Abstract: This disclosure relates to thermoplastic polyurethane (TPU) powders derived from expanded TPU and/or molding part thereof, wherein the average particle size D50 of the powders is no more than 1 mm, to a 3D molding formed from the same and to a process of forming the 3D molding. The TPU powders of the present invention can be used to prepare 3D products with low density, high rebound resilience and good mechanical properties, and the TPU powders of the present invention can be derived from a wide range of sources, and the TPU powders and 3D products of the present invention can be easily reused.

Abstract: This disclosure relates to thermoplastic elastomer (TPE) powders, wherein the average particle size D50 of the TPE powders is in the range from 10 ?m to 1 mm and at least one of average sphericity A and average sphericity B of TPE powders is no more than 0.6; to a process of preparing the TPE powders and to a method of preparing the 3D molding. The powders and the method according to the present invention allow to prepare a 3D molding with low density, high rebound resilience and good mechanical properties, especially a 3D molding comprising multiple areas having different properties.

Abstract: The present invention relates to a curable composition for 3D-printing, which comprises: (A) at least one reactive component: (B) at least one physical volatile agent; and (C) at least one photoinitiator, a process of forming a 3D-printed object from the same and a 3D-printed object prepared therefrom. The 3D-printed object formed from the composition has reduced density, stable dimension size, and uniform porous structure.

Abstract: The present disclosure relates to a thermoplastic pulverulent composition comprising (a) at least one silica particle treated with alkoxysilane; and (b) at least one thermoplastic polymer. The present disclosure also relates to a 3D-printed object formed from the thermoplastic pulverulent composition and a process of forming the 3D-printed object. The thermoplastic pulverulent composition shows good powder flowability and the printed object obtained from said thermoplastic pulverulent composition surprisingly shows high elongation at break, high impact strength, good toughness and low surface roughness.

Abstract: A blade or vane arrangement for a gas turbine engine has an array of aerofoils mounted to respective platforms about an axis and defining a passage through which a working gas flow passes. The arrangement has a datum and the aerofoil has a radial span. Each aerofoil has pressure side, a suction side, a leading edge region and a leading edge foot extending from the leading edge region, the leading edge foot has a ridge line. The platform defines a channel and a platform leading edge, the channel has a minimum radial height line, and the platform leading edge partly defines an outlet through which a secondary flow passes. The ridge line is aligned generally in the direction of the working gas flow and the minimum radial height line is aligned generally in the direction of the secondary flow.

Abstract: A turbine arrangement and a gas turbine engine including a rim seal is configured with two cavities. The main fluid path, the two cavities, and a disc space are furthermore separated from another, but still in fluid communication with another, via three annular seal passages. The turbine arrangement also includes a plurality of cooling fluid injectors arranged underneath a radially inner vane platform. The rim seal is configured for an upstream guide vane and a downstream rotor blade.

Abstract: A turbine arrangement and a gas turbine engine comprising a rim seal is configured with two cavities. The main fluid path, the two cavities, and a disc space are furthermore separated from another, but still in fluid communication with another, via three annular seal passages. A rim seal is configured for an upstream rotor blade and a downstream guide vane. The seal arrangement includes a trailing edge of the inner blade platform, a leading edge of the inner vane platform and a first annular cavity and a second annular cavity.

Abstract: A blade or vane arrangement for a gas turbine engine has an array of aerofoils mounted to respective platforms about an axis and defining a passage through which a working gas flow passes. The arrangement has a datum and the aerofoil has a radial span. Each aerofoil has pressure side, a suction side, a leading edge region and a leading edge foot extending from the leading edge region, the leading edge foot has a ridge line. The platform defines a channel and a platform leading edge, the channel has a minimum radial height line, and the platform leading edge partly defines an outlet through which a secondary flow passes. The ridge line is aligned generally in the direction of the working gas flow and the minimum radial height line is aligned generally in the direction of the secondary flow.

Abstract: Described is a gas turbine diffuser (300) comprising a strut (302) with a leading edge (304) extending between a first wall portion (308a) and a second wall portion (308b), wherein a first edge portion (304a) of the leading edge (304) is inclined towards a diffuser section outlet (326), i.e. in flow direction (328) of an exhaust stream, with regard to a normal direction (319a) perpendicular to the first wall portion (308a) at a first leading end point (320a) at which the leading edge (304) meets the first wall portion (308). Hence the leading edge (304) is partially inclined towards a diffuser section outlet (326).

Abstract: A turbine arrangement and a gas turbine engine including a rim seal is configured with two cavities. The main fluid path, the two cavities, and a disc space are furthermore separated from another, but still in fluid communication with another, via three annular seal passages. The turbine arrangement also includes a plurality of cooling fluid injectors arranged underneath a radially inner vane platform. The rim seal is configured for an upstream guide vane and a downstream rotor blade.

Abstract: A turbine arrangement and a gas turbine engine comprising a rim seal is configured with two cavities. The main fluid path, the two cavities, and a disc space are furthermore separated from another, but still in fluid communication with another, via three annular seal passages. A rim seal is configured for an upstream rotor blade and a downstream guide vane. The seal arrangement includes a trailing edge of the inner blade platform, a leading edge of the inner vane platform and a first annular cavity and a second annular cavity.

Abstract: A compressor vane or compressor blade is provided. The axial flow compressor includes an axial direction, a radial direction, a compressor hub and a compressor casing. The vane or blade includes an airfoil with airfoil sections having a span, a chamber line and a leading edge at which the chamber line includes a leading edge blade angle with the axial direction of the compressor and a trailing edge at which the chamber line includes a trailing edge blade angle with the axial direction of the compressor. The airfoil sections are stacked at the leading edge on a straight line extending along a radial direction of the compressor from the compressor hub towards a compressor casing and in that the leading edge angles of the airfoil sections vary along the span and are larger for airfoil sections close to the hub and close to the wall than for mid-span airfoil sections.

Abstract: Described is a gas turbine diffuser (300) comprising a strut (302) with a leading edge (304) extending between a first wall portion (308a) and a second wall portion (308b), wherein a first edge portion (304a) of the leading edge (304) is inclined towards a diffuser section outlet (326), i.e. in flow direction (328) of an exhaust stream, with regard to a normal direction (319a) perpendicular to the first wall portion (308a) at a first leading end point (320a) at which the leading edge (304) meets the first wall portion (308). Hence the leading edge (304) is partially inclined towards a diffuser section outlet (326).

Abstract: A compressor vane or compressor blade is provided. The axial flow compressor includes an axial direction, a radial direction, a compressor hub and a compressor casing. The vane or blade includes an airfoil with airfoil sections having a span, a chamber line and a leading edge at which the chamber line includes a leading edge blade angle with the axial direction of the compressor and a trailing edge at which the chamber line includes a trailing edge blade angle with the axial direction of the compressor. The airfoil sections are stacked at the leading edge on a straight line extending along a radial direction of the compressor from the compressor hub towards a compressor casing and in that the leading edge angles of the airfoil sections vary along the span and are larger for airfoil sections close to the hub and close to the wall than for mid-span airfoil sections.