Acoustic attenuator, tube assembly, combustor, gas turbine, and method for manufacturing tube assembly
An attenuator, sound technology, applied in combustion methods, gas turbine devices, combustion chambers, etc., to achieve the effect of easy assembly
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no. 1 approach
[0047] figure 1 It is a conceptual diagram showing the configuration of the gas turbine in the first embodiment of the present invention.
[0048] Such as figure 1 As shown, the gas turbine 10 includes: a compressor 20 that compresses air A; a plurality of combustors 40 that burn fuel in the air compressed by the compressor 20 to generate combustion gas G; and a turbine 30 that is driven by the combustion gas G.
[0049] The compressor 20 has a compressor rotor 21 rotating around a rotor axis Lr, a compressor housing 25 rotatably covering the compressor rotor 21 , and a plurality of fixed blade rows 26 . Hereinafter, the direction in which the rotor axis Lr extends is referred to as the rotor axis direction Da, one side of the rotor axis direction Da is referred to as the axial upstream side Dau, and the other side is referred to as the axial downstream side Dad. In addition, the circumferential direction around the rotor axis Lr is simply referred to as the circumferential ...
no. 2 approach
[0098] Next, a second embodiment of the present invention will be described with reference to the drawings. This second embodiment differs from the above-described first embodiment in that the extension portion 63 is not provided, and the main body damper spaces of adjacent main body damping units 71 of the main body 62A are communicated with each other through the communicating portion. Therefore, the same reference numerals will be assigned to the same parts as those in the above-mentioned first embodiment, and will be described. Also, detailed descriptions of the configurations that overlap with those of the first embodiment are omitted.
[0099] Figure 10 is the second embodiment of the present invention with Figure 5 The corresponding stereogram.
[0100] The canister assembly 80B of this second embodiment constitutes a part of the combustor 40 of the gas turbine 10 similarly to the canister assembly 80A of the above-mentioned first embodiment. Such as Figure 10 A...
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