metal capable of withstanding high temperatures without fusing. Applicants have found that stainless steel and copper are highly satisfactory materials, however numerous other materials may be employed with similarly advantageous results.
The above and other objects are effected by the invention as will be apparent from the following description taken in connection with the accompanying drawings, forming a part of this application, in which:
Fig. l is a perspective view of an axial flow compressor rotor blade with a portion cut away from clarity;
Fig. 2 is a longitudinal sectional view taken on line IIII of Fig. 1 and looking in the direction of the arrows;
Fig. 3 is a cross-sectional view taken on line III-III of Fig. 1 and looking in the direction of the arrows; and
Fig. 4 is a perspective view of the damping structure removed from the blade.
Referring to Fig. 1 of the drawing, there is illustrated a blade designed for the rotor of an axial flow compressor of the class adapted for use in an aviation gas turbine power plant (not shown). The blade 10 may be of conventional outward form, comprising a vane portion 11 of suitably warped airfoil contour, and an enlarged 2,920,858 Patented Jan. 12, 1960 ice base or root portion 12 which is adapted to be slidably engaged and suitably anchored in a mounting groove of the above mentioned rotor.
According to the invention, as best shown in Figs. 1, 2 and 3, the blade 10 has an envelope or casing including curved envelope walls 13 and 14 having complementary edges or abutting margins which are adapted to be brazed or otherwise suitably secured together to form leading and trailing edge joints 15 and 16 and an offset tip portion 17 for wearing in purposes.
The base or root portion 12 is formed by the central portion of the envelope and is of tubular shape with its central axis extending transversely of the longitudinal axisof the vane portion '11 and having openings at opposite ends. Within the base'portion 12 there is provided a solid core member 18 having attached thereto, by brazing or the like, a group of fine strands of wire 19 extending therefrom into the cavity 20 provided in the vane portion 11 by the complementary walls 13 and 14. The wire strands 19 are disposed at random and in intimate rubbing or frictional contact with each other and with the inner wall surfaces 13a and 14a of the vane portion 11. The strands of wire preferably extend the full length of the vane portion 11, as best shown in Fig. 2, and may be formed of any suitable metal having good Wearing properties, so that the coefiicient of friction between the strands does not change appreciably with wear, and capable of withstanding temperatures to which the blade is subjected in use.
Although the blade 10 may be manufactured in any desirable manner, the core member 18 is preferably formed with a longitudinal recess 18a in its periphery and the ends of the strands of Wire 19 are inserted in the recess 18a, and firmly anchored therein by means of brazing or the like to prevent detachment therefrom during rotation of the blade. The blade envelope in a preformed state is then placed around the structure shown in Fig. 4 and brazed at the leading edge 15, the trailing edge 16, and the tip 17. Subsequently thereto or simultaneously therewith the core member 18 is brazed within the base 12, thereby providing a rigid unitary structure of simple yet effective configuration.
The diameter of the strands 19 may be selected as desired depending upon the material of the envelope and the proportions of the vane 11. However, in any event the diameter of the strands is of a very small order and the number of strands is of a relatively large order occupying about 60% to of the total cross-sectional area of the cavity 20.
In operation, any vibration induced in the vane portion 11 is transmitted through the interior wall surfaces 13a and 14a of the vane portion 11 to the wire strands 19 and then transmitted from strand to strand therebyabsorbing or otherwise dissipating the vibrational energy of the envelope and effectively damping the vibrational tendencies of the blade.
-It will be seen that the invention provides a damped blade of relatively simple design and easy to manufacture, in which the dampening structure is formed of readily available material.
Also, it will be apparent that the invention provides a dampening structure which is not limited to any specific type of material for attaining the desired dampening and that stainless steel or copper strands may be utilized with equal effectiveness.
Although the invention has been described in conjunction with a blade adapted to be mounted on a rotor, it will be understood that the invention is not so limited and may be utilized in conjunction with stationary blades as well. Also, since in stationary blading rotational forces are absent, it will be understood that the strands need not be anchored and other strand materials may be utilized when the invention is applied to stationary blading.
While the invention has been shown in but one form, it will be obvious to those skilled in the art that it is not so limited, but is susceptible of various changes and modifications without departing from the spirit thereof.
What is claimed is:
'1. A fabricated blade for a rotor of an axial flow machine comprising a sheet metal envelope providing a hollow vane portion of air foil shape and a base portion adjacent one end of said vane portion, said base portion being of tubular shape and defining a passage open at both ends, said vane portion having interior wall surfaces defining a longitudinal opening therein communicating with the passage in said base portion, a group of fine strands of wire disposed at random and in closely packed side-byside relation within said vane opening, said group of strands extending lengthwise in said opening and contact- 4 7 ing said interior wall surfaces, means received within said base portion for anchoring said group of strands, said anchoring means comprising an elongated member having a longitudinal recess in its periphery and the terminal portions of said strands being firmly imbedded in said recess. 1
2. The structure recited in claim 1 in which the group of strands extends substantially to the tip portion of the vane.
References Cited in the file of this patent UNITED STATES PATENTS France May 12, 1954
US538576A 1955-10-05 1955-10-05 Dampened blade structure Expired - Lifetime US2920868A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US538576A US2920868A (en) 1955-10-05 1955-10-05 Dampened blade structure

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US538576A US2920868A (en) 1955-10-05 1955-10-05 Dampened blade structure

Publications (1)

Publication Number Publication Date
US2920868A true US2920868A (en) 1960-01-12

Family

ID=24147485

Family Applications (1)

Application Number Title Priority Date Filing Date
US538576A Expired - Lifetime US2920868A (en) 1955-10-05 1955-10-05 Dampened blade structure

Country Status (1)

Country Link
US (1) US2920868A (en)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3368795A (en) * 1967-07-12 1968-02-13 Gen Motors Corp Composite rotor blade having high modal frequencies
US3572971A (en) * 1969-09-29 1971-03-30 Gen Electric Lightweight turbo-machinery blading
US4884948A (en) * 1987-03-28 1989-12-05 Mtu Motoren-Und Turbinen Union Munchen Gmbh Deflectable blade assembly for a prop-jet engine and associated method
US5165860A (en) * 1991-05-20 1992-11-24 United Technologies Corporation Damped airfoil blade
US20070007260A1 (en) * 2003-08-18 2007-01-11 Erich Steinhardt Method for the production and/or repair of structural components for gas turbines
US20070041842A1 (en) * 2005-08-04 2007-02-22 Thompson Ewan F Aerofoil
US7413405B2 (en) 2005-06-14 2008-08-19 General Electric Company Bipedal damper turbine blade
US20080253898A1 (en) * 2007-04-10 2008-10-16 Randall Charles Bauer Damper configured turbine blade
US20080313899A1 (en) * 2007-06-25 2008-12-25 Randall Charles Bauer Bimaterial turbine blade damper
US20100028133A1 (en) * 2008-07-30 2010-02-04 General Electric Company Turbomachine component damping structure and method of damping vibration of a turbomachine component
US20140348657A1 (en) * 2013-05-23 2014-11-27 MTU Aero Engines AG Turbomachine blade
EP3034783A1 (en) * 2014-12-17 2016-06-22 Rolls-Royce Deutschland Ltd & Co KG A blade arrangement of a jet engine or an aircraft propeller and corresponding engine
EP2466072A3 (en) * 2010-12-16 2016-12-21 Howden Axial Fans AB Axial air movement fans
US9840916B2 (en) 2013-05-23 2017-12-12 MTU Aero Engines AG Turbomachine blade
US20180216469A1 (en) * 2017-01-31 2018-08-02 General Electric Company Turbomachine Rotor Blade

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2689107A (en) * 1949-08-13 1954-09-14 United Aircraft Corp Vibration damper for blades and vanes
FR1078510A (en) * 1952-03-19 1954-11-18 Rolls Royce Improvements to turbine blades
GB722341A (en) * 1952-03-19 1955-01-26 Rolls Royce Improvements relating to turbine blades

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2689107A (en) * 1949-08-13 1954-09-14 United Aircraft Corp Vibration damper for blades and vanes
FR1078510A (en) * 1952-03-19 1954-11-18 Rolls Royce Improvements to turbine blades
GB722341A (en) * 1952-03-19 1955-01-26 Rolls Royce Improvements relating to turbine blades

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3368795A (en) * 1967-07-12 1968-02-13 Gen Motors Corp Composite rotor blade having high modal frequencies
US3572971A (en) * 1969-09-29 1971-03-30 Gen Electric Lightweight turbo-machinery blading
US4884948A (en) * 1987-03-28 1989-12-05 Mtu Motoren-Und Turbinen Union Munchen Gmbh Deflectable blade assembly for a prop-jet engine and associated method
US5165860A (en) * 1991-05-20 1992-11-24 United Technologies Corporation Damped airfoil blade
US20070007260A1 (en) * 2003-08-18 2007-01-11 Erich Steinhardt Method for the production and/or repair of structural components for gas turbines
US7984547B2 (en) * 2003-08-18 2011-07-26 Mtu Aero Engines Gmbh Method for manufacturing and/or repairing components for gas turbines
US7413405B2 (en) 2005-06-14 2008-08-19 General Electric Company Bipedal damper turbine blade
US20070041842A1 (en) * 2005-08-04 2007-02-22 Thompson Ewan F Aerofoil
US7794197B2 (en) * 2005-08-04 2010-09-14 Rolls-Royce Plc Aerofoil blades with improved impact resistance
US7736124B2 (en) 2007-04-10 2010-06-15 General Electric Company Damper configured turbine blade
US20080253898A1 (en) * 2007-04-10 2008-10-16 Randall Charles Bauer Damper configured turbine blade
US20080313899A1 (en) * 2007-06-25 2008-12-25 Randall Charles Bauer Bimaterial turbine blade damper
US7824158B2 (en) 2007-06-25 2010-11-02 General Electric Company Bimaterial turbine blade damper
US20100028133A1 (en) * 2008-07-30 2010-02-04 General Electric Company Turbomachine component damping structure and method of damping vibration of a turbomachine component
EP2466072A3 (en) * 2010-12-16 2016-12-21 Howden Axial Fans AB Axial air movement fans
US20140348657A1 (en) * 2013-05-23 2014-11-27 MTU Aero Engines AG Turbomachine blade
US9765625B2 (en) * 2013-05-23 2017-09-19 MTU Aero Engines AG Turbomachine blade
US9840916B2 (en) 2013-05-23 2017-12-12 MTU Aero Engines AG Turbomachine blade
EP3034783A1 (en) * 2014-12-17 2016-06-22 Rolls-Royce Deutschland Ltd & Co KG A blade arrangement of a jet engine or an aircraft propeller and corresponding engine
US10012105B2 (en) 2014-12-17 2018-07-03 Rolls-Royce Deutschland Ltd & Co Kg Blade arrangement of a jet engine or an aircraft propeller
US20180216469A1 (en) * 2017-01-31 2018-08-02 General Electric Company Turbomachine Rotor Blade
US10577940B2 (en) * 2017-01-31 2020-03-03 General Electric Company Turbomachine rotor blade

Similar Documents

Publication Publication Date Title
US2920868A (en) Dampened blade structure
US2873944A (en) Turbine blade cooling
US3126149A (en) Foamed aluminum honeycomb motor
JP6124787B2 (en) Lightweight shroud for rotor blades
EP1602801B1 (en) Rotor blade with a stick damper
US2412615A (en) Bladed machine element
US3973874A (en) Impingement baffle collars
US3304056A (en) Turbine blades
US2742224A (en) Compressor casing lining
US3420502A (en) Fluid-cooled airfoil
US2479057A (en) Turbine rotor
US8596980B2 (en) Vibration damper assembly
US2942843A (en) Blade vibration damping structure
NO161818B (en) VOLTAGE-REDUCING SLEEVAL TIE CONNECTION.
US20130052032A1 (en) Vibration damper comprising a strip and jackets between outer platforms of adjacent composite-material blades of a turbine engine rotor wheel
JP2015531444A (en) Friction resistant fan case
US2957675A (en) Damping means
US3027138A (en) Turbine blades
US2394124A (en) Bladed body
US2463340A (en) Axial flow turbine blade structure
EP1985805B1 (en) Rotary machine
US2771267A (en) Lacing for compressor blades
US2833463A (en) Stator construction for axial flow compressor
US7967565B1 (en) Low cooling flow turbine blade
US2198784A (en) Turbine blade vibration damper