Fuel system and method for supplying a combustion chamber in an aircraft turboshaft engine with fuel
US-2024318601-A1 · Sep 26, 2024 · US
US2018252412A1 · US · A1
| Field | Value |
|---|---|
| Publication number | US-2018252412-A1 |
| Application number | US-201815907953-A |
| Country | US |
| Kind code | A1 |
| Filing date | Feb 28, 2018 |
| Priority date | Mar 2, 2017 |
| Publication date | Sep 6, 2018 |
| Grant date | — |
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A mixer having a housing, a duct within the housing, a first and a second injector arranged to inject a fluid at a centre zone of the duct, a third and a fourth injector arranged to inject the fluid at a wall zone of the duct. The first/third injectors are at a distance D1=v/2f1 or odd integer multiples of it from the second/fourth injectors in the absence of an acoustic node between them, or at a distance D1=λconv=v/f1 or full wave length integer multiples of it in the presence of an acoustic node between them. Advantageously f1 is greater than f2.
Opening claim text (preview).
1 . A mixer comprising: a housing; a duct within the housing; a first injector and a second injector arranged to inject a fluid at a centre zone of the duct; a third injector and a fourth injector arranged to inject the fluid at a wall zone of the duct, wherein: the first injector is at a distance D 1 =v/2f 1 or odd integer multiples of it from the second injector in an absence of an acoustic node between the second injector and the first injector, or at a distance D 1 =λ conv =v/f 1 or full wave length integer multiples of it in a presence of an acoustic node between the second injector and the first injector; and the third injector is at a distance D 2 =v/2f 2 or odd integer multiples of it from the fourth injector in an absence of an acoustic node between the third injector and the first injector, or at a distance D 2 =v/f 2 from the first injector in a presence of an acoustic node between the third injector and the first injector; wherein: f 1 is an oscillating frequency to be damped at the wall zone of the duct; f 2 is an oscillating frequency to be damped at the centre zone of the duct; and v is a fluid flow speed through the duct, wherein f 1 is greater than f 2 . 2 . The mixer of claim 1 , wherein both f 1 and f 2 are lower than 150 Hz. 3 . The mixer of claim 1 , wherein the first injector and/or the second injector and/or the third injector and/or the fourth injector comprise: a plurality of rows of nozzles close to one another. 4 . The mixer of claim 2 , wherein nozzles of different rows of nozzles of a same injector have different penetration. 5 . The mixer of claim 2 , wherein the nozzles of a same row of nozzles have different penetration. 6 . A gas turbine comprising: a compressor; a first combustion chamber; a second combustion chamber arranged to be fed with a fluid coming from the first combustion chamber; and a turbine, wherein between the first combustion chamber and the second combustion chamber a mixer is provided, which mixer includes: a housing; a duct within the housing; a first injector and a second injector arranged to inject a fluid at a centre zone of the duct; a third injector and a fourth injector arranged to inject the fluid at a wall zone of the duct, wherein: the first injector is at a distance D 1 =v/2f 1 or odd integer multiples of it from the second injector in an absence of an acoustic node between the second injector and the first injector, or at a distance D 1 =λ conv =v/f 1 or full wave length integer multiples of it in a presence of an acoustic node between the second injector and the first injector; and the third injector is at a distance D 2 =v/2f 2 or odd integer multiples of it from the fourth injector in an absence of an acoustic node between the third injector and the first injector, or at a distance D 2 =v/f 2 from the first injector in a presence of an acoustic node between the third injector and the first injector; wherein: f 1 is an oscillating frequency to be damped at the wall zone of the duct; f 2 is an oscillating frequency to be damped at the centre zone of the duct; and v is a fluid flow speed through the duct, wherein f 1 is greater than f 2 .
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