Abstract: An exhaust gas housing for a gas turbine, in which an annular gas passage, through which exhaust gas discharges from the gas turbine to the outside, is formed by a concentric inner casing and an outer casing which concentrically encompasses the inner casing at a distance, wherein the inner casing and the outer casing are interconnected by a plurality of radial struts which extend through the gas passage and have in each case a leading edge and a trailing edge with regard to the exhaust gas flowing through the gas passage, and wherein the struts, the outer casing and the inner casing are equipped in each case with a heat-resistant lining towards the gas passage, wherein the lining of the struts is at least partially mechanically decoupled from the lining of the inner casing and/or of the outer casing for reducing thermal stresses on the periphery of the struts.

Abstract: A high-pressure compressor (12), in particular in a gas turbine (10), has a compressor rotor (17) which is surrounded by a stator (18, 19) thereby forming a main flow channel (25) and which is delimited at the compressor outlet by an end face (30) substantially extending in the radial direction, along which end face cooling air (21) is conveyed in the radial direction for the purpose of cooling. A prolonged service life is achieved in that the end face (30) is provided with a first system (23, 24) for improving the heat transfer between the cooling air (21) and the end face (30).

Abstract: A pressure casing has a plurality of casing shells (10a, b) which can be connected in a pressure-tight manner in a parting plane (11) by a flange (13). The casing shells (10a, b) are pressed together with sealing effect in the parting plane (11) in the region of the flange (13) by at least one threaded bolt (19; 19a-d) which extends through the flange (13) perpendicularly to the parting plane (11). A reduced thermal loading of the threaded bolts (19; 19a-d) of the flanged joint is achieved by the at least one threaded bolt (19; 19a-d) being exposed over a part of its length towards the inner side of the casing (10).

Abstract: A rotor (1) of a gas turbine compressor comprises a multiplicity of welded-together rotor disks (3a, 3b, 4, 5), of which two or more rotor disks (3a, 3b), in a radially outer region (9?), are welded together, and, in a radially inner central region (9), are abutment-joined together. Via the abutment-joining of two rotor disks (3a, 3b), a heat flow (8) radially outward from the center of the rotor (1) is achieved so that the material temperature of the rotor (1) can be kept below a predetermined level during operation. As a result, the service life of the rotor (1) can be increased. In one embodiment, one rotor disk (3a), on its surface, additionally has a recess (7) which can be cooled from outside. The rotor disks (3a, 3b) according to the invention, which are welded and abutment-joined together, can especially be used at the last point in the flow direction of the compressor.

Abstract: A pressure casing has a plurality of casing shells (10a, b) which can be connected in a pressure-tight manner in a parting plane (11) by a flange (13). The casing shells (10a, b) are pressed together with sealing effect in the parting plane (11) in the region of the flange (13) by at least one threaded bolt (19; 19a-d) which extends through the flange (13) perpendicularly to the parting plane (11). A reduced thermal loading of the threaded bolts (19; 19a-d) of the flanged joint is achieved by the at least one threaded bolt (19; 19a-d) being exposed over a part of its length towards the inner side of the casing (10).

Abstract: A rotor (1) of a gas turbine compressor comprises a multiplicity of welded-together rotor disks (3a, 3b, 4, 5), of which two or more rotor disks (3a, 3b), in a radially outer region (9?), are welded together, and, in a radially inner central region (9), are abutment-joined together. Via the abutment-joining of two rotor disks (3a, 3b), a heat flow (8) radially outward from the center of the rotor (1) is achieved so that the material temperature of the rotor (1) can be kept below a predetermined level during operation. As a result, the service life of the rotor (1) can be increased. In one embodiment, one rotor disk (3a), on its surface, additionally has a recess (7) which can be cooled from outside. The rotor disks (3a, 3b) according to the invention, which are welded and abutment-joined together, can especially be used at the last point in the flow direction of the compressor.

Abstract: In a method for the fast cooling down of a gas turbine (1) after its operation, and also in a gas turbine (1) useful for carrying out the method, subsequent to the operation of a gas turbine (1), the rotor (8) is operated at low cooling speed (n) in order to cool down the gas turbine (1) which is heated up as a result of operation. This allows service or maintenance operations to be started early and therefore to reduce the shutdown periods of a gas turbine (1). After the operation of the gas turbine (1), cooling is not carried out a constant low cooling speed (n), but the cooling speed (n) is controlled as a function of at least one critical temperature (Tk) and/or of time (t). The cooling speed (n) in this case, in dependence upon the critical temperature (Tk), is kept as high as the resulting thermal and/or cyclic load allows for realizing a fast cool-down.

Abstract: Suitable means for driving a flow are arranged in annular or ring-segment-shaped cavities that are formed in particular in multi-shell casings of turbomachines. Arranged inside the cavity are ejectors that are supplied via suitable means with a motive-fluid flow which in turn excites the flow, preferably a circumferential flow or a helical flow. The invention is suitable in particular for avoiding casing distortions when turbomachines are at rest.

Abstract: In order to avoid the “buckling” of multi-shell turbomachine casings during a cooling phase following the shutdown, it is proposed to provide means in order to suitably discharge warm medium which collects at a point of the casing cavity situated at the highest geodetic level. In an embodiment, it is proposed to allow the corresponding lines to open out in the stack of a power plant; the stack draft effect assists the flow even further. Regulating members are advantageously provided in the lines in order to shut off these lines during operation of the turbomachine on the one hand and in order not to arrange the flow through the casing cavities too intensively on the other hand.

Abstract: In order to avoid the “buckling” of multi-shell turbomachine casings during a cooling phase following the shutdown, it is proposed to provide means in order to suitably discharge warm medium which collects at a point of the casing cavity situated at the highest geodetic level. In an embodiment, it is proposed to allow the corresponding lines to open out in the stack of a power plant; the stack draft effect assists the flow even further. Regulating members are advantageously provided in the lines in order to shut off these lines during operation of the turbomachine on the one hand and in order not to arrange the flow through the casing cavities too intensively on the other hand.

Abstract: Suitable means for driving a flow are arranged in annular or ring-segment-shaped cavities that are formed in particular in multi-shell casings of turbomachines. Arranged inside the cavity are ejectors that are supplied via suitable means with a motive-fluid flow which in turn excites the flow, preferably a circumferential flow or a helical flow. The invention is suitable in particular for avoiding casing distortions when turbomachines are at rest.