Abstract: A gas turbine engine includes coaxially arranged shafts mounted in a bearing chamber. An interior of the bearing chamber is sealed via sealing units which can be loaded with blocking air on sides facing away from the interior. The pressure of the blocking air is in each case greater than the pressure in the bearing chamber. An intermediate shaft sealing unit is provided radially between the shafts, and can be loaded with the blocking air on both sides in the axial direction, and seals a region between the shafts, adjoining the bearing chamber, from a further region between the shafts. Regions carrying blocking air, in which different pressure levels prevail during operation, are connected together for immediate pressure balance via openings on the side of the intermediate shaft sealing unit facing the sealing units, and on the side of the intermediate shaft unit facing away from the sealing units.

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: 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.