Patent US5403161A successfully refreshed from Google Patents.
US5403161A
Expired / Lapsed
US
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Air foil blade and methods of making same
Assignee: Boeing Co
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Filing: 1994-01-12
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Granted: 1995-04-04
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Expires: 2014-01-12
Abstract
Abstract For use in rear turbine stabilized helicopters, a air foil blade comprising an integrally formed and readily replicated spar and blade in which the blade is created from compounded plastic having cellular structure and adherent to the spar. The air foil blade is produced by a unique adaptation of an injection molding process using a foamed polypropylene thermoplastic material.
Inventors
- 👤 Dennis T. Nealon
- 👤 Robert J. Hudson, Jr.
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 17:32
CPC Classifications
B; B29; B29C; B29C44/00; B29C44/02; B29C44/12; F; F01; F01D; F01D5/00; F01D5/12; F01D5/14; F01D5/147; F04; F04D; F04D29/00; F04D29/26; F04D29/32; F04D29/38; F04D29/388; F05; F05C; F05C2225/00; F05C2225/08; F05D; F05D2300/00; F05D2300/40; F05D2300/43; Y; Y02; Y02T; Y02T50/00; Y02T50/60; Y10; Y10T; Y10T29/00; Y10T29/49; Y10T29/49316; Y10T29/49336; Y10T29/49337
Claims Analysis
Total Claims: 19
Claim 1
Independent Claim
143 words
An airfoil blade for use in rear turbine stabilized helicopters comprising: a metal spar having a body portion that is adapted for operative installation in a rear stabilizing turbine of a rear turbine stabilized helicopter, and an axially extending flange portion integrally formed with said body portion, said flange portion having a proximal segment, a narrower distal segment and a tapered transition segment operatively interposed between said proximal segment and said distal segment and integrally formed therewith, said flange portion having a plurality of openings defined therethrough in spaced relationship to each other; and an aerodynamically contoured thermoplastic blade member surrounding said flange portion and extending through said openings to integrally secure said blade member to said metal spar, said thermoplastic being such that said blade member will not self-destruct when installed in the rear stabilizing turbine of a rear turbine stabilizing helicopter.
Claim 2
Dependent Claim
143 words
An airfoil blade for use in rear turbine stabilized helicopters comprising: a metal spar having a body portion that is adapted for operative installation in a rear stabilizing turbine of a rear turbine stabilized helicopter, and an axially extending flange portion integrally formed with said body portion, said flange portion having a proximal segment, a narrower distal segment and a tapered transition segment operatively interposed between said proximal segment and said distal segment and integrally formed therewith, said flange portion having a plurality of openings defined therethrough in spaced relationship to each other; and an aerodynamically contoured thermoplastic blade member surrounding said flange portion and extending through said openings to integrally secure said blade member to said metal spar, said thermoplastic being such that said blade member will not self-destruct when installed in the rear stabilizing turbine of a rear turbine stabilizing helicopter.
Claim 3
Dependent Claim
63 words
An airfoil blade according to claim 1 in which said thermoplastic blade member is formed by injection molding a composition containing glass-fiber reinforced polypropylene and a foaming agent in relative amounts such that said composition, upon curing, forms a replicatable rigid cellular structure having a consistent weight and provides stability when used in the rear stabilizing turbine of a rear turbine stabilized helicopter.
Claim 4
Dependent Claim
27 words
An airfoil blade according to claim 2 in which said composition contains from about one to about four percent by weight of azodicarbonamide as the foaming agent.
Claim 5
Dependent Claim
30 words
An airfoil blade according to claim 3 in which said thermoplastic blade member has a 500,000 psi flexural modulus, 650 psi wind shear, low water absorption and excellent chemical resistance.
Claim 6
Dependent Claim
13 words
An airfoil blade according to claim 1 wherein said blade is abrasion resistant.
Claim 7
Dependent Claim
32 words
An airfoil blade according to claim 5 wherein said blade is capable of withstanding stresses on the order of magnitude of 5×10 5 psi flexural modulus and 6.5×10 2 psi wind shear.
Claim 8
Dependent Claim
17 words
An airfoil blade according to claim 6 which has a mass of no more than 44 grams.
Claim 9
Dependent Claim
32 words
An airfoil blade according to claim 2 wherein said blade is capable of withstanding stresses on the order of magnitude of 5×10 5 psi flexural modulus and 6.5×10 2 psi wind shear.
Claim 10
Dependent Claim
17 words
An airfoil blade according to claim 1 which has a mass of no more than 44 grams.
Claim 11
Dependent Claim
17 words
An airfoil blade according to claim 2 which has a mass of no more than 44 grams.
Claim 12
Dependent Claim
17 words
An airfoil blade according to claim 4 which has a mass of no more than 44 grams.
Claim 13
Dependent Claim
121 words
An airfoil blade for use in rear turbine stabilized helicopters comprising: a metal spar having a body portion and an axially extending flange portion integrally formed with said body portion, said flange portion having a proximal segment, a narrower distal segment and a tapered transition segment operatively interposed between said proximal segment and said distal segment and integrally formed therewith, said flange portion having a plurality of openings defined therethrough in spaced relationship to each other; an aerodynamically contoured thermoplastic blade member surrounding said flange portion and extending through said openings to secure said blade member to said metal spar; said metal spar including means for operatively securing said blade to the rear stabilizing turbine of a rear turbine stabilized helicopter.
Claim 14
Dependent Claim
121 words
An airfoil blade for use in rear turbine stabilized helicopters comprising: a metal spar having a body portion and an axially extending flange portion integrally formed with said body portion, said flange portion having a proximal segment, a narrower distal segment and a tapered transition segment operatively interposed between said proximal segment and said distal segment and integrally formed therewith, said flange portion having a plurality of openings defined therethrough in spaced relationship to each other; an aerodynamically contoured thermoplastic blade member surrounding said flange portion and extending through said openings to secure said blade member to said metal spar; said metal spar including means for operatively securing said blade to the rear stabilizing turbine of a rear turbine stabilized helicopter.
Claim 15
Dependent Claim
47 words
An airfoil blade according to claim 12 in which said thermoplastic blade is formed by injection molding a composition containing thermoplastic polypropylene and a foaming agent in an amount such that the blade, upon curing, has a replicatable rigid cellular core and an abrasion resistant skin thereabout.
Claim 16
Dependent Claim
25 words
An airfoil blade according to claim 13 in which said composition contains from about one to about four percent of azodicarbonamide as said foaming agent.
Claim 17
Independent Claim
164 words
A method of producing an airfoil blade for use in stabilizing the flight of rear turbine stabilized helicopters comprising: forming a mold having a mold cavity having a shape conforming to the shape of an aerodynamically contoured blade portion of an airfoil blade and complementary seating means formed on the mold for receiving and holding a preformed spar member thereupon, said spar member having a body portion seatable in said seating means and an axially extending flange portion extending into said mold cavity, said flange portion having a plurality of openings defined therethrough in spaced relationship to each other; preparing a mixture of thermoplastic polypropylene and a compatible foaming agent; and injecting said mixture into said cavity to surround said flange portion and fill said cavity and said openings; curing said molded foamed thermoplastic in said cavity to form an airfoil blade having a blade portion extending about and through said flange portion and inseparable therefrom; and removing said airfoil blade from said mold.
Claim 18
Independent Claim
164 words
A method of producing an airfoil blade for use in stabilizing the flight of rear turbine stabilized helicopters comprising: forming a mold having a mold cavity having a shape conforming to the shape of an aerodynamically contoured blade portion of an airfoil blade and complementary seating means formed on the mold for receiving and holding a preformed spar member thereupon, said spar member having a body portion seatable in said seating means and an axially extending flange portion extending into said mold cavity, said flange portion having a plurality of openings defined therethrough in spaced relationship to each other; preparing a mixture of thermoplastic polypropylene and a compatible foaming agent; and injecting said mixture into said cavity to surround said flange portion and fill said cavity and said openings; curing said molded foamed thermoplastic in said cavity to form an airfoil blade having a blade portion extending about and through said flange portion and inseparable therefrom; and removing said airfoil blade from said mold.
Claim 19
Dependent Claim
31 words
A process according to claim 15 wherein said blade is capable of withstanding stresses on the order of magnitude of 5×10 5 psi flexural modulus and 6×10 2 psi wind shear.
References Cited (Backward Citations)
FR901587A
Cited
US2423700A
Cited
FR1355427A
Cited
US3305196A
Cited
SU808685A1
Cited
US4477228A
Cited
JPS61215498A
Cited
US5076760A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1998-04-03 | 1998-10-03 | 1999-04-04 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2002-04-03 | 2002-10-03 | 2003-04-04 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2006-04-03 | 2006-10-03 | 2007-04-04 | $7700.00 | Window Closed / Lapsed |