Composite airfoil assembly

Title: Composite airfoil assembly

Abstract

A composite blade assembly for mounting on a turbine wheel includes a ceramic airfoil and an airfoil platform. The ceramic airfoil is formed with an airfoil portion, a blade shank portion and a blade dovetail tang. The metal platform includes a platform shank and a radially inner platform dovetail. The ceramic airfoil is captured within the metal platform, such that in use, the ceramic airfoil is held within the turbine wheel independent of the metal platform.

Inventors:: Garcia-Crespo, Andres Jose

Issue Date:: 2015-03-03

Research Org.:: General Electric Co., Schenectady, NY (United States)

Sponsoring Org.:: USDOE

OSTI Identifier:: 1171701

Patent Number(s):: 8967974

Application Number:: 13/342,599

Assignee:: General Electric Company (Schenectady, NY)

Patent Classifications (CPCs):: Y - NEW / CROSS SECTIONAL TECHNOLOGIES Y10 - TECHNICAL SUBJECTS COVERED BY FORMER USPC Y10T - TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION

F - MECHANICAL ENGINEERING F05 - INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04 F05D - INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

Show more

Y - NEW / CROSS SECTIONAL TECHNOLOGIES Y10 - TECHNICAL SUBJECTS COVERED BY FORMER USPC Y10T - TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
Y10T29/4932 - Turbomachine making
Y10T29/49321 - Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

F - MECHANICAL ENGINEERING F05 - INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04 F05D - INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
F05D2300/6033 - Ceramic matrix composites [CMC]

F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
F01D5/3007 - {of axial insertion type}

Y - NEW / CROSS SECTIONAL TECHNOLOGIES Y02 - TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE Y02T - CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
Y02T50/60 - Efficient propulsion technologies

F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
F01D5/3084 - {the blades being made of ceramics}
F01D5/147 - {Construction, i.e. structural features, e.g. of weight-saving hollow blades
F01D11/008 - {by spacer elements between the blades, e.g. independent interblade platforms}

Y - NEW / CROSS SECTIONAL TECHNOLOGIES Y10 - TECHNICAL SUBJECTS COVERED BY FORMER USPC Y10T - TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
Y10T29/49337 - Composite blade

F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
F01D5/284 - {Selection of ceramic materials}

Show less

DOE Contract Number:: FC26-05NT42643

Resource Type:: Patent

Resource Relation:: Patent File Date: 2012 Jan 03

Country of Publication:: United States

Language:: English

Subject:: 36 MATERIALS SCIENCE

Citation Formats


                    Garcia-Crespo, Andres Jose. Composite airfoil assembly.  United States: N. p., 2015. 
        Web.

Copy to clipboard


                    Garcia-Crespo, Andres Jose. Composite airfoil assembly.  United States.

Copy to clipboard


                    Garcia-Crespo, Andres Jose. Tue .  
        "Composite airfoil assembly".  United States.  https://www.osti.gov/servlets/purl/1171701.

Copy to clipboard


                    
@article{osti_1171701,

  title        = {Composite airfoil assembly},

  author       = {Garcia-Crespo, Andres Jose},

  abstractNote = {A composite blade assembly for mounting on a turbine wheel includes a ceramic airfoil and an airfoil platform. The ceramic airfoil is formed with an airfoil portion, a blade shank portion and a blade dovetail tang. The metal platform includes a platform shank and a radially inner platform dovetail. The ceramic airfoil is captured within the metal platform, such that in use, the ceramic airfoil is held within the turbine wheel independent of the metal platform.},

  doi          = {},

  journal      = {},
number       = ,

  volume       = ,

  place        = {United States},

  year         = {2015},

  month        = {3}

}

Copy to clipboard

Patent:

View Patent

Save / Share:

Export Metadata

Save to My Library

Works referenced in this record:

Ceramic turbine airfoils with cooled trailing edge blocks
patent, December 2001

Darkins, Jr., Toby G.; Shelton, Monty L.; Doughty, Roger L.
US Patent Document 6,325,593
URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect2=PTO1&Sect2=HITOFF&p=1&u=/netahtml/PTO/search-bool.html&r=1&f=G&l=50&d=PALL&RefSrch=yes&Query=PN/6325593

Similar Records in DOE Patents and OSTI.GOV collections:

Airfoil nozzle and shroud assembly

Patent Shaffer, James E [Maitland, FL]; Norton, Paul F [San Diego, CA]

An airfoil and nozzle assembly including an outer shroud having a plurality of vane members attached to an inner surface and having a cantilevered end. The assembly further includes a inner shroud being formed by a plurality of segments. Each of the segments having a first end and a second end and having a recess positioned in each of the ends. The cantilevered end of the vane member being positioned in the recess. The airfoil and nozzle assembly being made from a material having a lower rate of thermal expansion than that of the components to which the airfoil andmore » nozzle assembly is attached.« less
Full Text Available
Turbine engine airfoil and platform assembly

Patent Campbell, Christian X [Oviedo, FL]; James, Allister W [Chuluota, FL]; Morrison, Jay A [Oviedo, FL]

A turbine airfoil (22A) is formed by a first process using a first material. A platform (30A) is formed by a second process using a second material that may be different from the first material. The platform (30A) is assembled around a shank (23A) of the airfoil. One or more pins (36A) extend from the platform into holes (28) in the shank (23A). The platform may be formed in two portions (32A, 34A) and placed around the shank, enclosing it. The two platform portions may be bonded to each other. Alternately, the platform (30B) may be cast around the shankmore »« less
Full Text Available
Modular turbine airfoil and platform assembly with independent root teeth

Patent Campbell, Christian X; Davies, Daniel O; Eng, Darryl

A turbine airfoil (22E-H) extends from a shank (23E-H). A platform (30E-H) brackets or surrounds a first portion of the shank (23E-H). Opposed teeth (33, 35) extend laterally from the platform (30E-H) to engage respective slots (50) in a disk. Opposed teeth (25, 27) extend laterally from a second portion of the shank (29) that extends below the platform (30E-H) to engage other slots (52) in the disk. Thus the platform (30E-H) and the shank (23E-H) independently support their own centrifugal loads via their respective teeth. The platform may be formed in two portions (32E-H, 34E-H), that are bonded tomore »« less
Full Text Available
Method for controlling coolant flow in airfoil, flow control structure and airfoil incorporating the same

Patent Itzel, Gary Michael; Devine, II, Robert Henry; Chopra, Sanjay; ...

A coolant flow control structure is provided to channel cooling media flow to the fillet region defined at the transition between the wall of a nozzle vane and a wall of a nozzle segment, for cooling the fillet region. In an exemplary embodiment, the flow control structure defines a gap with the fillet region to achieve the required heat transfer coefficients in this region to meet part life requirements.
Full Text Available
Nuclear reactor composite fuel assembly

Patent Burgess, Donn M [Richland, WA]; Marr, Duane R [West Richland, WA]; Cappiello, Michael W [Richland, WA]; ...

A core and composite fuel assembly for a liquid-cooled breeder nuclear reactor including a plurality of elongated coextending driver and breeder fuel elements arranged to form a generally polygonal bundle within a thin-walled duct. The breeder elements are larger in cross section than the driver elements, and each breeder element is laterally bounded by a number of the driver elements. Each driver element further includes structure for spacing the driver elements from adjacent fuel elements and, where adjacent, the thin-walled duct. A core made up of the fuel elements can advantageously include fissile fuel of only one enrichment, while varyingmore »« less
Full Text Available

Similar Records

Title: Composite airfoil assembly

Abstract

Citation Formats

Ceramic turbine airfoils with cooled trailing edge blocks patent, December 2001

Ceramic turbine airfoils with cooled trailing edge blocks
patent, December 2001