Abstract:
PROBLEM TO BE SOLVED: To provide a shaft rotor section for a stationary gas turbine improved in installing and removing a seal element.SOLUTION: There are provided the rotor section 10, a rotor blade 18 and a block element 46 for a rotor of a gas turbine. The rotor section 10 includes a rotor disk 12 having the rotor blade 18 inserted into a holding groove part 16, and the rotor blade is fixed against the movement along the holding groove part 16 by using the seal element 30 arranged on an end surface. For disclosing an easy and simple method for a fixation in the circumferential direction of the seal element 30, each seal element 30 is fixed by using the block element 46, and this block element is engaged with a hole part arranged in a rotor blade root part 20 existing on the end surface in this case.
Abstract:
PROBLEM TO BE SOLVED: To provide an axial compressor, especially for a gas turbine, for compressing a flow medium.SOLUTION: The compressor includes a plurality of compressor stator blades, which are assembled to form stator blade rows and fastened in each case on a stator blade carrier, and a plurality of compressor rotor blades, which are assembled to form rotor blade rows and fastened in each case on a compressor disk of a compressor shaft, wherein two consecutive compressor disks in each case enclose a hollow space lying between them, and wherein the last compressor disk, as seen in the flow direction of the flow medium, delimits a rear hollow space.
Abstract:
The invention relates to a wheel disk assembly (1; 14; 26), comprising a wheel disk (2; 15; 27), a plurality of blade devices (3; 16; 28), which are fastened along the outer circumference of the wheel disk (2; 15; 27), and a plurality of sealing plates (4; 17; 29), which are retained in two annular grooves (5, 6; 18, 19; 30, 31) radially spaced apart from each other, the first annular groove (5; 18; 30) being provided in the wheel disk (2; 15; 27) and being bounded axially outward by an annular projection (7; 20; 32), and the second annular groove (6; 19; 31) being defined by a plurality of annular-groove segments arranged adjacently, which are provided in the individual blade devices (3; 16; 28), characterized in that at least one opening (8; 21; 33) extending axially through the annular projection (7; 20; 32) is provided, the minimum width of which opening in the circumferential direction is greater than the width of the sealing plates (4; 17; 29) at the inside diameter such that a sealing plate (4; 17; 29) can be axially inserted between the annular grooves (5, 6; 19, 19; 30, 31) through the opening (8; 21; 33) and can be moved in the circumferential direction while guided by the annular grooves. The invention further relates to a method for assembling such a wheel disk assembly.
Abstract:
The invention relates to a bolt (19) and to a sealing system comprising said bolt (19) and a cover plate (18) for sealing a joint between a rotor disk (17) and a blade root (15) of a rotor blade (14), said blade root (15) being disposed in a blade root slot in the rotor disk (17). The sealing arrangement is used in particular in a gas turbine (10).
Abstract:
The invention relates to a rotor (103) for a turbine (100), comprising a plurality of rotor components (130) lined up in the axial direction and connected by means of a connecting rod (144), wherein a groove (152) which extends in the circumferential direction and is open in the axial direction is disposed on one of the rotor components (130), wherein a coupling element (154) running around the connecting rod (144) in order to support the connecting rod (144) is disposed in the groove (152). Said rotor is intended to enable particularly stable support of the connecting rod in order to prevent vibrations by technically simple means. For this purpose the coupling element (154) is disposed on a retaining element (150) connected to the connecting rod (144).
Abstract:
The invention relates to a rotor (10) for an axial flow turbomachine comprising a number of a plurality of disc shaped (12) or drum shaped (16) rotor components and at least one pin shaped tie rod (20) extending through the rotor components (14) wherein a counter bearing (26, 28) is screwed onto each of the projecting ends of said tie rod for axially bracing the rotor components (14) arranged therebetween. The aim of the invention is to provide a rotor (10) by which shorter service intervals can be achieved. In order to achieve said aim a connecting means (34) is screwed onto the tie rod (20) between both counter bearings (26, 28) wherein after the release of one of the two counter bearings (28) the rotor components (12, 14) arranged between the connecting means (34) and the other of the two counter bearings (26) are braced with each other by means of said connecting means (34).
Abstract:
Rotor for an axial flow turbomachine and double nut for connecting two tie-rod elements. The invention relates to a rotor (10) for an axial flow turbomachine, comprising a number of a plurality of disc-shaped (12) or drum-shaped (16) rotor components and at least one pin-shaped tie-rod (20) extending through the rotor components (14), wherein a counter-bearing (26, 28) is screwed onto each of the projecting ends of said tie-rod for axially bracing the rotor components (14) arranged therebetween. The aim of the invention is to provide a rotor (10) by which shorter service intervals can be achieved. In order to achieve said aim, the tie-rod (20) comprises at least two axially adjacent tie-rod elements (30, 32) which are each connected to one another in a detachable manner by a connecting means (34). Double nut (35) for connecting two tie-rod elements (30, 32).
Abstract:
The invention relates to a rotor section (10) for a rotor of a gas turbine, to a rotor blade (18), and to a blocking element (46, 62). The rotor section (10) comprises a rotor disk (12) having rotor blades (18) that are inserted thereon in holding grooves (16) and that are secured against sliding along the holding grooves (16) by means of a sealing element (30) arranged at the end face. In order to specify a reliable, simple, and easy-to-design construction for the circumferential fixing of the sealing elements (30), it is proposed that each sealing element (30) be secured by one blocking element (46, 62), which engages in a hole (58) arranged at the end face in the rotor blade root (20).