Aircraft propellers

Abstract

An aircraft propeller taper bore insert apparatus is provided. The apparatus includes a tapered outer surface and an inner surface. The outer surface is dimensioned and configured to fit within and be of substantially a same size and shape as an aircraft propeller taper bore or an aircraft propeller balancing tube. The inner surface defines an inner cavity configured to receive a balancing medium and includes a plurality of retention formations arranged thereon and configured to support the balancing medium.

1 . An aircraft propeller taper bore insert apparatus comprising:
 a tapered outer surface that is dimensioned and configured to fit within and be of substantially a same size and shape as an aircraft propeller taper bore or an aircraft propeller balancing tube; and   an inner surface that defines an inner cavity configured to receive a balancing medium and includes a plurality of retention formations arranged thereon and configured to support the balancing medium.   
     
     
         2 . The apparatus of  claim 1 , wherein the balancing medium is arranged within the inner cavity and includes a filler material and balancing material. 
     
     
         3 . The apparatus of  claim 2 , wherein the filler material is a binder, adhesive, elastomer, gel, sealant, or wax. 
     
     
         4 . The apparatus of  claim 2 , wherein the balancing material is at least one of metal shot, metal pellets, ceramic shot, ceramic pellets, rocks, and sand. 
     
     
         5 . The apparatus of  claim 1 , wherein the retention formations are ribs formed on the inner surface. 
     
     
         6 . The apparatus of  claim 1 , wherein the retention formations are protrusions formed on the inner surface. 
     
     
         7 . The apparatus of  claim 1 , wherein the retention formations are grooves formed in the inner surface. 
     
     
         8 . A propeller blade comprising:
 a propeller body defining a taper bore surface that, in turn, defines a taper bore cavity;   a balancing tube that is arranged within the taper bore cavity and defines a balancing tube cavity; and   a taper bore insert that is configured to be received in the balancing tube cavity and includes:   a tapered outer surface that is dimensioned and configured to fit within and be of substantially a same size and shape as the balancing tube cavity; and   an inner surface that defines an inner cavity configured to receive a balancing medium and includes a plurality of retention formations arranged thereon and configured to support the balancing medium.   
     
     
         9 . The propeller blade of  claim 8 , wherein the balancing medium is arranged within the inner cavity and includes a filler material and balancing material. 
     
     
         10 . The propeller blade of  claim 9 , wherein the filler material is a binder, adhesive, elastomer, gel, sealant, or wax. 
     
     
         11 . The propeller blade of  claim 9 , wherein the balancing material is at least one of metal shot, metal pellets, ceramic shot, ceramic pellets, rocks, and sand. 
     
     
         12 . The propeller blade of  claim 8 , wherein the propeller blade comprises further a support body that is proximate the propeller body and includes a pitch change portion configured to change a pitch of the propeller body. 
     
     
         13 . The propeller blade of  claim 8 , wherein the balancing tube is formed of aluminum, titanium, an alloy of titanium, or an alloy of aluminum. 
     
     
         14 . The propeller blade of  claim 8 , wherein the plurality of retention formations are a plurality of ribs formed on the inner surface. 
     
     
         15 . The propeller blade of  claim 8 , wherein the retention formations protrusions formed on the inner surface. 
     
     
         16 . The propeller blade of  claim 8 , wherein the retention formations are grooves formed in the inner surface. 
     
     
         17 . An aircraft propeller system comprising:
 a propeller hub;   a first aircraft propeller blade that is arranged on the propeller hub; and   a second aircraft propeller blade that is arranged on the propeller hub, wherein each of the first and second aircraft propeller blades includes:
 a propeller body defining a taper bore surface that, in turn, defines a taper bore cavity; 
 a balancing tube that is arranged within the taper bore cavity and defines a balancing tube cavity; and 
 a taper bore insert that is configured to be received in the balancing tube cavity and includes:
 a tapered outer surface that is dimensioned and configured to fit within and be of substantially a same size and shape as the balancing tube cavity; and 
 an inner surface that defines an inner cavity configured to receive a balancing medium and includes a plurality of retention formations arranged thereon and configured to support the balancing medium. 
 
   
     
     
         18 . The system of  claim 17 , wherein the first and second aircraft propeller blades include further the balancing medium arranged within respective inner cavities and the balancing medium includes a filler material and balancing material. 
     
     
         19 . The system of  claim 18 , wherein the filler material is an adhesive, elastomer, gel, sealant, or wax. 
     
     
         20 . The system of  claim 18 , wherein the balancing material is at least one of metal shot, metal pellets, ceramic shot, ceramic pellets, rocks, and sand.