US3399731A - Rotor-blade - Google Patents

Rotor-blade Download PDF

Info

Publication number
US3399731A
US3399731A US654232A US65423267A US3399731A US 3399731 A US3399731 A US 3399731A US 654232 A US654232 A US 654232A US 65423267 A US65423267 A US 65423267A US 3399731 A US3399731 A US 3399731A
Authority
US
United States
Prior art keywords
rotor
blade
tip
main portion
cross
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.)
Expired - Lifetime
Application number
US654232A
Inventor
Jr Algy F Giles
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.)
ALGY F GILES JR
Original Assignee
Algy F. Giles Jr.
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 Algy F. Giles Jr. filed Critical Algy F. Giles Jr.
Priority to US654232A priority Critical patent/US3399731A/en
Application granted granted Critical
Publication of US3399731A publication Critical patent/US3399731A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/463—Blade tips

Definitions

  • This invention relates to air foil rotor blades, and more particularly to a high performance, low-noise rotor.
  • Another object of this invention is to provide a rotorblade which will impart a smoother ride at high speeds as well as low speeds and will greatly reduce the audible sound produced by the rotor, the construction greatly reducing the distorted air at the top and the bottom of the rotor.
  • FIGURE 1 is a top plan view showing a vertical-lift aircraft showing the present invention in operative use;
  • FIGURE 2 is an enlarged fragmentary plan view of the invention
  • FIGURE 3 is a cross-sectional view taken lines 3-3 of FIGURE 2;
  • FIGURE 4 is a cross-sectional view taken lines 4-4 of FIGURE 2;
  • FIGURE 5 is a cross-sectional view taken lines 5-5 of FIGURE 2;
  • FIGURE 6 is a cross-sectional view taken lines 6-6 of FIGURE 2;
  • FIGURE 7 is a cross-sectional view taken lines 7-7 of FIGURE 2;
  • FIGURE 8 is a cross-sectional view taken lines 8-8 of FIGURE 2;
  • FIGURE 9 is a cross-sectional view taken lines 9-9 of FIGURE 2.-
  • a rotor 10 is provided with along the along the along the along the along the along the along the along the swept back tips 12 having a semi-tear-drop shape crosssectional configuration as is shown in FIGURES 3 to 9 in the drawing.
  • a helicopter equipped with rotor 10 provides a smoother ride for the occupants and produces greater lift at low speeds and the noise usually associated with the prior art types of rotors is greatly reduced with rotors of this construction as presented herein.
  • the rotor 10 is made up of a number of radially extending members or blades 11, mounted for rotation about a central axis, and each having an elongated main portion and an outer end tip portion which is disposed in angular relation to the main portion and extends in a direction away from the direction of rotation of the rotor.
  • each rotor member or blade is of diminishing width from the main portion toward the free end of the tip, as seen in FIGURE 2, the tip being of substantially the same width as the main portion at the root end of the tip and tapering in thickness from said root end toward the free end of the tip.
  • the main portion and tip are disposed in a common central plane which is substantially normal to the axis of rotation of the rotor and, as shown in FIGURES 3 to 9 of the drawings each of the rotor members or blades is of symmetrical shape in crosssection throughout its length, that is, the member has substantially the same cross-sectional area above and below the common central plane of the main portion and tip portion at any location in the length of the member.
  • a rotor for vertical-lift aircraft comprising a plurality of angularly spaced apart airfoil members extending radially from and mounted for rotation about a central axis, each of said members being of substantially symmetrical, tear-drop shape in cross-section throughout its length having an elongated main portion and formed at its outer end with a tip portion disposed in swept-back relation to said main portion and tapering in thickness and decreasing in width from said main portion toward the free end of the tip portion, said main portion and tip portion being disposed in a common plane located centrally in the member and substantially normal to said axis.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

P 3, 1968 Q A. F. GILES, JR 3,399,731
ROTOR-BLADE Filed July 18, 1967 H Fi .6
- v w/Z Fi .9 J
INVENTOR.
F1372 I E G//es,Jx
United States Patent Oflice Patented Sept. 3, 1968 3,399,731 ROTOR-BLADE Algy F. Giles, Jr., 6010 Belneath, Houston, Tex. 77033 Filed July 18, 1967, Ser. No. 654,232 1 Claim. (Cl. 170-159) ABSTRACT OF THE DISCLOSURE A rotor-blade for helicopters which imparts a smoother ride and greaterlift at low speeds with a smoother ride at high speeds also. A swept-back tip at the end of each blade. This design greatly reduces the audible sound produced at the tips of the rotor.
This invention relates to air foil rotor blades, and more particularly to a high performance, low-noise rotor.
It is therefore the main purpose of this invention to provide a rotor-blade which will have swept-back tips, the tips imparting a smoother ride and greater lift at low speeds than the prior art high performance rotor conventionally used.
Another object of this invention is to provide a rotorblade which will impart a smoother ride at high speeds as well as low speeds and will greatly reduce the audible sound produced by the rotor, the construction greatly reducing the distorted air at the top and the bottom of the rotor.
Other objects of this invention are to provide a rotorblade which is simple in design, inexpensive to manufacture, rugged in constructioin, easy to use and efiicient in operation.
These and other objects will be readily seen upon a study of the following specification taken in connection with the attached drawing wherein:
FIGURE 1 is a top plan view showing a vertical-lift aircraft showing the present invention in operative use;
FIGURE 2 is an enlarged fragmentary plan view of the invention;
FIGURE 3 is a cross-sectional view taken lines 3-3 of FIGURE 2;
FIGURE 4 is a cross-sectional view taken lines 4-4 of FIGURE 2;
FIGURE 5 is a cross-sectional view taken lines 5-5 of FIGURE 2;
FIGURE 6 is a cross-sectional view taken lines 6-6 of FIGURE 2;
FIGURE 7 is a cross-sectional view taken lines 7-7 of FIGURE 2;
FIGURE 8 is a cross-sectional view taken lines 8-8 of FIGURE 2;
FIGURE 9 is a cross-sectional view taken lines 9-9 of FIGURE 2.-
According to this invention, a rotor 10 is provided with along the along the along the along the along the along the along the swept back tips 12 having a semi-tear-drop shape crosssectional configuration as is shown in FIGURES 3 to 9 in the drawing.
In use, a helicopter equipped with rotor 10 provides a smoother ride for the occupants and produces greater lift at low speeds and the noise usually associated with the prior art types of rotors is greatly reduced with rotors of this construction as presented herein.
As shown in FIGURE 1, the rotor 10 is made up of a number of radially extending members or blades 11, mounted for rotation about a central axis, and each having an elongated main portion and an outer end tip portion which is disposed in angular relation to the main portion and extends in a direction away from the direction of rotation of the rotor.
The tip portion of each rotor member or blade is of diminishing width from the main portion toward the free end of the tip, as seen in FIGURE 2, the tip being of substantially the same width as the main portion at the root end of the tip and tapering in thickness from said root end toward the free end of the tip. The main portion and tip are disposed in a common central plane which is substantially normal to the axis of rotation of the rotor and, as shown in FIGURES 3 to 9 of the drawings each of the rotor members or blades is of symmetrical shape in crosssection throughout its length, that is, the member has substantially the same cross-sectional area above and below the common central plane of the main portion and tip portion at any location in the length of the member.
What I claim is:
1. A rotor for vertical-lift aircraft comprising a plurality of angularly spaced apart airfoil members extending radially from and mounted for rotation about a central axis, each of said members being of substantially symmetrical, tear-drop shape in cross-section throughout its length having an elongated main portion and formed at its outer end with a tip portion disposed in swept-back relation to said main portion and tapering in thickness and decreasing in width from said main portion toward the free end of the tip portion, said main portion and tip portion being disposed in a common plane located centrally in the member and substantially normal to said axis.
References Cited UNITED STATES PATENTS 1,888,056 11/1932 Verzillo et a1 -159 2,408,788 10/1946 Ludington et al. 170-135.4 2,582,559 1/1952 Pearson 170-159 X 2,613,752 10/1952 Hawkins 170-159 X 3,065,933 11/1962 Williams 170-159 X FOREIGN PATENTS 46,968 8/1936 France.
EVERETTE A. POWELL, 1a., Primary Examiner.
US654232A 1967-07-18 1967-07-18 Rotor-blade Expired - Lifetime US3399731A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US654232A US3399731A (en) 1967-07-18 1967-07-18 Rotor-blade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US654232A US3399731A (en) 1967-07-18 1967-07-18 Rotor-blade

Publications (1)

Publication Number Publication Date
US3399731A true US3399731A (en) 1968-09-03

Family

ID=24624011

Family Applications (1)

Application Number Title Priority Date Filing Date
US654232A Expired - Lifetime US3399731A (en) 1967-07-18 1967-07-18 Rotor-blade

Country Status (1)

Country Link
US (1) US3399731A (en)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS4840197A (en) * 1971-09-22 1973-06-13
US3807083A (en) * 1972-10-04 1974-04-30 L Smith Insect exterminator
US3822105A (en) * 1971-09-22 1974-07-02 United Aircraft Corp Helicopter blade
US3854845A (en) * 1971-07-02 1974-12-17 De Water F Van Propeller having angularly disposed tip
FR2311713A1 (en) * 1975-05-19 1976-12-17 Westland Aircraft Ltd BLADES FOR HELICOPTER ROTOR
US4168939A (en) * 1977-09-08 1979-09-25 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Acoustically swept rotor
US4248572A (en) * 1978-12-11 1981-02-03 United Technologies Corporation Helicopter blade
US4324530A (en) * 1980-01-21 1982-04-13 United Technologies Corp. Helicopter blade with a tip having a selected combination of sweep, taper and anhedral to improve hover efficiency
US4334828A (en) * 1980-01-21 1982-06-15 United Technologies Corporation Helicopter blade with a tip having a selected combination of sweep, taper and anhedral to improve hover efficiency
EP0067097A1 (en) * 1981-06-05 1982-12-15 Office National d'Etudes et de Recherches Aérospatiales (O.N.E.R.A.) Tip for a rotor craft blade
JP2933949B2 (en) 1988-07-05 1999-08-16 ウエストランド・ヘリコプターズ・リミテッド Helicopter rotor blade, helicopter main rotor and helicopter
RU2209152C1 (en) * 2002-05-18 2003-07-27 ООО "Мидера-К" Closed wing for creating lift force and horizontal thrust
US7918309B1 (en) * 2010-07-07 2011-04-05 Robert Kenneth Vierra Apparatus for producing a continuous sonic boom
FR3110893A1 (en) * 2020-05-29 2021-12-03 Airbus Helicopters Method of construction of a rotor blade for a rotorcraft, blades and rotorcraft
US12448111B1 (en) * 2024-04-17 2025-10-21 Textron Innovations Inc. Method and system for inverse-tapered high-speed rotors

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1888056A (en) * 1932-05-31 1932-11-15 Verzillo Jack Four blade propeller
FR46968E (en) * 1936-01-16 1936-11-23 Avions Kellner Bechereau Soc D Improvements made to wings used in aeronautics
US2408788A (en) * 1939-06-16 1946-10-08 Ludington Charles Townsend Airfoil
US2582559A (en) * 1947-04-14 1952-01-15 Elmer O Pearson Variable pitch propeller
US2613752A (en) * 1951-01-12 1952-10-14 Amos E Hawkins Adjustable pitch propeller for aircraft
US3065933A (en) * 1960-05-20 1962-11-27 Frank Krause Jr A Helicopter

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1888056A (en) * 1932-05-31 1932-11-15 Verzillo Jack Four blade propeller
FR46968E (en) * 1936-01-16 1936-11-23 Avions Kellner Bechereau Soc D Improvements made to wings used in aeronautics
US2408788A (en) * 1939-06-16 1946-10-08 Ludington Charles Townsend Airfoil
US2582559A (en) * 1947-04-14 1952-01-15 Elmer O Pearson Variable pitch propeller
US2613752A (en) * 1951-01-12 1952-10-14 Amos E Hawkins Adjustable pitch propeller for aircraft
US3065933A (en) * 1960-05-20 1962-11-27 Frank Krause Jr A Helicopter

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3854845A (en) * 1971-07-02 1974-12-17 De Water F Van Propeller having angularly disposed tip
JPS4840197A (en) * 1971-09-22 1973-06-13
US3822105A (en) * 1971-09-22 1974-07-02 United Aircraft Corp Helicopter blade
US3807083A (en) * 1972-10-04 1974-04-30 L Smith Insect exterminator
FR2311713A1 (en) * 1975-05-19 1976-12-17 Westland Aircraft Ltd BLADES FOR HELICOPTER ROTOR
US4077741A (en) * 1975-05-19 1978-03-07 Westland Aircraft Limited Helicopter rotor blades
US4168939A (en) * 1977-09-08 1979-09-25 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Acoustically swept rotor
US4248572A (en) * 1978-12-11 1981-02-03 United Technologies Corporation Helicopter blade
US4324530A (en) * 1980-01-21 1982-04-13 United Technologies Corp. Helicopter blade with a tip having a selected combination of sweep, taper and anhedral to improve hover efficiency
US4334828A (en) * 1980-01-21 1982-06-15 United Technologies Corporation Helicopter blade with a tip having a selected combination of sweep, taper and anhedral to improve hover efficiency
EP0067097A1 (en) * 1981-06-05 1982-12-15 Office National d'Etudes et de Recherches Aérospatiales (O.N.E.R.A.) Tip for a rotor craft blade
US4451206A (en) * 1981-06-05 1984-05-29 Office Nationale D'etudes Et De Recherches Aerospatiales Blade end for rotary wing of an aircraft and rotary wing provided with such blade ends
JP2933949B2 (en) 1988-07-05 1999-08-16 ウエストランド・ヘリコプターズ・リミテッド Helicopter rotor blade, helicopter main rotor and helicopter
RU2209152C1 (en) * 2002-05-18 2003-07-27 ООО "Мидера-К" Closed wing for creating lift force and horizontal thrust
WO2003097452A1 (en) * 2002-05-18 2003-11-27 Obschestvo S Ogranichennoi Otvetsvennostyu 'midera-K' Closed wing
US20050230530A1 (en) * 2002-05-18 2005-10-20 Obschestvo S Ogranichennoi Otvetstvennostyu Mider Closed wing
US7918309B1 (en) * 2010-07-07 2011-04-05 Robert Kenneth Vierra Apparatus for producing a continuous sonic boom
FR3110893A1 (en) * 2020-05-29 2021-12-03 Airbus Helicopters Method of construction of a rotor blade for a rotorcraft, blades and rotorcraft
EP3925875A1 (en) 2020-05-29 2021-12-22 Airbus Helicopters Method for constructing a rotor blade intended for a rotorcraft, blade and rotorcraft
US11691719B2 (en) 2020-05-29 2023-07-04 Airbus Helicopters Method for constructing a rotor blade intended for a rotorcraft, blade and rotorcraft
US12448111B1 (en) * 2024-04-17 2025-10-21 Textron Innovations Inc. Method and system for inverse-tapered high-speed rotors
US20250326481A1 (en) * 2024-04-17 2025-10-23 Textron Innovations Inc. Method and System for Inverse-Tapered High-Speed Rotors

Similar Documents

Publication Publication Date Title
US3399731A (en) Rotor-blade
JP3414785B2 (en) Aircraft rotor blades with swept tip
JP3802209B2 (en) Wing with swept tip for aircraft rotor
US7566203B2 (en) Rotor blade
DE60031941T2 (en) Inclined airfoil with barrel-shaped leading edge
US6168383B1 (en) Rotor blade for rotary-wing aircraft
US3053325A (en) Aeronautical propeller
US3706512A (en) Compressor blades
JPH06305492A (en) Rotor blade
KR101537740B1 (en) a rotor blade, a rotor, an aircraft, and a method
US1758560A (en) Aircraft propeller
JPS6422698A (en) Wing of rotary wing for aircraft
JPH036039B2 (en)
EP1035014A3 (en) Rotor blade for rotorcraft
CN104704233A (en) Swallow tail airfoil
JP3051520B2 (en) Helicopter rotor blade
US2272439A (en) Aircraft sustaining rotor blade
US1879594A (en) Aeroplane wing
US3416725A (en) Dihedral bladed ventilating fan
CN109110124A (en) A kind of new Main Rotor Blade
US4451206A (en) Blade end for rotary wing of an aircraft and rotary wing provided with such blade ends
EP0262071B1 (en) Helicopter blade airfoil
US6142738A (en) Blade for rotary wing aircraft
CN112918668B (en) Rotor of rotor craft and rotor craft
US11267567B2 (en) Rotor blade for aircraft