Abstract: A process for protecting an article using an anti-icing coating includes the steps of applying upon at least one surface of an article an anti-icing composition comprising at least one polysiloxane free of additives; and curing the anti-icing composition to form an anti-icing coating exhibiting an ice shear strength of about 19 kPA to about 50 kPa.

Abstract: A hollow fan blade for a gas turbine engine provides improved resistance to buckling without adding wall thickness. The hollow fan blade includes a pressure side wall and a suction side wall separated and supported by ribs. In the present invention, each wall segment between each adjacent pair of ribs is straight, not curved. At least some of the adjacent walls segments extend at non-parallel angles relative to one another to form the airfoil shape to the hollow fan blade. The resulting fan blade side walls have faceted surfaces, rather than a continuous smooth, curved surface. The straight wall segments between adjacent ribs can withstand higher compressive forces without buckling. As a result, the wall thickness can be reduced.

Abstract: Hollow fan blades for turbo fan gas turbine engines are formed of two separate detail halves. Each detail half has a plurality of cavities machined out to reduce weight and form ribs. The ribs extend continuously and without intersecting one another in order to facilitate machining. The ribs extend in different directions in different regions of the detail half. In at least one region, the ribs extend in a serpentine pattern, such that concatenated rib segments are substantially perpendicular to one another, thereby providing stiffness in multiple directions.

Abstract: Hollow fan blades for turbo fan gas turbine engines are formed of two separate detail halves. Each detail half has a plurality of cavities and ribs machined out to reduce weight. The floor and opposite interior walls of each cavity are machined simultaneously. The configuration minimizes the number of cutter plunge cuts for the internal cavities, and maximizes cutter size, in order to minimize the time required to machine them. These detail halves are subsequently bonded and given an airfoil shape in the forming operation.

Abstract: Hollow fan blades for turbo fan gas turbine engines are formed of two separate detail halves. Each detail half has a plurality of cavities and ribs machined out to reduce weight. These detail halves are subsequently bonded and given an airfoil shape in the forming operation. In the present invention, the ribs are oriented biased to provide stiffness as needed in different sections of the fan blade with smooth transitions between regions. The ribs and cavities do not run solely radially or chordwise, but curve and change direction. The path of each cavity is curved sufficiently to eliminate any regions with long, straight cavities, which would have low inertia in cross sections through the cavity parallel to the rib. Preferably, cavities do not continue straight in any direction for lengths greater than half the blade chord (e.g. leading edge to trailing edge) before curvature causes the rib to intersect cross section.

Abstract: Hollow fan blades for turbo fan gas turbine engines are formed of two separate detail halves. Each detail half has a plurality of cavities and ribs machined out to reduce weight. These detail halves are subsequently bonded and given an airfoil shape in the forming operation. In the present invention, the ribs are oriented biased to provide stiffness as needed in different sections of the fan blade with smooth transitions between regions. The result is a blade with good protection from a wide spectrum of external threats.

Abstract: Hollow fan blades for turbo fan gas turbine engines are formed of two separate detail halves. Each detail half has a plurality of cavities and ribs machined out to reduce weight. These detail halves are subsequently bonded and given an airfoil shape in the forming operation. In one embodiment, contiguous cavities are formed around freestanding ends of the ribs to reduce the number of cavities required. The freestanding end of each rib is flared such that it has a larger width than the rest of the rib. The cavity extends continuously around the free, flared end of the rib.

Abstract: A hollow fan blade for turbo fan gas turbine engines is formed of two separate detail halves. Each detail half has a plurality of cavities and ribs machined out to reduce weight. These detail halves are subsequently bonded and given an airfoil shape in the forming operation. The present invention provides a hollow fan blade with internal cavity and rib geometry with improved durability that permits the bonding and forming to be performed without the need for gas pressurization. The ability to form the hollow fan blade of the present invention without gas pressurization is a result of the cavity and rib geometry and the orientation of the ribs. The ribs are tapered and transition into a compound radius of the floor that simulates the classical arch design element. The orientation of the ribs is generally in a parallel plane with the load vector that results from forming loads during the pre-form and final form operations.

Abstract: A level meter for motor vehicle fuel tanks comprises a float element. With the float element, a lever is connected that is adapted to be pivoted about a pivot axis. Further, the level meter comprises a position sensor as well as a position transmitter connected with the lever. At the level of the position sensor, the position transmitter is connected with the lever. The position transmitter cooperates with the position sensor in a contactless manner.

Abstract: A level meter for motor vehicle fuel tanks comprises a float element (26). With the float element (26), a lever (18) is connected that is adapted to be pivoted about a pivot axis (28). Further, the level meter comprises a position sensor (10) as well as a position transmitter (16) connected with the lever (18). At the level of the position sensor (10), the position transmitter (16) is connected with the lever (18). According to the invention, the position transmitter (16) cooperates with the position sensor (10) in a contactless manner.

Abstract: A fan blade (34) of a gas turbine engine (10) includes a pair of root rails (54) disposed on a bottom (56) of a dovetail root portion (44) thereof. The pair of root rails (54) has a wedge-shaped contour and is tapered in a decreasing cross-section from the leading edge (50) to the trailing edge (52). The root rails (54) provide a wide, stable base for the blade to minimize tangential motion during windmilling. A pair of slot rails (76) is provided on the base (70) of a dovetail-shaped slot (40) retaining the dovetail root portion (44) of the blade (34). The slot rails (76) of the dovetail slot (40) mate with the root rails (54) of the dovetail root portion (44).

Abstract: A fan blade (34) of a gas turbine engine (10) includes a pair of root rails (54) disposed on a bottom (56) of a dovetail root portion (44) thereof. The pair of root rails (54) has a wedge-shaped contour and is tapered in a decreasing cross-section from the leading edge (50) to the trailing edge (52). The root rails (54) provide a wide, stable base for the blade to minimize tangential motion during windmilling. A pair of slot rails (76) is provided on the base (70) of a dovetail-shaped slot (40) retaining the dovetail root portion (44) of the blade (34). The slot rails (76) of the dovetail slot (40) mate with the root rails (54) of the dovetail root portion (44).