Assembly containing a composite article and assembly method therefor
First Claim
1. An assembly comprising:
- a ceramic matrix composite article having oppositely-disposed first and second surfaces, a hole through the article and intersecting the first and second surfaces so as to define oppositely-disposed first and second openings at the first and second surfaces, respectively, and continuous chamfers along the entirety of the first and second openings;
a support structure adjacent the article; and
a fastener received in the hole and securing the article to the support structure, the fastener being formed of a softer material than the article.
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Accused Products
Abstract
An assembly that includes a CMC article, and a method of forming the assembly, so as to reduce the likelihood during a transient thermal condition of the CMC article becoming interlocked with the worn shank of a fastener used to secure the article to its support structure. The CMC article has oppositely-disposed first and second surfaces, a hole through the article and intersecting the first and second surfaces so as to define oppositely-disposed first and second openings at the first and second surfaces, respectively, and continuous chamfers along the entirety of the first and second openings. The assembly further includes a support structure adjacent the article, and a fastener received in the hole of the CMC article and securing the CMC article to the support structure. The location of the chamfers at the perimeter of each opening eliminates a relatively sharp edge that could interlock with the worn shank of the fastener during a thermal excursion.
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Citations
28 Claims
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1. An assembly comprising:
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a ceramic matrix composite article having oppositely-disposed first and second surfaces, a hole through the article and intersecting the first and second surfaces so as to define oppositely-disposed first and second openings at the first and second surfaces, respectively, and continuous chamfers along the entirety of the first and second openings;
a support structure adjacent the article; and
a fastener received in the hole and securing the article to the support structure, the fastener being formed of a softer material than the article. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8)
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9. An assembly installed in a gas turbine engine, the assembly comprising:
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a ceramic matrix composite article comprising multiple laminated layers that define oppositely-disposed first and second surfaces, a hole through the article and intersecting the first and second surfaces so as to define oppositely-disposed first and second openings at the first and second surfaces, respectively, and continuous chamfers along the entirety of the first and second openings;
a metal structure contacting the article so that one of the surfaces of the article faces a surface of the metal structure; and
a metal fastener received in the hole and securing the article to the metal structure, the fastener being formed of a metal that is softer than the article. - View Dependent Claims (10, 11, 12, 13, 14)
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15. A method of assembling a composite matrix composite article to a support structure, the method comprising the steps of:
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forming the article to have oppositely-disposed first and second surfaces, a hole through the article and intersecting the first and second surfaces so as to define oppositely-disposed first and second openings at the first and second surfaces, respectively, and continuous chamfers along the entirety of the first and second openings;
positioning the article adjacent the support structure; and
thensecuring the article to the support structure with a fastener received in the hole, the fastener being formed of a softer material than the article. - View Dependent Claims (18, 19, 20, 21, 22)
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16. A method according to claim 115, wherein the chamfers are formed in the article so as to be disposed at approximately equal angles relative to an axis of the hole.
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17. A method according to claim 115, wherein the chamfers are formed in the article so as to be disposed at an angle of about 30 to about 45 degrees relative to the axis of the hole.
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23. A method of assembling a composite matrix composite article to a metal structure of a gas turbine engine, the method comprising the steps of:
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forming a ceramic matrix composite article comprising multiple laminated layers that define oppositely-disposed first and second surfaces, a hole through the article and intersecting the first and second surfaces so as to define oppositely-disposed first and second openings at the first and second surfaces, respectively, and continuous chamfers along the entirety of the first and second openings;
positioning the article adjacent a metal structure of a gas turbine engine so that one of the surfaces of the article faces a surface of the metal structure; and
thensecuring the article to the metal structure with a metal fastener that is received in the hole as a result of the securing step, the fastener being formed of a metal that is softer than the article. - View Dependent Claims (24, 25, 26, 27, 28)
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Specification