摘要:
The invention relates to a method for cooling and sealing of a heat shield element (13) , comprising a main wall (15) with an inner side (151) , which is restricted by side walls (14) or rims, and an outer side (153) , which can be exposed to a hot fluid, and wherein a coolant (K) is introduced into an impingement region (17) of that heat shield element (13) and an impingement flow (19) of said coolant (K) is directed on a surface area (23) of that inner side (151) through a plurality of impingement holes (21) , effecting an impingement pressure drop (Delta PI) . In the method discharge flow (25) is metered through a number of discharge holes (27) through said side wall (14) or rims from the inner side (151) to the outer side (153) of the main wall (15) , generating a discharge pressure drop (Delta PD) in series with the impingement pressure drop (Delta PI) .
摘要:
Provided is a burner (3) having two ignition electrodes (4) and having a bracket (2), wherein the bracket (2) is arranged on the outer surface of the burner (3) and the ignition electrodes (4) are held, at in each case three points (1) of their periphery, in a fixed position by means of the bracket (2).
摘要:
According to the invention, a device for the generation of eddies creates or destroys eddies in a flowing medium (S) in a particularly simple manner, with particularly low energy requirement with the lowest possible pressure drop, whereby the device comprises one or more profiles (1), for the flowing medium (S) to flow around, which are provided with an external drive for a periodic movement relative to the flowing medium (S) with an angular frequency O. The profiles (1) are thus periodically displaced with an angular frequency O by an external drive.
摘要:
According to the invention, a device for the generation of eddies creates or destroys eddies in a flowing medium (S) in a particularly simple manner, with particularly low energy requirement with the lowest possible pressure drop, whereby the device comprises one or more profiles (1), for the flowing medium (S) to flow around, which are provided with an external drive for a periodic movement relative to the flowing medium (S) with an angular frequency O. The profiles (1) are thus periodically displaced with an angular frequency O by an external drive.
摘要:
Provided is a burner (3) having two ignition electrodes (4) and having a bracket (2), wherein the bracket (2) is arranged on the outer surface of the burner (3) and the ignition electrodes (4) are held, at in each case three points (1) of their periphery, in a fixed position by means of the bracket (2).
摘要:
The invention relates to a wall structure (3) with an intermediate partition (12) between an inner wall (6) and an outer wall (7). An inlet (9) leading to an external cooling area (13) located in between the outer wall and the intermediate partition (12) and an outlet (10) leading to an inner cooling area (10) located in between the intermediate partition (12) and the inner wall (6) are provided for the cooling liquid, especially for cooling vapour (14). The intermediate partition (12) has openings (15) allowing cooling fluid (11) to flow through. The invention further relates to a method for cooling a gas turbine combustion chamber (1) with vapour.
摘要:
An annular combustion chamber (RBK) for a gas turbine is disclosed, which permits a sealed air cooling, such that high powers and efficiencies can be achieved with low NOx emissions. The two-piece annular combustion chamber housing (1,3) surrounds a thin-walled sealed liner (4,41), which guides the hot gas escaping from the burners (5) to the turbine inlet (8) in a gas-tight manner. A variable annular chamber (7) is located between the liner and the annular combustion chamber housing (1,3), in which the cooling air is collected as a counter-current to the hot gas and fed to the burners (5) ( closed air cooling ). The surfaces of the liner (4,41) are variably cooled with efficient baffle cooling devices (14) and drilled patterns in (1,3). The thermally-elastic liner constructed from submerged arc-welded rings is axially fixed at the flange (36) only and for the remainder provided with reinforcing circumferential beading. The freely expanding liner (4,41) is otherwise concentrically fixed to the cold annular combustion chamber housing (1,3) by means of elastic tensioning elements (10). The above efficient, economical and simple construction further offers significant service advantages due to the following construction features:- the burners (5) can be completely (dis)assembled from outside without opening the housing. Both the liner (4, 41) and also a ring which integrates the first row of turbine guide vanes in the annular combustion chamber can be removed as service pieces in other words exchanged without opening the turbine and compressor housing and without removal of a rotor.
摘要:
The invention relates to a wall structure (3) with an intermediate partition (12) between an inner wall (6) and an outer wall (7). An inlet (9) leading to an external cooling area (13) located in between the outer wall and the intermediate partition (12) and an outlet (10) leading to an inner cooling area (10) located in between the intermediate partition (12) and the inner wall (6) are provided for the cooling liquid, especially for cooling vapour (14). The intermediate partition (12) has openings (15) allowing cooling fluid (11) to flow through. The invention further relates to a method for cooling a gas turbine combustion chamber (1) with vapour.
摘要:
The invention relates to a wall structure (3) with an intermediate partition (12) between an inner wall (6) and an outer wall (7). An inlet (9) leading to an external cooling area (13) located in between the outer wall and the intermediate partition (12) and an outlet (10) leading to an inner cooling area (10) located in between the intermediate partition (12) and the inner wall (6) are provided for the cooling liquid, especially for cooling vapour (14). The intermediate partition (12) has openings (15) allowing cooling fluid (11) to flow through. The invention further relates to a method for cooling a gas turbine combustion chamber (1) with vapour.