摘要:
The invention relates to a turbine guide vane support (10) for an axial-flow gas turbine, comprising a tubular wall (20) having an inflow-side end (16) and an outflow-side end (18) for a hot gas flowing in the interior (40) of the turbine guide vane support (10) in a flow path of the gas turbine, wherein at least one cooling channel (26) for a coolant is provided in the wall (20), said cooling channel extending from a coolant inlet (32) to a coolant outlet (36), respectively. In order to design the turbine guide vane support (10) to withstand especially high operating temperatures, it is proposed that at least one of the inlets (32) and one of the outlets (36) be respectively disposed at the outflow-side end (18) of the turbine guide vane support (10), wherein the cooling channel (26) associated with the respective inlet (32) and outlet (36) extends up to the inflow-side end (16) of the turbine guide vane support (10) and transitions there to a redirecting area (34) from which the respective cooling channel further extends to the outflow-side end (18).
摘要:
A gas turbine (1), with a fixed inner housing (37), arranged concentric to the rotor (3), with a throughflow of working medium, is disclosed. The housing comprises at least two serial rings (25, 26) with an annular gap (23) left between two directly adjacent rings (25, 26), whereby an annular sealing means is arranged in at least one peripheral groove (31) for sealing the annular gap (23). According to the invention, a sealing means is provided which permits a greater movement of both components forming the gap, whereby the annular gap (23) is formed by partly overlapping rings (25, 26), running against the flow direction of the working fluid (20) in the radial sense and the frontmost of the two rings (25), in the sense of the flow direction, comprises a locating annular surface (32) for the sealing means embodied as an annular spring element (24) on which the spring element (24) rests under tension such as to seal the annular gap (23).
摘要:
The invention pertains to a sealing element (1) for sealing a gap (5) which can form between two components (2a, 2b) liable to move relative to one another as a result of thermal action and each provided with an opposing groove (3a, 3b). The sealing element (1) in one cross-section is substantially perpendicular to a main line (21) along a median line (4). It has a first end (6a), a second end (6b) opposite the first end, and a central region (10) between the two ends, and is provided with teeth. The sealing element (1) is especially suitable for use in sealing a gap (5) between guide vanes (12) at high temperatures in a gas-turbine facility (22) as a means of preventing gas flow from a cool gas region (8) to a hot gas region (11).
摘要:
A gas turbine (1), with a fixed inner housing (37), arranged concentric to the rotor (3), with a throughflow of working medium, is disclosed. The housing comprises at least two serial rings (25, 26) with an annular gap (23) left between two directly adjacent rings (25, 26), whereby an annular sealing means is arranged in at least one peripheral groove (31) for sealing the annular gap (23). According to the invention, a sealing means is provided which permits a greater movement of both components forming the gap, whereby the annular gap (23) is formed by partly overlapping rings (25, 26), running against the flow direction of the working fluid (20) in the radial sense and the frontmost of the two rings (25), in the sense of the flow direction, comprises a locating annular surface (32) for the sealing means embodied as an annular spring element (24) on which the spring element (24) rests under tension such as to seal the annular gap (23).
摘要:
Sealing plate (40) comprises a number of sheets (50) with two opposite-lying sheets arranged parallel to the plate plane (49). An independent claim is also included for a rotor blade system with the sealing plate; and #Gas turbine with the rotor blade system. Preferred Features: An intermediate sheet (52) with a number of recesses (56) is arranged between the sheets. Each sheet has a number of cooling air holes (58).