US20130287586A1 - Propeller blade with lightweight insert and bulkheads - Google Patents

Propeller blade with lightweight insert and bulkheads Download PDF

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Publication number
US20130287586A1
US20130287586A1 US13/873,711 US201313873711A US2013287586A1 US 20130287586 A1 US20130287586 A1 US 20130287586A1 US 201313873711 A US201313873711 A US 201313873711A US 2013287586 A1 US2013287586 A1 US 2013287586A1
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US
United States
Prior art keywords
insert
propeller blade
component
camber
face
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
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US13/873,711
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English (en)
Inventor
Bruno Seminel
Bruno PETELLAZ
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Ratier Figeac SAS
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Ratier Figeac SAS
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Filing date
Publication date
Application filed by Ratier Figeac SAS filed Critical Ratier Figeac SAS
Publication of US20130287586A1 publication Critical patent/US20130287586A1/en
Assigned to RATIER-FIGEAC SAS reassignment RATIER-FIGEAC SAS ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: PETELLAZ, BRUNO, Seminel, Bruno
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
    • F01D5/28—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
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/16—Blades
    • B64C11/20—Constructional features
    • B64C11/26—Fabricated blades

Definitions

  • the present invention relates to propellers and, in particular, to propeller blades that include a lightweight insert disposed in them.
  • Modem propeller blades typically include root portions which extend into the hub arm of the hub of the propeller system and which are secured to and rotatable relative to the hub arm via a retention assembly.
  • the retention assembly includes one or a plurality of ball bearing assemblies which permit the rotation of the blade in the hub arm for accomplishing pitch change of the blade for altering the speed of the propeller and accordingly, the aircraft.
  • the blades are typically formed by surrounding a foam spar core with a resin impregnated fabric. Leading and trailing edges of the blade are then formed over the fabric and surrounded by, for example, a Kevlar sock. Such blades are light and effective for their intended purposes.
  • a propeller blade that includes a foam core and a structural layer that surrounds at least a portion of the foam core and includes a face side and a camber side is disclosed.
  • the propeller blade of this embodiment also includes an insert disposed in the foam core in operable contact with the face side and the camber side of the structural layer and one or more bulkheads disposed in the form core and oriented normal to the insert.
  • a method of forming a propeller blade includes providing a mold; disposing an insert in the mold; disposing a first bulkhead near an end of the insert and oriented normal to the insert; forming a foam core; and forming a structural layer that surround the foam core and includes a face side and a camber side such that the face side and the camber side are in operable contact with the insert and the bulkheadbrief description of the drawings
  • FIG. 1 is a plan-view of a propeller blade according to one embodiment of the present invention
  • FIG. 2 is a cross-section of the propeller blade shown in FIG. 1 ;
  • FIGS. 3A-3E are side views that illustrate different configurations of an insert that can be provided within the propeller blade shown in FIGS. 1 and 2 ;
  • FIG. 4 is a perspective view of one embodiment of an insert according to the present invention.
  • FIG. 5 is a cross-section of a propeller blade that includes two separate inserts in accordance with one embodiment of the present invention.
  • FIG. 6 is a plan-view of a propeller blade according to another embodiment of the present invention.
  • FIG. 1 a plan view of a propeller blade 100 according to one embodiment of the present invention is illustrated.
  • FIG. 2 is a cross-section of the propeller blade 100 of FIG. 1 taken along line A-A.
  • the blade 100 is formed by first forming a spar 102 .
  • the spar 102 includes a spar foam core 104 surrounded by a structural layer 106 .
  • the core 104 is typically formed of a foam material that is injected into a mold but could also be pre-molded and machined and then inserted into the mold.
  • the mold can include a layer of fiberglass or carbon on the walls thereof to which the foam of the core 104 adheres.
  • the core 104 can be surrounded by a layer of fiberglass or carbon (not shown) in one embodiment but this is not required.
  • the foam that forms the core 104 can be selected from one of: polyurethane (PU), polyisocyanurate, or polymethacrylimide (PMI).
  • an insert 105 can be provided in the mold.
  • the foam of the core 104 is disposed within open spaces defined by the insert 105 .
  • the foam of the core 104 is also disposed in the remainder of the area of the mold not occupied by the insert 105 .
  • the insert 105 can be formed of carbon, fiberglass or any other suitable composite or non-composite material.
  • the structural layer 106 is typically formed of a fabric material (e.g. a braided carbon material) and disposed such that it surrounds the core 104 (and the fiberglass or carbon layer if it is included).
  • the structural layer 106 is impregnated with a resin.
  • the spar 102 is heated to set the resin in the structural layer 106 . It has been discovered that, in some instances, additional structure is required to transfer shear force from the face 107 and camber 109 sides of the blade 100 to prevent foam core 104 cracking.
  • the face 107 and camber 109 sides ( FIG. 2 ) of the spar 102 in general (and the corresponding face and camber sides of the structural layer 106 , in particular) are kept in a fixed relation to one another. As such, the possibility of the core 104 cracking may be reduced.
  • the spar 102 is formed such that a portion of it surrounds a root portion 108 that allows the blade 100 to be connected to a hub (not shown). Rotation of the hub causes the blade 100 to rotate and, consequently, causes the generation of thrust to propel an aircraft. In the following discussion, it shall be assumed that the blade 100 rotates in the clockwise direction.
  • the root portion 108 is sometimes referred to as a “tulip” in the industry and is typically formed of a metal.
  • leading edge foam 112 and trailing edge foam 114 are formed on the leading and trailing edges 115 , 116 respectively of the spar 102 .
  • the leading edge foam 112 , trailing edge foam 114 and the spar 102 can then be encased in an outer layer 118 .
  • the outer layer 118 can be formed of Kevlar and be in the form of a sock that is pulled over the assembly that includes the leading edge foam 112 , trailing edge foam 114 and the spar 102 .
  • the outer layer 118 could be formed in other manners as well.
  • the insert 105 can take on any number of shapes and, as illustrated in FIGS. 1 and 2 can have a length l i a width w i and a depth d i . It shall be understood that depending on the shape and location along length the blade 100 , the values w i and d i will generally vary to conform them to the desired shape of the blade 100 . In one embodiment, the length l i spans a portion of the length of the blade 100 that is within the first half of the length l blade of blade 100 measured from the end 130 of the blade 100 where the root 108 is located. Of course, the length l i of the insert 105 can be any length that is less than the length l blade of the blade 100 .
  • the insert includes a face component 202 and a camber component 204 that generally define the width w i of the insert 105 on the face and camber sides 107 , 109 of the blade 100 .
  • the face component 202 and the camber component 204 are connected by two cross members 206 .
  • the insert 105 can include one or more cross members 206 that connect the face component 202 and the camber component 204 .
  • the face component 202 and the camber component 204 extend beyond the cross members 206 towards both the leading edge foam 112 and the trailing edge foam 114 .
  • either or both the face component 202 and the camber component 204 could extend beyond the cross members 206 towards only one of the leading edge foam 112 and the trailing edge foam 114 or not at all.
  • FIGS. 3A-3E illustrate side views of different embodiments of inserts 105 that could be utilized in accordance with the teachings herein.
  • All of the inserts 105 shown in FIGS. 3A-3E include a face component 202 and the camber component 204 and could be disposed in the blade 100 as illustrated in FIGS. 1 and 2 such that the face component 202 contacts the face side 107 of the structural layer 106 and the camber component 204 contacts the camber side 109 of the structural layer 106 .
  • the names given the inserts 105 described below may be understood if they are rotated 90 degrees but they are shown in the particular manner to maintain consistency with FIG. 2 .
  • FIG. 3A illustrates a c-shaped insert 105 that includes a cross member 206 connecting ends of the face component 202 and the camber component 204 .
  • the cross member 206 of FIG. 3A (as well as any other cross member 206 in any other figure) could be formed as a plurality of substantially co-planar cross-members 206 separated by spaces 402 as is illustrated in FIG. 4 .
  • FIG. 3B illustrates an I-shaped insert 105 that includes a cross member 206 that connects the face component 202 and the camber component 204 at a location that is not at the end of either.
  • the cross member 206 is perpendicular to both the face component 202 and the camber component 204 .
  • the cross member 206 could be disposed at other angles relative to one or both of the face component 202 and the camber component 204 .
  • FIG. 3C illustrates a box-shaped insert 105 that includes two cross members 206 a and 206 b that connect respective ends of the face component 202 and the camber component 204 .
  • the insert 105 illustrated in FIG. 3C is similar to that shown in FIG. 2 except that the face component 202 and the camber component 204 do not extend beyond the cross members 206 .
  • FIG. 3D illustrates a z-shaped insert 105 that includes a cross member 206 that connects opposite ends of the face component 202 and the camber component 204 together.
  • FIG. 3E illustrates an s-shaped insert 105 that includes a curved cross member 206 that connects opposite ends of the face component 202 and the camber component 204 together. It shall be understood that one or both of the face component 202 and the camber component 204 could also be curved.
  • multiple inserts 105 could be provided within a single blade 100 .
  • two c-shaped inserts 105 FIG. 3A oriented in opposing directions and disposed within blade 100 .
  • the inserts 105 have lengths that cross a single vertical plane.
  • the inserts 105 could be offset from one another such that no vertical cross section intersects the length of the both inserts (assuming the blade is oriented as shown in FIG. 1 ).
  • the inserts 105 disclosed herein can reduce the possibility of the spar core 104 from cracking.
  • the inserts 105 disclosed herein can have the effect of preventing one or both of the face side 107 and the camber side 109 bulging outward, reducing the stresses in the blade spar.
  • span wise X, chord wise Y and depth Z directions are defined.
  • all of the inserts 105 have been described have a length and a width.
  • the width is the shortest distance between the face and camber components and extends in the depth Z direction when located in blade 100 and the length extends substantially in the span wise X direction.
  • one or more bulkheads 602 can be disposed at ends of the inserts 105 or even within the insert 105 .
  • the bulkheads 602 can be formed in the same or similar manner to the inserts 105 as described above.
  • the bulkheads 602 have a length that extends in the chord wise Y direction and can have a width that extends from the face to the camber sides in the depth Z direction. That is, the bulkheads 602 can be arranged at an angle at or about 90 degrees relative to the inserts 105 .
  • the blades 100 shown herein could be formed in many manners.
  • the spars could be formed and then have portions removed to allow for the inserts and bulkheads to be inserted.
  • a portion of the spar could be removed and then the remaining portions bonded to the inserts/bulkheads that are placed in the portion of the spar that was removed.
  • the structural layer could be bonded around the combined spar, insert and bulkhead combination.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Composite Materials (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Moulding By Coating Moulds (AREA)
  • Laminated Bodies (AREA)
US13/873,711 2012-04-30 2013-04-30 Propeller blade with lightweight insert and bulkheads Abandoned US20130287586A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP12305484.3A EP2660143B1 (fr) 2012-04-30 2012-04-30 Pale d'hélice avec insert léger et cloisons
EP12305484.3 2012-04-30

Publications (1)

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US20130287586A1 true US20130287586A1 (en) 2013-10-31

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US13/873,711 Abandoned US20130287586A1 (en) 2012-04-30 2013-04-30 Propeller blade with lightweight insert and bulkheads

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EP (1) EP2660143B1 (fr)

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4022546A (en) * 1974-01-03 1977-05-10 Textron, Inc. Helicopter rotor blade
US4329119A (en) * 1977-08-02 1982-05-11 The Boeing Company Rotor blade internal damper
US4639284A (en) * 1983-03-18 1987-01-27 Societe Nationale Industrielle Aerospatiale Process for manufacturing a variable pitch multi-blade propeller by molding resin-impregnated fails around a preform
US5222297A (en) * 1991-10-18 1993-06-29 United Technologies Corporation Composite blade manufacture
US5634771A (en) * 1995-09-25 1997-06-03 General Electric Company Partially-metallic blade for a gas turbine
US5791879A (en) * 1996-05-20 1998-08-11 General Electric Company Poly-component blade for a gas turbine
US20070065291A1 (en) * 2005-09-16 2007-03-22 General Electric Company Hybrid blisk
US20100209254A1 (en) * 2009-02-17 2010-08-19 Airbus Operations (Societe Par Actions Simplifiee) Vane for aircraft turbine engine receiver, provided with two hollow cores lodged in one another
US8083489B2 (en) * 2009-04-16 2011-12-27 United Technologies Corporation Hybrid structure fan blade
US20120163982A1 (en) * 2010-12-27 2012-06-28 Edward Claude Rice Airfoil, turbomachine and gas turbine engine
US20140212625A1 (en) * 2012-08-26 2014-07-31 Maria Estela Seitz Light weight rotective clothing and accessories

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2381662A1 (fr) * 1977-02-28 1978-09-22 Aerospatiale Pale, notamment pour un rotor d'helicoptere, et son procede de fabrication
US4295790A (en) * 1979-06-21 1981-10-20 The Budd Company Blade structure for use in a windmill
FR2574752B1 (fr) * 1984-12-19 1987-02-20 Aerospatiale Pale pour rotor d'helicoptere en materiau composite multilongeron a caissons de torsion et son procede de fabrication
FR2602739B1 (fr) * 1986-07-28 1988-11-18 Aerospatiale Pale en materiaux composites, a structure bilongeron et bicaisson, et a revetement stratifies a sandwich de nid d'abeilles, et son procede de fabrication
FR2617119B1 (fr) * 1987-06-26 1989-12-01 Aerospatiale Pale en materiaux composites, a noyau structural et revetement d'habillage profile, et son procede de fabrication

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4022546A (en) * 1974-01-03 1977-05-10 Textron, Inc. Helicopter rotor blade
US4329119A (en) * 1977-08-02 1982-05-11 The Boeing Company Rotor blade internal damper
US4639284A (en) * 1983-03-18 1987-01-27 Societe Nationale Industrielle Aerospatiale Process for manufacturing a variable pitch multi-blade propeller by molding resin-impregnated fails around a preform
US5222297A (en) * 1991-10-18 1993-06-29 United Technologies Corporation Composite blade manufacture
US5634771A (en) * 1995-09-25 1997-06-03 General Electric Company Partially-metallic blade for a gas turbine
US5791879A (en) * 1996-05-20 1998-08-11 General Electric Company Poly-component blade for a gas turbine
US20070065291A1 (en) * 2005-09-16 2007-03-22 General Electric Company Hybrid blisk
US20100209254A1 (en) * 2009-02-17 2010-08-19 Airbus Operations (Societe Par Actions Simplifiee) Vane for aircraft turbine engine receiver, provided with two hollow cores lodged in one another
US8083489B2 (en) * 2009-04-16 2011-12-27 United Technologies Corporation Hybrid structure fan blade
US20120163982A1 (en) * 2010-12-27 2012-06-28 Edward Claude Rice Airfoil, turbomachine and gas turbine engine
US20140212625A1 (en) * 2012-08-26 2014-07-31 Maria Estela Seitz Light weight rotective clothing and accessories

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EP2660143B1 (fr) 2021-07-07
EP2660143A1 (fr) 2013-11-06

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Legal Events

Date Code Title Description
AS Assignment

Owner name: RATIER-FIGEAC SAS, FRANCE

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:SEMINEL, BRUNO;PETELLAZ, BRUNO;REEL/FRAME:032448/0312

Effective date: 20120425

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION