Abstract: A case body of a fan case in a jet engine is formed by use of a composite material of carbon fiber reinforced plastic. Metal rings are respectively attached to a leading edge and a trailing edge of the case body. The metal rings are electrically connected together by a conductive cable. Both of the metal rings and the conductive cable constitute a path of a lightning current.

Abstract: A cylindrical case main body, and a connecting ring body fitted and fixed to a first end of the case main body and having an annular groove open in the centrifugal direction, are provided. The connecting ring body has a notch open to a side opposite to a second end of the case main body. Into the notch of the connecting ring body, a reinforcement body is fitted, and the reinforcement body has an arc-shaped groove continuing to the annular groove of the connecting ring body in a state where the reinforcement body is fitted into the notch of the connecting ring body. In addition to attaining high rigidity, reduction in weight and reduction in manufacturing cost can also be achieved.

Abstract: A cylindrical case body made of a composite material; a linking ring made of aluminum, fitted and fixed to a rear end portion of the case body and having an annular groove which receives a reverse thrust load from a reverse thrust transmission body; and ring constituent bodies made of titanium alloy, each of which is placed in the rear end portion of the case body and has an arcuate groove which undertakes a reverse thrust load larger than that received by the linking ring, are provided in a fan case. The ring constituent bodies are fitted in notches of the linking ring and are brought into contact with outward receiving walls of the linking ring. The ring constituent bodies are positioned relative to the case body in the axis direction and in the radial direction, and the annular groove and the arcuate grooves continue to each other.

Abstract: A cylindrical case includes a case main body, and a groove disposed annularly at one end of the case main body. A peripheral wall of the case main body is formed by alternately laminating a biaxial fabric layer, which includes a biaxial fabric of a non-crimp structure composed of reinforcing fiber bands having an orientation angle of ±45°, and a roving layer. A groove wall of the groove is formed by alternately laminating the biaxial fabric layer, which continues to the case main body side, and a triaxial fabric layer, which includes a triaxial fabric of a non-crimp structure composed of reinforcing fiber bands having an orientation angle of ±45° and a reinforcing fiber band having an orientation angle of 0°.

Abstract: An additional pad 27 is additionally and integrally arranged from an outer surface of a flange 17 opposite to a contacting side of the flange 17 to a small-diameter curved surface of a bend 19 and from there to an end of an outer surface of a part body 13. On an outer surface side of the additional pad 27, a fastening seat 27f is formed by machining. An area end PAe of a processed area PA formed by machining is positioned on the part body 13 beyond the bend 19.

Abstract: A case body of a fan case in a jet engine is formed by use of a composite material of carbon fiber reinforced plastic. Metal rings are respectively attached to a leading edge and a trailing edge of the case body. The metal rings are electrically connected together by a conductive cable. Both of the metal rings and the conductive cable constitute a path of a lightning current.

Abstract: A cylindrical case main body, and a connecting ring body fitted and fixed to a first end of the case main body and having an annular groove open in the centrifugal direction, are provided. The connecting ring body has a notch open to a side opposite to a second end of the case main body. Into the notch of the connecting ring body, a reinforcement body is fitted, and the reinforcement body has an arc-shaped groove continuing to the annular groove of the connecting ring body in a state where the reinforcement body is fitted into the notch of the connecting ring body. In addition to attaining high rigidity, reduction in weight and reduction in manufacturing cost can also be achieved.

Abstract: A cylindrical case body made of a composite material; a linking ring made of Al, which is fitted and fixed to a rear end portion of the case body and has an annular groove which receives a reverse thrust load from a reverse thrust transmission body; and ring constituent bodies made of Ti alloy, each of which is placed in the rear end portion of the case body and has an arcuate groove which undertakes a reverse thrust load larger than that received by the linking ring, are included. The ring constituent bodies are fitted in notches of the linking ring and are brought into contact with, and are fixed to, outward receiving walls of the linking ring, whereby the ring constituent bodies are positioned relative to the case body in the axis direction and in the radial direction respectively, and the annular groove and the arcuate grooves are allowed to continue to each other. The ring constituent bodies made of Ti alloy, which receive a large reverse thrust load, can be placed with high positioning accuracy.

Abstract: A cylindrical case includes a case main body, and a groove disposed annularly at one end of the case main body. A peripheral wall of the case main body is formed by alternately laminating a biaxial fabric layer, which includes a biaxial fabric of a non-crimp structure composed of reinforcing fiber bands having an orientation angle of ±45°, and a roving layer. A groove wall of the groove is formed by alternately laminating the biaxial fabric layer, which continues to the case main body side, and a triaxial fabric layer, which includes a triaxial fabric of a non-crimp structure composed of reinforcing fiber bands having an orientation angle of ±45° and a reinforcing fiber band having an orientation angle of 0°.

Abstract: An additional pad 27 is additionally and integrally arranged from an outer surface of a flange 17 opposite to a contacting side of the flange 17 to a small-diameter curved surface of a bend 19 and from there to an end of an outer surface of a part body 13. On an outer surface side of the additional pad 27, a fastening seat 27f is formed by machining. An area end PAe of a processed area PA formed by machining is positioned on the part body 13 beyond the bend 19.

Abstract: A method for manufacturing a cylindrical structure having an axial direction includes: winding a first layer around a mandrel; winding a second layer around the mandrel; winding a third layer around the mandrel; and joining the layers together by using a resin. Each layer includes a plurality of fabrics each made of fibers. The fabrics of each layer form a join line extending in a circumferential direction with edges of the fabrics in contact with each other. The join lines of the first, second and third layers are displaced in the axial direction from one another.

Abstract: A shroud segment is incorporated in a gas turbine engine so as to suppress influence of hot combustion gas on a turbine case which has a groove and a hook for engagement with the shroud segment. The shroud segment is provided with a back plate formed in an arc shape, a front end of the back plate being supported by the groove so as to allow displacement in an axial direction of the gas turbine engine, a slot circumferentially formed on an outer surface of the back plate, the slot being engaged with the hook so as to be immovable in the axial direction and a touching member integrally formed on an inner surface of the back plate for touching with a rotating turbine blade. The slot is configured so as to satisfy an inequality of v<t?(v+0.1 mm), where v is a length of the hook and t is a width of the slot.

Abstract: A shroud segment for being incorporated in a gas turbine engine so as to suppress influence of hot combustion gas on a turbine case of the gas turbine engine is provided with a back plate having first and second plate portions formed in an arc shape and supported by the turbine case, a touching member integrally formed on an inner surface of the back plate for touching with a rotating turbine blade, a pair of first seal slots for receiving a pair of first spline seal plate, a pair of second seal slots for receiving a pair of second spline seal plate and a pair of seal gaps respectively communicating with the first seal slots and the second seal slots. The seal gaps are respectively provided with abutment surfaces recessed from front surfaces of the second seal slots so as to receive front ends of the first spline seal plates.

Abstract: A shroud segment for being incorporated in a gas turbine engine having a turbine case and a rear turbine case connected with a rear end of the turbine case so as to suppress influence of hot combustion gas on the turbine case and the rear turbine case, is provided with a back plate formed in an arc shape and supported by the turbine case, a touching member integrally formed on an inner surface of the back plate for touching with a rotating turbine blade; and a jet shield extended from a rear end of the back plate and slanted radially inward so as to shield the rear turbine case from a jet of the hot combustion gas.

Abstract: A shroud segment for being incorporated in a gas turbine engine so as to suppress influence of hot combustion gas on a turbine case of the gas turbine engine is provided with a back plate having first and second plate portions formed in an arc shape and supported by the turbine case, a touching member integrally formed on an inner surface of the back plate for touching with a rotating turbine blade, a pair of first seal slots for receiving a pair of first spline seal plate, a pair of second seal slots for receiving a pair of second spline seal plate and a pair of seal gaps respectively communicating with the first seal slots and the second seal slots. The seal gaps are respectively provided with abutment surfaces recessed from front surfaces of the second seal slots so as to receive front ends of the first spline seal plates.

Abstract: A shroud segment for being incorporated in a gas turbine engine having a turbine case and a rear turbine case connected with a rear end of the turbine case so as to suppress influence of hot combustion gas on the turbine case and the rear turbine case, is provided with a back plate formed in an arc shape and supported by the turbine case, a touching member integrally formed on an inner surface of the back plate for touching with a rotating turbine blade; and a jet shield extended from a rear end of the back plate and slanted radially inward so as to shield the rear turbine case from a jet of the hot combustion gas.

Abstract: A shroud segment is incorporated in a gas turbine engine so as to suppress influence of hot combustion gas on a turbine case which has a groove and a hook for engagement with the shroud segment. The shroud segment is provided with a back plate formed in an arc shape, a front end of the back plate being supported by the groove so as to allow displacement in an axial direction of the gas turbine engine, a slot circumferentially formed on an outer surface of the back plate, the slot being engaged with the hook so as to be immovable in the axial direction and a touching member integrally formed on an inner surface of the back plate for touching with a rotating turbine blade. The slot is configured so as to satisfy an inequality of v<t?(v+0.1 mm), where v is a length of the hook and t is a width of the slot.