Washing nozzles and gas turbine engines
Nozzle used for spraying a liquid substance towards a compressor of a gas turbine engine, comprising an elongated body having an end for ejecting the liquid substance, a conduit for the liquid substance internal to the elongated body and extending up to the end, a recess located at the end, wherein the conduit ends in the recess; wherein the recess opens towards the lateral surface of the elongated body, typically a cylindrical body, and the conduit is tangential to the bottom of the recess.
1. A nozzle for spraying a liquid substance towards a compressor of a gas turbine engine, the nozzle comprising:
an elongated body having an end for ejecting the liquid substance,
a conduit for the liquid substance internal to the elongated body and extending up to the end,
a recess located at the end, wherein the conduit ends in the recess, and wherein a shape of a cross-section of the recess includes a partially flat portion and a partially curved portion, the partially curved portion comprising an arc of circle or parabola or hyperbola;
wherein the recess opens towards a lateral surface of the elongated body and wherein the conduit is substantially tangential to a bottom of the recess.
2. The nozzle of claim 1 , wherein the elongated body is a cylindrical body.
3. The nozzle of claim 1 , wherein the recess is arranged according to a diameter direction of the elongated body.
4. The nozzle of claim 1 , wherein the partially flat portion of the shape of the cross-section of the recess and the partially curved portion of the shape of the cross-section of the recess corresponds to the bottom of the recess.
5. The nozzle of claim 1 , wherein the conduit has a first cross section at a first end and smaller second cross section at a second end.
6. The nozzle of claim 5 , wherein the conduit has a bottleneck in a lower portion of an intermediate portion of the nozzle above the recess.
7. The nozzle of claim 2 , wherein the recess is arranged according to a diameter direction of the elongated body.
8. A gas turbine engine comprising a compressor, a turbine downstream of the compressor, and a plurality of nozzles for spraying a detergent liquid substance towards an inlet of the compressor; wherein each of the plurality of nozzles is according to claim 1 .
9. The gas turbine engine of claim 8 , wherein the plurality of nozzles are located at a mouth of the compressor.
10. The gas turbine engine of claim 9 , wherein the plurality of nozzles are located on a circle centered on an axis of the gas turbine engine.
11. The gas turbine engine of claim 10 , wherein the plurality of nozzles are equi-spaced on the circle.
12. The gas turbine engine of claim 9 , further comprising a manifold in fluid communication with the plurality of nozzles, wherein a manifold is located behind the mouth of the compressor.
13. The gas turbine engine of claim 8 , wherein the recess opens downstream of a flow entering the compressor.