Abstract: The present disclosure provides an improved second stage airfoil for a compressor blade having a unique chord length (CD) stagger angle (?) and camber angle (??). The stagger angle (?) and camber angle (??) provide improved aerodynamics while the chord length (CD) provides for reduced airfoil weight.

Abstract: A compressor has a rotor (13), which rotor (13) has a number of rows of rotor blades (14, 14?) which are at a distance from one another, one behind the other in the axial direction, with a number of thermal barrier segments (10), which are detachably attached to the rotor (13) and are mounted such that they can move in the circumferential direction, being arranged one behind the other in the circumferential direction on the circumference of the rotor (13), and with securing devices (15) being provided on the thermal barrier segments (10), which secure the thermal barrier segments (10) against being moved in the circumferential direction. In the case of such a rotor (13), production and assembly are simplified in that only some of the thermal barrier segments (10) are equipped with the securing devices (15).

Abstract: The present disclosure provides an improved second stage airfoil for a compressor blade having a unique chord length (CD), a stagger angle (?), and camber angle (??). The stagger angle (?) and camber angle (??) provide improved aerodynamics while the chord length (CD) provides for reduced airfoil weight.

Abstract: The present disclosure provides an improved first stage airfoil for a compressor blade having a unique chord length (CD), stagger angle (?) and camber angle (??). The stagger angle (?) and camber angle (??) provide improved aerodynamics while the chord length (CD) provides for reduced airfoil weight.

Abstract: The disclosure provides blades, and the modification thereof, for stages 18-22 of an axial compressor wherein the blades have reduced susceptibility to tip cracking. The blades and blades manufactured by the provided method have a thickened profile that results in reduced stress in response to multi frequency impulses and can have increased frequency response of the chord wise bending mode.

Abstract: A rotor (20) for a compressor, in particular in a gas turbine, has a number of rotor blades (25) which are arranged around the rotation axis of the rotor (20) in the form of a rim and are each held in a circumferential recess (21) on the rotor (20) by a blade root (26), with the blade root (26) having a widening lower part (27) which engages behind two shoulders (24) that are formed on the side walls of the recess (21). In such a rotor, the life is lengthened in that the recess depth (T) of the recess (21) is substantially greater than a minimum recess depth (Tmin) which results in the rotor (20) having sufficient strength in the area of the blade attachment for starting, based on the predetermined material characteristics of the rotor (20) and the operating conditions of the compressor.

Abstract: A rotor end piece (1) for a rotor (6) of a thermal turbomachine, having at least one circumferential slot (3) in which moving blades and intermediate pieces are provided, includes a residual gap (15) formed between an end blade (2) and an end part (11), in which residual gap (15) two end piece halves (4, 4) are arranged which have securing tabs (8, 8) which are in each case connected to the latter in one piece and are in engagement with the end blade (2) and with the end part (11), respectively.

Abstract: A compressor rotor blade (1) includes a rotor blade (2), a platform (3) that adjoins the rotor blade (2) and blade footing (4) that adjoins the platform (3). The rotor blade (4) is embodied so as to be massive, without an internal cooling system, and exhibits a leading and a trailing edge (5, 6), a suction and a compression side, as well as a blade tip (7). The compressor rotor blade (1) is distinguished by virtue of the fact that the rotor blade (2) of the compressor rotor blade (1) exhibits a recess (8) on the trailing edge (6) of the blade tip (7).

Abstract: A rotor end piece (1) for a rotor of a thermal turbomachine, having at least one circumferential slot (3) in which press blades, intermediate pieces and two end blades (4), between which a residual gap is formed, are fitted, the rotor end piece (1) having two end piece halves (9, 9) and a wedge (7), is characterized in that a clip (8) is arranged in the residual gap, this clip (8) absorbing the forces of the two end piece halves (9, 9) and two shim halves (5, 6) arranged between the end piece halves (9, 9) and restrained with the wedge (7). As a result, the disadvantages of the prior art are avoided and a rotor end piece is provided which exerts no axial forces on the rotor and no forces on adjacent blades in the circumferential direction, so that an occurrence of disturbing rotor vibrations and jamming of adjacent blades is effectively avoided.

Abstract: A rotor end piece for a rotor of a thermal turbomachine having a circumferential slot includes two end piece halves having side faces opposite one another in the installed state and top surfaces adjoining one another, the side faces of the end piece halves being connected to one another in a form-fitting manner by means of a dovetail interlocking connection, and a whole intermediate end piece having a top surface, the two interlocked end piece halves being firmly connected to the whole intermediate end piece in the region of the top surfaces via a weld.

Abstract: The invention relates to a rotor end piece (1) for rotors (2) of thermal turbomachines with a circumferential slot (3), consisting of two end piece halves (4, 4?) having side faces (5, 5?) opposite one another in the installed state and of a wedge (6) which is pushed in between them and which, in the installed state, is anchored in the side faces (5, 5?) of the end piece halves (4, 4?) in a form-fitting manner, the rotor end piece (1) being arranged in the axial direction of the rotor (2) between two moving blades (7, 7?). It is characterized in that each of the end piece halves (4, 4?) is fastened in the axial direction of the rotor (2) to the two adjacent moving blades (7, 7?) by means of one interlocking connection (8, 8?, 9, 9?) each. These four interlocking connections (8, 8?, 9, 9?), instead of the rotor (2), now absorb the axial forces which are caused by the centrifugal force and the caulked wedge (6). In this way, disturbing rotor vibrations are advantageously avoided.

Abstract: A rotor end piece for a rotor of a thermal turbomachine having a circumferential slot includes two end piece halves having side faces opposite one another in the installed state and top surfaces adjoining one another, the side faces of the end piece halves being connected to one another in a form-fitting manner by means of a dovetail interlocking connection, and a whole intermediate end piece having a top surface, the two interlocked end piece halves being firmly connected to the whole intermediate end piece in the region of the top surfaces via a weld.

Abstract: A rotor end piece (1) for a rotor (6) of a thermal turbomachine, having at least one circumferential slot (3) in which moving blades and intermediate pieces are provided, includes a residual gap (15) formed between an end blade (2) and an end part (11), in which residual gap (15) two end piece halves (4, 4) are arranged which have securing tabs (8, 8) which are in each case connected to the latter in one piece and are in engagement with the end blade (2) and with the end part (11), respectively.

Abstract: A compressor has a rotor (13), which rotor (13) has a number of rows of rotor blades (14, 14?) which are at a distance from one another, one behind the other in the axial direction, with a number of thermal barrier segments (10), which are detachably attached to the rotor (13) and are mounted such that they can move in the circumferential direction, being arranged one behind the other in the circumferential direction on the circumference of the rotor (13), and with securing devices (15) being provided on the thermal barrier segments (10), which secure the thermal barrier segments (10) against being moved in the circumferential direction. In the case of such a rotor (13), production and assembly are simplified in that only some of the thermal barrier segments (10) are equipped with the securing devices (15).

Abstract: A rotor (20) for a compressor, in particular in a gas turbine, has a number of rotor blades (25) which are arranged around the rotation axis of the rotor (20) in the form of a rim and are each held in a circumferential recess (21) on the rotor (20) by a blade root (26), with the blade root (26) having a widening lower part (27) which engages behind two shoulders (24) that are formed on the side walls of the recess (21). In such a rotor, the life is lengthened in that the recess depth (T) of the recess (21) is substantially greater than a minimum recess depth (Tmin) which results in the rotor (20) having sufficient strength in the area of the blade attachment for starting, based on the predetermined material characteristics of the rotor (20) and the operating conditions of the compressor.

Abstract: A fixing method for blading of a fluid-flow machine, in which first of all the turbine blades (31, 32) are inserted into the fastening slot (1) of a rotor (2) or stator until only the intermediate fitting gap is left, into which two insert elements designed as end piece halves (41, 42) are then inserted. After that, a wedge (6) is inserted into the gap between the end piece halves (41, 42), and the end piece halves (41, 42) together with the wedge (6) are welded by a joining weld (10). With the method according to the invention and the arrangement according to the invention, axial forces which can warp the rotor (2) and thus cause increased rotor vibrations are advantageously avoided. The invention also relates to a fixing arrangement according to the invention.

Abstract: A rotor end piece (1) for a rotor of a thermal turbomachine, having at least one circumferential slot (3) in which press blades, intermediate pieces and two end blades (4), between which a residual gap is formed, are fitted, the rotor end piece (1) having two end piece halves (9, 9) and a wedge (7), is characterized in that a clip (8) is arranged in the residual gap, this clip (8) absorbing the forces of the two end piece halves (9, 9) and two shim halves (5, 6) arranged between the end piece halves (9, 9) and restrained with the wedge (7). As a result, the disadvantages of the prior art are avoided and a rotor end piece is provided which exerts no axial forces on the rotor and no forces on adjacent blades in the circumferential direction, so that an occurrence of disturbing rotor vibrations and jamming of adjacent blades is effectively avoided.

Abstract: A rotor end piece (1) for rotors (2) of thermal turbormachines is provided with circumferential slot (3), including two end piece halves (4, 4?) having side faces (5, 5?) opposite one another in the installed state and top surfaces (6, 6?) adjoining one another. The rotor end piece (1) side faces (5, 5?) of the end piece halves (4,4?) are connected to one another in a form-fitting manner. To this end, the side faces (5, 5?) are designed in such a way that a dovetail interlocking connection of the two end piece halves (4, 4?) is preferably realized. The interlocked end piece halves are then secured with a weld (8). The firm anchoring of the rotor end piece (1) achieved in this way prevents detachment during operation and damage to the turbomachine caused as a result.

Abstract: In a method of improving the flow conditions on the suction side (21) of the blade (12) of an axial-flow compressor (10) provided for compressing air, in which method vortices running in the direction of flow are generated on the suction side (21), a marked improvement is achieved in a simple and reliable manner by the vortices being generated by local air jets (18) formed on the suction side (21).

Abstract: A compressor rotor blade (1) includes a rotor blade (2), a platform (3) that adjoins the rotor blade (2) and blade footing (4) that adjoins the platform (3). The rotor blade (4) is embodied so as to be massive, without an internal cooling system, and exhibits a leading and a trailing edge (5, 6), a suction and a compression side, as well as a blade tip (7). The compressor rotor blade (1) is distinguished by virtue of the fact that the rotor blade (2) of the compressor rotor blade (1) exhibits a recess (8) on the trailing edge (6) of the blade tip (7).