Blade for turbomachine receiving part, comprising an airfoil part including a mechanical fuse
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0708237
(2010-02-18)
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등록번호 |
US-8573936
(2013-11-05)
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우선권정보 |
FR-09 51112 (2009-02-20) |
발명자
/ 주소 |
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출원인 / 주소 |
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대리인 / 주소 |
Oblon, Spivak, McClelland, Maier & Neustadt, L.L.P.
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인용정보 |
피인용 횟수 :
0 인용 특허 :
5 |
초록
▼
A blade for an aircraft turbomachine receiving part including a root, and an airfoil part prolonging this root. The airfoil part includes a mechanical fuse located at a distance from the bottom of the blade, along the length direction of the airfoil part, between 0.25 and 0.5 times the length of the
A blade for an aircraft turbomachine receiving part including a root, and an airfoil part prolonging this root. The airfoil part includes a mechanical fuse located at a distance from the bottom of the blade, along the length direction of the airfoil part, between 0.25 and 0.5 times the length of the airfoil part along this length direction.
대표청구항
▼
1. A blade for an aircraft turbomachine receiving part, comprising: a root; andan airfoil part prolonging said root, said airfoil part including an aerodynamic shell surrounding a hollow structural core,wherein said blade further includes a bowl with a head at a first end thereof and a stem extendin
1. A blade for an aircraft turbomachine receiving part, comprising: a root; andan airfoil part prolonging said root, said airfoil part including an aerodynamic shell surrounding a hollow structural core,wherein said blade further includes a bowl with a head at a first end thereof and a stem extending from said bowl head, said bowl head being located in said shell and said bowl stem being located outside said shell, said bowl stem presenting a junction with a reduced cross-section connecting said airfoil part to said root,wherein said hollow structural core extends along a length direction of said airfoil part and is located in external radial continuity with said bowl head such that a first end of said hollow structural core faces said bowl head,wherein a sleeve surrounds said first end of said bowl and said first end of said hollow structural core, andwherein said airfoil part includes a mechanical fuse provided at an interface between said bowl head and said hollow structural core, and the mechanical fuse is located at a distance from a bottom of the blade along the length direction of the airfoil part, between 0.25 and 0.5 times the length of said airfoil part along the length direction. 2. The blade according to claim 1, wherein said distance is equal to approximately 0.3 times the length of said airfoil part along said length direction. 3. The blade according to claim 1, wherein said root is separated into two root portions, one mounted on the other, each extending over the entire length of said root. 4. The blade according to claim 1, wherein said airfoil part forming a bowl is separated into two bowl portions, one mounted on the other, each extending over the entire length of said bowl. 5. The blade according to claim 4, wherein said root is separated into two root portions, one mounted on the other, each extending over the length of said root, and each bowl portion of the two bowl portions is made in a single piece with one of two root portions of the root. 6. A turbomachine for an aircraft comprising a receiving part equipped with a plurality of blades according to claim 1. 7. An aircraft comprising a plurality of turbomachines according to claim 6. 8. The blade according to claim 1, wherein the mechanical fuse is a plane and is orthogonal to the length direction.
이 특허에 인용된 특허 (5)
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Thompson, Ewan F; Read, Simon, Aerofoil blades with improved impact resistance.
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Nelson Joey L. (Cincinnati OH) Elston ; III Sidney B. (Marbelhead MA) Tseng Wu-Yang (West Chester OH) Hemsworth Martin C. (Cincinnati OH), Counterrotating aircraft propulsor blades.
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Kray, Nicholas Joseph; Crall, David William; Mollmann, Daniel Edward, Method and apparatus for gas turbine engines.
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Vance, Steven J., Multiple piece turbine engine airfoil with a structural spar.
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