US20150078909A1 - Rotor blade and structural system for coupling the rotor blade in a rotor hub - Google Patents

Rotor blade and structural system for coupling the rotor blade in a rotor hub Download PDF

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Publication number
US20150078909A1
US20150078909A1 US14/027,733 US201314027733A US2015078909A1 US 20150078909 A1 US20150078909 A1 US 20150078909A1 US 201314027733 A US201314027733 A US 201314027733A US 2015078909 A1 US2015078909 A1 US 2015078909A1
Authority
US
United States
Prior art keywords
bolt
rotor blade
distance
hole
rotor
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
US14/027,733
Other languages
English (en)
Inventor
Mark A. Wiinikka
Nathan P. Green
Robert A. Self, Jr.
John R. McCullough
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.)
Bell Helicopter Textron Inc
Original Assignee
Bell Helicopter Textron Inc
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 Bell Helicopter Textron Inc filed Critical Bell Helicopter Textron Inc
Priority to US14/027,733 priority Critical patent/US20150078909A1/en
Assigned to BELL HELICOPTER TEXTRON INC. reassignment BELL HELICOPTER TEXTRON INC. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Green, Nathan P., MCCULLOUGH, JOHN R., SELF, ROBERT A., WIINIKKA, MARK A.
Priority to EP14153177.2A priority patent/EP2848524B1/fr
Priority to CA2862588A priority patent/CA2862588C/fr
Priority to BR102014022531A priority patent/BR102014022531A2/pt
Priority to CN201410471653.8A priority patent/CN104443375B/zh
Publication of US20150078909A1 publication Critical patent/US20150078909A1/en
Abandoned legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/473—Constructional features
    • B64C27/48—Root attachment to rotor head
    • 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

Definitions

  • the present application relates to a rotor blade, as well as a structural system for coupling the rotor blade to a rotor hub.
  • rotor blades have been coupled to the rotor hub in a variety of ways.
  • One conventional rotor blade attachment system involves attaching the rotor blade with two bolts oriented along a chordwise axis at the root end of the rotor blade.
  • Another conventional rotor blade attachment system involves attaching the rotor blade with two bolts oriented along a spanwise axis at the root end of the rotor blade.
  • FIG. 1 is a side view of a rotorcraft having a rotor blade, according to an example embodiment
  • FIG. 2 is perspective view of the rotor hub, according to an example embodiment
  • FIG. 3 is a top view of the rotor hub, according to an example embodiment
  • FIG. 4 is a top view of the rotor hub, according to an example embodiment
  • FIG. 5 is a top view of the rotor hub, according to an example embodiment
  • FIG. 6 is a cross-sectional view of the rotor hub, taken from section lines 6 - 6 in FIG. 5 , according to an example embodiment
  • FIG. 7 is a perspective view of a rotor blade, according to an example embodiment.
  • FIG. 8 is a partial perspective view of the rotor blade of FIG. 7 , according to an example embodiment.
  • Rotorcraft 101 has a rotor system 103 with a plurality of rotor blades 105 .
  • the pitch of each rotor blade 105 can be selectively controlled in order to selectively control direction, thrust, and lift of rotorcraft 101 .
  • Rotorcraft 101 further includes a fuselage 107 , anti-torque system 109 , and an empennage 111 .
  • Rotorcraft 101 further includes a landing gear system 113 , to provide ground support for the aircraft. It should be appreciated that rotorcraft 101 is merely illustrative of a variety of aircraft that can implement the embodiments disclosed herein. Other aircraft implementations can include hybrid aircraft, tilt rotor aircraft, unmanned aircraft, gyrocopters, and a variety of helicopter configurations, to name a few examples.
  • Rotor hub 103 includes a yoke 109 coupled to a mast 113 .
  • Each rotor blade 105 is coupled to the yoke 115 with a grip 119 .
  • An inboard portion of each grip 119 is secured within an opening of the yoke 115 with a centrifugal force bearing 135 .
  • Grip 119 is a single continuous member having an upper extension 137 and a lower extension 139 .
  • Rotor blade 105 is attached to the outboard portion of grip 119 with a unique arrangement of a first bolt 129 , a second bolt 131 , and a third bolt 133 .
  • a pitch horn 123 is interposed between rotor blade 105 and the upper and lower extensions 137 , 139 of grip 119 .
  • a damper 121 is attached between yoke 115 and a damper attachment portion 141 of with pitch horn 123 .
  • the torsional loading about pitch change axis 143 can induce bending along an axis formed by the two spanwise located bolts.
  • the beam bending in direction 149 can induce bending along an axis formed by the two chordwise located bolts.
  • the two bolts must be sized in order to react the bending loads, which can add weight since a larger diameter bolt can increase edge distance requirements, bolt weight, and rotor blade structure at the root end.
  • the embodiments of the present disclosure include a three-bolt triangular pattern that collectively react the operation loads in such a manner so as to reduce the size of the bolts and corresponding attachment lugs in both the rotor blade 105 and grip 119 , thereby reducing the overall weight of rotor system 103 and increasing the useful load of the rotorcraft 101 .
  • the aerodynamic drag of the three-bolt pattern is actually less than two-bolt chordwise arrangement.
  • utilizing more than three bolts can add unnecessary weight, and further add complexity to the manual rotor blade folding procedure.
  • the three rotor blade attachment bolt arrangement includes the first bolt 129 , which is the most inboard of the three bolts, and lies upon a center spanwise plane of rotor blade 105 .
  • the three rotor blade attachment bolt arrangement also includes the second bolt 131 and the third bolt 133 that are aligned along a chordwise plane, and offset from the first bolt 129 in an outboard spanwise direction by a distance D1.
  • the second bolt 131 and the third bolt 133 are offset from the center spanwise plane by chordwise distances C1 and C2, respectively.
  • C1 is equal to C2.
  • first bolt 129 The combination and arrangement of the first bolt 129 , the second bolt 131 , and the third bolt 133 for attachment of the rotor blade 105 to grip 137 has unique advantages.
  • first bolt 129 If first bolt 129 did't present, then second bolt 131 and third bolt 133 would be subject to relatively large bending forces from the beam bending in direction 149 due to the second bolt 131 and third bolt 133 being aligned in a chordwise direction.
  • first bolt 129 acts to greatly reduce the bending forces on second bolt 131 and third bolt 133 by creating a heel/toe effect.
  • first bolt 129 inboard to the chordwise oriented second bolt 131 and third bolt 133 , the rotor blade 105 can taper down or become more narrow at the root end.
  • the tapering of rotor blade 105 at the root end allows for clearance between the root end of rotor blade 105 and the damper attachment portion 141 of pitch horn.
  • Rotor blade 105 can have a leading 701 , a trailing edge 703 , a root end 705 and a tip end 707 . It should be appreciated that rotor blade 105 can take on a wide variety of configurations. For example, rotor blade 105 can have a degree of built-in twist between root end 705 and tip end 707 . Describing another example, rotor blade 105 can have an anhedral tip, or any other desirable aerodynamic profile. Rotor blade 105 includes holes 709 , 711 , and 713 which provide corresponding apertures for bolts 129 , 131 , and 133 , respectively.
  • holes 709 , 711 , and 713 can include bushings, or similar, located therein as a bearing surface for the shanks of bolts 129 , 131 , and 133 .
  • Rotor blade 105 can include a forward taper 715 and an aft taper 717 that each taper toward a centerline axis of the rotor blade until joining at a rounded portion 719 .
  • Rounded portion 719 can have a radius that is a function of a desired edge distance from hole 709 .
  • first bolt 129 and third bolt 133 are illustrated as quick removable expandable bolts configured to be removed without the need for a tool.
  • a pin can be removed from the lower portion, allowing the handle to be pivoted, which actuates a cam member allowing the bolt to be removed.
  • the rotor blade 105 is free to be rotated about second bolt 131 .
  • all of the first bolt 129 , the second bolt 131 , and the third bolt 133 can be conventional bolts.
  • FIGS. 5 and 6 illustrate all of the first bolt 129 , the second bolt 131 , and the third bolt 133 as conventional bolts.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US14/027,733 2013-09-16 2013-09-16 Rotor blade and structural system for coupling the rotor blade in a rotor hub Abandoned US20150078909A1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US14/027,733 US20150078909A1 (en) 2013-09-16 2013-09-16 Rotor blade and structural system for coupling the rotor blade in a rotor hub
EP14153177.2A EP2848524B1 (fr) 2013-09-16 2014-01-30 Pale de rotor et système structural pour le couplage de la pale de rotor dans un moyeu de rotor
CA2862588A CA2862588C (fr) 2013-09-16 2014-09-09 Pale de rotor et systeme structurel pour couplage de la pale de rotor a un moyeu de rotor
BR102014022531A BR102014022531A2 (pt) 2013-09-16 2014-09-11 cubo e pá de rotor
CN201410471653.8A CN104443375B (zh) 2013-09-16 2014-09-16 旋翼叶片和用于将旋翼叶片联接于旋翼毂中的结构系统

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US14/027,733 US20150078909A1 (en) 2013-09-16 2013-09-16 Rotor blade and structural system for coupling the rotor blade in a rotor hub

Publications (1)

Publication Number Publication Date
US20150078909A1 true US20150078909A1 (en) 2015-03-19

Family

ID=50028858

Family Applications (1)

Application Number Title Priority Date Filing Date
US14/027,733 Abandoned US20150078909A1 (en) 2013-09-16 2013-09-16 Rotor blade and structural system for coupling the rotor blade in a rotor hub

Country Status (5)

Country Link
US (1) US20150078909A1 (fr)
EP (1) EP2848524B1 (fr)
CN (1) CN104443375B (fr)
BR (1) BR102014022531A2 (fr)
CA (1) CA2862588C (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20190031328A1 (en) * 2017-07-25 2019-01-31 Bell Helicopter Textron Inc. Rotorcraft Centrifugal Force Bearing
US20190039727A1 (en) * 2017-08-01 2019-02-07 Bell Helicopter Textron Inc. Rotorcraft Centrifugal Force Bearing
US11155347B2 (en) * 2019-04-02 2021-10-26 Textron Innovations Inc. Rotorcraft blade grip
US11174017B2 (en) 2019-05-30 2021-11-16 Lockheed Martin Corporation Rotor blade folding system

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10597143B2 (en) * 2017-08-22 2020-03-24 Bell Helicopter Textron Inc. Low moment rotor hub
CN111361369B (zh) * 2020-04-23 2022-06-10 苏德海 一种飞行汽车
CN113319531B (zh) * 2021-05-31 2022-07-12 安徽省飞腾航空科技有限公司 一种可调节式直升机主旋翼及其生产工艺

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2795284A (en) * 1954-02-19 1957-06-11 United Aircraft Corp Tail rotor counterweight
CH443006A (de) * 1964-02-29 1967-08-31 Schneider Hans Rotorblatt für Helikopter
US3392788A (en) * 1965-12-03 1968-07-16 Bell Aerospace Corp Rotor blade
US3728045A (en) * 1971-09-22 1973-04-17 United Aircraft Corp Helicopter blade
US4304525A (en) * 1978-06-02 1981-12-08 Societe Nationale Industrielle Aerospatiale Helicopter rotor
US20140178199A1 (en) * 2012-12-21 2014-06-26 Bell Helicopter Textron Inc. System and Method for Linkage Length Adjustment
US9157474B2 (en) * 2013-09-30 2015-10-13 Bell Helicopter Textron Inc. System and method of monitoring wear in a bearing

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB655217A (en) * 1947-09-12 1951-07-11 United Aircraft Corp Improvements in or relating to rotor assemblies particularly for helicopters
US2684722A (en) * 1952-05-22 1954-07-27 John A Perry Helicopter rotor structure
FR2092720B1 (fr) * 1970-06-11 1974-07-12 Scemm
US4373862A (en) * 1981-10-26 1983-02-15 United Technologies Corporation Rotor blade shaft integrity monitoring system
US5211538A (en) * 1991-11-27 1993-05-18 Bell Helicopter Textron Inc. Method for folding helicopter main rotor blades
US5562416A (en) * 1995-08-10 1996-10-08 Sikorsky Aircraft Corporation Helicopter rotor blade mounting assembly
ATE490914T1 (de) * 2008-05-22 2010-12-15 Agusta Spa Drehmomentausgleichs-heckrotorblatt für hubschrauber
EP2457830B1 (fr) * 2010-11-25 2014-11-12 AIRBUS HELICOPTERS DEUTSCHLAND GmbH Connexion d'une aube avec le moyeu du rotor

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2795284A (en) * 1954-02-19 1957-06-11 United Aircraft Corp Tail rotor counterweight
CH443006A (de) * 1964-02-29 1967-08-31 Schneider Hans Rotorblatt für Helikopter
US3392788A (en) * 1965-12-03 1968-07-16 Bell Aerospace Corp Rotor blade
US3728045A (en) * 1971-09-22 1973-04-17 United Aircraft Corp Helicopter blade
US4304525A (en) * 1978-06-02 1981-12-08 Societe Nationale Industrielle Aerospatiale Helicopter rotor
US20140178199A1 (en) * 2012-12-21 2014-06-26 Bell Helicopter Textron Inc. System and Method for Linkage Length Adjustment
US9157474B2 (en) * 2013-09-30 2015-10-13 Bell Helicopter Textron Inc. System and method of monitoring wear in a bearing

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20190031328A1 (en) * 2017-07-25 2019-01-31 Bell Helicopter Textron Inc. Rotorcraft Centrifugal Force Bearing
US10864985B2 (en) * 2017-07-25 2020-12-15 Textron Innovations Inc. Rotorcraft centrifugal force bearing
US20190039727A1 (en) * 2017-08-01 2019-02-07 Bell Helicopter Textron Inc. Rotorcraft Centrifugal Force Bearing
US10836476B2 (en) * 2017-08-01 2020-11-17 Textron Innovations Inc. Rotorcraft centrifugal force bearing
US11155347B2 (en) * 2019-04-02 2021-10-26 Textron Innovations Inc. Rotorcraft blade grip
US11453486B2 (en) 2019-04-02 2022-09-27 Textron Innovations Inc. Rotorcraft glade grip
US11174017B2 (en) 2019-05-30 2021-11-16 Lockheed Martin Corporation Rotor blade folding system

Also Published As

Publication number Publication date
BR102014022531A2 (pt) 2016-01-19
CA2862588A1 (fr) 2015-03-16
EP2848524A1 (fr) 2015-03-18
CN104443375A (zh) 2015-03-25
CN104443375B (zh) 2018-04-13
CA2862588C (fr) 2017-05-30
EP2848524B1 (fr) 2015-09-23

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Owner name: BELL HELICOPTER TEXTRON INC., TEXAS

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:GREEN, NATHAN P.;MCCULLOUGH, JOHN R.;WIINIKKA, MARK A.;AND OTHERS;SIGNING DATES FROM 20130830 TO 20130912;REEL/FRAME:031212/0911

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STCB Information on status: application discontinuation

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