GB556679A - Improvements in or relating to propeller blade construction - Google Patents

Improvements in or relating to propeller blade construction

Info

Publication number
GB556679A
GB556679A GB11752/42A GB1175242A GB556679A GB 556679 A GB556679 A GB 556679A GB 11752/42 A GB11752/42 A GB 11752/42A GB 1175242 A GB1175242 A GB 1175242A GB 556679 A GB556679 A GB 556679A
Authority
GB
United Kingdom
Prior art keywords
relating
propeller blade
blade
blade construction
propellers
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
Application number
GB11752/42A
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 Aircraft 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 Aircraft Corp filed Critical United Aircraft Corp
Publication of GB556679A publication Critical patent/GB556679A/en
Expired legal-status Critical Current

Links

Classifications

    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

556,679. Screw propellers. UNITED AIRCRAFT CORPORATION Aug. 20, 1942, No. 11752. Convention date, Oct. 22, 1941. [Class 114] Metal blades for aircraft propellers are formed with a forward curvature towards their tips, so that the blade tends to straighten under the action of centrifugal force during rotation, and the rearward face 24 is consequently placed under compression. The resistance of the blade to vibratory stress is thereby increased and the weakening effect of scratches or abrasions, caused by the impact of stones, cinders &c. on the rear face, is reduced.
GB11752/42A 1941-10-22 1942-08-20 Improvements in or relating to propeller blade construction Expired GB556679A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US556679XA 1941-10-22 1941-10-22

Publications (1)

Publication Number Publication Date
GB556679A true GB556679A (en) 1943-10-15

Family

ID=21999394

Family Applications (1)

Application Number Title Priority Date Filing Date
GB11752/42A Expired GB556679A (en) 1941-10-22 1942-08-20 Improvements in or relating to propeller blade construction

Country Status (1)

Country Link
GB (1) GB556679A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104002966A (en) * 2014-06-03 2014-08-27 北京航空航天大学 Rotor blade structure design capable of inhibiting rotation chattering of tilt rotor

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104002966A (en) * 2014-06-03 2014-08-27 北京航空航天大学 Rotor blade structure design capable of inhibiting rotation chattering of tilt rotor

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