Abstract: A wheelchair assembly featuring an adjustable support comprised of two inflatable pillows that are housed in a single cover or separate, discrete covers which are releasably adjoined to each other. The support is releasably attached by adjustable straps to wheelchair armrests and is adapted to provide enhanced support for the user's body and remain stationary when the user's body is rested thereon. The invention is also directed to a wheelchair support comprising two inflatable pillows housed in a single cover or two separate covers. The invention is further directed to a highly adjustable travel pillow comprised of two inflatable cushions that are preferably housed in separate, discrete covers which are releasably adjoined to each other. The back of the travel pillow cover has an anti-skid material to maintain its position.

Abstract: A travel pillow comprising a front having a thin planar portion for receiving the user's head and one or two lateral forwardly projecting cushioning portions. The distance the lateral cushioning portions project forward gradually increases from the thin planar portion to a peripheral portion of the travel pillow in an arced manner. The back of the pillow comprises an anti-skid material such as silicone coated fiberglass weave which keeps the pillow stationary when the user rests his/her head against the pillow. The user places the pillow on the seat and then rest the back of his/her head on the thin planar portion of the pillow. The user can then tilt or turn his/her head in many different positions on a lateral cushion and the pillow will remain stationary.

Abstract: Methods and apparatus for fabricating a rotor blade for a gas turbine engine are provided. The rotor blade includes an airfoil having a first sidewall and a second sidewall, connected at a leading edge and at a trailing edge. The method includes forming the airfoil portion bounded by a root portion at a zero percent radial span and a tip portion at a one hundred percent radial span, the airfoil having a radial span dependent chord length C, a respective maximum thickness T, and a maximum thickness to chord length ratio (Tmax/C ratio), forming the root portion having a first Tmax/C ratio, forming the tip portion having a second Tmax/C ratio, and forming a mid portion extending between a first radial span and a second radial span having a third Tmax/C ratio, the third Tmax/C ratio being less than the first Tmax/C ratio and the second Tmax/C ratio.

Abstract: Methods and apparatus for fabricating a rotor blade for a gas turbine engine are provided. The rotor blade includes an airfoil having a first sidewall and a second sidewall, connected at a leading edge and at a trailing edge. The method includes forming the airfoil portion bounded by a root portion at a zero percent radial span and a tip portion at a one hundred percent radial span, the airfoil having a radial span dependent chord length C, a respective maximum thickness T, and a maximum thickness to chord length ratio (Tmax/C ratio), forming the root portion having a first Tmax/C ratio, forming the tip portion having a second Tmax/C ratio, and forming a mid portion extending between a first radial span and a second radial span having a third Tmax/C ratio, the third Tmax/C ratio being less than the first Tmax/C ratio and the second Tmax/C ratio.