This disclosure pertains to a composite fan containment case for a gas turbine engine.
A gas turbine engine may include a fan section containing fan blades that are surrounded by a fan case supported within a nacelle. The function of the fan case is to contain fractured and separated parts of the fan blades in a radial direction. Metallic fan cases can be undesirably heavy to perform this containment function. A composite fan case constructed of non-metallic materials can reduce weight and provide the same containment capability as a metallic fan case.
While these fan cases have many desirable characteristics, one challenge is the components must be attached to the outer periphery of the case, typically through threaded fasteners. However, the material utilized to form the fan case has not been accommodating of bolt holes. Moreover, composite material manufacturing and forming techniques are limited in the range of tolerances that can be reliably obtained.
In one example, a fan case for a gas turbine engine includes a composite fan containment case including an outer surface, a front and a rear. An attachment flange and a mounting ring are respectively provided on the front and the rear. A bolt attachment is supported on the outer surface. The composite fan containment case has a containment shell providing an outer case in a containment area that is configured to be aligned with a fan blade. A ballistic liner is arranged in the containment area inward of the outer case.
In a further embodiment of the above, the fan containment case includes multiple composite layers that define a generally cylindrical case. An attachment flange extends radially outward from the cylindrical case at the front. The attachment flange comprises a portion of the composite layers. A metallic backing is secured to the attachment flange.
In a further embodiment of any of the above, the mounting ring is metallic and is secured to the outer surface at the rear.
In a further embodiment of any of the above, the composite fan containment case includes multiple composite layers that define a generally cylindrical case. The mounting ring is integral with the composite layers.
In a further embodiment of any of the above, the bolt attachment includes an internal composite boss having at least one metallic insert. The boss is attached to the outer surface with at least one fiber reinforce ply and an adhesive.
In a further embodiment of any of the above, the ballistic liner is manufactured from one of a resin impregnated KEVLAR, a ceramic material and a metallic material.
In another example, a fan case for a gas turbine engine includes a composite fan containment case including an outer surface, a front and a rear. An attachment flange and a mounting ring are respectively provided on the front and the rear. A bolt attachment is supported on the outer surface.
In a further embodiment of the above, the composite fan containment case includes multiple composite layers defining a generally cylindrical case. An attachment flange extends radially outward from the cylindrical case at the front. The attachment flange includes a portion of the composite layers, and a metallic backing ring is secured to the attachment flange.
In a further embodiment of any of the above, the mounting ring is metallic and is secured to the outer surface at the rear.
In a further embodiment of any of the above, the composite fan containment case includes multiple composite layers defining a generally cylindrical case. The mounting ring is integral with the composite layers.
In a further embodiment of any of the above, the bolt attachment includes an internal composite boss having at least one metallic insert. The boss is attached to the outer surface with at least one fiber reinforce ply and an adhesive.
The disclosure can be further understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein:
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Returning to
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Once the mount ring 32 is positioned on the fan case 30, fasteners 54 are arranged through openings 56 within the mount ring 32 and openings 58 in the composite structure 46 to attach the mount ring 32 and the composite structure 46 to the fan exit guide vanes 30. The combination of the interference fit along with the plurality of fasteners 54 secure the mount ring 32 to the composite structure 46. Further, the mount ring 32 is secured to the engine core 12 by way of the guide vanes 30.
Referring to
Another attachment feature of the fan containment case 26 is illustrated in
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With reference to
In one example, the ballistic liner 136 is a cylindrical shell of a rigid material such as a resin impregnated KEVLAR material such as KEVLAR XP™ for Hard Armor, LEXAN, metallic structures, or ceramic materials. That is, the ballistic liner 136 is hard and operates as a rigid impact liner on the radially inner surface of the outer case 138 which may be manufactured of a composite material such as a carbon composite. The ballistic liner 136 need only extend a relatively short axial length as the hard ballistic liner 136 is radially located directly outboard of the fan blades 28.
In another example, the ballistic liner 136 generally includes a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers as described in Applicant's co-pending application entitled “Case with Ballistic Liner,” filed on the same date as the present application and which is incorporated by reference in its entirety. Generally, each of the plurality of unidirectional roving fiber layers is about half the thickness of each of the plurality of non-crimp fabric layers. In one embodiment, each of the plurality of unidirectional roving fiber layers includes three plies and each of the plurality of non-crimp fabric layers includes two plies in the ballistic liner 136.
Although example embodiments have been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of the claims. For that reason, the following claims should be studied to determine their true scope and content.
This disclosure is a continuation-in-part of U.S. patent application Ser. Nos. 12/551,018 filed Aug. 31, 2009; 12/636,388 filed Dec. 11, 2009; 12/892,037 filed Sep. 28, 2010; 12/912,189 filed Oct. 26, 2010; 12/986,209 filed Jan. 7, 2011; and 13/024,386 filed Feb. 10, 2011.
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DuPont Launches Kevlar XP for Hard Armor Applications, http://www/prweb.com/releases/dupont/hard-armor-applications/prweb4682244. |
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International Search Report and Written Opinion for International Application No. PCT/US2013/025690 completed on Oct. 22, 2013. |
Number | Date | Country | |
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20120148392 A1 | Jun 2012 | US |
Number | Date | Country | |
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Parent | 12551018 | Aug 2009 | US |
Child | 13397771 | US | |
Parent | 12636388 | Dec 2009 | US |
Child | 12551018 | US | |
Parent | 12892037 | Sep 2010 | US |
Child | 12636388 | US | |
Parent | 12912189 | Oct 2010 | US |
Child | 12892037 | US | |
Parent | 12986209 | Jan 2011 | US |
Child | 12912189 | US | |
Parent | 13024386 | Feb 2011 | US |
Child | 12986209 | US |