Patent Application
20130280079
The present invention relates to propellers and, in particular, to propeller blades formed having a metallic foam spar core.
Modern propeller blades typically include root portions which extend into the hub arm of the hub of the propeller system and which are secured to and rotatable relative to the hub arm via a retention assembly. Typically the retention assembly includes one or a plurality of ball bearing assemblies which permit the rotation of the blade in the hub arm for accomplishing pitch change of the blade for altering the speed of the propeller and accordingly, the aircraft.
The blades are typically formed by surrounding a foam spar core with a resin impregnated fabric that is braided on to the form spar core. Leading and trailing edges of the blade are then formed over the fabric and surrounded by, for example, a Kevlar sock. Such blades are light and effective for their intended purposes.
According to one embodiment, a propeller blade includes a metallic foam core and a structural layer that surrounds at least a portion of the metallic foam core.
According to another embodiment, a method of forming a propeller blade includes: forming a metallic foam core; and disposing a structural layer over at least a portion of the metallic foam core.
The subject matter which is regarded as the invention is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features, and advantages of the invention are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:
Referring now to
The blade 100 is formed by first forming a spar 102. The spar 102 includes a spar foam core 104 surrounded by a structural layer 106. The core 104 is typically formed of a foam material that is injected into a mold. The mold can include a layer of fiberglass on the walls thereof that to which the foam of the core 104 adheres. As such, the core 104 can be surrounded by a layer of fiberglass (not shown). The foam that forms the core 104 is typically selected from one of: polyurethane (PU), polyisocyanurate, or polymethacrylimide (PMI).
The structural layer 106 is typically formed of a dry braided carbon fiber which is subsequently resin injected or a resin-impregnated fabric material (e.g. resin impregnated carbon fiber fabric) and disposed such that it surrounds the core 104 (and the fiberglass layer if it is included). The structural layer 106 is typically braided onto the core 104. In some cases, the spar 102 is heated to set the resin in the structural layer 106. Considerable thermal stresses can occur in the core 104 as the spar 102 is cooled due to the differences in the coefficients of thermal expansion (CTE) of the core 104 and the structural layer 106.
In some instances, the spar 102 is formed such that a portion of it is surrounded by a root portion 108 that allows the blade 100 to be connected to a hub (not shown). Rotation of the hub causes the blade 100 to rotate and, consequently, causes the generation of thrust to propel an aircraft. In the following discussion, it shall be assumed that the blade 100 rotates in the clockwise direction. The root portion 108 is sometimes referred to as a “tulip” in the industry and is typically formed of a metal.
After the spar 102 is formed, leading edge foam 110 and trailing edge foam 112 are formed on the leading and trailing edges 114, 116, respectively of the spar 102. The leading edge foam 110, trailing edge foam 112 and the spar 102 can then be encased in an outer layer 118. The outer layer 118 can be formed of Kevlar and be in the form of a sock that is pulled over the assembly that includes the leading edge foam 110, trailing edge foam 112 and the spar 102. Of course, the outer layer 118 could be formed in other manners as well.
As described above, considerable thermal stresses can occur in the core 104 as the spar 102 is cooled due to the differences in the coefficients of thermal expansion (CTE) of the core 104 and the structural layer 106. In addition, thermal stresses can be created between the core 104 and the structural layer 106 due to the wide range of temperatures experienced by the propeller blade 100 in normal operation.
According to one embodiment, rather than utilizing the foam core 104 described above, at least a portion of the foam core is replaced with metallic foam. In one embodiment, the entire foam core 104 is replaced with metallic foam. In another embodiment, only a portion of the foam core is replace with metallic foam. The metallic foam is coupled to the remaining portions of the conventional foam.
Provision of a metallic spar foam may provide for a better bond between the core and the structural layer 106. This may be due do the fact that a metal foam has a higher strength and greater bonding surface area due to the potential for an open cell structure than the polyurethane foam typically used which has a resin skin on the surface that closes off the cell structure. In one embodiment, the metallic foam may be coated with either a film or paste adhesive to optimize bond strength to the surrounding structural layer. The metallic foam core may extend along the full length of the blade, or its length may be optimized to reduce weight. The metallic foam would also be appropriately surface prepared (e.g., in the case of aluminum foam, by conversion coating or anodizing) to enhance the bonding process beyond mechanical interlock of the adhesive to the metal foam. Proper surface preparation will promote adhesion to the metallic foam and enhance the durability of the bond joint.
As used herein, a metallic foam shall refer to a cellular structure consisting of a solid metal, containing a large volume fraction of gas-filled pores. The metallic foam used herein can have pores that are sealed (closed-cell foam), or they can form an interconnected network (open-cell foam).
A structural layer 206 can then be formed around the adhesive layer 205. In one embodiment, the structural layer 206 is formed of dry braided carbon fiber which is subsequently resin injected or a resin-impregnated fabric material (e.g. resin impregnated carbon fiber fabric) and disposed such that it surrounds the core 204 (and the fiberglass layer if it is included). In some cases, the spar 202 is heated to set the resin in the structural layer 206.
After the spar 202 is formed, leading edge foam 210 and trailing edge foam 212 are formed on the leading and trailing edges 214, 216, respectively of the spar 202. It shall be understood that the leading and trailing edge foam 210, 212 could be formed of metallic foam in one embodiment or of any other type of foam currently used in composite propeller blade construction. The leading edge foam 210, trailing edge foam 212, and the spar 202 can then be encased in an outer layer 218. The outer layer 218 can be formed of Kevlar and in the form of a sock that is pulled over the assembly that includes the leading edge foam 210, trailing edge foam 212, and the spar 202. Of course, the outer layer 218 could be formed in other manners as well.
While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. Additionally, while various embodiments of the invention have been described, it is to be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.
