Method and apparatus for cleaning a jet engine
An apparatus for cleaning a jet engine includes a supply device configured to make cleaning medium available, a nozzle device configured to introduce the cleaning medium into the jet engine, and a line connection between the supply device and the nozzle device. The cleaning medium can be solid carbon dioxide. A system including a jet engine and the apparatus. A method for cleaning a jet engine using solid carbon dioxide.
1. An apparatus for cleaning a jet engine, comprising:
a supply device configured to make a cleaning medium available;
a nozzle device configured to introduce the cleaning medium into the jet engine, the nozzle device comprising a rotationally fixed connection configured to connect to a shaft of a turbofan of the jet engine;
a line connection between the supply device and the nozzle device; and
a rotary coupling provided between the nozzle device and the line connection,
wherein the cleaning medium comprises solid carbon dioxide.
2. The apparatus of claim 1 , wherein the solid carbon dioxide is in the form of carbon pellets.
3. The apparatus of claim 1 , wherein the solid carbon dioxide is in the form of carbon flakes.
4. The apparatus of claim 1 , wherein the nozzle device is configured to introduce the cleaning medium into compressor stages of the jet engine.
5. The apparatus of claim 1 , wherein the nozzle device comprises at least two nozzles.
6. The apparatus of claim 1 , wherein the distribution of mass of the nozzle device is rotationally symmetrical about an axis of rotation of the nozzle device.
7. The apparatus of claim 1 , wherein nozzles of the nozzle device are flat-jet nozzles.
8. The apparatus of claim 7 , wherein a jet plane in a region of an outlet orifice of the nozzles points essentially in a radial direction of the jet engine.
9. The apparatus of claim 7 , wherein a jet plane forms an angle of incidence with an axis of rotation of the jet engine.
10. The apparatus of claim 7 , wherein outlet orifices of the nozzles are arranged in an axial end region of the nozzle device which points away from an axis of rotation of the nozzle device.
11. The apparatus of claim 1 , wherein the rotationally fixed connection to the shaft of the turbofan of the jet engine comprises a fastener for fastening to blades of the turbofan.
12. The apparatus of claim 1 , wherein the rotationally fixed connection to the shaft of the turbofan of the jet engine comprises a device for essentially positive attachment onto a shaft hub of the turbofan.
13. The apparatus of claim 12 , wherein the device for essentially positive attachment onto the shaft hub of the turbofan comprises at least one ring part and guy ropes.
14. The apparatus of claim 13 , wherein spring devices are provided for prestressing the guy ropes.
15. The apparatus of claim 13 , wherein a fastener is provided for fastening the guy ropes to blades of the turbofan.
16. The apparatus of claim 1 , wherein the supply device comprises at least one storage tank for the cleaning medium and at least one pump for acting with pressure upon the nozzle device with the cleaning medium, the storage tank being capable of at least one of being acted upon with pressure and being heat-insulated.
17. The apparatus of claim 16 , wherein the storage tank comprises a cooling device.
18. A system comprising:
a jet engine; and
an apparatus according to claim 1 for cleaning the jet engine,
wherein the apparatus is arranged such that nozzles of the nozzle device are directed onto an intake of the jet engine so that the cleaning medium passes into the jet engine.
19. The system of claim 18 , wherein:
the nozzle device is connected fixedly in terms of rotation to a shaft of a turbofan of the jet engine;
the axis of rotation of the turbofan of the jet engine and the axis of rotation of the nozzle device are arranged essentially concentrically along a common axis of rotation;
the nozzles of the nozzle device are at a radial distance from the common axis of rotation, the radial distance being shorter than a radius of an inlet orifice of a first compressor stage; and
outlet orifices of the nozzles are arranged behind a plane of the turbofan in the axial direction and/or the nozzles are arranged in interspaces of blades of the turbofan and/or the nozzles are aligned with interspaces of the blades of the turbofan so that nozzle jets can pass, essentially unimpeded, through the plane of the turbofan.
20. The system of claim 19 , wherein a jet plane of the nozzles forms an angle of incidence with the axis of rotation which corresponds essentially to an angle of incidence of the blades of a front compressor stage in a direction of flow of the jet engine.