Abstract: Aspects of the disclosure regard a bolt assembly which comprises a bolt extending in a longitudinal direction through a flange connection, the bolt comprising a first portion and a second portion, the first portion comprising a threaded section at a first side of the flange connection and the second portion comprising a head portion at a second side of the flange connection. The bolt assembly further comprises a nut screwed on the threaded section and a spacer arranged between the nut and the flange connection or between the head portion and the flange connection. The bolt is comprised of a titanium alloy.

Abstract: Composite liners (such as acoustic panels, fan track liners, and/or ice impact panels or boxes for turbofan engines) and techniques for forming composite liners. In some examples, the composite liner includes at least one region comprising a reinforcement architecture comprising a matrix material, a plurality of relatively tough polymer-based reinforcement elements, and a plurality of second reinforcement elements. The plurality of relatively tough polymer-based reinforcement elements and the plurality of second reinforcement elements are embedded in the matrix material.

Abstract: A composite aerofoil may include an aerofoil body defining a leading edge and a trailing edge, wherein the body comprises a composite material including a plurality of relatively higher-modulus reinforcement elements, a plurality of relatively tougher polymer-based reinforcement elements, and a matrix material substantially encapsulating the plurality of relatively higher-modulus reinforcement elements and the plurality of relatively tougher polymer-based reinforcement elements. The plurality of relatively higher-modulus reinforcement elements are different from the plurality of relatively tougher polymer-based reinforcement elements. The disclosure also describes techniques for forming composite aerofoils.

Abstract: An airfoil includes a base, a tip, a suction side face, and a pressure side face. The pressure side face includes an outer surface, an inner surface located between the outer surface and the suction side face, and a transition surface that extends between and interconnects the outer surface and the inner surface so as to form a pocket in the airfoil.

Abstract: The disclosure describes composite liners (such as acoustic panels, fan track liners, and/or ice impact panels or boxes for turbofan engines) and techniques for forming composite liners. In some examples, the composite liner includes at least one region comprising a reinforcement architecture comprising a matrix material, a plurality of relatively tough polymer-based reinforcement elements, and a plurality of second reinforcement elements. The plurality of relatively tough polymer-based reinforcement elements and the plurality of second reinforcement elements are embedded in the matrix material.

Abstract: A fan assembly for use in a gas turbine engine of an aircraft includes a fan disk having a number of fan blades and a windage shield coupled to the fan disk to move therewith. The fan assembly supplies air for use in the engine. The windage shield rotates with the fan disk during operation of the gas turbine engine and directs air supplied by the fan blade.

Abstract: An airfoil includes a base, a tip, a suction side face, and a pressure side face. The pressure side face includes an outer surface, an inner surface located between the outer surface and the suction side face, and a transition surface that extends between and interconnects the outer surface and the inner surface so as to form a pocket in the airfoil.

Abstract: A composite aerofoil may include an aerofoil body defining a leading edge and a trailing edge, wherein the body comprises a composite material including a plurality of relatively higher-modulus reinforcement elements, a plurality of relatively tougher polymer-based reinforcement elements, and a matrix material substantially encapsulating the plurality of relatively higher-modulus reinforcement elements and the plurality of relatively tougher polymer-based reinforcement elements. The plurality of relatively higher-modulus reinforcement elements are different from the plurality of relatively tougher polymer-based reinforcement elements. The disclosure also describes techniques for forming composite aerofoils.

Abstract: The disclosure describes composite nosecones and techniques for forming composite nosecones including a matrix material, relatively higher-modulus reinforcement elements, and relatively tougher polymer-based reinforcement elements. An example composite nosecone includes a body substantially symmetrical around a central axis. The body includes a side wall defining a diameter of the body that increases from a forward side of the body to an aft side of the body. The body includes a composite material including a plurality of relatively higher-modulus reinforcement elements, a plurality of relatively tougher polymer-based reinforcement elements, and a matrix material substantially encapsulating the plurality of relatively higher-modulus reinforcement elements and the plurality of relatively tougher polymer-based reinforcement elements. The plurality of relatively higher-modulus reinforcement elements are different from the plurality of relatively tougher polymer-based reinforcement elements.

Abstract: An annulus filler may include an outer lid defining an airflow surface for air being drawn through the engine in an axial airflow direction and a support structure configured to connect the outer lid to a rotor disc. The annulus filler may include a composite material including a plurality of relatively high-modulus reinforcement elements, a plurality of relatively tough polymer-based reinforcement elements, and a matrix material substantially encapsulating the plurality of relatively high-modulus reinforcement elements and the plurality of relatively tough reinforcement elements.

Abstract: A fan case for use in a gas turbine engine of an aircraft includes an outer shroud and a liner extending along the outer shroud. The fan case provides a protective band that blocks fan blades from being thrown out of the fan case in case of a blade-off event in which a fan blade is released during operation of the gas turbine engine.

Abstract: According to one aspect, a fan containment case for a gas turbine engine is provided which includes a barrel having a first band of material on an outside of the barrel. The first band is made of carbon fiber composite. The barrel further includes a second band of material inboard of the fan case and made of poly p-phenylene-2,6-benzobisoxazole (PBO) composite. The barrel also includes a third band of material made of carbon fiber composite inboard of the second band.

Abstract: A soft wall containment system having a casing, a liner system, a containment blanket, and a barrel including multiple features is provided. The soft wall containment system may selectively be installable in a gas turbine engine having a turbine with multiple airfoils. The barrel features may be disposed outboard of the airfoils. The casing barrel may have a first thickness, the casing barrel features may have a second thickness, and the first thickness may be greater than the second thickness. Additionally, the features may be slots that extend through the thickness of the barrel.

Abstract: A fan assembly for use in a gas turbine engine of an aircraft includes a fan disk having a number of fan blades and a windage shield coupled to the fan disk to move therewith. The fan assembly supplies air for use in the engine. The windage shield rotates with the fan disk during operation of the gas turbine engine and directs air supplied by the fan blade.

Abstract: A fan assembly for use in a gas turbine engine of an aircraft includes a fan disk having a number of fan blades and a windage shield coupled to the fan disk to move therewith. The fan assembly supplies air for use in the engine. The windage shield rotates with the fan disk during operation of the gas turbine engine and directs air supplied by the fan blade.

Abstract: The disclosure describes composite nosecones and techniques for forming composite nosecones including a matrix material, relatively higher-modulus reinforcement elements, and relatively tougher polymer-based reinforcement elements. An example composite nosecone includes a body substantially symmetrical around a central axis. The body includes a side wall defining a diameter of the body that increases from a forward side of the body to an aft side of the body. The body includes a composite material including a plurality of relatively higher-modulus reinforcement elements, a plurality of relatively tougher polymer-based reinforcement elements, and a matrix material substantially encapsulating the plurality of relatively higher-modulus reinforcement elements and the plurality of relatively tougher polymer-based reinforcement elements. The plurality of relatively higher-modulus reinforcement elements are different from the plurality of relatively tougher polymer-based reinforcement elements.

Abstract: An annulus filler may include an outer lid defining an airflow surface for air being drawn through the engine in an axial airflow direction and a support structure configured to connect the outer lid to a rotor disc. The annulus filler may include a composite material including a plurality of relatively high-modulus reinforcement elements, a plurality of relatively tough polymer-based reinforcement elements, and a matrix material substantially encapsulating the plurality of relatively high-modulus reinforcement elements and the plurality of relatively tough reinforcement elements.

Abstract: According to one aspect, a flange fastening assembly for a gas turbine engine includes a first flange having a first hole therein, a second flange having a second hole disposed adjacent to the first flange, and a shoulder bolt disposed through the first hole and the second hole. The shoulder bolt has a head portion, a stem portion, and a thread portion, and the stem portion and the thread portion define a shoulder. A bolt nut is disposed on the thread portion and a first spacer is disposed between the bolt nut and the first flange such that the first spacer overhangs the shoulder.

Abstract: A soft wall containment system having a casing, a liner system, a containment blanket, and a barrel including multiple features is provided. The soft wall containment system may selectively be installable in a gas turbine engine having a turbine with multiple airfoils. The barrel features may be disposed outboard of the airfoils. The casing barrel may have a first thickness, the casing barrel features may have a second thickness, and the first thickness may be greater than the second thickness. Additionally, the features may be slots that extend through the thickness of the barrel.

Abstract: According to one aspect, a flange fastening assembly for a gas turbine engine includes a first flange having a first hole therein, a second flange having a second hole disposed adjacent to the first flange, and a shoulder bolt disposed through the first hole and the second hole. The shoulder bolt has a head portion, a stem portion, and a thread portion, and the stem portion and the thread portion define a shoulder. A bolt nut is disposed on the thread portion and a first spacer is disposed between the bolt nut and the first flange such that the first spacer overhangs the shoulder.