Power plants – Combustion products used as motive fluid – Process
Reexamination Certificate
1998-05-07
2002-07-16
Casaregola, Louis J. (Department: 3746)
Power plants
Combustion products used as motive fluid
Process
Reexamination Certificate
active
06418725
DESCRIPTION:
An embodiment of a gas turbine combustion system according to the present invention will be described below with reference to the accompanying drawings.
FIG. 1 illustrates the structure of the gas turbine combustion system according to the prevent embodiment. As shown in the figure, the combustion system is provided with a combustor 1 having a cylindrical, for example, structure closed at one end by a header H and including a first combustion chamber 2 a having a three-stage combustion portion, and a second combustion chamber 2 b having a two-stage combustion portion. The first combustion chamber 2 a has a structure in which a pair of inner tubes 1 a and 1 b having small diameters are coupled to each other in the direction of a gas stream.
The small-diameter inner tube la located on an upstream side in the first combustion chamber 2 a is provided with a pilot burner 3 , premixing units 4 a and at least one micro burner 5 a (which may be a heater rod heated by an electric heater or other ignition device designed to discharge ignition energy by utilizing electric or magnetic energy). The pilot burner 3 is on the other end mounted to the header H. The small-diameter inner tube 1 b located on a downstream side in the first combustion chamber 2 a is provided with premixing units 4 b and at least one micro burner 5 b. The premixing units 4 a or 4 b , each having a configuration of a premixing duct, are arrayed in a number ranging from 4 to 8 in a peripheral direction of the inner tube 1 a or 1 b. Fuel nozzles 6 a and 6 b are disposed at air inlets of the premixing units 4 a and 4 b , respectively.
The second combustion chamber 2 b includes an inner tube 7 having a diameter larger than those of the inner tubes 1 a and 1 b, premixing units 4 c and 4 d and at least one micro burner 5 c. The premixing units 4 c or 4 d , each having a configuration of a premixing duct, are arrayed in a number ranging from 4 to 8 in a peripheral direction of the large-diameter inner tube 7 .
Fuel nozzles 6 c and 6 d are disposed at upstream sides of the premixing units 4 c and 4 d , respectively. The premixing units 4 a , 4 b , 4 c and 4 d are fixed to a dummy inner tube 9 by means of supports 8 a and 8 b (only part of which is illustrated). The axial position of the dummy inner tube 9 is set by supports 11 fixed to a casing 10 so that the dummy inner tube 9 can receive thrusts acting on the small-diameter inner tubes 1 a and 1 b and the large-diameter inner tube 7 .
An inner wall 12 of a tail pipe and an outer wall 13 of a tail pipe 13 are provided downstream of the large-diameter inner tube 7 . The tail pipe outer wall 13 is formed with a large number of cooling holes 14 . Similarly, a flow sleeve 15 , having a large number of cooling holes 16 , is provided on an outer peripheral side of the large-diameter inner tube 7 . A tie-in portion between the large-diameter inner tube 7 and the tail pipe inner wall 12 and a tie-in portion between the flow sleeve 15 and the tail pipe outer wall 13 are sealed by means of spring seals 17 , respectively.
A premixed fuel injection port 18 of the first stage is provided at the upstream end of the small-diameter inner tube 1 a. Outlets of the premixing units 4 a , 4 b , 4 c and 4 d provided in the inner tubes 1 a , 1 b and 7 serve as premixed fuel injection ports of the second, third, fourth and fifth stages 19 a , 19 b , 19 c and 19 d , respectively. The premixed fuel injection ports of the second, third, fourth and fifth stages 19 a , 19 b , 19 c and 19 d are disposed at predetermined intervals which ensure that the series combustion can be conducted adequately in the axial direction of the combustor. The premixed fuel may be injected from the injection ports 19 a , 19 b , 19 c and 19 d toward the center of the combustor. The injection ports may also be disposed in a spiral fashion so that the gas stream can have a swirling component, as shown in FIG. 2 .
The pilot burner 3 includes a diffusion fuel nozzle 20 located along a central axis of the small-diameter inner tube 1 a, a premixed fuel nozzle 21 and
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patent: 5069029 (1991-12-01), Kuroda et al.
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patent: 5431017 (1995-07-01), Kobayashi et al.
patent: 2 280 022 (1995-01-01), None
patent: WO 93/09339 (1993-05-01), None
Iwai Yasunori
Maeda Fukuo
Sato Yuzo
Casaregola Louis J.
Kabushiki Kaisha Toshiba
Oblon & Spivak, McClelland, Maier & Neustadt P.C.
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