Abstract: The present invention relates to a lever for adjusting an adjustable vane of a turbomachine, wherein the lever has a fulcrum for the rotatable mounting of the lever about an axis of rotation, a first load arm with a first adjusting connection point for at least indirect connection to an adjustable vane and a first force arm with a first actuating connection point for connection to an adjusting device, wherein the lever further has a first strut, which connects the first adjusting connection point and the first actuating connection point to each other and thereby extends in an arc-shaped manner about the axis of rotation.

Abstract: The present invention relates to a lever for adjusting an adjustable vane of a turbomachine, wherein the lever has a fulcrum for the rotatable mounting of the lever about an axis of rotation, a first load arm with a first adjusting connection point for at least indirect connection to an adjustable vane and a first force arm with a first actuating connection point for connection to an adjusting device, wherein the lever further has a first strut, which connects the first adjusting connection point and the first actuating connection point to each other and thereby extends in an arc-shaped manner about the axis of rotation.

Abstract: A connecting structure (10) for load transfer, in particular in a gas turbine (1), including a strut (20) and at least one wall element (30) is provided. The strut (20) at one end is integrally joined to the wall element (30), and the strut (20) and the wall element (30) are enclosed by a fillet (40), at least in areas, and integrally joined to same. An elastic deformation of the involved elements of the structure during the load transfer and/or load absorption is improved in that a root section (50) that is formed by a ridge (56) and that extends from the strut (20) to the wall element (30) is situated on the fillet (40).

Abstract: A guide blade arrangement (20) for a turbomachine (1), including a guide blade airfoil (22) and a platform (21). The guide blade airfoil (22) is situated at a side (21.1) of the platform (21) facing the gas channel, an opposite side (21.2) of the platform (21) facing away from the gas channel being contoured at least in one area (30.1, 30.2) with elevations (25) and depressions (26) that follow one another in the circumferential direction (23) in relation to a longitudinal axis (2) of the turbomachine (1), and the elevations (25) and depressions (26) at the side (21.2) facing away from the gas channel being set via a platform thickness (31), taken radially in each case, that is variable in the circumferential direction (23) and that repeatedly increases and decreases with a continuous profile.

Abstract: An adjustment lever adjusts a stator vane of a turbomachine. The adjustment lever has: a first connection site, of a plurality of connection sites, the first connection site being configured to join to an adjustment ring; a second connection site, of the connection sites, the second connection stie being configured to join to the stator vane; and a joining member arranged between the first connection site and the second connection site. The joining member is shaped having at least two struts which adjoin at least one of the connection sites.

Abstract: A gas turbine component, in particular a stator vane cluster (10), having at least one radial flange (12, 13) with a radial slot (20) for spoke-type centering of a gas turbine element, in particular an inner ring (100), the radial slot (20) having a first slot flank (21), a slot base (23) adjoining the same, and a second slot flank (22) adjoining the same, the slot base (23) being asymmetric with respect to a mid-plane (M) which extends radially and perpendicularly to the circumferential direction and centrally between the two slot flanks (21, 22).

Abstract: A gas turbine component, in particular a stator vane cluster (10), having at least one radial flange (12, 13) with a radial slot (20) for spoke-type centering of a gas turbine element, in particular an inner ring (100), the radial slot (20) having a first slot flank (21), a slot base (23) adjoining the same, and a second slot flank (22) adjoining the same, the slot base (23) being asymmetric with respect to a mid-plane (M) which extends radially and perpendicularly to the circumferential direction and centrally between the two slot flanks (21, 22).

Abstract: The present invention relates to a gas turbine casing arrangement having a gas turbine casing element (10), a guide-vane ring with an outer ring (20), and a coated ring (30), which lies radially opposite a rotor grid (40) adjacent to the guide-vane ring, whereby an intermediate ring (50) by a downstream front face (51) engages behind an upstream stop (61; 61?) fixed in place on the casing element, and by an upstream front face (52) of a radial flange (53) of the intermediate ring engages behind a downstream stop (22) fixed in place on the outer ring, in order to secure the guide-vane ring axially at the gas turbine casing element in the direction of through-flow.

Abstract: The present invention relates to a gas turbine casing arrangement having a gas turbine casing element (10), a guide-vane ring with an outer ring (20), and a coated ring (30), which lies radially opposite a rotor grid (40) adjacent to the guide-vane ring, whereby an intermediate ring (50) by a downstream front face (51) engages behind an upstream stop (61; 61?) fixed in place on the casing element, and by an upstream front face (52) of a radial flange (53) of the intermediate ring engages behind a downstream stop (22) fixed in place on the outer ring, in order to secure the guide-vane ring axially at the gas turbine casing element in the direction of through-flow.

Abstract: The present invention relates to oligomeric tetraalkylpiperidine light stabilizers for polymers, to the preparation thereof from known polyalkyldiazaspirodecanes and epoxides, and to the use thereof for stabilizing polymers against the damaging effect of light, heat and oxygen.

Abstract: Novel diazaspirodecanes of the general formula ##STR1## are prepared from known diazaspirodecane compounds and epoxy compounds or by reacting diazaspirodecane-substituted epoxy compounds with alcohols or amines and are excellent light stabilizers for synthetic polymers.

Abstract: 1-Oxa-3,8-diaza-4-oxo-spiro-[4,5]-decane compounds of the formula ##STR1## are new light stabilizers for protecting polymers from the damaging effect of UV radiation.

Abstract: 1-Oxa-3-oxo-4,8-diaza-spiro[4,5]decane compounds of the formula ##STR1## are novel light stabilizers for protecting polymers from the damaging effect of UV radiation.

Abstract: The reaction for the preparation of 1-oxa-3,8-diaza-4-oxo-spiro[4.5]decane compounds of the formula ##STR1## proceeds more rapidly and more completely if it is performed in the presence of a phase transfer catalyst in an aromatic hydrocarbon which is liquid at room temperature.