A turbine vane includes an airfoil having a leading edge and a trailing edge, an inner shroud disposed at one end of the airfoil to support the airfoil, and an outer shroud disposed opposite to the inner shroud at the other end of the airfoil to support the airfoil, wherein a corner part is formed at a portion where the airfoil and the inner shroud or the outer shroud meet, the corner part including a first round portion connected in an arc shape to the inner shroud or the outer shroud, a first inclined portion connected to the first round portion and outwardly extending in an inclined shape, and a second round portion connected to the first inclined portion and outwardly extending in an arc shape.

Disclosed herein is an interlocking shroud assembly for a turbine engine with a plurality of radially extending, circumferentially spaced airfoils terminating in a shroud element and having opposing radial sides with first and second interlock elements. Further provided is a method of forming a shroud about a plurality of rotating blades in a turbine engine.

A component pair is provided. The component pairs includes a first component comprising a first mating surface defining a first geometry associated with a geometric key, and a second component comprising a second mating surface defining a second geometry, the second geometry being determined using the geometric key and being complementary to the first geometry. The first component and the second component may be properly mated together only when the first geometry is received by the second geometry.

A gas turbine engine 10 is provided in which a fan having fan blades 139 in which the camber distribution relative to covered passage of the fan 13 allows the gas turbine engine to operate with improved efficiency when compared with conventional engines, whilst retaining an acceptable flutter margin.

A turbine blade includes a blade extending from a platform to a free end and having an airfoil-shaped cross section, the blade including a leading edge, a trailing edge, a pressure side extending from the leading edge to the trailing edge, and a suction side extend-ing from the leading edge to the trailing edge, one or more internal cooling passages through which cooling air flows, a trailing edge slot formed along the trailing edge and con-nected to the internal cooling passage, and a pin-fin array including a plurality of pin-fins positioned in the internal cooling passage connected to the trailing edge slot, each pin-fin including a main body and chamfered or filleted portions respectively connected to the pressure side and the suction side at respective ends of the main body, wherein among the pin-fins of the pin-fin array, a portion of the pin-fins have relatively large chamfered or filleted portions as compared with remaining pin-fins.

A method of forming a mated component pair includes forming a first geometry on a first mating surface of a first component and a complementary second geometry on a second mating surface of a second component. The first geometry and the second geometry can be determined from a geometric key associated with a component identifier, e.g., by inputting the geometric key into a mathematical algorithm or random number generator. When a replacement for the second component is needed, the component identifier may be obtained from the first component, the component identifier may be used to obtain the geometric key, and the geometric key may then be used to determine the second geometry. The second geometry may then be formed on the second component such the second component may properly mate with the mated first component.

A gas turbine engine 10 is provided in which a fan having fan blades 139 in which the camber distribution relative to covered passage of the fan 13 allows the gas turbine engine to operate with improved efficiency when compared with conventional engines, whilst retaining an acceptable flutter margin.

A method of forming a mated component pair includes forming a first geometry on a first mating surface of a first component and a complementary second geometry on a second mating surface of a second component. The first geometry and the second geometry can be determined from a geometric key associated with a component identifier, e.g., by inputting the geometric key into a mathematical algorithm or random number generator. When a replacement for the second component is needed, the component identifier may be obtained from the first component, the component identifier may be used to obtain the geometric key, and the geometric key may then be used to determine the second geometry. The second geometry may then be formed on the second component such the second component may properly mate with the mated first component.

A gas turbine engine 10 is provided in which a fan having fan blades 139 in which the camber distribution relative to covered passage of the fan 13 allows the gas turbine engine to operate with improved efficiency when compared with conventional engines, whilst retaining an acceptable flutter margin.

A gas turbine engine 10 is provided in which a fan having fan blades 139 in which the camber distribution relative to covered passage of the fan 13 allows the gas turbine engine to operate with improved efficiency when compared with conventional engines, whilst retaining an acceptable flutter margin.