Patent Application
20140133995
This application claims priority to European Patent Application No. 12305483.5, filed Apr. 30, 2012, and all the benefits accruing therefrom under 35 U.S.C. §119, the contents of which in its entirety are herein incorporated by reference.
The present invention relates to propellers and, in particular, to propeller blades formed having a 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. 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 that includes a foam core and a structural layer formed of multiple layers that surrounds at least a portion of the foam core is disclosed. The propeller blade of this embodiment further includes at least one section of fibers formed separately from the structural layer located between two of the multiple layers.
According to another embodiment, a method of forming a propeller blade includes forming a foam core; disposing a first layer of a structural layer over at least a portion of the foam core; disposing a fabric sheet including directionally oriented fibers over the first layer; and disposing a second layer of the structural layer of the fabric sheet and the first layer.
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 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 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.
In one embodiment, an optional adhesive layer 205 is formed on the outside of the core 204. The adhesive layer 205 is formed of an elastomeric or other high strain rate adhesive material. Examples of suitable adhesives include polyurethane adhesive and polysulfide adhesive.
A structural layer 206 can then be formed around the adhesive layer 205. In one embodiment, the structural layer 206 is formed of a resin-impregnated fiber material, such as a resin-impregnated braided carbon sheet, and disposed such that it surrounds the core 204 (and the fiberglass layer if present). The structural layer 206 is formed by a plurality of layers that are separately braided on. For instance, a braiding machine can be used to wrap resin coated fibers around the spar from the one end thereof to the other in the span wise direction X (or the opposite direction) shown in
In operation, the blade 200 can be a high-performance propeller blade that is relatively long in the span wise direction X as compared to their thickness. As such, the spar is stiff in the span wise direction X for optimum blade frequency placement and, as such is quite flexible in the chord wise Y direction. According to one embodiment of the present invention, one or more patches of span wise fibers 230 are introduced between the layers of braiding forming the structural layer 206. The span wise fibers 230 can be contained in fabric sheets that include a plurality of fibers. In one embodiment, the span wise fibers 230 can be located such they result in a balanced spar. The span wise fibers 230 increase the section modulus of the blade 200 cross-section, thereby reducing operational stresses in the spar foam 204.
Referring now to
Both the span wise fibers 230 and chord wise fibers 240 may be may be made of carbon, fiberglass, or other suitable composite material. The added plies may be located along full length of the blade, or their lengths may be optimized to reduce cost and weight. It shall be understood that both span wise 230 and chord wise 240 could be included in a single blade in one embodiment.
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.
| Number | Date | Country | Kind |
|---|---|---|---|
| 12305483.5 | Apr 2012 | EP | regional |
