US20140010662A1 - Composite airfoil with integral platform - Google Patents

Composite airfoil with integral platform Download PDF

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Publication number
US20140010662A1
US20140010662A1 US13/540,872 US201213540872A US2014010662A1 US 20140010662 A1 US20140010662 A1 US 20140010662A1 US 201213540872 A US201213540872 A US 201213540872A US 2014010662 A1 US2014010662 A1 US 2014010662A1
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US
United States
Prior art keywords
plies
overwrap
ply
airfoil
platform
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.)
Abandoned
Application number
US13/540,872
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English (en)
Inventor
Shelton O. Duelm
Erica L. Prevost
Conway Chuong
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies 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 United Technologies Corp filed Critical United Technologies Corp
Priority to US13/540,872 priority Critical patent/US20140010662A1/en
Priority to EP13840016.3A priority patent/EP2870065A4/de
Priority to PCT/US2013/049070 priority patent/WO2014046764A2/en
Publication of US20140010662A1 publication Critical patent/US20140010662A1/en
Abandoned legal-status Critical Current

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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
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/302—Details of the edges of fibre composites, e.g. edge finishing or means to avoid delamination
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/0025—Producing blades or the like, e.g. blades for turbines, propellers, or wings
    • 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
    • F01D5/14—Form or construction
    • 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
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/08—Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
    • B29L2031/082—Blades, e.g. for helicopters
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction
    • 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
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49332—Propeller making

Definitions

  • Blades and vanes in a gas turbine engine typically require platform features to establish continuity of flowpath.
  • these platforms are required to be structural, load bearing features as they transfer aerodynamic loads from the component to the engine static structure.
  • a method of forming an airfoil with an integrated platform includes: a) providing an airfoil core; b) wrapping a first overwrap ply around the airfoil core; c) darting a first end of the first overwrap ply to allow the overwrap ply to extend at an angle to the airfoil core to form a first platform; d) filling the darted parts of the first overwrap ply with one or more filler plies; e) wrapping a second overwrap ply around the first overwrap ply; f) darting a first end of the second overwrap ply to allow the second overwrap ply to extend adjacent to the first overwrap ply to form the first platform; g) filling the darted parts of the second overwrap ply with one or more filler plies; and h) placing a cap ply in the shape of the platform adjacent to at least one of the first and second overwrap plies.
  • An airfoil with an integrated platform includes an airfoil core with a leading edge and a trailing edge; a plurality of overwrap plies extending along the exterior of the airfoil core and extending at an angle to the airfoil core to form a first platform on a first end of the airfoil, wherein the overwrap plies are split in the first platform area to form at least one of a v-dart and a slit dart; one or more filler plies shaped to fit any v-darts in the overwrap plies; and a plurality of cap plies connecting adjacent to darted overwrap plies in the first platform.
  • FIG. 1A is a perspective view of an airfoil with integrated platforms.
  • FIG. 1B is a cross-sectional view of FIG. 1A through the airfoil.
  • FIG. 1C is an exploded view of the airfoil with integrated platforms of FIG. 1A .
  • FIG. 1D is a bottom view of an overwrap ply used in the airfoil of FIG. 1A .
  • FIG. 2 is a method of forming the airfoil of FIG. 1A .
  • FIG. 1A is a perspective view of airfoil 10 with integrated platforms 12 , 14 and FIG. 1B is a cross sectional view of airfoil 10 .
  • FIG. 1C is an exploded view of airfoil 10 showing one overwrap ply 26 and two cap plies 28 and
  • FIG. 1D is a bottom view of an overwrap ply 26 .
  • Airfoil 10 includes airfoil body 11 , first platform 12 at first end 13 , second platform 14 at second end 15 , hollow core 16 , internal plies 18 , filler 20 , leading edge 22 , trailing edge 24 , overwrap plies 26 , cap plies 28 , filler plies 30 and darts 32 , 34 .
  • airfoil 10 is hollow and core 16 of airfoil 10 includes internal plies 18 to form the basic airfoil hollow pressure vessel and filler 20 to fill the portion of airfoil 10 that has a radius smaller than the fibers of internal plies 18 can form without breaking while maintaining the aerodynamic trailing edge shape 24 .
  • Filler 20 can be laminated composite plies stacked vertically, monolithic ceramic inserts, continuous fiber tow oriented in specific directions, chopped composite fibers, or other options that can hold the shape of airfoil 10 and provide sharp edges desired for aerodynamic properties.
  • Airfoil 10 can be used as a static airfoil in various gas turbine engine parts, for example, the mid-turbine frame.
  • Overwrap plies 26 and internal plies 18 can be two-dimensional fiber architectures. Elongated fibers extend through plies 18 , 26 at specified orientations and give plies 18 and 26 strength. Plies 18 and 26 can vary in size, shape and fiber orientation. Plies 18 and 26 can comprise a woven fabric or a unidirectional material.
  • the fabric may be a plain weave, five harness stain (5HS) weave, 8 harness satin (8HS) weave, or any other common woven fiber architecture. During lay-up, these fabrics may be oriented at any desired angle.
  • the plies, whether fabric or unidirectional may be woven from a variety of fibers, including, but not limited to, carbon, glass, aramid and ceramic.
  • Plies 18 and 26 can vary in shape and size.
  • the design or ply layup of plies 18 and 26 can be controlled to manage the locations of specific materials and to manage the locations of the edges of plies 18 , 26 and darts 32 , 34 .
  • a ply drop is formed at the edge of each ply 18 or 26 .
  • Ply drops can provide initiation sites for damage and cracks.
  • the weakest region for laminated composites is often the interlaminar region between plies. High interlaminar stress, such as that caused by operational loads and foreign object strikes, can cause ply delamination that compromises the structural integrity of the structure.
  • Cap plies 28 can be the same material as internal plies 18 or overwrap plies 26 or can be different depending on airfoil 10 requirements.
  • Airfoil 10 with integrated platforms 12 , 14 is formed by wrapping a plurality of overwrap plies 26 over core 16 and forming platforms 12 , 14 with overwrap plies 26 and ply caps 28 .
  • a first overwrap ply 26 is wrapped around core 16 .
  • Overwrap ply 26 is then cut, in the case of a fabric, or separated in the case of a unidirectional material, to form darts 32 , 34 , allowing it to extend at an angle, for example, perpendicularly, from airfoil body 11 at first end 13 and second end 15 .
  • Darts can be v-darts 32 or slit darts 34 .
  • V-darts 32 are necessary at locations of convex curvature around the perimeter of the airfoil, forcing a cut or separation of tows to allow overwrap ply 26 to extend at an angle from airfoil body 11 .
  • V-darts 32 can then be filled with filler plies 30 cut to the shape of v-darts 32 .
  • Slit darts 34 are required at locations of concave curvature around the perimeter of the airfoil, necessitating that material be removed to allow the ply to cover the desired area without overlapping itself.
  • Another overwrap ply 26 is then wrapped around first overwrap ply 26 and darted to lay adjacent to first overwrap ply 26 on airfoil body 11 and platforms 12 and 14 .
  • Airfoil 10 can be made of a plurality of overwrap plies 26 , for example ten, intermixed with cap plies 28 in platforms 12 , 14 .
  • Cap plies 28 are cut in the shape of platforms 12 , 14 to sit adjacent to one or more overwrap plies 26 in platforms 12 , 14 to provide a continuous reinforcement layer in platforms 12 , 14 .
  • Cap plies 28 can be placed, for example, between every two or three overwrap plies 26 .
  • Cap plies 28 can also be placed on the gas flow path side of airfoil 10 to give a smooth air flow surface.
  • Darts 32 , 34 allow overwrap plies 26 to lay flat and not wrinkle or bunch when extending perpendicularly from airfoil body 11 .
  • Filler plies 30 are inserted to fill in v-darts 32 , and cap plies 28 are used to further reinforce platforms 12 , 14 .
  • FIG. 2 shows method 40 of forming airfoil 10 of FIG. 1A .
  • Method 40 includes the steps of providing an airfoil core (step 42 ), providing a cap ply for each end of the airfoil (step 44 ), wrapping a first overwrap ply around the airfoil core (step 46 ), cutting or separating the ends of the first overwrap ply to form darts which allow the ply to extend at an angle to the airfoil core at first and second ends (step 48 ), cutting filler plies to match v-darts (step 50 ), inserting the cut filler plies into the v-darts (step 52 ), wrapping a second overwrap ply around the first overwrap ply (step 54 ), cutting or separating the ends of the second overwrap ply to form darts which allow the ply to extend adjacent to the first overwrap ply at the platforms (step 56 ), cutting filler plies to match the v-dart
  • Airfoil core 16 can vary in shape, size and properties, but generally must form at least a portion of airfoil for overwrap plies 26 to connect around.
  • Providing a cap ply for each end of the airfoil involves obtaining two cap plies 28 , one in the shape of first platform 12 and one in the shape of second platform 14 . These will act as the airflow surface plies for platforms 12 , 14 , giving a smooth airflow surface for greater aerodynamic properties.
  • Cap plies can be made or cut from the same material as overwrap plies, or can be different materials depending on airfoil 10 requirements.
  • Wrapping a first overwrap ply 26 around airfoil core can involve using a wet lay-up, a prepregged material or a tackifier on overwrap ply 26 to allow it to stick to the core when wrapping.
  • the tackifier is compatible with the matrix material used in composite airfoil 10 .
  • Cutting or separating the ends of first overwrap ply 26 to form darts 32 , 34 , allowing ply to extend at an angle to first and second ends 13 , 15 adjacent to cap plies 28 can be done using any cutting tool that works with the material of overwrap ply 26 .
  • the large radius of curvature of airfoil 10 produces wrinkling of the fabric as it is extended at an angle to airfoil body 11 to form platforms 12 , 14 .
  • slit darts 34 are cut to remove fabric from overwrap ply 26 .
  • v-darts 32 are cut.
  • Filler plies 30 are then cut to match the shapes of v-darts 32 (step 50 ) and inserted into v-darts 32 to form a flat surface on platforms 12 , 14 (step 52 ).
  • Another overwrap ply 26 is then wrapped around first overwrap ply (step 54 ), the ends of the second overwrap ply are cut or separated (in the same manner as first overwrap ply 26 ) to form darts allowing the second overwrap ply to extend adjacent to the first overwrap ply at platforms (step 56 ).
  • Darts 32 , 34 between adjacent overwrap plies 26 are staggered to avoid weak fault lines, which could lead to weaker overall platform 12 , 14 .
  • Filler plies 30 are then cut to match v-darts in second overwrap ply (step 60 ), as discussed in relation to first overwrap ply 26 .
  • Additional plies 18 , 26 , 28 can be connected (step 64 ) to form airfoil 10 in the same manner as in steps 46 through 62 . These steps can be performed any number of times, or may be performed in any order, depending on the desired requirements for airfoil 10 .
  • One example could include an airfoil 10 with five internal pressure vessel plies 18 , five overwrap plies 26 and cap plies 28 between every two platform plies 18 , 26 .
  • the outer edges of each side of platforms 12 , 14 can be covered with cap plies 28 to provide a smooth, continuous outer surface.
  • Alternative embodiments could use cap plies 28 between every overwrap ply 26 , between every three overwrap plies 26 or not at all.
  • Performing additional finishing operations can include curing airfoil 10 , machining airfoil 10 and/or performing controlled high temperature cycles.
  • a Resin Transfer Molding (RTM) process may be used in which internal plies 18 , overwrap plies 26 , cap plies 28 and filler 20 are placed in a mold, injected with resin and cured.
  • Example resins include but are not limited to epoxy resins and epoxy resins containing an additive, such as rubber.
  • airfoil plies 18 , 26 , 28 can be pre-impregnated composites, (i.e. “prepregs”) such that resin is not directly added to the mold.
  • a pre-ceramic polymer is used as that matrix material.
  • airfoil 10 Once airfoil 10 is cured, it can be put through high temperature cycles in a controlled environment that convert the pre-ceramic polymer into a ceramic. This conversion causes the volume to change, resulting in a porous material. The part is then put in another bath of the matrix to fill any crack or voids caused by the change of volume, followed by another controlled high temperature cycle. This can be repeated a number of times until airfoil 10 reaches the desired density. Machining can be done at various steps as well.
  • Method 40 allows for the forming of airfoil 10 with integral platforms 12 , thereby providing an airfoil with increased strength and stability for handling and transferring loads.
  • Darts 32 , 34 allow for extending plies to form platforms 12 , 14 integrally and preventing wrinkling of the fabric as plies are extended perpendicularly to airfoil body 11 .
  • Cap plies 28 provide a continuous surface to reinforce platforms 12 , 14 and overall airfoil 10 and can provide a smooth surface for increased aerodynamic performance.
  • airfoil 10 core 16 is shown as a hollow airfoil with internal plies 18 and filler 20
  • core 16 can be made of other materials, such as metal and/or can be solid depending on system requirements.
  • FIGS. 1A-1D show a static airfoil with two platforms, the airfoil could also have only one platform and could be a rotating airfoil or it could have two platforms and multiple airfoils.
  • airfoil platforms 12 , 14 are shown as being made by extending overwrap plies 26 (and using cap plies 28 ), inner plies (if used in airfoil construction) can also be extended and darted in the same manner as overwrap plies 26 to form platforms 12 , 14 .
  • internal plies have been discussed to be constructed from individually wrapped plies with staggered seams
  • internal plies 18 can be constructed by continuously wrapping internal plies around core 16 as many times as needed, reducing the number of overall seams.
  • a method of forming an airfoil with an integrated platform includes: a) providing an airfoil core; b) wrapping a first overwrap ply around the airfoil core; c) darting a first end of the first overwrap ply to allow the overwrap ply to extend at an angle to the airfoil core to form a first platform; d) filling the darted parts of the first overwrap ply with one or more filler plies; e) wrapping a second overwrap ply around the first overwrap ply; f) darting a first end of the second overwrap ply to allow the second overwrap ply to extend adjacent to the first overwrap ply to form the first platform; g) filling the darted parts of the second overwrap ply with one or more filler plies; and h) placing a cap ply in the shape of the platform adjacent to at least one of the first and second overwrap plies.
  • Additional and/or alternative embodiments include: placing a cap ply adjacent to the first overwrap ply to form the surface of the platform flow path; repeating steps (b)-(h) at least one time; darting a second end of the first overwrap ply to allow it to extend at an angle to the airfoil core to form a second platform; filling the darted parts of the second overwrap ply with one or more filler plies; step (f) further comprising darting a second end of the second overwrap ply to allow it to extend at an angle to the airfoil core adjacent to the first ply to form the second platform; step (g) further comprising filling the darted portions of the second end of the second overwrap ply with one or more filler plies; step (h) further comprising placing a second cap ply in the shape of the platform adjacent to the second overwrap ply forming the second platform; repeating steps (b)-(h) at least one time; step (a) further
  • An airfoil with an integrated platform includes an airfoil core with a leading edge and a trailing edge; a plurality of overwrap plies extending along the exterior of the airfoil core and extending at an angle to the airfoil core to form a first platform on a first end of the airfoil, wherein the overwrap plies are cut in the first platform area to form at least one of a v-dart and a slice dart; one or more filler plies shaped to fit any v-darts in the overwrap plies; and a plurality of cap plies connecting adjacent to darted overwrap plies in the first platform.
  • Additional and/or alternative embodiments include a second platform formed by darting the overwrap plies on a second end of the airfoil to include at least one of v-darts and slice darts; the second platform further comprising one or more filler plies to fit into the areas of the v-darts in the second platform; and one or more cap plies to fit adjacent to darted overwrap plies in the second platform; locally staggering the darts; at least one of the cap plies being located between every two darted plies; a cap ply forming the flow path surface on the first platform; and/or the airfoil core being hollow.
  • a method of forming an airfoil includes (a) providing an airfoil core; (b) wrapping internal plies around the airfoil core; (c) inserting filler material; (d) wrapping a first overwrap ply around the internal plies and filler material; (e) darting the first overwrap ply in one or more places at a first end to allow the first overwrap ply to extend at an angle to the airfoil core to form a first platform; (f) inserting one or more first filler plies in any darts formed from darting the first overwrap ply; (g) covering the first overwrap ply with a second overwrap ply; (h) darting the second overwrap ply in one or more places at the first end to allow it to extend at an angle to the airfoil core adjacent to the first overwrap ply on the first platform; (i) inserting one or more second filler plies into any darts formed from darting the second overwrap
  • Additional and/or alternative embodiments include performing steps (d)-(j) a plurality of times; extending internal plies to the first platform; forming a pressure vessel from the internal plies and forming a sharp trailing edge from filler; (i) darting the overwrap ply in one or more places at a second end to allow it to extend at an angle to the airfoil core to form a second platform; (j) inserting one or more third filler plies in any darts formed from darting the first overwrap ply at the second end; (k) darting the second overwrap ply in one or more places at the second end to allow it to extend perpendicular to the airfoil core adjacent to the first overwrap ply on the second platform; (1) inserting one or more fourth filler plies into any darts formed from darting the second overwrap ply at the second end; and (m) attaching a second cover ply in the shape of the second platform adjacent to one or more of the first and second pl

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Composite Materials (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Pharmaceuticals Containing Other Organic And Inorganic Compounds (AREA)
US13/540,872 2012-07-03 2012-07-03 Composite airfoil with integral platform Abandoned US20140010662A1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US13/540,872 US20140010662A1 (en) 2012-07-03 2012-07-03 Composite airfoil with integral platform
EP13840016.3A EP2870065A4 (de) 2012-07-03 2013-07-02 Verbundstofftragfläche mit integrierter plattform
PCT/US2013/049070 WO2014046764A2 (en) 2012-07-03 2013-07-02 Composite airfoil with integral platform

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US13/540,872 US20140010662A1 (en) 2012-07-03 2012-07-03 Composite airfoil with integral platform

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