SU236492A1 - TURBOCHARGER - Google Patents

Description

Turbo-refrigeration systems are known for aircraft in-flight Co-systems, and for which bearings are lubricated with oil sucked through a pipe from an oil-retaining centrifugal wheel mounted on an assembly shaft. In such a system, bearing lubrication at low speeds is not obesechii, when there is not yet created a vacuum in the bearing cavity, which is necessary for oil leaks, as well as careful sealing of the bearing cavity.

The proposed turbo-cooler differs from the well-known bodies1 that gas-jet injectors are integrated into the bearing spacer, the working nozzles of which are connected to the inlet pipe of the turbine using channels in the housing and spacer sleeve, and the receiving chambers are equipped with an oil sump, and the diffusers are open in the treatment of bearings. This ensures reliable bearing lubrication regardless of the number of revolutions.

The drawing shows the scheme of the proposed turbo-cooler.

It consists of a housing /, in which the shaft 3 rotates with the bearings 2 with the impellers of the centrifugal compressor 4 and the radial turbine 5.

Separate oil supply to the left and right bearings is carried out by two injectors 6, built into the spacer sleeve 7.

Each injector consists of a working nozzle (V, a receiving chamber 9, a mixing chamber 10 and a diffuser n. A receiving chamber 9 is connected by a feeder 12 immersed under the oil level with an oil sump 13.

The working air to the nozzles 8 is supplied through an annular channel 14, which through the channel 15, the tube 16 and the annular air cooler / 7 is connected to the inlet pipe 18 of the turbine. In the air cooler located at the outlet of the turbine 19, the air is pre-cooled. If air cooling is not required, it enters the inlet duct directly through channel 20.

The prompter 21 and the oil separator 22 serve to discharge the exhaust air from the cavity of the ShchININ1 KOV.

The lubrication system works as follows.

When the turbine cooler is mounted, the working air simultaneously enters the turbine 5 and into the annular channel 14, from where it separates into the right and left working nozzles 8. The air flow leaves the nozzle into the receiving chamber 9 at high speed, creating a vacuum and pulling the oil particles From the crankcase, the feeder of air and oil enters the mixing chamber 10, and then into the diffuser, from where the oil in the fine spray reaches the subsurface.

The oil, reflected bearing separatorol, as well as passing through the bearing and thrown off by the reflective ring 23, is drained back into the crankcase through the channels 24. Exhaust air 1 EXIT from the bearing cavity through the hole 25 and the breather. The separator separates the oil droplets that are captured by the exit of the W. IM air.

Subject invention

A turbo-cooler, comprising a housing, turbine and compressor impellers mounted on a shaft mounted on ball bearings, lubricated with oil from the crankcase through feeders, and spacer bushing bearings with an annular channel, characterized in that, for the purpose of reliable lubrication rotational speeds, gas burners 41 are inserted into the spacer sleeve of underfills. The working nozzles of which are connected to the inlet pipe of the turbo pipe through the channels in the housing and the spacer sleeve, and the receiving chambers from the oil m crankcase and diffusers open in the direction of the bearings.