US3737250A - Fiber blade attachment - Google Patents

Fiber blade attachment Download PDF

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Publication number
US3737250A
US3737250A US3737250DA US3737250A US 3737250 A US3737250 A US 3737250A US 3737250D A US3737250D A US 3737250DA US 3737250 A US3737250 A US 3737250A
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Prior art keywords
blade
cavity
fiber
root
fitting
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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
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W Pilpel
S Torell
C Spaeth
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US Secretary of Navy
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US Secretary of Navy
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30Fixing blades to rotors; Blade roots ; Blade spacers
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12Blades
    • F01D5/28Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282Selecting composite materials, e.g. blades with reinforcing filaments
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/60Efficient propulsion technologies
    • Y02T50/67Relevant aircraft propulsion technologies
    • Y02T50/671Measures to reduce the propulsor weight
    • Y02T50/672Measures to reduce the propulsor weight using composites

Abstract

A fiber composite compressor blade having spanwise fiber elements cast within an appropriate composite material wherein at the root end of the blade the fiber elements are looped over transverse pins extending across a hollow root fitting. The root fitting is generally formed to dovetail into peripheral slots extending across a compressor disc. The exterior of each blade is enclosed by layers of crossply fiber cloth and the cavity within the root fitting is filled with an appropriate potting compound to respectively provide strength and rigidity to the blade.

Description

United States Patent Pllpel et al. 1 June 5, 1973 54] FIBER BLADE ATTACHMENT 2,919,889 1/1960 Rube] ..416/230 x 2,929,755 3/1960 Porter ..416/230 x [75] Inventors. Walter Pilpel, West Hartford;

Spencer Tore, New Britain; 3,487,879 1/1970 McCarthy et a1. ..416/220 ux g p Manchester, all FOREIGN PATENTS 0R APPLICATIONS 0 01111.

787,500 12/1957 Great Britain ..416/230 The United States of America as represented by the Secretary of the Navy, Washington, D.C.

Filed: June 16, 1971 Appl. No.: 153,720

Assignee:

US. Cl. ..4l6/219, 416/230, 416/241, 416/248 Int. Cl ..F0ld 5/30 Field of Search ..416/220, 230, 249, 416/248, 215, 219, 241 A References Cited UNITED STATES PATENTS 11/1958 Warnken ..416/230 X 1/1959 Hampshire et a1. ..4l6/230 Primary Examiner-Everette A. Powell, Jr. Attorney- R. S. Sciascia and Henry Hansen A fiber composite compressor blade having spanwise fiber elements cast within an appropriate composite material wherein at the root end of the blade the fiber elements are looped over transverse pins extending across a hollow root fitting. The root fitting is generally formed to dovetail into peripheral slots extending across a compressor disc. The exterior of each blade is enclosed by layers of crossply fiber cloth and the cavity within the root fitting is filled with an appropriate potting compound to respectively provide strength and rigidity to the blade.

ABSTRACT 4 Claims, 4 Drawing Figures 17/] saw/1,1,

FIBER BLADE ATTACHMENT STATEMENT OF GOVERNMENT INTEREST The invention described herein may be manufactured and used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.

BACKGROUND OF THE INVENTION The present invention relates to turbine apparatus, and more particularly, to replaceable turbine blades constructed of fiber composite material.

In the field of turbine powerplants and particularly in turbine powerplants adapted to aircraft use, one of the most critical design items is the turbine blade. Considerations of powerplant cycle efficiency and weight usually require high blade tip speeds with resulting high centrifugal forces tending to separate the blade away from the retaining fixture or blade carrying disc. Accordingly there is a constant search in this art to obtain blade structures which are relatively strong in tension as compared to their weight or cross section. Generally one technique of constructing high strength blades of an axial turbine or compressor is to construct the blades using fiber composite materials. In order to utilize to best advantage the characteristically high tensile properties of the fibers the fibers are laid spanwise along the blade. In this manner high rotational blade speeds can be attained with a relatively low blade mass and cross section. At the root end the fibers of each blade are retained in a dovetailed fitting shaped to conform to a corresponding broached slot formed in the periphery of a blade carrying disc, such that the individual blades together with the root fittings are replaceable. Thus the root ends of the fibers are attached to a fitting which in turn attaches to the disc and the root attachment of the fibers becomes the limiting consideration of fiber composite blades. Typically in the prior art the centrifugal load transferred through the fibers is collected at the root fitting by various squeezing and wedging combinations such that the load is carried from the fibers to the fitting in shear. It is one of the well-known properties of fiber composites that they usually exhibit relatively low shear stress allowables as compared to their particular tensile stress allowables, thus the prior art techniques of blade root attachment result in critical limitations on blade manufacture and maximum blade rotational speed.

SUMMARY OF THE INVENTION Accordingly it is the general purpose and object of the present invention to provide a root attachment technique for attaching fiber composite blades wherein the tensile properties of the fibers are used to best advantage. Other objects of the invention are to provide a blade root attachment means which will conveniently accommodate various blade profiles, as well as blade root attachment means which are easily assembled.

These and other objects are accomplished according to the present invention by providing mounting pins extending across a cavity formed in a blade root fitting around which fibers are looped extending outwardly therefrom along the span of the blade. The blade root fitting is generally shaped on the exterior surfaces thereof to conform with the convolutions of a corresponding broached slot fabricated in the periphery of a blade disc and when in position the lateral motion of the pins is restrained by the slot. The spanwise fibers are looped in bundles around the respective pins, positioned laterally along the pin in conformance with the profile of the blade, thus within the limits of the root fitting cavity various blade profiles can be accommodated. The respective fibers arranged according to the profile of the blade are then potted in place by appropriate potting compound and the blade is formed by surrounding the fibers with the composite material. A crossply woven fiber cloth covers the exterior of the blade to further strengthen the blade and to prevent fiber separation or fraying.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1. shows in plan view a compressor disc assembly having blades constructed according to the invention mounted on the periphery thereof;

FIG. 2 is a fragmentary view shown in partial cross section along line 22 of FIG. 1 of one blade constructed according to the present invention;

FIG. 3 is a cross section view of the blade drawn along lines 33 of FIG. 2; and

FIG. 4 is a cross section view taken along line 4-4 of FIG. 2 of a blade root fitting constructed according to the present invention.

DESCRIPTION OF THE PREFERRED EMBODIMENT The present invention provides a technique of root attachment of fiber composite blades specifically directed at the transmission of tensile stress from the composite structure to the attachment fixture. It is particularly useful in applications where the tensile properties of fiber composite structures are found advantageous, such as, attachment of composite helicopter rotor blades or,as shown specifically in this embodiment, attachment of compressor blades in turbine machinery.

Referring to FIG. 1 a compressor disc assembly 10 is shown comprising a plurality of replaceable blades 11 each blade terminating in a dovetailed root fitting 13. Each root fitting 13 is shown inserted into respective broached slots 14 formed across a peripheral flange of a disc 12. Each blade 11 extends radially away from the disc 12 and during rotation of assembly 10 is pulled outwardly by the centrifugal force. Accordingly the major component force is in tension transmitted through fitting 13 to the convolutions of slot 14 to the peripheral flange of disc 12. I

As shown in more detail in FIG. 2 blade 11 is formed of a composite material comprising fiber elements 20, such as glass fibers impregnated in a suitable thermosetting resin, extending generally along a spanwise direction of the blade. The root end of the blade extends into a cavity 21 formed in fitting 13 wherein fitting 13 is generally similar in shape to a flowerbox or a bathtub. A plurality of pins 25 extend through corresponding openings 26 across and between the lateral sides of the root fitting 13 extending across the cavity 21 proximate the bottom surface thereof, in a plane generally orthogonal to the longitudinal axis of blade 11. Fiber elements 20, separated into bundles, are looped around the respective pins 25 extending radially outward therefrom generally along the platform of the blade 11. A corresponding number of ribs 28 are shown adjacent and parallel to the pins 25 extending between the lateral sides of fitting l3 inside cavity 21 proximate the upper opening thereof. Ribs 28 areprovided for the purpose of separating the fiber bundles thereby facili rating the assembly thereof and the installation of pins 25. Once disposed in their respective positions fibers 20 are surrounded by an appropriate composite material 45, such as potting compound or resin, generally formed or cast to conform to the dimensions of the blade. The exterior of blade 11 thus formed is then wrapped with one or more layers of crossply fiber cloth 30 which strengthens the blade laterally to reduce possibility of fraying. Cavity 21 is also filled with a composite material 45 such as resin or potting compound providing a relatively rigid attachment of the fiber elements 20 to fitting l3 and securing the root edge of cloth 30.

Referring to FIGS. 3 and 4 the fiber elements 20 are looped in bundles over the open sections of pins 25 generally filling the thickness of the blade 11, the individual bundles of fiber elements 20 being displaceable along pins 25, within cavity 21, such that they generally can be arranged to conform to any root profile section of blade 11. This particular feature allows for convenient assembly of various blade profiles which is particularly significant during the development stages of assembly for any specific application. The individual bundles are affixed in their respective location by the potting compound allowing for the positioning of the fiber elements in the best location for efficient tensile load transfer within the cross section of blade 11.

Some of the many advantages of the present invention should now be readily apparent. The invention provides a convenient attachment configuration for a composite blade which is typically critical in tensile load transfer at the root end thereof. The invention also provides convenient freedom of fiber deployment such that many blade profiles can be easily accommodated within the limits of a standardized root fitting. This the invention accomplishes without any trade-off in reduced structural simplicity and convenience in blade replacement.

Obviously many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.

What is claimed is:

1. A fibercomposite blade for a rotor disc having slots of dovetail shape, comprising:

a root fitting having cross sections of outer dovetail shape uniform between the ends of said fitting and corresponding to the shape of the disc slots for contiguous and slidable insertion therein, the cross sections being transverse to the direction of insertion, a radially outwardly communicating cavity, and pin attachment means extending across said cavity transverse to the direction of root fitting insertion fiber elements looped around said pin attachment means the free ends thereof extending outwardly from said cavity; and a composite material interstitially surrounding said fiber elements, filling said cavity, and formed into a blade configuraton radially extending from said cavity. 2. A fiber composite blade according to claim 1, further comprising:

said root fitting including a plurality of pairs of coaxial openings on opposite sides of the cavity, the axes of said openings being normal to the direction of insertion; said pin attachment means including pins inserted at either end into said openings; said fiber elements being grouped in bundles, each being looped around respective ones of said pins within said cavity. 3. A fiber composite blade according to claim 2, further comprising:

said root fitting including transverse ribs extending across the opening of said cavity adjacent and parallel to said pins. 4. A fiber composite blade according to claim 3, further comprising:

one or more layers of fiber cloth enclosing said composite material, contiguously attached to the exterior surfaces thereof.

Claims (4)

1. A fiber composite blade for a rotor disc having slots of dovetail shape, comprising: a root fitting having cross sections of outer dovetail shape uniform between the ends of said fitting and corresponding to the shape of the disc slots for contiguous and slidable insertion therein, the cross sections being transverse to the direction of insertion, a radially outwardly communicating cavity, and pin attachment means extending across said cavity transverse to the direction of root fitting insertion fiber elements looped around said pin attachment means the free ends thereof extending outwardly from said cavity; and a composite material interstitially surrounding said fiber elements, filling said cavity, and formed into a blade configuraton radially extending from said cavity.
2. A fiber composite blade according to claim 1, further comprising: said root fitting including a plurality of pairs of coaxial openings on opposite sides of the cavity, the axes of said openings being normal to the direction of insertion; said pin attachment means including pins inserted at either end into said openings; said fiber elements being grouped in bundles, each being looped around respective ones of said pins within said cavity.
3. A fiber composite blade according to claim 2, further comprising: said root fitting including transverse ribs extending across the opening of said cavity adjacent and parallel to said pins.
4. A fiber composite blade according to claim 3, further comprising: one or more layers of fiber cloth enclosing said composite material, contiguously attached to the exterior surfaces thereof.
US3737250A 1971-06-16 1971-06-16 Fiber blade attachment Expired - Lifetime US3737250A (en)

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Cited By (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3834832A (en) * 1971-12-21 1974-09-10 Rolls Royce 1971 Ltd Fibre reinforced composite structures
JPS5267405A (en) * 1975-12-03 1977-06-03 Mitsubishi Heavy Ind Ltd Revoluting body
US4031601A (en) * 1975-02-11 1977-06-28 Dayton Scale Model Company Method of fabricating and mounting a fiberglass fan blade
US4037990A (en) * 1976-06-01 1977-07-26 General Electric Company Composite turbomachinery rotor
US4111606A (en) * 1976-12-27 1978-09-05 United Technologies Corporation Composite rotor blade
US4232996A (en) * 1978-10-06 1980-11-11 The United States Of America As Represented By The Secretary Of The Air Force Light weight fan assembly
US4354804A (en) * 1979-11-30 1982-10-19 Williams Research Corporation Composite turbine wheel, method of manufacture and fixture therefor
US4643647A (en) * 1984-12-08 1987-02-17 Rolls-Royce Plc Rotor aerofoil blade containment
EP0284778A2 (en) * 1987-03-28 1988-10-05 Mtu Motoren- Und Turbinen-Union München Gmbh Fan blade, particularly for prop-fan engines
GB2208125A (en) * 1987-06-04 1989-03-01 Mtu Muenchen Gmbh Compressor blade and mounting arrangement
FR2626617A1 (en) * 1988-01-30 1989-08-04 Mtu Muenchen Gmbh blade for a rotor of an engine unit, particularly for commercial aircraft
EP0353672A2 (en) * 1988-08-03 1990-02-07 Mtu Motoren- Und Turbinen-Union München Gmbh Composite propeller blades
US5013216A (en) * 1988-09-09 1991-05-07 Airfoil Textron Inc. Composite blade perform with divergent root
US5018271A (en) * 1988-09-09 1991-05-28 Airfoil Textron Inc. Method of making a composite blade with divergent root
US5049036A (en) * 1988-09-09 1991-09-17 Airfoil Textron Inc Composite blade with divergent root and method for making same
EP0496550A1 (en) * 1991-01-25 1992-07-29 General Electric Company Wide chord fan blade
FR2685732A1 (en) * 1991-12-31 1993-07-02 Snecma Turbomachine blade made of composite material.
DE4203205A1 (en) * 1992-02-05 1993-08-12 Muehlbauer Luftfahrttechn Gmbh Location for propeller blade made of fibre cpd. - has loop rail with bearing shaft extending through propeller blade root with loop rail extending around bearing shaft
US5240377A (en) * 1992-02-25 1993-08-31 Williams International Corporation Composite fan blade
US5340280A (en) * 1991-09-30 1994-08-23 General Electric Company Dovetail attachment for composite blade and method for making
US5464325A (en) * 1993-06-25 1995-11-07 Institut Fuer Luft- Und Kaeltetechnik Gemeinnuetzige Gesellschaft Mbh Turbo-compressor impeller for coolant
WO1997036108A1 (en) * 1996-03-27 1997-10-02 The Scott Fetzer Company Flexible impeller with one-piece hub
US20100014982A1 (en) * 2005-11-21 2010-01-21 Detlef Haje Turbine Blade for a Steam Turbine
US7972113B1 (en) 2007-05-02 2011-07-05 Florida Turbine Technologies, Inc. Integral turbine blade and platform
US20120051924A1 (en) * 2010-08-31 2012-03-01 General Electric Company Turbine Blade Assembly
JP2013510994A (en) * 2009-11-17 2013-03-28 シーメンス アクティエンゲゼルシャフト Turbine blades or compressor blades
GB2498077A (en) * 2011-12-23 2013-07-03 Ratier Figeac Soc Propeller blade with redundant anchoring in a hub
US20130309435A1 (en) * 2012-05-15 2013-11-21 Hexcel Corporation Over-molding of load-bearing composite structures
US9777579B2 (en) 2012-12-10 2017-10-03 General Electric Company Attachment of composite article
US9797257B2 (en) 2012-12-10 2017-10-24 General Electric Company Attachment of composite article
RU2638234C2 (en) * 2012-04-24 2017-12-12 Дженерал Электрик Компани Turbomachine (versions) and gas turbine engine

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB787500A (en) * 1955-05-12 1957-12-11 Rolls Royce Improvements relating to axial flow compressor blading and methods of manufacture thereof
US2859936A (en) * 1954-03-03 1958-11-11 Cincinnati Testing & Res Lab Compressor blade and method of forming same
US2868439A (en) * 1954-05-07 1959-01-13 Goodyear Aircraft Corp Plastic axial-flow compressor for gas turbines
US2919889A (en) * 1955-03-03 1960-01-05 United Aircraft Corp Blade mounting
US2929755A (en) * 1958-07-24 1960-03-22 Orenda Engines Ltd Plastic blades for gas turbine engines
US3487879A (en) * 1967-08-02 1970-01-06 Dowty Rotol Ltd Blades,suitable for propellers,compressors,fans and the like

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2859936A (en) * 1954-03-03 1958-11-11 Cincinnati Testing & Res Lab Compressor blade and method of forming same
US2868439A (en) * 1954-05-07 1959-01-13 Goodyear Aircraft Corp Plastic axial-flow compressor for gas turbines
US2919889A (en) * 1955-03-03 1960-01-05 United Aircraft Corp Blade mounting
GB787500A (en) * 1955-05-12 1957-12-11 Rolls Royce Improvements relating to axial flow compressor blading and methods of manufacture thereof
US2929755A (en) * 1958-07-24 1960-03-22 Orenda Engines Ltd Plastic blades for gas turbine engines
US3487879A (en) * 1967-08-02 1970-01-06 Dowty Rotol Ltd Blades,suitable for propellers,compressors,fans and the like

Cited By (41)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3834832A (en) * 1971-12-21 1974-09-10 Rolls Royce 1971 Ltd Fibre reinforced composite structures
US4031601A (en) * 1975-02-11 1977-06-28 Dayton Scale Model Company Method of fabricating and mounting a fiberglass fan blade
JPS5267405A (en) * 1975-12-03 1977-06-03 Mitsubishi Heavy Ind Ltd Revoluting body
US4037990A (en) * 1976-06-01 1977-07-26 General Electric Company Composite turbomachinery rotor
US4111606A (en) * 1976-12-27 1978-09-05 United Technologies Corporation Composite rotor blade
US4232996A (en) * 1978-10-06 1980-11-11 The United States Of America As Represented By The Secretary Of The Air Force Light weight fan assembly
US4354804A (en) * 1979-11-30 1982-10-19 Williams Research Corporation Composite turbine wheel, method of manufacture and fixture therefor
US4643647A (en) * 1984-12-08 1987-02-17 Rolls-Royce Plc Rotor aerofoil blade containment
EP0284778A3 (en) * 1987-03-28 1989-03-15 Mtu Muenchen Gmbh Fan blade, particularly for prop-fan engines
EP0284778A2 (en) * 1987-03-28 1988-10-05 Mtu Motoren- Und Turbinen-Union München Gmbh Fan blade, particularly for prop-fan engines
GB2208125A (en) * 1987-06-04 1989-03-01 Mtu Muenchen Gmbh Compressor blade and mounting arrangement
US4877376A (en) * 1987-06-04 1989-10-31 Motoren-Und Turbinen-Union Munchen Gmbh Attachment of a rotor blade of fiber reinforced plastic to a metal rotor hub
GB2208125B (en) * 1987-06-04 1992-02-19 Mtu Muenchen Gmbh Mounting a fibre-technology formed rotor blade.
FR2626617A1 (en) * 1988-01-30 1989-08-04 Mtu Muenchen Gmbh blade for a rotor of an engine unit, particularly for commercial aircraft
US4929154A (en) * 1988-01-30 1990-05-29 Mtu Motoren-Und Turbinen-Union Munchen Blade arrangement for a propulsion rotor
EP0353672A2 (en) * 1988-08-03 1990-02-07 Mtu Motoren- Und Turbinen-Union München Gmbh Composite propeller blades
US4966527A (en) * 1988-08-03 1990-10-30 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Composite blade construction for a propeller or rotor blade
EP0353672A3 (en) * 1988-08-03 1990-09-19 Mtu Muenchen Gmbh Composite propeller blades
US5018271A (en) * 1988-09-09 1991-05-28 Airfoil Textron Inc. Method of making a composite blade with divergent root
US5049036A (en) * 1988-09-09 1991-09-17 Airfoil Textron Inc Composite blade with divergent root and method for making same
US5013216A (en) * 1988-09-09 1991-05-07 Airfoil Textron Inc. Composite blade perform with divergent root
EP0496550A1 (en) * 1991-01-25 1992-07-29 General Electric Company Wide chord fan blade
US5340280A (en) * 1991-09-30 1994-08-23 General Electric Company Dovetail attachment for composite blade and method for making
FR2685732A1 (en) * 1991-12-31 1993-07-02 Snecma Turbomachine blade made of composite material.
US5292231A (en) * 1991-12-31 1994-03-08 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Turbomachine blade made of composite material
DE4203205A1 (en) * 1992-02-05 1993-08-12 Muehlbauer Luftfahrttechn Gmbh Location for propeller blade made of fibre cpd. - has loop rail with bearing shaft extending through propeller blade root with loop rail extending around bearing shaft
US5240377A (en) * 1992-02-25 1993-08-31 Williams International Corporation Composite fan blade
WO1993016914A1 (en) * 1992-02-25 1993-09-02 Williams International Corporation Composite fan blade
US5464325A (en) * 1993-06-25 1995-11-07 Institut Fuer Luft- Und Kaeltetechnik Gemeinnuetzige Gesellschaft Mbh Turbo-compressor impeller for coolant
WO1997036108A1 (en) * 1996-03-27 1997-10-02 The Scott Fetzer Company Flexible impeller with one-piece hub
US20100014982A1 (en) * 2005-11-21 2010-01-21 Detlef Haje Turbine Blade for a Steam Turbine
US7972113B1 (en) 2007-05-02 2011-07-05 Florida Turbine Technologies, Inc. Integral turbine blade and platform
JP2013510994A (en) * 2009-11-17 2013-03-28 シーメンス アクティエンゲゼルシャフト Turbine blades or compressor blades
US20120051924A1 (en) * 2010-08-31 2012-03-01 General Electric Company Turbine Blade Assembly
GB2498077A (en) * 2011-12-23 2013-07-03 Ratier Figeac Soc Propeller blade with redundant anchoring in a hub
GB2498077B (en) * 2011-12-23 2018-02-14 Ratier Figeac Soc Blade with redundant anchoring in a hub, propeller, turboprop engine and aircraft
RU2638234C2 (en) * 2012-04-24 2017-12-12 Дженерал Электрик Компани Turbomachine (versions) and gas turbine engine
US20130309435A1 (en) * 2012-05-15 2013-11-21 Hexcel Corporation Over-molding of load-bearing composite structures
US9393745B2 (en) * 2012-05-15 2016-07-19 Hexcel Corporation Over-molding of load-bearing composite structures
US9777579B2 (en) 2012-12-10 2017-10-03 General Electric Company Attachment of composite article
US9797257B2 (en) 2012-12-10 2017-10-24 General Electric Company Attachment of composite article

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